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Human Factors Engineering Collection
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Human Factors Engineering Collection
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spc_hfac_000001
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Brian Nelson and Nelson Brown conduct Human Factors Engineering experiments on the KC-135 Vomit Comet.
Creator
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United States. National Aeronautics and Space Administration
Date
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1968-05
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1960-1969
Subject
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Brown, Nelson
Nelson, Brian
Human factors in engineering design
KC-135 (Tanker aircraft)
Type
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Contact sheets
Photographs
Still Image
Source
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Human Factors Engineering Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
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This item was digitized for the Apollo 11 50th anniversary celebration.
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en
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Human Factors Engineering Collection
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Human Factors Engineering Collection
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spc_hfac_000002
Title
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Brian Nelson and Nelson Brown conduct Human Factors Engineering experiments on the KC-135 Vomit Comet.
Creator
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United States. National Aeronautics and Space Administration
Date
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1968-05
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1960-1969
Subject
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Brown, Nelson
Nelson, Brian
Human factors in engineering design
Type
The nature or genre of the resource
Contact sheets
Photographs
Still Image
Source
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Human Factors Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Provenance
A statement of any changes in ownership and custody of the resource since its creation that are significant for its authenticity, integrity, and interpretation. The statement may include a description of any changes successive custodians made to the resource.
This item was digitized for the Apollo 11 50th anniversary celebration.
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en
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.w
WTELEDYNE
BROWN ENGINEERING
TECHNICAL LETTER ASD-ASTN-20102
TO:
J. W. Stokes
S&E-ASTN-SMH
FROM:
Human Factors Engineering Branch
Systems Engineering Department
Aerospace Support Division
SUBJECT:
Final Crew System Corollary Experiment
Input to the Skylab Final Mission Evaluation
Report
DATE:
Fe b r u a r y 1 5 , 1 9 7 4
In response to AVO No. 140, dated February 8, 1974, and in partial
fulfillment of Technical Directive S-3-500, paragraph I. D. 1, the subject
report is enclosed.
Originated by:
R. A. Curtis
"Originated by:
D. W. Dodson
APPROVED:
(
A-
/ /
J. H. Ofenloch, Task Manager
Man/Systems Engineering
Section, ASD-SHE
R. L. Edgeton, 'Manager
Man/Systems Engineering
Branch, ASD-SH
1 Enc:
As stated
cc: S&E-ASTN-SM, Mr. Thompson, w/oenc.
ASD-S, Mr. Turney, w/o enc.
/
S&E-ASTN-SMH, Mr. Reaves
AF-01-PP (38732)
�MISSION E V A L U A T I O N R E P O R T
SKYLAB COROLLARY EXPERIMENTS
Prepared by:
C R E W S Y S T E M S MISSION S U P P O R T G R O U P
MARSHALL SPACE FLIGHT CENTER
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
February 9, 1974
�13.22
COROLLARY EXPERIMENTS
13.22. 1
General
-
The corollary experiments involved three major
i t e g o r i e s of e x p e r i m e n t a t i o n c o n s i s t i n g o f ; t h e s c i e n t i f i c , w i t h o b j e c t i v e s
> acquire photographic data of solar and stellar phenomena; the technological,
with objectives to measure contamination levels surrounding the Orbital
Assembly; and the operational, with objectives to assess technological
innovations which assist the crew in performing space related tasks.
Performance of the corollary experiments during the three Skylab missions
achieved most of the designed and planned functional objectives.
The know
ledge obtained from their operation and the acquired data have provided
insight that will be implemented into the design and operational require
ments of future manned spacecraft.
Significant information has been acquired a s a result of the corollary experi
ment activities performed during Skylab.
Ihe following are some conclusions
derived from the on-orbit corollary experimentation that is applicable to
future spacecraft hardware designs and operations.
•
An adequate maintenance workstation with appropriate
tools and restraints should be included in future space
craft design.
•
Crew manipulation of large experiment equipment
caused no problems.
Multiple, small items were
�found to be difficult to constrain and handle.
It is
recommended that handles be provisioned on all large
mass items to facilitate their manipulation.
Also, a
system is required to control the manipulation of
multiple, small items.
Of the experiments requiring extension/retraction
through the Scientific Airlock (SAL) to space, it was
found that the retraction forces were somewhat higher,
as anticipated, and that a warm-up period was required
prior to final retraction and removal of experiments
from the SAL to prevent formation of condensation/
frost.
Through operations of M509 and T020 the feasibility of
a one-man maneuvering unit was successfully demonstrated.
Corollary experiment T013 demonstrated that crew
motion within a large spacecraft does impact its
stability and guidance control and should be considered
in future designs.
�13.22.2
Scientific Experiments
13.22.2.1
S009 - Nuclear Emulsion
a.
Operations - Experiment S009 was scheduled to be performed
throughout the SL-2 mission to investigate aspects of cosmic radiation.
Prior to experiment initiation, the S009 detector package was to be removed
from the OWS film vault, transferred to the MDA and installed in the S009
experiment housing.
The crewman was then to initiate experiment operation
by setting the proper beta angle and activating the open-close cycle for the
experiment.
S009 was to operate automatically throughout SL-2 with the crew
making periodic checks and/or corrections to the experiment beta angle
and open-close cycle.
At the completion of the experiment, the S009
detector package was to be removed from the experiment housing and stowed
in the CM for earth return.
b. Usage/Anomalies -
The S009 experiment was conducted on
SL-2 despite a concern of possible S009 detector emulsion degradation due
to the high OWS temperatures present during the beginning of the SL-2
mission.
During the S009 detector package installation considerable difficulty
was encountered.
It was determined that due to the high OWS temperatures,
the emulsion package had expanded thereby reducing the tolerances between
the package and experiment housing.
After two we ks of operation the door on the S009 experiment housing
began to bind and finally would not close properly.
The crew performed
�malfunction procedures and concluded that the motor/drive train for the
experiment door had failed.
As a result the S009 door was left open,
the automatic open-close cycle was inhibited and manual pointing was
maintained throughout the duration of the SL-2 mission for data collection.
At the end of SL-2 the S009 detector package was stowed in the CM and
returned to earth.
On ground analysis of the package revealed that the
emulsion layers had been fused together due to the high OWS temperatures
and the data was of little use.
On SL-3 a new S009 door motor was launched for replacement but
replacement was not accomplished due to scheduling reasons.
On SL-4 a new emulsion package was launched.
During malfunction
procedures the crew replaced the defective door motor (an hour operation)
and installed the resupplied detector package.
S009 was then activated and
performed satisfactorily throughout the remainder of the SL-4 mission.
completion of the experiment, the detector package was stowed in the
CM and returned to earth.
c.
Assessments/Recommendations -
Experiment S009
operations, including malfunction procedures, were straightforward and
no crew interface problems were experienced.
The hardware unstowage
and experiment activation was a one-man operation and the restraints
Up
�provided in the MDA for S009 operations were considered adequate.
No
problems were encountered during the SL-4 S009 motor replacement and
resupply of the detector package.
13.22.22.2
a.
S019 - UV Stellar Astronomy
Operations - The S019 UV Stellar Astronomy experiment
was scheduled to be performed during 12 selected night orbits in each
of the first two missions, SL-2 and SL-3.
The equipment to be used was an optical canister and the Articulated
Mirror System (AMS), launched in individual stowage containers, and
the film canister, launched in the OWS film vault.
One crewman was to
be required to set up and operate the experiment hardware in the Scientific
Airlock (SAL) to obtain a total of 150 slides of data from a minimum of
36 starfields.
Three starfields, with three exposures per starfield,
were to be photographed during each operation.
To maximize the scientific
return of S019, the astronaut was to be allowed as much flexibility in the
choice of starfields and exposure times a s possible.
b. Usage/Anomalies - During the initial activation of the AMS
a problem occurred in the operation of the tilt mechanism.
this S019 operation was aborted and no data was acquired.
As a result,
Through
extensive malfunction procedure checkout and finally, disassembly of the
AMS tilt mechanism, the crew discovered an Allen screw binding on a
�small gear of the tilt mechanism.
This was corrected and the unit
functioned properly during the remainder of the experiment's data
acquisition operations.
During the repair of the AMS tilt mechanism, the m i r r o r was inadvertently
touched leaving a finger print on the mirror.
At the request of the
Principle Investigator (PI), no corrective procedure was implemented,
to remove the finger print.
This was to prevent possible additional
damage to the mirror surface.
Trying to clean the mirror could have
been more degrading to the mirror's viewing function than the imposed
finger print.
During SL-3 operations of S019 it was reported that the luminescence
h a d c o m e o u t o f t h e d i g i t s o n o n e of t h e r o t a t i o n d i a l s .
However, by
close inspection, the operator could still distinguish the engraved
impressions of the digits to permit proper operation of the rotational dial.
The S019 spectrometer mechanism jammed during retraction following
a SL-3 pass.
Retraction was eventually accomplished some 30 hours
subsequent to the initial failure and normal operations were restored.
Due to this S019 experiment retraction failure, warm-up procedures
for all experiments placed in the SAL were observed prior to exposure
of their mechanism to OWS environment for all subsequent experiment
operations.
�During a SL-3 S019 pass the crew reported that the film advance/
shutter lever stopped at the carriage retracted position, and could not
be moved on to the slide retracted position.
This film canister was
replaced with the new canister and the remaining exposures were taken
as scheduled during SL-3.
The failed canister was taken to an area of
subdued light (the head, with lights out and door closed), the cover was
removed, and the sliding film hatch was opened.
Inspection by feel was
performed on part of the carriage and shutter mechanism.
The crew
identified no apparent damage or discrepancy that could be corrected by
their action.
Consequently, the film canister unit was returned to earth
for malfunction analysis.
It was found from the review of acquired data that during performance of
the S019 experiment, the system was extremely sensitive to motion and
some blurs occurred on one S019 slide.
It was felt that this could have
been caused when the canister was used as a writing surface.
The PI
requested that the S019 system not be touched when taking data.
was necessary to the acquisition of clear photography.
This
The crew had
no difficulties complying with this request except when opening or closing
the shutter.
At this time momentary jiggling of the S019 system could not
be prevented.
Although S019 operations were not originally scheduled for SL-4, the
�SL-4 mission extension created additional crew experiment time and
allowed assignment of S019 to SL-4.
New S019 film canisters
replacement S019 mirror were launched.
and a
During replacement of the
S019 AMS mirror the crew reported the new mirror was dusty and had
three very narrow white streaks.
The new mirror was touched by the
crewman leaving a 3/4 inch long smudge which extended 3/ 16 inch in
from the edge.
This was caused by the gloves being packed under the
mirror and the crewman having to remove the mirror bare handed.
Numerous problems were experienced with the S019 canisters jamming
during SL-4.
The canister would not go into the slide retract position and
the problem was believed to be with the nylon sleeve on the film slides.
The first canister to jam was placed in stowage however when the second
canister jammed the crew decided to use brut force to put the lever in
the slide retract position.
The canister then operated normally
except higher forces were required on the operating mechanism.
This
canister eventually jammed again and broke when the crewman forced
it into the slide retract position.
Malfunction procedures were
performed but the canister was considered completely broken.
The
first canister was operated using excessive force but the crew felt it
could jam at any time.
Both canisters were returned for evaluation.
�There was a continual gradual degradation in the indicator on the rotation
dials of the AMS.
In addition to the luminescence coming out of the units
digit,the crew reported they were experiencing slippage between the mirror
rotation attitude control knob and the indication dial.
The belt broke and
the degree indicator did not move even though the crank was turning.
No
repair was attempted due to the radioactivity from the luminescence in
the sealed dials.
For all subsequent operations the crew had to count the
number of turns of the crank to determine the rotation settings.
The T002
sextant was used to check misalignment of the m i r r o r .
A failure of the S019 reticle light was identified on one S019 canister.
The crew reported earlier that the reticle light was dim and it was assumed
that the battery charge was too low to illuminate the bulb.
The bulb and
battery were not replaceable but the reticle was for reference only and
no data was lost due to the failure.
No corrective action was necessary
except the crew turned off the reticle light when it was not required to
verify pointing accuracy.
An additional S019 operation requirement was incorporated during SL-4
to reduce possible S019 data degradation due to OWS influenced disturbances
o n t h e SO 1 9 p o i n t i n g a c c u r a c y .
During SL-4 all ergometer and Mark I
exerciser operations were prohibited during S019 operations.
�c.
Assessment/Recommendations -
The crew recommended
that the first couple of S019 pads be relatively easy to give them a chance
to re-familiarize themselves with S019 operations.
The crew felt that
80% of all crew e r r o r s would probably occur during the first runs of the
experiment.
They also stated that S019 procedures needed to be updated
with more exact information concerning photography exposure times.
Differences existed between the forces required to operate the controls
of the different S019 canisters.
Some canister's carriage retract systems
operated easily while others were quite stiff.
normal as they were not all the same.
The PI stated that this was
The operating controls should have
been designed with appropriate stop positions to eliminate the necessity
of counting crank turns to the full extended or full retracted position.
The crew also recommended not using the locks on the shaft rotation or
extension controls as they were no longer required after placing the
controls in the unlocked position.
The S019 timelines were too close and the crew recommended that 30
seconds to 1 minute be allocated for the operator to perform a change
in S019 pointing.
They also suggested allowing 15 to 30 minutes extra
to the timeline for the first running of the experiment to allow familiarization
with the equipment.
�The crew requested that the same crewman not be asigned to an ATM
pass and a S019 pass with no time in between.
Otherwise any falling
behind in the ATM pass immediately impacted the S019 operations.
The
crewman should be allowed to go into S019 with nothing else on his mind
and not cluttered with what he had just finished.
The crew suggested having a T-handle on top of the winding valve instead
of the knob.
The knob was very slippery when their hands were moist
and a T-handle would have been better for winding the film.
E x p e r i m e n t SO 1 9 h a n d l i n g w a s e a s y o n o r b i t c o m p a r e d t o g r o u n d h a n d l i n g .
The crew felt that the carrying handle for the optical canister was a
necessity.
T h e p r o c e d u r e s f o r c h a n g i n g t h e v i e w i n g c o o r d i n a t e s d u e t o t h e NTJ Z
were very satisfactory but there was a definite source of potential error
with the sign and albegraic manipulations required to compute the
rotation.
The crew had never trained for these calculations and felt
that they should have had such training for the calculations to be apparent.
There was no problem with dark adaptation when operating experiment
S019.
The critical adjustments required to prevent dark adaptation
problems were the position of the eye to the eye piece and the focus.
The repair work performed on the AMS tilt mechanism would have been
�aided by the addition of a Skylab Inflight Maintenance facility composed
of a work bench and a high intensity light.
