Browse Items (970 total)

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  "Evolutionary Steps in S-IVB Development."

  The injection stage of a multistage launch vehicle must be partially a velocity stage and partially a spacecraft; it must not only boost the payload, it must also perform cooperative mission operations with the payload after orbital insertion. These hybrid requirements result in intrinsic stage versatility which permits consideration of new and challenging missions for the stage which were unanticipated during initial design.; Prepared by T. J. Gordon, Director, Advance Space Stations and Planetary Systems, Space Systems Center, Douglas Aircraft Company, Huntington Beach, California.
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  "Minimax control of large launch boosters."

  Keith D. Graham is principal mathematician, Systems and Research Center, Honeywell, Inc., 2345 Walnut Street, St. Paul, Minnesota.; Work done under NASA contract NAS 8-11206 from the George C. Marshall Space Flight Center.; ABSTRACT: A method of specifying the gains of a linear controller for a large launch booster using a new application of optimal control theory is described in this paper. Results for a specific example are included. An important control requirement is to maintain cost variables (such as bending moment, engine gimbal deflection, and lateral deviation from desired trajectory) within specified limits in the presence of load disturbances. This requirement is met by using a performance index which depends explicitly on maximum achievable values of the cost variables in a finite time interval.
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  "Payload integration for space experimentation."

  Space experimentation requires an increasingly complex planning and systems engineering effort to meet the demand for highest precision and reliability of all measurements and observations. A companion paper discusses the interfaces between the scientific/technical areas of space experimentation and the instruments, subsystems and support systems within the spacecraft. This paper deals with the organization and the procedures which are needed to perform the difficult payload integration process for space experimentation. In the course of this process it is necessary to define the experiments completely, to describe all instruments in terms of engineering specifications, to investigate the commonality of equipment, to group the experiments into mission compatible payloads, to specify acceptable loads on all subsystems and astronauts (when present) and to plan for all contingencies during the flight.
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  Technical Reports" Bibliography.

  Bibliography of technical reports from 1957-1963
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  "Philosophy and practices of reliability as applied in the design of the Saturn Instrumentation System."

  The basic engineering approach used in the Saturn instrumentation system has evolved to provide a highly reliable design for short periods of operation. The airborne measuring and telemetry systems including preflight tests, inspection, documentation, and feedback between the users and designers are discussed. The apparent differences between the practice and theory of reliability are rationalized. Some consideration is given to new problems in designing systems that must operate in hostile environments for long periods. The potential contribution of redundancy as a design concept is discussed.; This paper is concerned with the airborne measuring and telemetry systems; it does not attempt to treat the entire Saturn instrumentation system which consists of tracking devices including optical, radar, and Doppler, plus television, film cameras, and a myriad of instruments connected with factory checkout, ground test, and launch.
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  "Liquid Rocket Engines."

  This paper presents a discussion on liquid propellant rocket engines. The first part contains a discussion on liquid propellants, including a description of various propellant types such as cryogenic, storable,bipropellant, and monopropellant. This part also points out desirable physical properties and includes a section on performance outlining the methods by which performance is calculated and shows performance for various liquid rocket propellant combinations.
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  "The NASA/Grumman Apollo lunar module"

  Handwritten in pencil on the document. Describes the layout and function of various sections of the Apollo lunar module.
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  "Structure of the NASA/Grumman lunar module."

  Describes the structure and function of each part of the NASA Lunar Module
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  "Manufacturing history - LM-5."

  Essay that focuses on the achievements of the Grumman Aerospace Corporation.
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  "LM System Description."

  Report that describes the major systems of the Lunar Module.