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"Propulsion development problems associated with large liquid rockets."
NASA technical memorandum, Propulsion and Mechanism Branch. Propulsion and Vehicle Engineering Division, Research and Development Operations. -
"Pratt & Whitney Aircraft RL10 liquid hydrogen rocket engine"
Photograph of a Pratt & Whitney rocket engine. -
"Pratt & Whitney Aircraft RL10 liquid hydrogen rocket engine."
Photograph of a liquid hydrogen rocket engine. -
"Manned space flight schedules. Vol. III, launch vehicles : book 4, engines."
OMSF Program Status Review October 1965.; Edition "A" -
"Nondestructive testing of space vehicle liquid propellant rocket engines."
Presented at the Western Metals Congress, Los Angeles, California, 15 March 1967.; Archive copy is a photocopy.; ABSTRACT: This report describes the various nondestructive test methods employed to evaluate materials and processes used in the manufacture of large liquid propellant rocket engines at the Rocketdyne Division of North American Aviation, Inc. The contents of the paper were purposely oriented for an audience of aerospace, design and materials engineers. A brief description of liquid propellant rocket engine reliability is presented. The relationship of standards and specifications to nondestructive testing is discussed and various test methods are described along with a discussion of their applications and limitations. The sequence of events leading up to the use of nondestructive testing in production inspection is presented. Finally, the organization of labor directly related to nondestructive testing is given. -
"News from Rocketdyne : Project Saturn."
Press release exploring the rockets and projects of the Saturn project. -
"Memorandum to Dr. Seamans from Mr. Holmes. Subject: F-1 engine combustion instability problems."
Memorandum discussing a presentation regarding problems that needed solving, a "Dr. Evvard's" lack of cooperation and letters to Wernher von Braun. -
F-1 engine photograph.
8 x 10 inch black and white photograph. Engine parts are labeled. -
"Decision Procedure for Minimizing Costs of Calibrating Liquid Rocket Engines."
Prior to acceptance of a liquid rocket engine for use in Saturn vehicles, the average thrust of two consecutive tests without an intervening calibration must satisfy specification requirements. The contractor may recalibrate after the first and subsequent tests if he so chooses, based upon decision limits, until the above requirement is met. -
"The Challenge of Change vs the Control of the Process."
The introduction states, "This paper is designed to present the Rocketdyne engine program as it applies to the Saturn launch vehicles and will apply to the Apollo program of manned flight to the moon (Fig. 1). The vehicle that will launch this flight is the Saturn V, the largest and most powerful of the Saturn family. This vehicle, 362 feet tall and 33 feet in diameter, will be capable of sending a 45-ton payload to the moon or placing a 120-ton payload in earth orbit. Five F-1 engines power the first stage of the Saturn V; five J-2 engines, the second stage; and one J-2 engine, the third stage. The thrust of the first-stage engines alone will be equivalent to 160 million horsepower. Both of these engines, the F-1 and the J-2, were designed at, and are currently being produced by Rocketdyne."