An optics cleaning kit would
have been valuable to remove the finger print contamination from the
AMS mirror and should be provided on future flights.
13. 22. 2. 3
S020 - UV X-Ray Solar Photography
a. Operations - Experiment S020 was scheduled to be performed
on SL-3 and SL-4 through the solar Scientific Airlock (SAL) to photograph
x-ray and extreme ultraviolet spectrums of the sun in wavelength regions
from 10 to 200 A.
Two crewmen were to perform the setup and checkout of the experiment
in the SAL.
When notified that a solar flare might occur, the crewmen
were to point the equipment at the solar disc and obtain quiet on active sun
flare exposures as required.
b.
Usage/Anomalies - Due to the parasol thermal shield
occupying the solar SAL, additional operating methods were devised.
special EVA bracket was designed and launched on SL-3.
A
The EVA bracket
was fit checked and an operational decal was installed by the SL-3 crew.
S020 was successfully performed on three SL-4 EVA's with
exposures up to one hour being obtained.
During deployment of the S020 camera the crew experienced some slight
difficulty in attaching the mount to the ATM truss.
the knob to tighten it the whole mount twisted.
In screwing down
The ball joint on the
mount was also difficult to adjust and the crew felt a larger ball would
have made it easier to adjust.
�During S020 preparation for the final SL-4 EVA the crew reported a
number of pin holes in each of the two filters.
Some were detected by
the naked eye and others were detected with a flashlight and magnifying
glass.
It was felt that the size of the holes a s described by the crew
would not allow enough light through to cause any problems.
c.
Assessment/Recommendations - The interface between
the S020 equipment and the EVA bracket was well designed.
The experi
ment hardware and procedures were adequate and experiment operations
were accomplished without any anomalies being reported.
13.22.2.4
S063 - UV Airglow Horizon Photography
a. Operations - Experiment S063 was scheduled to be
performed on SL-3 and SL-4 to photograph in the visible and ultraviolet
(UV) spectra the earth's ozone layers and twilight airglow.
The equipment to be used included the visible and UV cameras, with
related accessories, and the respective mounting structures for the
related cameras at the Scientific Airlock (SAL) and wardroom windows.
One crewman was to attach the cameras to the SAL or wardroom window,
make appropriate exposure time and shutter settings, and perform
exposures during approximately 28 selected orbits of the mission.
�b.
Usage/Anomalies -
Some difficulty was experienced
during the loading of a new Nikon camera for S063 operations.
Upon
investigation it was found that a bit of epoxy-like material prevented
the film system from positioning properly.
The crew removed this
material with a knife and the camera operated satisfactorily for the
remainder of the mission.
Due to solar SAL obstructions by the parasol thermal shield, the S019
Articulated Mirror System (AMS) was utilized to obtain some of the S063
data.
�During initial S063 operations there was a problem with a timer mal
functioning.
Analysis established that the motor drive switch was out
of configuration and that the timer was being operated incorrectly.
This
problem necessitated the use of the crewman's wristwatch in conjunction
with the timer for all subsequent S063 operations.
Additional lighting was required for S063 operations as the crewman had
to use
a
flashlight to read the watch and timer.
The crew also requested
an additional 45 seconds preparation time between S063 exposures. At the reque
of the crew, information on how to interpret the S063 optical sight reticle
was provided by the ground and posted next to the experiment for future
reference by the crew.
S063 operations called for eight second exposure times but due to a problem
encountered in setting the viewing equipment some exposures may have
been 10 second exposures.
The marker on the viewing equipment had a
bright edge and light glinted off the leading edge of the marker through
the window.
The viewing equipment was set on this leading edge rather
than the white mark.
This added about two seconds to the exposure.
One visible photography portion of a S063 run was not obtained because
a battery powering the visible camera had tape covering one terminal.
This tape was removed and no futher problems were encountered with
the battery.
�The crew reported that during hand-held photography through the ward
room window they tended to point the camera so as not to view through
any of the contamination on the window.
During SL-3 it was noted that an adapter between the AMS and the S063
window was missing a bolt.
This missing bolt did not interfere with S063
operations but a requirement for a replacement bolt was provided for SL-4.
The crew also reported fixing a looseness of the interface between the
mounting shear and the optical sight of the camera.
Tape was used to
tighten and thus reduce the wobble in this interface.
This provided better
resolution than previously with the camera wiggle in the system.
During the initial SL-4 S063 operation the remote timer did not operate.
This complicated the S063 operation in that the crewman had to use manual
timing in addition to tracking and controlling the rotation and tilt settings.
The problem with the timer occurred when the crew mistakenly used a
timer without any batteries.
the problem.
A new battery in the remote timer fixed
For subsequent operations the crew removed the batteries
after each use and taped them to the timer to insure nothing in the timer
would drain the batteries down.
The crew reported the ring site was looking in the wrong direction and
that it should be looking more towards the axis.
Part of the sight was
obscured such that you could not see the whole mirror.
The crewman
�assumed that although his sight was getting a truncated view the camera
was getting the full view,therefore he centered it in the circle and not the
truncated portion of the field of view.
The crewman found that by looking
right below everything, straight at the AMS mirror,he could get a better
field of view than looking through the sights.
A problem was experienced with the S063 reticle light not illuminating.
The crew checked the prime and backup batteries and they checked out
a t 1.6 v o l t s c o m p a r e d t o a 3 . 1 v o l t s p r e f l i g h t .
The battery contacts were
scraped however neither battery would illuminate the reticle light.
A
substitute battery pack was fabricated from two (2) spare "C" cells, tape,
and two (2) multimeter leads.
The substitute battery pack was installed by
inserting the probe ends of the leads into the female terminals of the
optical sight housing and normal reticle operation was restored.
c.
Assessment/Recommendations - The SO63 stowage and
unstowage went as planned and the S063 procedures related to the equip
ment went very well.
In some instances the crew had to hurry to get
two photographs on the same target, but the tracking task using the
hardware was reasonable.
The time allocated for stowage and preparation
for S063 and AMS equipment was adequate.
The stowage location of the twin filter underneath the S063 stowage
container lid was inadequate because of poor lighting and visibility in
�in the area.
This filter stowage inadequacy was identified in training
but never corrected.
The crew stated that they should have had one extra Nikon camera body
and a minimum of six extra cassettes of 2485 fast film for photography
of targets of opportunity.
to properly photograph
board.
A great opportunity may have been missed
the Aurora because these items were not on
The crew recommended replacing the Hasselblad in the CM with
a Nikon.
The crew recommended that some type of suction-cup type mount be
supplied for cameras used in hand-held photography.
could then be restrained at any window.
These cameras
Such a restraint should be light,
have a shutter release, and so provisioned that it could be moved to any
position.
The crew recommended that the Principle Investigator (PI) provide a
small color chart identifying the different shades of gray or white that
the night airglow might look like to the crew.
This would make identification
easier for the crew and provide a commonality point between ground and
on orbit data.
Crew training for experiment S063 appeared to be inadequate as the timer
was operated incorrectly and the crew had to request information on how
to interpret the S063 reticle.
The crewman stated that the problem with
the timer was 25% incorrect configuration and 75% his e r r o r .
�The SL-4 crew stressed that due to the lack of a simulator the first
couple of runs with the S063 would have to be accepted a s training sessions.
Any operations that called for manual dexterity could not be learned by
talking through them.
The crew stated they had more difficulty with
S063 than with other more complicated experiments which they had
trained for.
Even with a relatively simple task, when you encounter
something new, a couple of familiarization runs a r e required before
it goes smoothly.
There was a confusion factor in determining the frame count from the
UV Nikon camera.
The frame count on the top of the Nikon read
differently than the frame count on the bottom of the c a m e r a .
decided to use only the bottom frame count indicator.
only one frame count indicator provided on a camera.
The crew
There should be
�13. 22. 2. 5
S073/T027 - Gegenschein Zodiacal Light and ATM
Contamination Measurement
a.
Operations - Experiment S073/T027 was scheduled for
operation during SL-2 and SL-3.
The purpose of S073 was to measure
surface brightness and polarization of night glow in visible spectrum.
The purpose of T027 was to determine changes in properties of optical
samples due to deposition of contaminates and to measure sky brightness
background due to solar illumination of contaminates.
The experiment employed the T027 Photometer canister with the automatic
programmer.
The combined photometer system and Data Acquisition
Camera (DAC) system, which was attached to the T027 Universal
Extension Mechanism (UXM), was to be mounted to and deployed through
the SAL into the space environment for acquisition of data.
S073/T027
was to require one crewman for operation.
b.
Usage/A noma lies - During SL-2, the S073/T027 photometer
system was activated and operated with no major difficulties.
ware anomalies were identified.
No hard
During one T027 retraction, the photo
meter system could not be lined up to effect/permit its retraction
into the Scientific Airlock (SAL) and the T027 canister.
This was a T027
�systems operations problem in that the system had been driven hard
over, past the desired alignment.
After being bumped against the OWS
and physically forced, the system was retracted into the SAL and T027
canister as required.
During SL-3, the first crew operations with the T027 UXM system was
to retract the S149
system which had been left extended through the SAL
during the unmanned period between SL-2 and SL-3.
with some difficulty.
This was accomplished
The final extension rod lacked about one inch from
full retraction and engagement of the UXM capture latch.
the SAL door was closed to permit warm up of the system.
up, the final retraction was accomplished.
At this point
After warm
The T027/S149 system was
removed from the SAL and stowed as required.
The SL-3 crew had performed the T027 photometer extension and data
gathering for only a short time when during the retraction mode it failed
to align to the required position to permit its retraction as had previously
occurred during the SL-2 mission.
All malfunction operations performed
on the system to effect its retraction failed.
Consequently, the UXM
with the photometer and S073 system attached was jettisoned on MD-8
of SL-3.
�The SL-3 and SL-4 crews utilized the T025 hardware to perform some
S073 Gegenschein and Zodiacal light photography.
The equipment was
installed upside-down in the anti-solar SAL and the occulting disc was
moved out of the cameras view.
No anomalies were reported with this
mode of operation.
c.
Assessment/Recommendations -
Experiment T027 handling
was a one man operation and was facilitated by the canister handle's proper
location through the center of gravity.
On movable items of large volume
and mass (i.e. T027, S183) handles were definitely required.
These
handle(s) should be located such that the crewman would have complete
control of the object during maneuvering operations.
No problems existed during photometer head changeout/maintenance even
with the compressed operational envelope caused by the parasol canister/
tripod protrusion.
Instead of restowing T027 in its launch container
between operations, the crew recommended that leaving the photometer
attached to the launch container lid become the nominal stowage procedure.
As T027 operations progressed, the crew noticed that the photometer
UXM rods became increasingly difficult to screw together.
This was
thought to be caused by a buildup of moisture and contamination.
Also,
during rod retraction, the crew reported that the thermal gloves were
indeed required and did not hinder the crewman's rod retraction operations.
The SL-3 crew indicated that the T027 system should have been checked
out completely and possibly operated inside the OWS prior to its use.
�13.22.2.6
S149 - Particle Collection
a.
Operations - Experiment S149 was scheduled to be
performed in four different exposure periods; during SL-2, the unmanned
period between SL-2 and SL-3, during SL-3, and the unmanned period
between SL-3 and SL-4.
Its design objective was to acquire data to assist
the determination of mass distribution of micrometeorites in near-earth space.
On orbit, the S149 Motor Drive/Cassette Support Unit (MD/CSU) was to
be unstowed, fitted with the detector cassettes, and attached to the 1027
Photometer Universal Extension Mechanism (UXM).
The T027 canister
was to then be installed in the anti-solar SAL and the S149 MD/CSU
extended into space.
Power was to be applied to the experiment and
switches configured for ground activation of cassette exposure.
In the
event of a ground command failure, the experiment had a manual control
capability which could be operated by the crew.
At completion of the exposure time, the crew was to be notified and was
to retract, remove, and stow the hardware.
The S149 detector cassettes
were to be removed from the MD/CSU and stowed in the CM for earth
return.
b.
Usage/Anomalies - During SL-2 the first of four s e t s of
S149 detector cassettes was deployed through the anti-solar SAL.
Prior
to crew return to earth, ground commanded the MD/CSU to "Open" for
cassette exposure and subsequent data collection between missions.
A problem was reported by the SL-3 crew during retraction of the SL-2
�deployed S149 MD/CSU.
During retraction operations by the crew, the
UXM tended to extend back out to space by itself.
The crew had to
maintain a continuous retraction force on the UXM rod while the SAL
door was closed (this involved a two man effort).
closed the system still lacked full retraction.
Once the SAL door was
The final extension rod
lacked about one inch from full retraction and engagement in the UXM
capture latch.
After allowing the system to warm up, the full retraction
and engagement of the capture latch was accomplished.
The T027 UXM
system canister containing S149 was then removed from the SAL, dis
mantled and stowed.
Prior to the SL-3 deployment of the second set of S149 detector cassettes,
the T027 Photometer / UXM malfunctioned and was jettisoned, thereby
losing the hardware required to nominally deploy and expose the S149
detector cassettes.
As a back-up method for S149 deployment, hardware
had been fabricated and launched on SL-3 for EVA deployment.
Therefore,
during the first SL-3 EVA, the crew mounted the S149 MD/CSU and
bracketry on the ATM thermal shield lip and manually exposed the detector
cassettes.
It was later retrieved by EVA on SL-3 and the two sets of
detector cassettes were stowed and returned to earth.
On SL-4 the third set of cassettes was deployed and later retrieved by
EVA.
During retrieval the crew reported that the small discs on S149
�were debonding and popping off.
Several discs were lost and the others
were peeling up due to their bonding not holding.
stowed and no further action was taken.
The experiment was
The fourth set was deployed
during the final SL-4 EVA and has been scheduled for possible retrieval
during the Apollo-Soyuz Test Program (ASTP) in 1975.
�c.
Assessments/ Recommendations - S149 hardware, for both
nominal and contingency operations, was well designed and operated
as planned.
The contingency hardware used in EVA deployment
of S149 functioned well during EVA.
The bracket used in mounting the
MD/CSU on the ATM thermal shield was a little loose but caused no
problems.
The ATM thermal shield paint was scratched as the mounting
clamp was attached but this was not considered to be detrimental.
Concern was stated that proper precautions be taken to mark the return
container that housed the exposed cassettes to assure that the CM
returned cassettes were those that had been exposed.
13.22.2.7
S183 - Ultraviolet Panorama
a.
Operations - The S183 experiment was scheduled for
performance during each of the Skylab missions to obtain photographs
of a wide field of view of individual s t a r s and extended s t a r fields in the
ultraviolet.
