A Contribution to the Study of Galactic Dimensions by Shapley H.

By Shapley H.

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GnI . I EngineComponent I, FinalizedDesign I Fig. 2-1 Flowchart for rocket-engine preliminary design. 23 24 D E S I G N OF L I Q U I D - P R O P E L L A N T R O C K E T ENGINES ("crash program") will raise the cost and will unfavorably affect reliability. A longer design and development period m a y not necessarily reduce cost, but it will offer higher values in exchange for the dollar~higher reliability, refined (lower) weight, and an optimized (smaller) envelope. Thrust Level This engine parameter, a basic one, similar to the power rating of a gasoline engine or electric motor, will affect most of the other engine parameters and many of the development considerations.

03. 15. The relation among correction factors may be expressed as follows: r/v = r/v * r/v = I/~w "~e (1-43) (1-44) During the 1970s, the joint Army, Navy, and Air Force (JANNAF) c o m m i t t e e on r o c k e t - e n g i n e p e r f o r m a n c e d e v e l o p e d analytical procedures anchored o n test data to calculate the performancecorrection parameters in a rigorous manner. Because of the extensive nature of the subject and the fact that examples throughout this book are based on coefficients defined by Eq.

Adequate venting systems are needed for the developed gases. Storage and handling equipment and components are extremely sensitive to atmospheric or other moisture; even minute quantities may cause a jamming of, for instance, a valve. The design criteria, including materials selection for engine systems using cryogenic propellants, must consider the very low temperatures involved. The mechanical design of engine components for cryogenic-propellant applications will be discussed in subsequent chapters.

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