P r i o r to activation of S183 for operation, the crewman was to be required
to prepare the S183 support hardware; the Scientific Airlock (SAL) and
�the S019 Articulated Mirror System (AMS).
Once the SAL was prepared,
the S019 AMS, used for S183 pointing, was to be inserted.
The S183
e x p e r i m e n t w a s t o b e u n s t o w e d a n d a t t a c h e d t o t h e SO 1 9 A M S .
The S183
film carrousel was to then be removed from the OWS film vault and
installed into S183 along with a 16mm Data Acquisition Camera (DAC)
for comparison photographic data.
The crewman was to then power up
S183, open the SAL door and extend the AMS mirror.
The S019 AMS
mirror was to be aligned to the desired starfield and S183 photography
was to commence as outlined by the checklist.
Once this photographic
sequence had been completed, the S183 experiment was to be deactivated,
the S019 AMS retracted and the SAL closed.
The experiment hardware
was to be dismantled, removed from the SAL and stowed.
b.
Usage/Anomalies - Throughout the entire Skylab mission
all crew comments and other related data to on-orbit operations of S183
experiment identified no operational/handling anomalies.
Problems
experienced with the S183 system were of a mechanical nature.
After
two nominal SL-2 performances with S183, the film plate jammed and
the operations were discontinued.
Malfunction procedures were performed
and the problem was isolated to the film carrousel.
Due to this problem
all subsequent photographic data for the SL-2 and SL-3 performances
was obtained through use of the 16mm DAC.
One other anomaly was
�reported and involved a focus problem with the 16mm DAC.
Changing
to another DAC did not alleviate the problem but indicated that the S183
DAC optic system was the problem.
On SL-4 a replacement DAC optic system was launched and interchanged
with the original.
S183 DAC.
This corrected the focus problem associated with the
In conjunction with the optics replacement, the crew
performed additional malfunction procedures and were successful
in correcting the S183 film carrousel anomaly.
This permitted the
experiment to be operated as scheduled throughout the mission to acquire
S183 photographic data as originally planned.
Both DAC optic systems were
returned for evaluation.
Upon removal of the carrousel from the spectrograph during the second
S183 operation on SL-4, a fragment of the SC-5 glass film plate was
discovered.
It was reported that the carrousel was misaligned 45° from
the "00" position.
A plate was protruding and the crewman pushed it into
the carrousel and stowed the carrousel.
Prior to the next operation an
alignment procedure was performed with no problems or loose glass
being reported.
position.
Pliers were used to rotate the carrousel 45° to the "00"
During the fourth operation of the spectrograph an additional
fragment of the SC-5 plate was discovered.
glass was jamming the carrousel.
the plate was unsuccessful.
It was concluded that the
A malfunction procedure to remove
In addition, an "E" clip retaining a spring
�used to force the carrousel into the indexing detents was lost.
This did
not eliminate the use of the carrousel but it did require that the crewman
check the orientation marks prior to each usage.
Extreme care had to
be used when inserting the carrousel into the spectrograph as any sudden
torquing around the cylindrical axis would misalign the unit and cause
difficult if not impossible installation.
The SL-4 crew experienced sequence problems with the logic counter
and the carrousel index due to hardware problems and procedural mix-ups.
The SL-3 crew had failed to reset the logic counter.
The SL-4 crew cycled the
plate advance reset switch and returned the reading to 01.
However the
logic counter i s completely independent of the carrousel indexing and
the film carrousel rotated to plate 33 and not back to plate 1.
This
resulted in plate 34 becoming detached from the carrousel and thus being
exposed to cabin light.
The extent of the anomaly appeared to be the loss
of one plate and degradation of two others.
The operation of S183 spectro
graph and film carrousel was not affected.
In an effort to eliminate the
condition which caused the film plate to slip out of place a malfunction/
synchronization procedure was done to sychronize the carrousel with the
logic counter.
The SL-4 crew experienced a jamming problem with the DAC camera and
S183 magazine 04.
After performing trouble shooting procedures the
�problem was isolated to a blown fuse inside the S183 spectrograph
assembly.
The malfunction was duplicated on the quality test unit in
France and the French experiment developer recommended a workaround
procedure which would bypass the blown fuse by connecting an existing
wire from a DAC connector on the spectrograph assembly to an adjacent
connector.
The procedure was successful and S183 operations were
resumed with the carrousel.
c.
Assessment/Recommendations -
The S183 experiment
activation and manipulation was easily a one-man operation.
The latching
technique and decals on the experiment launch stowage structure were
adequate.
The crew stated that for maneuvering the large mass of S183,
the handholds supplied were a definite necessity.
In addition, the crew
recommended that on large masses (i.e. S183, T027) it would be best
to have handles provided to facilitiate two-handed manipulation for better
control during large mass handling/maneuvering.
The maneuvering
technique used was to stabilize one's body and carefully push the mass
in front of oneself.
Then let the mass and oneself move to the terminal
location making positional corrections while in flight.
considered a problem.
Braking was not
This maneuvering technique was documented by
experiment M151, Time and Motion Study.
The S183 operations timeline did not allow enough time between exposures.
One minute was added to these times to allow for crew adjustments
�in pointing and timing for the upcoming exposure.
The crew also complained
about being rushed between an ATM pass and S183 operations.
The timeline
did not allow enough time to debrief the ATM pass and then get started on the
S183 operations.
During S183 operations, the crew reported no problems
associated with the OWS lighting levels.
13.22.2.8
S201 - XUV Electronographic Camera
a.
Operations - Experiment S201 was scheduled to be performed
on SL-4 to photographically collect Extreme Ultraviolet (XUV) imagery
data on comet Kohoutek.
The experiment consisted of a canister-enclosed XUV electronographic
camera (with film-transport box), a second film-transport box, and an
EVA bracket.
The experiment was to be used in two operating configu^itions;
(1) through the anti-solar Scientific Airlock (SAL) utilizing the S019
Articulated Mirror System (AMS) a s support equipment or (2) bracketmounted to the ATM truss for EVA operations.
Power was to be provided
by the Data Acquisition Camera (DAC) cable during the EVA and SAL
operations.
Experiment S201 data was to be recorded on special NTB-3
film and returned to the Photographic Technological Laboratory at JSC
for post-flight processing.
b.
Usage/Anomalies - While performing a S201 experiment
operation through the anti-solar SAL the crew noted that the green
exposure sequence indicator light was actually brownish red and very
low in brightness and would probably be difficult to read during the EVA
operations.
During the second SL-4 EVA, three S201 data takes were
�performed even though the crew could not see the comet.
It was hoped
that the comet would be detectable on the photographic data.
c.
Assessment/Recommendations - S201 experiment operations
were performed as scheduled through the anti-solar SAL and during the
SL-4 EVA's.
The procedures and equipment were adequate and the crew
reported no significant problems in performing S201.
13.22.2.9
S228 - Trans-Uranic Cosmic Rays
a.
Operations - Experiment S228 was scheduled to be performed
on SL-2, SL-3, and SL-4 to obtain knowledge of the abundance of nuclei
with an atomic number greater than 26 in the cosmic radiation.
A crewman was to deploy the detector module harness on SL-2 from floor
to ceiling in the OWS experiinent compartment using velcro straps.
Thirty-
six detector modules were to be launched and deployed with the harness.
At the conclusion of the SL-3 mission, one module was to be removed
and returned.
One S228 detector module was to be launched on SL-4
and deployed during the first SL-4 EVA.
It was to be retrieved during
the last SL-4 EVA and returned to earth along with the remaining harness
detector modules.
b.
Usage/Anomalies - Experiment S228 was performed as
scheduled and no anomalies were reported.
During the SL-4 EVA deploy
ment, the crew observed some expansion of the experiment package which
was an indication of outgassing.
normal limits.
This bulging was expected and was within
On the final Skylab EVA, this experiment package was
�retrieved and was stowed with the remaining harness detector modules
for return to earth.
c.
Assessment/Recommendations - Experiment S228 deploy
ment and retrieval went as scheduled and no crew systems assessments
were reported.
�13.22.2.10
a.
S230 - Magnetospheric Particle Composition
Operations - Experiment S230 was scheduled for perfor
mance during SL-3 and SL-4 EVA's.
Its purpose was to acquire data for
measuring fluxes and composition of precipitating magnetospheric ions
and trapped particles through the use of a foil collection technique.
The experiment hardware was composed of two (2) collector spools,
two (2) inner collector assemblies, two (2) outer collector assemblies
and two (2) return pouches.
The collector spools, providing support
for the inner and outer collector assemblies, were to be launched on SL-1
attached to the ATM deployment truss D2 handrail.
During an EVA on
both SL-3 and SL-4 the crew was to retrieve one (1) of the two remaining
collector assemblies.
These collector assemblies were to be stowed
and returned to earth for analysis.
b.
Usage/Anomalies - On the first SL-3 EVA the two (2) outer
collector assemblies of S230 were retrieved and a calibration shield was
installed on the forward inner collector spool.
During the final SL-3
EVA the crew retrieved one of the two remaining inner collector
assemblies.
It was stowed in the CM with the previously retrieved
outer collector assemblies and returned to earth.
On SL-4 a new inner collector assembly was launched and on the first
�SL-4 EVA was attached to the empty collector spool.
During a sub
sequent EVA for ATM film resupply and Kouhotek photography the
crew reported that the S230 calibration shield was missing.
Evidently,
the shield had been brushed by one of the crew during EVA operations
and knocked loose.
On the final SL-4 EVA the remaining two (2) inner
collector assemblies were retrieved.
During AM repressurization
operations, one of the two samples was damaged by the rush of air from
equalization valve 311.
10% of the sample.
The crew reported the damage to effect approximately
The samples were placed in the CM stowage and
returned to earth.
c.
Assessment/Recommendations - The EVA procedures
for the collector assembly retrievals were straightforward and no problems
were reported.
The crew reported that they were very careful during
retrieval so as not to touch and consequently contaminate the collectors.
The calibration shield and the one (1) collector assembly deployment were
performed without any reported crew interface problems.
The restraint/
stability provisions were considered adequate for performing the S230
crew tasks.
�13.22.2.11
a.
S232 - Barium Plasma Observations
Operations - Experiment S232 was scheduled to be per
formed on SL-4 to obtain data necessary for determining the effects of
plasma conductivity and geomagnetic activity upon the motion of barium
plasma.
The experiment operations involved one crewman whose objectives were
to photograph the barium cloud injected to outer space by a ground launched
rocket.
The crewman was notified three hours prior to the scheduled
launch as to the photographic settings and procedures.
A Nikon 35mm
camera was attached to the universal mount and then mounted to the OWS
wardroom window to obtain the photographic data.
A total of seven barium
rocket launches were scheduled during SD-4 with the crewman obtaining
a minimum of 40 photographs.
b.
planned.
Usage/Anomalies - Experiment S232 was performed as
Due to problems involved with the rocket launches and resulting
launch cancellations all premission planned photographic data was not
obtained.
The crew reported that the experiment set-up was a lengthy
operation and took approximately two (2) hours to complete.
The barium
injection was visible to the naked eye and was photographed by the crew
using numerous time exposures.
During these photographic sessions the
crew reported some difficulties with damping the oscillations of the
camera/universal mount after exposure actuation.
As the experiment
�progressed and the crew technique improved these oscillations were
reduced.
c.
Assessment/Recommendations - S232 experiment photo
graphy was performed during SL-4 and photographs of the barium plasma
infection were obtained.
Other than the initial oscillation problem with
the camera/universal mount the hardware performed satisfactorily.
13. 22. 2. 12
a.
S233K - Kohoutek Photometric Photography
Operations - Kohoutek Photometric Photography, experiment
S233K, was scheduled to be performed during SL-4 to obtain a series of
visible light photograph's suitable for photometry and to provide a synoptic
history of the comet Kohoutek.
Experiment S223K used the Nikon 35mm camera and mounting braketry
to obtain photographs through the left viewing window of the CM and the STS
window.
The crewman was required to take a sequence of photographs
every 12 hours throughout the comet acquisition periods.
b.
Usage/Anomalies - S233K was performed throughout the
designated periods of SL-4 and photographs of comet Kohoutek were
obtained.
All pre-mission scheduled photographic exposures could not
be obtained by the crew due to window field of view limitations and
faintness of the comet.
c.
Assessments/Recommendations - The S233K operations
were straightforward and were performed as scheduled.
anomalies were reported.
No hardware
�13.22.3
Technology Experiments
13.22.3.1
D024 - Thermal Control Coatings
a.
Operations - Experiment D024 sample panels retrieval
was scheduled for the SL-2 EVA and for the last EVA of SL-4.
The
equipment for experiment D024, consisting of two thermal control coating
sample and two polymeric film sample panels, was mounted and launched
�externally on the AM support structure.
Experiment D024 was not to require a specific EVA for its performance
as it was to be performed in conjunction with the ATM experiments
film retrieval.
D024 sample retrieval was to require two crewman
(designated EV1 and EV2).
EV2 was to retrieve two sample panels, stow
them in the return container, then pass the container to EV1 who was to
temporarily stow it in the AM.
Upon completion of the EVA activities
the sample return container was to be stowed in the CM for return to
earth.
b.
Usage/Anomalies - Experiment D024 sample panel retrieval
was performed as scheduled on SL-2 with one thermal control coating
sample panel and one polymeric film strip sample panel being returned.
Due to the total time in orbit it was decided that the remaining two sample
panels had received adequate exposure by the end of SL-3 and that they
should be retrieved on the last EVA of SL-3 and returned to earth.
To
alleviate handling of multiple items the crewman placed the sample into
the return container prior to removing the pip pin.
It was noted that
some of the samples were becoming slightly debonded, although none
were actually loose or lost as the samples were put into the return
containers.
After the return of the remaining two samples on SL-3,
two additional sample panels with return container were launched on SL-4
for deployment on the first EVA and retrieval at the end of the mission.
�During deployment of the sample it was difficult for the crewman to
align the snaps due to lack of visibility and lack of dexterity caused by
the EVA glove.
However, he was eventually able to attach the panel by
touching the center samples with his finger, possibly contaminating them.
The samples were retrieved on the final SL-4 EVA and returned to earth.
c.
Assessment/Recommendations - The problem the crew
experienced with the deployment of the sample panels could have possibly
been eliminated with the addition of guide pins and alignment marks on
the mounting plates and the sample panels.
However, the experiment
a s it was originally designed, did not call for the deployment of the sample
on orbit as they were launched in place.
The retrieval of the D024 samples was quite easy to perform per the
checklist.
The crewman was able to fold the retrieved specimen and
correctly stow it in the appropriate return container slot.
The crew
reported no problems in retrieving and stowing the D024 samples and
stated that the overall design was adequate.
The crew voiced their
opinion that a heel restraint would have been helpful at the D024 location
to assist their stabilization when retrieving samples.
13.22.3.2
M512 (M551, M552, M553, M555) - Materials Processing
In Space
M479 - Zero Gravity Flammability
M518 - Multipurpose Electric Furnace System
a.
Operations -
The M512 experiment facility was designed
to utilize a common spacecraft interface for a group of experiments in
�in materials science and technology.
It was scheduled to be used
on SL-2, SL-3, and SL-4.
The facility was to permit exploration of space manufacturing applications
of molten metal phenomena such as metal flow, freezing patterns, thermal
stirring, fusion across gaps, and surface tension.
be required to perform the experiments.
One crewman was to
The basic functions performed
were to be installation of the experiment equipment or specimen in the
work chamber, systems control operation, observation, photography, and
monitoring of the experiment, and removal and stowage of the equipment
and specimen after experiment completion.
Experiments M551, M552,
M553, M555, M518, and M479 were to utilize the M512 facilities.
b.
Usage/Anomalies - During initial use of the M512 facility
it was believed that the electron beam gun had shifted due to loads
experienced at launch.
Upon later analysis the problem was found to
be with a new mirror installed at KSC.
The mirror was reversed so
only one of two retaining screws could be fastened when mating it inside
the facility.
During a performance of the M553 experiment, difficulty was experienced
with the installation of the shield over the electron beam gun.
This
problem was caused by a hardware installation sequence error.
The
shield should have been installed first instead of last a s performed by
the crewman.
�Due to M512 operational problems the crew was asked to use the main
circuit breaker to shut off the M512 facility power when performing
experiment M553 spherical forming.
During cutting of the M553 speci
men stinger, the jaw of the cutting pliers broke.
Wheel number one of
the experiment was completed and wheel number two had two balls that
were not released and three that were released.
Wheel two was returned
to earth along with the released specimen balls from wheels one and two.
A long period of time was required to obtain a sufficient vacuum in the
facility on orbit.
To obtain the vacuum the crew had to leave the vent
valve in the "Vent" rather than the "Open" position during their sleep
period.
Experiment M479 was performed at the end of SL-4 with the only anomaly
reported being with the water quench system.
The lower nozzle appeared
to be completely plugged and the upper nozzle emitted only a dribble.
The
crewman completely reserviced the system but it still did not function
properly.
In order to get any spray at all the crewman had to grab the
accumulator knob and pull sharply on it to force water through the
system.
There was no time for extensive trouble shooting but the problem
was believed to be with a water supply valve not being turned on.
While burning sample number three the crewman stated there was an
operator error in that he left the chamber repress valve in the open
�position.
The only effect was the sample burned slightly longer.
c.
Assessment/Recommendations - M512 experiment perfor
mance on orbit was similar to on-ground training with exception of the
times required to heat or cool the experiment specimen and to obtain
a sufficient vacuum in the facility.
The crew stated that the training unit
was excellent, just like the flight unit, but they never experienced
pumping the facility to a vacuum during their training.
Consequently,
the first time the vacuum gauge was used on orbit the crew thought that
the slow bleed down time indicated a faulty gauge.
As experienced,a
longer time than expected was necessary to obtain an acceptable operational
vacuum in the facility.
During M553 operations in the M512 facility no problem developed with
the facility or the accessory equipment.
However, pressure build up
in the facility chamber during the firing of the electron beam gun occurred
more rapidly on orbit than experienced during training.
In some instances
the balls on the M553 experiment wheel stings formed a pear shape or did
not release.
The crew experienced no problems in handling the specimens
as long as they observed proper cool down times.
The crew enjoyed performing the M518 Multipurpose Electric Furnace
experiment because it was new and different.
The equipment worked
as designed and was easily installed into the M512 facility chamber.
The specimen cartridges were numbered (identified) in an excellent
manner to permit their insertion and cooidination.
The operations
�were clearly defined and no problems were experienced performing
the M518 series in the M512 facility.
The M551 experiment welds looked basically the same as during training
with the exception of a non-round dwell pattern on the stainless steel
specimen.
The welds built up quicker in flight than on the ground.
No
high external chamber temperatures were experienced during any of
the facility operations.
All M479 specimen samples were in excellent condition and the burning
had no effect on the view ports.
The view ports remained clean throughout
the experiment performance.
Restraints associated with M512 were no problem.
The foot restraint
grid was used only in the beginning of the experiment and was later
discarded.
Handholds were adequate.
�The M512 chamber hatch did not appear to have proper friction hinges
as per the experiment design requirements.
No detrimental crew
comments were received but during video downlink of M512 facility
operations the hatch was observed to be floating free
13.22.3.3
T002 - Manual Navigation Sightings
a.
Operations -
Experiment T002 was scheduled to be
performed on SL-2, SL-3, and SL-4 with batteries for the sextant and
stadimeter being resupplied on SL-3 and SL-4.
Sightings were to be
distributed uniformly throughout the mission on a non-interference basis.
The crewmember performing the experiment was to remove and stow
the wardroom window shield, obtain and install the T002 hood over the
wardroom window and obtain the sextant or stadimeter from locker W740.
The batteries for the sextant and stadimeter were to be installed by the
crewmember during experiment activation.
Wardroom lights near the
wardroom window were to be dimmed and the reticle light adjusted before
the crewman proceeded with the experiment sightings.
b.
Usage/Anomalies - Experiment T002 was performed on
all three Skylab missions and was satisfactorily completed.
Due to a
residue pattern formed on the wardroom window during SL-3 and SL-4,
the operator had to move around during his sightings to avoid viewing
through this residue.
affected his sightings.
He was concerned that his moving may have
�The SL.-4 crew emphasized the importance of body position and posture
in obtaining accurate sightings with the T002 sextant.
During an early
operation the crewman developed muscle cramps in his arms and legs.
The crewman devised a restraint system to hold him over to the window
using a long strap hooked over the S063 bar.
improved the accuracy of his sightings.
The crewman felt this
The crewman also stated that
there was a distinct difference in ease, ability and accuracy you get
whether the stars were located up and down relative to your body posture
or left to right.
c.
Assessment/Recommendations -
The T002 window hood
which was used to shield the wardroom window from internal reflection
was considered a definite necessity.
The crewman found it difficult to
hold the sextant steady during sightings and also felt it would be extremely
helpful to have the sextant readout inside the reticle so you would not lose
sight of the star while taking readings.
The stowage configuration and
location in locker W740 was excellent and the foot restraint provisions at
the wardroom window were considered adequate.
The crew stated it was difficult to remove their fingers from the pointing
control knobs on the sextant without moving it.
ment but
They could get a good align
when they released their fingers the knob would move slightly.
This created some mediocre scatter in the system.
The control knobs
should have been easy to move but not so sensitive that they could not
remove their fingers without moving it.
The crew also stated the knobs
on the filters were poorly designed in that they could not tell whether they
�w e r e in. o r o u t .
The crew experienced pointing difficulties due to the shape of the case and
the location of the strap.
This made it difficult to hold the sextant in the
proper position at the window.
The crew stated they needed phosflorescent
alignment marks to get the line of sight directed between two s t a r s .
They
also suggested the use of a colored filter s o that they would not lose track
of which star they were sighting.
sextant at odd angles.
This was a problem when holding the
The system should have been designed so that all
controls could be operated without the crewman removing his eyes from
the reticle sight.
13.22.3.4
T003 - In-Flight Aerosol Analysis
a.
Operations -
Experiment T003 was scheduled to be
performed on SL-2, SL-3, and SL-4.
Multiple measurements were to
be taken daily to determine the concentration and size distribution of
particles suspended in the OWS atmosphere.
A crewman was to transport the portable self-contained aerosol analyzer
throughout the OWS observing the readout and recording the data on the
T003 data cards.
At the completion of each mission the data cards
and the filter impactor unit from the aerosol analyzer were to be
returned to earth.
b.
Usage/Anomalies - Operation of experiment T003 went
as scheduled with all functional objectives being accomplished.
Results
�showed that the OWS was cleaner than most hospital operating rooms
with a particle count of 3000 per cubic foot.
The crew reported that T003
readout time was adequate for recording the data on the data cards.
The
only anomaly reported was a filter change which was missed due to a
tardiness of the detailed pads up-linked from the ground.
c.
Assessment/Re commendations - Experiment T003 operations
were straight forward and no problems were experienced in stabilizing
at the various sample stations.
The crew did report that the data cards
were not large enough to allow sufficient area to record all the information.
13.22.3.5
T025 - Coronagraph Contamination Measurement
a.
Operations - Experiment T025 was scheduled to be performed
on SL-2, SL-3, and SL-4 through the solar Scientific Airlock (SAL) to
determine the existence and presence of any changes in particle atmosphere
due to transfer firings, waste dumps, vehicle orientation, and time decay
of such atmospheric concentrations.
The T025 experiment equipment to be used was the coronagraph canister
including the occulting discs and extension boom assembly with the
photographic equipment.
One crewman was to set up the experiment
apparatus in the SAL and complete a 27 photographic exposure sequence
during five (5) non-consecutive orbits.
�b.
Usage/Anomalies - T025 was not performed as scheduled
because the solar SAL was occupied by the parasol thermal shield.
All
T025 operations were cancelled for SL-2 as alternate performance
methods had to be developed.
The SL-3 crew utilized the T025 hard
ware to obtain some experiment S073 Gegenschein and Zodiacal light
photography.
The equipment was installed upside-down in the anti-
solar SAL and the occulting disc was moved out of the c a m e r a ' s view.
During this operation the crew used their finger to control the Data
Acquisition Camera (DAC) shutter release.
fatiguing.
This was difficult and
In readiness for subsequent operations the DAC was prepared
for operation with the DAC push button cable.
However, the SL-3 crew was
not asked to repeat the experiment.
As an alternate method of performing T025 and viewing the Kohoutek comet,
an EVA bracket was designed and launched on SL-3.
The SL-3 crew fit
checked the bracket to the T025 experiment and attached operational decals
readiness for EVA deployment on SL-4.
Problems occurred during the first SL-4 EVA operation of T025 which
prohibited the acquiring of all planned data.
planned 40 were obtained.
Five photographs out of a
The view finder on the camera was loose and
the shutter speed knob came off during operation.
The crewman was able
to replace the knob but it did not engage enough to permit use.
During
�EVA trouble shooting with the T025 equipment, the thermal blanket
cover was removed.
The T025 hardware was stowed in the AM to
permit further trouble shooting at a more opportune time in the OWS.
After completion of the EVA, the crew successfully repaired the shutter
speed knob and the T025 hardware was utilized during subsequent EVA's
to obtain ultraviolet and visible photographs of the Kohoutek comet.
All
subsequent T025 experiment performances were without incident.
c.
Assessment/Recommendations - The T025 experiment
was performed from the SAL without any problems.
The T025 hookup
with the extension rod worked very well and the procedures/checklists
and hardware used for night photography were adequate.
Pad updates
for the experiment should remind the crew to inhibit the fire sensors
prior to experiment initiation.
The fire alarm was initiated on SL-3
when the SAL was opened with T025 installed.
T025 was not originally designed for EVA use but with the addition of
the specially designed EVA bracket ultraviolet and visible photographs
of the Kohoutek comet were obtained.
13.22.3.6
T027 - Sample Array
a.
O p e r a t i o n s - T h e T 0 2 7 S a m p l e A r r a y (SA) e x p e r i m e n t w a s
scheduled to be performed during SL-2 to acquire data for determining
the change in optical properties of various transmissive windows, mirrors,
and defraction gratings, caused by deposition of contaminants found
�about the orbital assembly.
The experiment equipment included a canister system with one extension
rod, an ejection rod, and a launch stowage container.
One crewman was
to prepare the T027 SA experiment and then install it through the antisolar Scientific Airlock (SAL) for exposure to the space environment.
Upon completion of the exposure the SA was to be retracted, removed
from the SAL and re stowed in its launch container for return to earth.
b.
Usage/Anomalies - The T027 SA experiment was installed
in the SAL and deployed as planned.
Due to the parasol deployment and
resulting requirements for usage of the anti-solar SAL by other e x p e r i
ments, the T027 SA exposure time was reduced.
It was then removed
from the SAL, stowed in its launch container and returned for earth
analysis.
T h e o n l y p r o b l e m i d e n t i f i e d d u r i n g o p e r a t i o n of t h e T 0 2 7 S A o c c u r r e d
during closing of the array valve prior to retraction and removal of
the SA system from the SAL.
When the crewman closed the array
valve, by turning the vane control, the valve did not seat completely.
Force in excess of that recommended during training was applied to the
vane control, and the valve was closed.
The problem was attributed
to the low temperature of the system, forming frost, preventing the
normal closure of the array valve.
�c.
Assessments/Recommendations -
For some reason the
requirement to let the T027 SA system warm up prior to its removal
from the SAL had been crossed out of the checklist and omitted from
the experiment pad.
This procedural information concerning warm up
prior to removal was required, and should not have been omitted, as
indicated by the minor problem which occurred as a result of its
omission.
13.22.4
Operations Experiments
13.22.4.1
M487 - Habitability/Crew Quarters
a.
Operations - Experiment M487 was scheduled for operation
on each of the three Skylab missions and was charged with evaluating and
reporting on the OWS habitability provisions.
The methods of M487 data collection were to depend primarily on the
crewmen.
Where possible the experiment task was to augment or coincide
with the operational activity to be observed.
When the activity was not
scheduled or predictable, the elements of the activity were to be grouped
into a staged demonstration to optimize time and effort.
First the crew
man was to obtain, calibrate as required, and position the various
monitoring devices throughout the OWS.
The crewman was to then
obtain, position, and operate the various equipment that was required
for photography and data collection.
�b.
Usage/Anomalies -
M487 was performed as planned through
out each Skylab mission, accomplishing all pre-mission requirements.
One hardware problem occurred during the SL-2 mission.
During the
initial calibration of the sound level meter/frequency analyzer the crew
man could not obtain the correct calibration factor.
A second calibration
was attempted at a later time and the correct factor was obtained.
The
cause of the problem encountered during the first calibration attempt
was undetermined.
c.
Assessment/Recommendations - The hardware supplied
by this experiment to supplement the crews' observations was considered
unnecessary as was shown by its lack of use throughout the Skylab missions.
For this reason, few comments concerning the M487 hardware were
available.
It was reported that both the ambient and digital thermometers
required a lengthy time to stabilize when measurements were made where
a large change in temperature was involved.
Both the digital and ambient
thermometers were used over the three Skylab missions in support of
other hardware evaluation and the 10' tape was used in several science
demonstrations.
These items should be included on future missions as
operational support hardware.
Some crewmembers expressed their dislikings toward the lengthy and
time consuming cn-board debriefings.
They felt that this orbit time
�could be better utilized and that the debriefings could be conducted
post-mis sion.
It was felt that the data compiled from M487 would form the basis for
verifying existing spacecraft habitability criteria and would establish
requirements for more advanced spacecraft.
13.22.4.2
M509 - Astronaut Maneuvering Equipment
a.
Operations - Experiment M509 was scheduled to be
performed on SL-2 and SL-3.
Each test pilot was to perform four runs
with the Automatically Stabilized Maneuvering Unit (ASMU) while an
observer assisted.
Runs 1, 2, and 4 were designated to be performed
unsuited whereas run 3 was to be performed while wearing the Skylab
Extravehicular Mobility Unit (EMU).
Prior to the experiment performance, the M509 hardware and support
hardware was to be unstowed and reconfigured for operation, including
Propellant Supply System (PSS) bottle and battery charging.
Once the
experiment preparation was completed and the OWS forward experiment
area was cleared of equipment not required for the experiment, the
observer was to assist the test pilot in donning the ASMU.
The test
pilot was to then undock from the donning station and perform the
designated M509 maneuvers.
Upon completing these maneuvers, the
subject was to return to the donning station and dock the ASMU, thereby
concluding the experiment performance.
�b.
Usage/Anomalies - The M509 experiment performance
for SL-2 was limited to operational configuration and checkout.
Due
to the OWS meteoroid shield problem and resulting high temperatures
i t w a s c o n c l u d e d t h a t a h a z a r d o u s c o n d i t i o n m i g h t e x i s t if t h e M 5 0 9
batteries were discharged.
If the batteries were used an internal short
might have occurred resulting in a possible explosion.
The ASMU, PSS
bottle rack and AM N£ recharge station were reconfigured to their
inflight usage configurations and the PSS bottles were recharged.
After
reconfiguration/checkout of the M509 ASMU and the PSS bottle installation,
the unit was powered up from OWS power while still in the docking station
and the backpack and Hand-Held Maneuvering Unit (HHMU) thrusters
were fired.
Between missions, onground testing determined that the flight M509
batteries were acceptable for use and on SL.-3 and SL-4 the experiment
was successfully operated.
The unit was flown in all four modes, both
suited and unsuited.
One modification was made to the planned M509 activities after the first
suited performance.
During this performance the test pilot noted that
the Life Support Umbilical (LSU) imparted undersirable dynamic forces
on the ASMU during maneuvering.
In hopes of reducing/eliminating
these dynamic effects the crew stripped the LSU of all wiring and
�insulation, leaving only the 02 line.
This modified LSU was then used
on all subsequent M509 and T020 suited runs not utilizing the Secondary
Oxygen Packs (SOP).
During a SL-4 suited run battery problems arose causing the experiment
run to be shortened.
The batteries were being depleted much faster than
anticipated due to time consuming delays during the M509 run.
One delay
was experienced when the crewman encountered problems attaching the
AM recharge station quick disconnect to the PSS bottle connector.
An
additional delay was experienced when the SOP was depleted and had to
be replaced by the LSU.
During both these delays the ASMU was on
battery power thus draining the battery.
batteries to the 26 volt minimum
These delays drained both M509
and the M509 run was terminated after
completing only 2 / 3 of the run's objectives.
M509 was performed through
out the remainder of SL-4 and no anomalies were reported.
c.
Assessment/ Recommendations -
well designed and easy to fly.
The M509 ASMU was
Intuitive skills, common to all astronauts
because of their flight training, was all that was required to navigate
M509.
Ground based training for this experiment using the Denver
simulator was not necessary.
This was verified during an unscheduled
M509 performance by a crewmember who had never trained for M509
nor had ever used the training simulator.
His flight was performed with
ease and was considered a complete success.
�During the M509 maneuvers four potential flying modes were evaluated
and, in order of preference, were DIRECT, CMG, RATE GYRO and
HHMU.
The DIRECT mode was far the easiest and the more intuitive
to control.
The CMG and RATE GYRO modes were very good but the
precesion inherent to these modes was unnecessary for a future EVA
maneuvering device.
The HHMU was given a poor rating and was
recommended by the crew to be deleted from consideration as an EVA
maneuvering mode.
The difficulty with the HHMU was in locating the
center of gravity which turned out to be an important factor in this
maneuvering mode.
In future testing of a maneuvering unit the HHMU
should be eliminated from consideration because it was not an intuitive
device to operate, as it required unique and undeveloped skills.
In flying M509 actual EVA conditions were simulated to evaluate all
phases of maneuvering.
the LSU and SOP.
Suited operations were conducted using both
The SOP configuration was preferred over the LSU
configurations because of the dynamic effects present with the LSU.
The LSU, due to its mass and elastic characteristics, imparted an
inertia on the M509 ASMU which proved to be an annoyance to the test
pilot, in that guidance corrections to the unit were constantly required.
Safety was a principle concern in pre-mission design and planning of
M509.
But due to the ease of operations and maneuverbility of the
�ASMU the pre-mission concern of inadvertant and possible catastrophic
collisions was shown to be invalid.
The ASMU, though very large and
h e a v y , w a s n o t b o t h e r s o m e o r i n c a p a b l e of b e i n g h a n d l e d b y t h e t e s t
pilot.
The test pilots were confident that even with the large ASMU
m a s s and a maximum maneuvering velocity of 3-4 f t / s e c that they
could, in the event of a thruster failure, reposition themselves and
absorb the energy of an impact without bodily or hardware damage.
The M509 hardware and supporting equipment was well designed both
from a functional and integration standpoint with one exception.
The
ASMU had too many controls located in too many diverse and remote
positions.
If possible these controls should be relocated on a common
panel to facilitate crew operations.
The safety goggles and ear plugs
were required and were used by all crewmen.
The unstowage/stowage
of the M509 hardware was straightforward with no problems occurring.
PSS bottle charging required the crew to translate to and from the AM
recharge, station with the bottles.
This entire procedure,including
recharge, took less than 10 minutes to perform and it was reported that
the bottles during recharging only reached a temperature of approximately
100°F.
Translation with the bottle was accomplished by the crewman holding
the bottle ahead of him, pushing off and then following along behind the hardwar
Prior to reaching his destination, through a mental integrative process, the
crewmember could reposition himself between the hardware and contact
�point for a safe landing.
The ASMU was a good translational device but was found to be severly
limited in its use as a workstation/platform for performing work related
tasks.
In performing relatively easy tasks, the crewman's body torques
would over saturate the ASMU gyros and cause a loss of stability.
To
perform EVA tasks the ASMU, as designed, would have to be docked/ •
restrained at the designated work area to achieve the necessary stability
required to perform the task.
The next generation EVA maneuvering device should be back mounted
with the pilot-to-backpack restraint system providing a tight, secure
and comfortable (seat padding recommended) fit.
should be designed as an one man function.
Backpack donning/doffing
The backpack must have six
degrees of freedom, with the propulsion thrusters located around the
center of gravity of the pilot/backpack combination, and should be hand
controlled.
The hand controllers should have the capability of being
relocated/moved during flight to allow multiple working postures for the
pilot.
The DIRECT mode should be selected as the maneuvering mode
with a capability of a 3-4 f t / s e c velocity.
Restraints/docking provisions
(i. e. manipulative arms) must be provided to adequately stabilize the pilot
and permit him to perform the designated task.
A backpack spotlight
should be incorporated to provide the pilot with an illumination source
at his work area.
Separate isolation valves/circuit breakers for each
�thruster or set of thrusters should be provided to insure against a single
point failure.
The backpack should contain all systems required for
EVA such that no umbilical or LSU is required.
The unit should contain
a pressure control system, oxygen system and maneuvering system with
all system monitoring displays/readouts being illuminated.
With such a
system the pilot could suit up, don and plug in the maneuvering unit and
perform an EVA as a free entity.
�13.22.4.3
T013 - Crew/Vehicle Disturbances
a.
Operations -
Experiment T013 was scheduled to be
performed on SL-3 to measure the effects of crew motions on the
dynamics of manned spacecraft.
Two crewmen were required for T013 operations; one designated as the
subject and the other as the observer.
A third crewman was required
during performance of the worst case control system input task.
Data
was to be collected employing the 16mm Data Acquisition Camera (DAC),
mounted in the OWS forward compartment.
The Limb Motion Sensor
(LIMS) suit assembly including the LIMS data cable was to be removed from
stowage.
The subject was to don the LIMS suit and then connect the experi
ment data cable between the LIMS and the Experiment Data System (EDS).
Prior to start of the experiment performance, the observer was to don a
communications headset and turn on the AM tape recorder and cameras
for data collection.
The Force Measurement Units (FMU) were to then be
uncaged and calibrated.
During the experiment performance of body and
limb motions and free soaring activities, the observer was to assist in
securing the subject to and releasing him from FMU No. 1 at appropriate
�times during the experiment.
Upon conclusion of the experiment performance,
the cameras, AM tape recorder and the EDS were to be turned off and the
FMU's caged and pinned.
The EDS data cable was to then be disconnected
and stowed together with LIMS suit assembly in the T013 stowage container.
b.
Usage/Anomalies -
by the experiment checklist.
T013 was performed on SL-3 as designated
Upon completion of the experiment performance
the crew reported that the experiment had functioned as planned.
T013 was performed on SL-3 but during the first pushoff of the soaring
activities a malfunction occurred in the load cells of FMU No. 2 causing a
partial loss of data.
Malfunction procedures were performed on both
FMU's and deformation of the load cell flexures was uncovered.
As part
of the malfunction procedures a FMU calibration was performed and the
results indicated that load cells 4 and 5 of FMU No. 2 had failed and were
considered lost.
To satisfy the experiment mission requirements, a rerun of the T013
soaring activities was performed, but the crew failed to activate the
T013 Experiment Data System (EDS) and no experiment data was received.
Again, in attempt to satisfy the experiment requirements, a third run
of T013 was performed by the SL-3 crew and all ATM and photography
data was successfully gathered.
requirements.
This performance satisfied all T013
�During performance of the T013 worst case input task only two crewmen
participated instead of the three required.
Since the third man, designated
as observer, did not contribute to the data input and was required only for
safety reasons, the omission of his participation had no effect on the
experiment results.
c.
Assessments/Recommendations - Other than the FMU
anomaly, experiment T013 operations were straightforward and easy to
perform.
Stowage/unstowage was simple, the LIMS suit fit well and the
camera positioning was no problem.
Soaring between the FMU's was
quite easy, in fact, the FMU's could have been placed much farther apart
without effecting the crewman's soaring accuracy.
The FMU's placed
as they were, were so close that it was difficult for the performing
crewman to soar between them and land feet first.
During the worst case task, the second performer could not soar between
the film vault and the food lockers.
He had to soar between the food lockers
and the lockers adjacent to the film vault.
During the simultaneous
soaring both crewmen performed their push-offs together but due to the
differences in soaring distances their impacts were not simultaneous.
�•
,
»
«
13.22.4.4
T020 - Foot Controlled Maneuvering Unit
a.
Operations - Experiment T020 was scheduled to be
performed in the OWS forward compartment area during SL-3 and SL-4.
A total of 5 runs by each test pilot was scheduled with the Foot Controlled
Maneuvering Unit (FCMU) while a second crewman acted as observer,
OWS cameraman and safety man.
Of the 5 performances conducted by each
test pilot three were to be operated in shirtsleeves and two while suited.
Prior to the experiment performance, the T020 hardware and support hardware
were to be unstowed and reconfigured for operation, including M509 PSS
bottle and battery charging.
Once experiment preparation was completed
and the OWS forward experiment area was cleared according to the T020
checklist, the observer was to assist the test pilot in donning the T020
maneuvering equipment.
The test pilot would then undock from the T020
docking station and perform the required maneuvers.
Upon completion of
these maneuvers, the subject, with aid from the observer, would return
to the docking station and dock the FCMU, thereby concluding the experiment
performance.
b.
Usage/Anomalies -
Experiment T020 was performed as
planned on SL-3 with the test pilots operating the FCMU five times.
The first three runs were performed in shirtsleeves while the last two runs
were flown suited.
Life Support
The two suited runs were conducted utilizing both the
Umbilical (LSU) and Secondary Oxygen Pack (SOP) configurations.
On SL-4, T020 was performed twice.
The first run was performed suited whereas
the second was performed in shirtsleeves.
�Two modifications were added to T020 during its performance on SL-3.
After
the first maneuvering operation with T020 it was evident that a better
restraint system was needed.
A modified system was devised on ground
and then information was uplinked to the crew.
This restraint system
provided the added stability sought by the test pilot and was used through
out the remaining SL-3 T020 performances.
The second modification was performed by the SL-3 crew on the LSU in
hopes of reducing or eliminating the dynamic effects it imparted on the
maneuvering units.
Using a scapel and sissors, the LSU was stripped of
all wiring and insulation, leaving only the 02 line.
This LSU was used on
all subsequent M509 and T020 suited runs not utilizing the SOP configuration.
Because of the lack of rigidity experienced with the T020 restraint system
during SL-3 a new rigid restraint system was designed and fabricated
between missions.
This rigid restraint system was launched on SL-4
and used by the crew in their T020 operations.
The first SL-4 T020 run was performed suited and utilized the new rigid
restraint system.
The crew reported that the system worked extremely
well and reduced practically all body/backpack motions.
The second T020 performance was conducted in shirtsleeves.
The crew
operated T020 with both the rigid and original restraint systems.
Again,
�the rigid system was considered highly effective whereas the non-rigid
system was considered extremely poor.
This was the last evaluation of experiment T020 a s scheduling considerations
prohibited any additional performances.
c.
Assessment/Recommendations - T020 stowage/unstowage
was fairly simple, although between operations it was left stowed in such
a manner that would not require much time to reactivate. . . a casual type
of stowage.
The T020 restraints and harness were not satisfactory.
was improvised and is definitely required.
Also, seat padding
The restraints did not give
the operator a secure or tight feeling in the unit.
The harness, due
to its unusual design, was difficult to don and connect.
The backpack
assembly was not contoured correctly and was too loose when donned.
Incorporation of the required restraint system removed most of the
sloppiness between the backpack and FCMU and gave the pilot a more
secure fit with the T020 hardware.
The shoe plates seemed to work well although it was easy to kick your
foot/shoe plate out of the FCMU.
thrusters were too high.
Also the shoe plate forces for the
These seemingly high shoe plate forces could
be attributed to a possible deconditioning of the crew's leg muscles due
to the zero gravity environment.
�T020 must have six (6) degrees of freedom to be fairly evaluated.
As
designed, it is completely unacceptable as a maneuvering vehicle and
the crew sees no advantage in its concept of foot-controlled maneuvering.
13. 22. 5
Student Project Experiments
13.22.5.1
ED 23 - Ultraviolet from Quasars
a.
Operations - Student experiment ED 23 was scheduled
to be performed on SL-3 a s an additional data pass of baseline experi
ment S019 to obtain spectrographic data of selected quasars.
The crew was to use experiment S019 as support equipment for ED 23.
With S019 mounted in the Scientific Airlock (SAL), ultraviolet photographs
were to be taken of pre-designated galaxies.
ED 23 data was to be
recorded in the S019 portion of the log book and photographs were to
be returned in the S019 film canister.
b.
Usage/Anomalies - Student experiment ED 23 was
performed as scheduled and no anomalies were reported.
c.
Assessment/Recommendations - The crew felt that experi
ment training was good but that a decision needed to be made as to experi
ment operational priority so as to better appropriate crew training
requirements.
�13. 22. 5. 2
ED 25 - X-Rays From Jupiter
a.
Operations - Student experiment ED 54 was scheduled to
be performed on SL-3 to detect x-rays from Jupiter.
The experiment was to be performed with the use of ATM experiment
S054 under Joint Observation Program (JOP) 13.
The vehicle was to
be maneuvered so that the ATM could observe celestrial bodies away from
the sun.
b.
Usage/Anomalies - Student experiment ED 25 was
performed during the ATM performance of JOP 13 a s scheduled and no
anomalies were reported.
c.
Assessment/Recommendations - The crew felt that the
procedures were adequate and that the hardware performed satisfactorily.
13.22.5.3
ED 26 - Ultraviolet From Pulsars
a.
Operations - Student experiment ED 26 was scheduled to be
performed on SL-3 as an additional data pass of baseline experiment
S019 to search for pulsars in ultraviolet wavelengths.
The crew was to use experiment S019 as support equipment for ED 26.
W i t h SO 1 9 m o u n t e d i n t h e S A L , u l t r a v i o l e t p h o t o g r a p h s w e r e t o b e t a k e n
of designated galaxies.
ED 26 data were to be recorded in the S019 log
b o o k a n d t h e p h o t o g r a p h s w e r e t o b e r e t u r n e d i n t h e SO 1 9 f i l m c a n i s t e r .
�b.
Usage/Anomalies - Student experiment ED 26 was
performed as planned and no anomalies were reported.
c.
Assessment/Re commendations - Student experiment ED 26
used only film and S019 experiment hardware, therefore all crew inter
face assessments are included with the assessment of S019.
13.22.5.4
ED 31 - Bacteria and Spores
a.
Operations - Student experiment ED 31 was scheduled to
be performed on SL-3 to determine the effects of weightlessness and
space radiation on the survivability, growth rate, and mutation of several
vegetative bacterial species.
A crewman was to inoculate the 15 petri dishes containing nutrient agar.
Nine cultures were to then be incubated in the Inflight Medical Support
System (IMSS) incubator and the remaining six at OWS ambient temperatur
Observation and photography of these cultures were to take place a t 12
hour intervals until the colony growth was attenuated by cooling in the
OWS and chiller.
The petri dishes were to be returned a t the end of the
mission for laboratory study.
b.
Usage/Anomalies -
Due to the degradation caused by the
SL-2 launch delay and the elevated OWS temperatures, ED 31 was
investigated and a decision was made to perform the experiment on SL-2,
assess the data, and consider performance on SL-4, if necessary.
The
15 ED 31 petri dishes were inoculated, incubated and photographed on
�SL-2.
Petri dishes one through four had water drops but no visible
growth.
Photographs were not taken of dishes one through four but
were taken of dishes five through fifteen.
Only dishes number 7 and
number 9 showed any growth and they had three and one colonies
respectively.
The experiment was completed using reduced mission
protocol and the 15 dishes were returned on SL-2.
The 15 plates were
not chilled and they were returned in a food overcan because the IMSS
resupply container was not on board SL-2.
Ground studies indicated
that the high temperatures experienced on SL-2 had possibly affected
the experiment results and it was decided to repeat the experiment
on SL-4.
ED 31 was repeated on SL-4 as planned and successfully
completed.
c.
Assessment/Re commendations - The crew was satisfied
with the experiment hardware performance and reported no difficulty
in inoculating the petri dishes in a zero-gravity environment.
13.22.5.5
ED 32 - Invitro Immunology
a.
Operations - ED 32 was scheduled to be performed on the
SL-3 mission to determine the effects of zero gravity on the antigenicity.
To perform ED 32, a crewman was to inject each of the three (3) immuno
diffusion plates with antigen and was to then periodically photograph the
plates throughout the incubation period.
To photograph the plates, the
crew was to attach them to OWS light number 1 using the photo clip
�supplied in the ED 32 hardware.
b.
Usage/Anomalies - Antigen injection of the three diffusion
plates was accomplished early in the SL-3 mission.
Ten days later,
the plates were attached to the OWS light and photographed with the
35mm Nikon camera.
This constituted completion of the ED 32 experi
ment requirements.
c.
Assessment/Recommendations - No assessments or
recommendations were received from the crew concerning ED 32.
Therefore it was assumed that the experiment hardware, procedures
and interfaces were well designed and all functioned as planned.
13.22.5.6
ED 41 - Motor Sensory Performance
a.
Operations - ED 41, Motor Sensory Performance, was
scheduled to be performed on SL-4 to obtain motor sensor performance
data which could be used in planning, training, and equipment development
for future manned space missions.
The method of measuring motor sensory performance used in ED 41 was
a standardized eye-hand coordination test using a maze with a 119-hole aiming
pattern, stylus, and cable assembly.
During operation the unit was attached
to the wardroom window shelf by velcro strips and the cable was connected
to the speaker intercom assembly connector.
The experiment
was
performed once early and again late in the mission by the same astronaut
and no activities imposing either intense physical exertion or mental/
�emotional strain preceded performance of the experiment.
Inflight
performance was compared with pre-flight and post-flight tests performed
by the same subject.
b.
Usage/Anomalies - Student experiment ED 41 was performed
as scheduled by all three crewmen and no anomalies were reported.
c.
Assessment/Re commendations - Procedures for ED 41
were straightforward and the hardware performed satisfactorily.
13.22.5.7
ED 52 - Web Formation
a.
Operations - Student experiment ED 52 was scheduled to
be performed on SL-3 to observe the web building process of the Araneus
diadematus (cross) spider in a zero-gravity environment and compare
this process with one performed in a one "g" earth environment.
A
prime and backup spider were to be launched.
The crewman performing the experiment was to deploy the experiment
enclosure which permits observations of spider activity.
The spider
was to be released from her vial into the experiment enclosure and
allowed to spin her web.
During the experiment performance a crew
man was to periodically provide food and water for the spider.
Still
photographs were to be made with the 35mm Nikon camera and correlated
�to Ground Elapsed Time (GET) by voice recorded comments.
Movie
photographs were to be made with the DAC 16mm camera utilizing the
automatic camera actuator which detected spider motion to start/stop
the motion picture camera.
Upon completion of the experiment the
spiders were to be disposed of through the trash airlock.
b.
Usage/Anomalies -
Prior to releasing the prime spider,
Arabella, the crew reported a problem with the automatic camera
actuator.
Malfunction procedures were conducted on the automatic
camera actuator with no results.
The actuator was considered failed
and therefore the web forming photography objective was not met.
Photographs were taken periodically by the crew using the hand-held
camera.
Due to the actuator failure some additional crew time was
spent taking hand-held photographs.
Both the prime and backup spiders
died in orbit and were returned to earth along with web samples.
c.
Assessment - Other than the actuator failure and resulting
increased time requirement for the crewman the experiment was performe
as scheduled.
13.22.5.8
ED 61/62 - Plant Growth/Plant Phototropism
a.
Operations - ED 61/62 was scheduled for performance
during SL-2 to observe difference in root and stem growth of rice
seeds germinated in the Skylab environment.
�Eight seed groups were to be implanted by the crewman with the seed
planter into a compartmental container filled with clear agar.
This
container was to be fitted with neutral density filters to enable a variation
in the total light impinging on the eight separate seed groups.
Following
implantation, the crewman was to photograph the seed groups daily for 14
days using the 35mm Nikon camera.
b.
Usage /Anomalies - Due to the high OWS temperatures
after launch, and subsequent on ground testing, the ED 61/62 performance
was cancelled for SL-2.
Resupply and performance of ED 61/62 was
accomplished during SL-4.
Prior to seed implantation the experiment
was relocated because existing light levels were felt to be too low for
adequate growth.
In addition, the portable light was incorporated to
provide additional lighting to insure good growth.
Finally the seeds were
implanted and photographed as scheduled with no anomalies reported.
c.
Assessment/Recommendations - No assessment or
recommendations were received from the crew concerning ED 61/62.
Therefore it was assumed that the experiment hardware, procedures
and interfaces were well designed and all functioned as planned.
13.22.5.9
ED 63 - Cytoplasmic Streaming
a.
Operations - Experiment ED 63 was scheduled for operation
on the SL-3 mission to observe the effects of zero gravity on cytoplasmic
streaming in plants.
�Crew activation operations for ED 63 were to consist of restraining the
ED 63 transparent container, containing the elodea water plants, near
a specific light in the OWS wardroom to maintain photosynthesis during
the mission.
Then, once early in the mission and again late in the
mission, the crew was to detach a leaf from the elodea plant and, with
use of the Inflight Medical Support System (IMSS) microscope and
associated hardware, examine the leaf for cytoplasmic streaming.
The
16mm Data Acquisition Camera (DAC) was to be used to document the
data.
b.
SL-3.
Usage/Anomalies - ED 63 was performed as scheduled on
During the first performance the crewman reported that all three
plant vials had a sulphurous smell and that the leaves from the three
plants showed no resistance when detached.
Two slides were prepared
from one of the plants and no cytoplasmic streaming was observed.
In conjunction with this in-flight performance of ED 63, a ground based
performance was conducted.
A sample slide was prepared on each of
the three plants and observed under a microscope.
Two of the three
elodea plants appeared to be totally dead, the third appeared normal
and exhibited good cytoplasmic streaming.
The vials containing the
two dead plants smelled of hydrogen sulfide and the leaves showed no
resistance when detached.
Based on this, it was considered probable
that one or more of the plants in orbit were dead.
�From a later on ground performance of ED 63 it was discovered that
a previously considered dead plant had exhibited some cytoplasmic
streaming.
Therefore, the crew were requested to prepare slides on
all three plants and examine for possible streaming.
and no streaming was observed.
The crew complied
This resulted in a termination of the
experiment for SL-3 and an eventual resupply for a SL-4 performance.
During the SL-4 performance of ED 63, a hardware anomaly was
reported concerning the DAC camera/IMSS microscope adapter.
The
crewman examining for cytoplasmic streaming could not acquire a full
field of view.
It was his assessment that the adapter was the cause of
the problem.
The SL-4 performance of this experiment approximated the results obtained
from SL-3.
During the first cytoplasmic streaming observation one plant
provided some evidence of streaming.
In subsequent observations the elodea
plant leaves showed no resistance when detached, there was a sulphurous
smell present and no cytoplasmic streaming was observed.
It was decided
that the plants were dead and the experiment was terminated.
The plants
were removed from their vials and placed in the trash airlock.
c.
Assessment/Recommendations - Other than the DAC
camera/IMMS microscope adapter anomaly, the ED 63 performances
were conducted as planned.
The crew reported that the experiment
�procedures and hardware functioned well and felt that everything possible
was done on their part to acquire usable data.
From the results of this
experiment, it was concluded that zero-gravity has an undesirable
effect on cytoplasmic streaming in plants.
�13.22.5.10
a.
ED 72 - Capillary Study
Operations - Student experiment ED 72, Capillary Study,
was scheduled to be performed on SL-4 to demonstrate capillary action
as a liquid pumping mechanism.
The experiment hardware consisted of two separate capillary tube modules
and an additional capillary wick module.
Each capillary tube module •
contained a reservoir, lever valve system and three transparent capillary
tubes of graduated sizes.
oil.
One module contained water, the other Krytox
The capillary wick module contained three capillaries of twill and
mesh screens.
The crewman was to activate the lever valve of the
capillary tube modules and photograph the capillary action of the fluid.
The entire experimental sequence was to be photographed, beginning with
the actuation of the capillary valve and ending with the time that the slowest
fluid volume reached the end of the capillary tube.
b.
Usage/Anomalies - The wicking segment of student experiment
ED 72 was successfully performed as scheduled with photographic data and
crew sketches being obtained for data.
The capillary segment of ED 72 was unsuccessful.
During preparation
of this portion the crewman observed that both the oil and water had
leaked from their reservoirs.
capillary action was observed.
When the lever valves were operated no
The failure was attributed to the reservoir
�leakage.
The ground later suggested attempting to refill the reservoirs
but the crew had already disposed of the modules through the trash airlock.
The leakage was documented on film.
c.
Assessment / Recommendations - The wicking portion of ED 72
was successfully completed with the hardware functioning as designed.
However, the capillary segment was unsuccessful due to the hardware
failure resulting in the leakage of the capillary modules.
�13.22.5.11
ED 74 - Mass Measurement
a.
Operations - Experiment ED 74 was scheduled to be
performed on SL-3 to demonstrate the use of harmonic motion to
measure the mass of an object.
To operate ED 74, a crewman was to first remove ED 74 from launch
stowage in the OWS film vault and then bolt it to the film vault.
The
device was to then be calibrated using the calibration weights included
with the ED 74 hardware.
Next the mass of four (4) small objects was
to be determined through use of the ED 74 hardware.
This was to conclude
the ED 74 performance.
b.
Usage/Anomalies - During SL-3, ED 74 was performed
twice instead of only once a s scheduled.
It was decided that this experi
ment was a good candidate to be downlinked by real time TV coverage.
c'
Assessment/Recommendation - During both pgr fnr manioc
the hardware functioned as planned and no anomalies were reported.
The crew stated during the final performance that ED 74 worked very
well.
13.22.5.12
a.
ED 76 - Neutron Analysis
Operations - Student project experiment ED 76 was
scheduled for operation during all three Skylab missions.
Its purpose
was to acquire data for measurement of the ambient neutron flux a t
Skylab orbital attitudes.
�The hardware for ED 76 was comprised of ten (10) neutron detectors
and stowage containers.
During SL-2 the ten neutron detectors,
consisting of chemically coated films, were to be deployed on the
inboard surfaces of the OWS.
At designated times during SL-2 and
SL-4 the crew was to deactivate certain detectors and stow them for
ultimate return to earth.
b.
Usage/Anomalies -
During SL-2 the ten (10) neutron flux
detectors were deployed as planned.
A t t h e e n d of t h i s m i s s i o n f o u r ( 4 )
detectors were deactivated, stowed and returned.
The remaining six
detectors continued data collection throughout the Skylab missions and
were deactivated and stowed in the CM by the SL-4 crew just prior to
their return.
The SL-4 crew stated that dector Bravo 3 was poorly placed in that as
they came through the hatch from the forward compartment to the experi
ment compartment it was in a very natural place to grab.
If t o u c h i n g
degraded it, it was definitely degraded as it was touched numerous times.
c.
Assessment/Re commendations - No assessments or
recommendations were reported by the Skylab crews concerning ED 76.
Therefore it was assumed that the experiment hardware, procedures and
interfaces were well designed and all functioned as planned.
13.22.5.13
a.
ED 78 - Liquid Motion
Operations -
Experiment ED 78 was scheduled to be
�performed on SL-3 to study the dynamic response of a liquid/gas inter
face when subjected to an impulse in zero gravity.
The crewman was to excite a gas bubble, surrounded by a liquid, by
activation of the calibrated force supplied by the ED 78 piston/ spring
mechanical system.
Photographs were to be supplied to the student
investigator to provide ED 78 data interpretation.
b.
Usage/Anomalies -
Experiment ED 78 was set up and
initiated during SL-3 but the hardware did not operate properly.
piston/spring mechanism did not function when activated.
corrective procedures were attempted with no success.
The
Several
It was deter
mined that the diaphram in the piston/spring mechanism was ruptured
and that no corrective actions were possible.
The ED 78 hardware was
terminated and stowed.
During SL-3 and SL-4, liquid motion scientific demonstrations were
performed and data from these demonstrations were provided to the
ED 78 student investigator.
This data provided sufficient information
to satisfy the requirements of ED 78.
c.
Assessment/Recommendations - Other than information
concerning the ED 78 hardware anomaly, the crew made no comments
concerning the assessments/recommendaticns for this experiment.
�
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Human Factors Engineering Collection
Identifier
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Human Factors Engineering Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/12">View the Human Factors Engineering Collection finding aid in ArchivesSpace</a>
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sdsp_skyl_000059
Title
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"Final Crew System Corollary Experiment Input to the Skylab Final Mission Evaluation Report."
Description
An account of the resource
This report describes the experiments onboard Skylab, what the data the experiments gather indicates, and the equipment that the experiments utilize. This includes the spider experiment.
Creator
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United States. National Aeronautics and Space Administration
Date
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1974-02-15
Temporal Coverage
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1970-1979
Subject
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George C. Marshall Space Flight Center
Skylab Program
Experimentation
Apollo Telescope Mount
Airlock modules
Extravehicular mobility units
Skylab 1
Skylab 2
Skylab 3
Skylab 4
Type
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Reports
Text
Source
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Human Factors Engineering Collection
Box 2, Folder 2
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
Skylab Document Scanning Project Metadata
Skylab 50th Anniversary
-
http://libarchstor2.uah.edu/digitalcollections/files/original/46/14395/sdsp_skyl_000060_001.pdf
11825ce2945e9c0a8ab900531c9504cc
PDF Text
Text
L I V I N G
NASA
PROJECTS
APOLLO
SATURN
SKYLAB
SHUTTLE
I N
S P
�The documentary archive described in this catalogue
will be sold as a single lot by auction at Sotheby's
in their Large Galleries 34/35 New Bond Street, W1A 2AA
[Telephone 01-493 8080 Telex: London 24454 SPBLONG)
at approximately 8 p.m. on Monday 20th July 1981
All enquiries about this sale should be made to the Manuscript
Department
Sold subject to conditions printed in the main catalogue
In sending commissions this catalogue may be referred to
as "Shuttle"
Front cover designed by Raymond Loewy
�S • T H E B Y ' S
��Raymond Loewy and Living in Space
Significance of Space Exploration and of its History
With the successful mission of the first re-useable Space Shuttle, code-named Columbia, from
12 to 14 April 1981, man's vision of living in space was given practical reality and assured of a future. The
Shuttle marks a new era in space exploration and in the history of mankind.
The potential benefits arising from this momentous event are virtually limitless, but already it is
envisaged Cand the first 60 flights are already committed] that payloads of regular Shuttles will establish:
• journeys into orbit as routine as commercial airline flights with Shuttles operating under their own
power without the necessity of lift-off boosters
• military communications, navigation, weather and surveillance satellites ["the nation that controls
space will control the world"]
• the construction of a giant 96-inch telescope operating high above the distorting effects of the
atmosphere enabling astronomers for the first time to see any planets around nearby stars, to
observe objects 100 times dimmer than those that can be seen through ground-based telescopes
and perhaps also to detect light emanating from the very edge of the visible universe, which will
contribute to our understanding of evolution and the origin of life
• the construction of space platforms and even of space colonies with space nations under their own
governments, flags and laws
• the construction of the European spacelab
• a network of permanently located satellites able to destroy enemy atomic missies
• the return of raw materials from space and the extraction of unlimited energy from the Sun
• the solar polar mission
• a new industrial revolution: the development of virtual vacuum-free technosphere manufacturing
plants free of gravity, thus making possible, for instance, the production of an estimated 400 alloys
from metals that do not successfully mix under the pull of Earth's gravity which tends to separate
the lighter metals from the heavier ones; the manufacture of perfect ball-bearings: stable foams;
crystals of new semi-conductor materials: and super-pure vaccines and drugs produced in totally
antiseptic conditions.
f U
success of the Columbia Shuttle will also refocus attention on all aspects of the development
of the Shuttle and its forerunners as subjects for academic investigation and exhibition in museums and
industrial centres.
��The Raymond Loewy Files
The present collection - from the files of Raymond Lcewy, NASA's official Habitability Consultant
from 1967 to 1973 - is a unique and fundamental record relating to the first steps in manned utilization of
space and the birth of space exploration. It contains material that NASA itself does not have, such as the
original drawings and sketches and the abandoned and experimental designs, or which, as a government
agency, it is not at liberty to release. However, under American Government regulations all drawings,
documents, blue-prints, statistical data, sketches and scale models remain the personal property of the
consultant.
The importance of the collection and of Loewy's contribution are reflected in the success of Skylab
and the Space Shuttle, for both of which Raymond Loewy was retained as Habitability Consultant. His
designs will form the basis for all American manned spacecraft: "Manned space stations of the future will
require few design changes for man to work comfortably in Zero-G operations, based on the 171-day
occupancy of the Skylab workshop by nine astronauts" Aviation Week & Space Technology, 8 April 1974.
This documentary archive comprises some 3,500 items and includes:
• original conceptual drawings, designs, sketches and detailed sections together with finished
art-work executed with airbrush or body-colour, on card, paper or tracing paper Cc. 520] some
initialled or signed by Loewy and a few consisting of reproductions reworked by hand; mechanical
drafts; blue-prints; reflex negatives Ca number on large sheets]; coloured and black and white
photographs Cused by modern designers particularly in relation to mockups]; negatives; VU-graphic
overlapping transparencies; plates; plans; emblems; textual matter; reports; notes; photocopies;
lithographs; press-type samples and data format cards contained in large folders.
• two space work-overalls and one jacket
• four scale models:
•• Apollo-Saturn V
•• crew's quarters ejected from the Shuttle Orbiter
•• a future space base
•• Skylab
�Habitability Reports prepared for NASA
�• the official reports of the habitability consultant, in 47 illustrated volumes, mostly with spiral
bindings, containing some 4,800 pages, sent by the Loewy team to NASA and consisting of
13 Final and Contract Summary reports C7 or them in two volumes], relating to Earth Orbital
Space Stations (Skylab], the Shuttle, a Modular Space Station and a Wardroom Gallery Module
together with general habitability studies covering all areas of human survival in space-sleeping,
nourishment, hygiene, waste-management, the collection of samples, their dehydration,
identification, dating and freezing for chemical analysis upon return to Earth after 90 or more
days in orbit (27 being duplicates and a small number in photocopy]
• NASA's Habitability Design Support Technical Summary Statement for the design of the Shuttle
dated 1972 as sent to Loewy by NASA's Deputy Chief of Manned Spacecraft Design
• commemorative photographs and letters signed by NASA officials and astronauts including
Frank Borman, Buzz Aldrin and John Stafford.
• Raymond Loewy's own compilation consisting of originals and copies, relating to his part in the
NASA Programmes, including magazine reports
• a space collage by Raymond Loewy, signed and dated
• index volume of NASA's terms and definitions
Skylab and the need for a Habitability Consultant
George Rodney, Director of Martin Marietta Aerospace and NASA's Contractor, explained the need
for a Habitability Consultant in a letter to Raymond Loewy dated 12 February 1975: "Our space programs Mercury, Gemini, Apollo and Skylab - have been the exclusive preserve of the scientist, the engineer and the
medical doctor It was only with Skylab that we first recognised that, if man were to survive for extended
times in space, perhaps we engineers needed some added help." As it stood, all characteristics of existing
space vehicles [primarily Saturn IVB] had been determined entirely by their function as a fuel cell and were
heavily mission-orientated. Grids and internal structural members had been designed for the container's
rigidity and suitability to cryogene liquid hydrogen fuel flowing through it. This produced a hostile metallic
environment with distracting reflective light sources coming from the aluminium foil dome lining and filtered
through the multi-layered grid flooring. To heighten the visual confusion and sense of a mechanical not a
human environment, colour had been used to emphasise the different structural elements rather than
acting as an organising medium.
�CONTRACT SUMMARY REPORT
A1 - MSC Shuttle Orbiter Crew Compartment/X-Axis Docking
HABITABILITY STUDY
SHUTTLE ORBITER
JANUARY 1972/DECEMBER 1372
PREPARED FOR NASA BY
RAYMOND LOEWY/WILLIAM SNAITH, INC.
1 1• EAST 5 3 STREET. NEW YORK. N.Y. 10022
�Skylab, the first manned space station, in fact supported three separate crews for 171 days in
space between 15 May 1973 and 8 February 1974. Clearly, as much attention had to. be paid to "the
physiological safety and comfort of the astronauts" as had been paid to getting them into space. In the pithy
dictum of Dr. George Mueller, NASA's Deputy Administrator for Manned Space-Flights: "what comes out of
the sliding rule is not necessarily compatible with human life."
Raymond Loewy: reasons selected as Habitability Consultant
Following an investigation of various organisations, Dr. J. L. McLaughlin, Chief of NASA's Division of
Space Medicine, recommended Raymond Loewy and his team and confirmation of the appointment was
made on 15 November 1967
Loewy was a pioneer in industrial design and had had a distinguished career in both commercial
and public projects (see curriculum vitae at the end of the catalogue].
In 1962 he had designed the exterior markings and interior appointments of the U.S. Presidential
Air Force One and, "on the floor of the Oval Office", had explored with President Kennedy the idea of
"re-designing America". Kennedy had arranged a meeting between Raymond Loewy and Jim Webb, then
Administrator of NASA.
In the 1950s and 1960s Loewy had established the habitability standards of the U.S. Navy, Coast
Guard and Department of Commerce Maritime Administration. He had also worked on the experimental
submarine Tektite, emergency flying hospitals, helicopter ambulances and the interiors of the White House
helicopters. He had also had comprehensive experience in solving human problems in such projects as the
design of trains, passenger ships, aeroplanes, automobiles, buses, hotels, houses, hospitals, hydrofoils,
interior components for the Inter-Allied Command Headquarters in Washington during the Second World
War and even a prison.
��The Skylab Assignment
Raymond Loewy's task in 1967 was outlined by George Rodney, the Project Director of Martin
Marietta Aerospace:
• "Consultant is to conceive and develop means to insure the psycho-physiological comfort and
safety of the crew operating for prolonged periods in exotic conditions of Zero Gravity [Zero G],
while exposed to micrometeorites and other risks inherent to frequent EVA's [Extra Vehicular
Activities] in deep space"
• "Consultant to suggest ways and means to organise the interior of the workshop to allow the crew
to operate efficiently in a confined semi-dark space, while exposed to claustrophobia and little-known
forms of space sickness"
• "Desirability for the designer to keep in mind possibilities of psychic disturbances, even among men
of outstanding physical and intellectual excellence, triggered by isolation and impossibility of rescue
in case of serious operational failure and/or acute sickness"
• Establish a system to evaluate the fitness of individuals to become astronauts.
Special Problems and Unknown Factors
In 1967 the U.S. had little experience of manned space-flight and none of extended missions.
There were four constants for the designer, each with unknown consequences for human physical and
pyschological endurance:
• Zero Gravity, producing weightlessness
• Missions of long duration
• A surrounding hostile environment [including micrometeorites]
• A totally closed system with no visual access to Earth
Owing to the unique limitations of space, weight and materials, almost everything displayed or
discussed was outside the range of accepted habitability standards and practices. For instance, in 1967,
no one was certain how the crew would move about the station and the Apollo project was too undeveloped
to provide data on how to translate from point to point in a Zero Gravity environment.
Ignorance of the potential problems resulted in the proliferation of development designs, many of
them, such as for protective helmets, sleeping devices and exercising and guide rails, ultimately proving to
be unnecessary. Such unused designs greatly add to the historical value of the collection.
�HiCwLAa A<Tiy»Tf
SATURN FIVE SPACE STATION
HABITA6ILITY STUDY
RAYMOND IOEWY|WILLIAM S:.'
NASA
Extra-vehicular activity (EVA]
HQ
�Lack of knowledge also demanded some bizarre experiments, such as the following described
by Loewy:
"Because of the impossibility of reproducing weightlessness on Earth nobody knew whether or not
the device we had designed to collect fecal matter [for eventual analysis on re-entry] would create
sufficient suction to be effective. An engineer from the team with which we collaborated had an
idea in order to obtain visual confirmation of correct vacuum suction. View-ports were provided at
strategic locations in the fecal collectors installed in a fast aircraft. Volunteers were paid $50 to be
fed pure prune juice and after a pre-established time interval the aircraft took off at a steep climb.
At a given signal, it went into an outside loop creating for a few seconds a Zero Gravity condition of
weightlessness. Any volunteer that produced the necessary bowel movement was given an extra
$50 bonus payment for its contribution to the project's development."
Raymond Loewy^s General Recommendations for Skylab
After an initial briefing and indoctrination in Zero-Gravity living Raymond Loewy realised that the life
of the crewmen "would take place while subjected to many unfamiliar, often forbidding influences and
stresses, both physical and psychological. Besides discomfort, there might occur strange expressions of
space-sickness compounded with EVA risk and, perhaps, deep emotional distress. However, I felt that even
men of transcendental courage, and physical fitness, thoroughly trained through simulation devices and
prepared for all sorts of contingencies, would react in predictable ways in regard to atavistic personal and
social needs. Successful behaviour in prolonged 0-G and in close proximity to other men in cramped
quarters deserved subtle understanding and plenty of down-to-earth feelings on our part.
In addition, I felt that there was a value in surrounding them with a semblance of life-on-Earth
familiarity at least in social areas. To induce relaxation and relieve strain were, I thought, necessary
requirements.
I did not pretend, I freely admitted, that my opinions were necessarily based upon scientific
premise; they were simply a case of what we called 'educated intuition', the result of decades of field
experience."
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�A plenary session was held at NASA's Headquarters in Washington under the chairmanship of
Dr. George Mueller attended by scientists, psychologists, space medical doctors, engineers and astronauts.
Loewy was invited to express his views. He made the following general recommendations, which have
influenced all later concepts:
• A port-hole to maintain visual contact with Earth [debriefing remarks by crewmen as reported by
NASA after Skylab's first mission included the statement that the most important off-duty activity
was the window, and they wished they had more and larger windows)
• The need for sleeping areas giving total privacy for each crewman with the possibility of reading
and listening to recorded music ["primary recreational activity during 70.5 million miles of manned
space flight was listening to taped music..." recorded on wire to avoid fire risk. Aviation Week and
Space Technology, 8 April 1974)
• The necessity of a wardroom providing some measure of communal living at meal times and during
leisure periods
• The importance of adopting a vertical up-and-down monodirectional [Zero G) mode of living or
stance [foot restraints were particularly important in achieving this)
• The development of systems to prevent the ascendency of one crew member over his fellows
[the triangular eating surface was one outcome of this)
Practical Solutions by Raymond Loewy, primarily for Skylab
Raymond Loewy began his work under the enormous limitations imposed by the concept of a "wet"
launch [based on the crewmen's moving all internal equipment from the Multiple Docking Adaptor to the
Earth Orbital Space Station after the evacuation of residual fuel — Skylab was at first to be in a used fuel
tank). With the change to a "dry" launch [whereby the laboratory would be fitted out before launch) the
designer came into his own: among the many practical solutions produced by Loewy's team [working in
conjunction with the technical consultants) were:
��• WASTE MANAGEMENT — details of positioning, privacy and configuration taking into consideration
the impossibility of using toilet paper because the fibres floating in Zero Gravity could cause
pneumonia. The waste management system was one of the most significant technical and
habitability advancements of Skylab over earlier missions. The system was highly sophisticated and
enabled measured samples of urine and fecal matter to be retained in a freeze-dried state for
analysis on return to Earth to detect possible chemical changes in body due to Zero Gravity.
• FGOD MANAGEMENT — including designs for food preparation and utensils, with packaging Csome
collapsible) for convenience, attractiveness and control of errant food debris and surfaces that were
flush and easy to clean to prevent the accumulation of matter ejected through space sickness.
• HEADGEAR—the design of helmets to prevent injury through collision in Zero G [ultimately proved
to be unnecessary).
• CREW QUARTERS — the initial suggestion was that the living deck be divided into areas for exercise
and experiment, dining, waste management, sleep and storage: Loewy provided designs for privacy
and group relationships in three areas with toilets separate from basins.
• COLOUR SELECTION — with emphasis on a congenial, warm spectrum.
• PERSONAL HYGIENE — remembering that showers do not work in space.
• SLEEP STATIONS OR AREAS —the first layout made this a communal space with bunks and
storage pouches arranged in conventional bunkrooms. This took account only of the comatose
state of sleeping; but sleeping also involves undressing, a period of reflection, awakening, rousing
and dressing. Loewy insisted on privacy. The summary report stated: "Joe reads in his sleep
compartment at night. At night Pete uses the headset so no one else has to listen to the music."
• RESTRAINTS — so that while sitting and moving the crewmen could stabilize themselves by making
toe-holds with the toe-cleats in their sandals into the honeycomb floors or ceilings.
• RECREATIONAL ACTIVITIES — Robert L. Bond, Principal Investigator for Skylab Crew Activities
and Maintenance Studies reported:
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�.. they all say the most important item is the window - and they wish they had more of them and
bigger ones. They didn't start reading until the spacecraft altitude became such that they couldn't
track the ground out CofD the wardroom window, or when the major daylight ground track took them
primarily over water — they have used the balls a few times mainly out of curiosity. Paul is the
champ holding two records - C1) a toss from the MDA that bounced off the lid of the Trash A/L and
went into the CM without touching a thing (2) a toss around the same path the run around the
lockers that continued to strike the lockers in sequence 111 times before running out of gas and
going off line. No one has used any of the exercise gear. They prefer to ride the bike or lope around
the lockers. They all use the binoculars to look at the ground Cevery day). They all enjoy the tapes
and use the recorders in the wardroom, at the ATM, and in the bedrooms... they all feel that the
unique effects of Zero-G are just about enough to fill their off-duty time with interesting things to
do. They also feel that Earth bound interests stay with them in orbit and whatever a guy's hobby
or fun things to do on the ground might be is also what he would enjoy having for relaxation in flight within design reason. Oh yeah - and the darts don't work!"
Assessment of Raymond Loewy^s Achievement
Loewy's contribution has been the subject of laudatory articles in numerous magazines and
reports, but perhaps most telling are the assessments in letters from members of the NASA team.
Dr. George Mueller, Deputy Administrator of NASA's Manned Spacecraft Division wrote to Loewy
on 29 July 1974:
Dear Raymond:
Two significant events in the last decade will, I believe, shape the future course of human history.
The first was landing on the Moon with its demonstration that humanity was no longer bound to the
Earth. The second was the manned orbiting space station with its demonstration that man could
live for indefinite periods of time in a weightless environment and that he could perform useful,
yes, unique work in that environment.
Raymond, in my opinion, you and your organization played a crucial role in the latest of these
momentous steps that man is taking to the stars. I do not believe that it would have been possible
for the Skylab crews to have lived in relative comfort, excellent spirits, and outstanding efficiency
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�had it not been for your creative design, based on deep understanding of human needs, of the
interior environment of Skylab and the human engineering of the equipment and furnishings which
the astronauts used. That design and engineering applied, in turn, to our follow-on space stations
has provided the foundation for man's next great step - an expedition to the planets.
You should be proud, as all of us who know of your contribution are proud, of the key role you have
played in laying the foundation for man to live in space.
My most sincere congratulations for your work on the Skylab Program and my best wishes for
your continued contributions to man's role in space.
Sincerely,
George Mueller,
Chairman and President.
William Schneider, Director of the Skylab Programme, wrote to Caldwell Johnson, Principal
Investigator at the Johnson Space Centre, about his and Loewy's work:
".. .Your contributions both to the basic concept for the workshop living provisions and to many
of the detailed features that made it work well, were clearly instrumental in making Skylab the good
place for living and working that the crews found it to be. And the systematic collection and
organization of data from the missions will surely be of inestimable value in the design of the
Shuttle, the Spacelab, and the experiment hardware they will carry into orbit..."
��George Rodney, NASA's Contractor and Chief of Martin Marietta Aerospace, wrote to Raymond
Loewy on 12 February 1975:
Dear Raymond:
It was a pleasure to hear that the works of Raymond Loewy are going to be displayed at the
Smithsonian Institute. That thought has caused me to reflect on the unique place you have had
in our infant space program.
Our space programs - Mercury, Gemini, Apollo and Skylab - have been the exclusive preserve
of the scientist, the engineer and the medical doctor. It was only in Skylab that we first recognised
that, if man were to survive for extended times in space, perhaps we engineers needed some
added help. We enlisted the aid of Loewy Snaith Inc.; and it was your influence, Raymond, that
caused us to soften the lines, provide better crew accommodations, and consider the colors and
light and the many other factors that helped make life reasonable for the astronauts. You, in short,
among your many other firsts were the first to introduce the fine arts into space. Your imagination
and personal enthusiasm left an imprint on both the hardware and all of us who had the good
fortune to be associated with you.
Skylab has convincingly proved that we can live and work for indefinite periods in space and,
therefore, manned space travel to other areas of the universe is practical. I for one am convinced
that our civilization, if it continues to advance at all, will be setting forth on other planets within the
next fifty years. So I say to you my dear friend that, as you reflect on the many achievements
in your fabulous career, you can take special pride in your contribution to this next major step in
man's evolution.
My best personal regards.
Sincerely yours,
George A. Rodney
In 1973 Raymond Loewy was invited to become Habitability Consultant for The Space Programme of
the USSR. He declined.
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�Raymond Loewy
Raymond Loewy is generally recognised as one of the founders of the profession known as
industrial design.
Under the headline "A brilliant designer streamlined the shape of things by joining form to function
in bold new looks", he was hailed [in company with Edison, Bell, Ford and the Wright brothers] as one of the
major influences on the American way of life in a special report in Life magazine [bicentennial issue, 19753
entitled "The 100 events that shaped America". He was also listed as "One of the Thousand Makers of the
Twentieth Century" in the London Sunday Times [colour magazine], 1969.
Loewy's career was summarised thus in Life magazine: "Operating on the principles that 'form
must follow function' and that 'weight is the enemy', Loewy, in 1929, began by remodelling an ugly
duplicating machine into a handsome piece of office equipment. Subsequently Loewy's streamlined and
elegantly simple designs shaped thousands of products - from locomotives, tractors and refrigerators to...
vacuum cleaners. He created the revolutionary 'lean and hungry' postwar Studebaker. Later he designed
the interior of the Skylab and the emblem of the U.S. Postal Service. His innovations in packaging, like the
white wartime packet he created for the formerly green-packeted Lucky Strikes, started the trend toward
clean designs in which bold letters seemed to jump out at customers' eyes. Through the influence of Loewy
and his contemporaries, manufacturers now spend millions to make their products and the packages they
come in physically attractive, and in testing to determine which designs the public likes best."
When creating him a Grand Officer of the Legion d'Honneur President Giscard d'Estaing wrote
to Loewy:
"Vous n'avez cesse d'associer le nom de la France aux brillants succes qui font de vous I'une
des personnalites les plus marquantes de notre temps et de servir la cause de I'amitie entre la France
et I'Amerique."
��Among the many products and designs with which Raymond Loewy was involved may
be mentioned:
• Coca Cola bottle and can
• U.S. Postal Service emblem
• Lucky Strike packet
• Greyhound buses 1945-1950
• Studebakercars
• Presidential aircraft Air Force One
• Coldspot refrigerator
• Gestetner duplicating machine
• Kennedy memorial stamp
• Concorde interior and cutlery
• Shell and BP emblems, service stations and packages
• Heinz soup packaging
• Four Square Tobacco package
• Avanti cars
• Wrigley's chewing gum package
• Pennsylvania Railroads, locomotives and passenger cars CGG1;
K4S; S1;T1)
• Schick razors
• Total - service stations
• Hupmobile cars
• Lever Brothers packaging
• USSR - design of a large range of mass-manufactured
products
• Rosenthal crockery
• Sucaryl bottle
• De Dietrich - kitchen products
• Canada Dry soda bottle
• Black Label beer can
• Bird's coffee package
• Vosene medicated shampoo
• U.S. Navy nuclear destroyer 1938
• Exxon - Standard Oil of New Jersey's new trade mark
• Roots Brothers' Cars
• Hilton Hotels
• Austin 1948 model
• Fridgedair products
• Elna sewing machines
• Howard Hughes private aircraft 1951
• International Harvester trademark and tractors
• Aerodynamic ailerons
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�Raymond Loewy was born in Paris in 1893. He became a naturalized American citizen in 1937 and
married Viola Erickson in 1948.
His honours and positions include:
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Grand Officer of the Ldgion d'Honneur, 1980
Croix de Guerre, 1914-1918, four citations
Inter-Allied medal
Liaison Officer with American Expeditionary Force 1914-1918
Founder; Fellow and former President of the American Society of Industrial Design
Fellow of the Royal Society of Arts, London
Member of the American Academy of Achievement, Hall of Fame, Boston
Honorary Doctor of Fine Arts at the University of Cincinnati, Arts Center College, Los Angeles and the University of Linz, Austria
Award of Honor, California Design Institute, Los Angeles, 1979
Member of the Board of Education, New York City
Citizen of Honour of France, New York City, Chicago and Palm Springs
Member of the Psycho-Physiological Institute, Washington
Honorary life member of the American Railroad Association, Washington
Counsel to the American Society for the study of human factors in aviation
Lecturer at MIT, Harvard, UCLA, University of Paris and of Leningrad, USSR State Committee for Science and Technology, the
All-Union Institute of Industrial Research, Moscow, and U.S. Academy of Engineering, Washington
• Habitability Consultant to NASA's Saturn-Apollo Applications Programme, Skylab and Shuttle Orbiter projects
• Member of the U.S. Space Medicine Association
Exhibitions of his designs have been held at the Smithsonian Institute, Washington DC "The Designs
of Raymond Loewy" in 1975; and at Centre Beaubourg, Paris, 1975.
Articles about him have appeared in Time [cover 1949); Los Angeles Times ("Loewy puts his
stamp on the 20th century"); Life magazine "The Great Packager" (1949), as quoted above or in the main
body of the catalogue and elsewhere.
He is author of The Locomotive, its aesthetics; Never Leave Well Alone (his autobiography);
Raymond Loewy: Industrial Design and "Second-Best is not Enough" Reader's Digest 1963.
Last year the U.S. Foundation for the Arts made a television documentary about Loewy entitled
"Looking Back to the Future".
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Illustrations on pages 1, 2. 4, 25 and on the back cover by courtesy of NASA.
Printed and bound in Great Britain by Mackays of Chatham Ltd.
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Human Factors Engineering Collection
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Human Factors Engineering Collection
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/12">View the Human Factors Engineering Collection finding aid in ArchivesSpace</a>
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sdsp_skyl_000060
Title
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"Raymond Loewy Living in Space."
Description
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This biographical portfolio booklet describes the role that industrial designer Raymond Loewy's designs played in the Skylab program.
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Sotheby's
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1970-1979
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Skylab Program
Space habitats
Human factors in engineering design
Extravehicular mobility units
Spent Stage Workshop
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Portfolios (Groups of Works)
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Human Factors Engineering Collection
Box 2, Folder 3
University of Alabama in Huntsville Archives and Special Collections, Huntsville, Alabama
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
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Skylab Document Scanning Project Metadata
Skylab 50th Anniversary