Results 241 to 250 of about 16,009 (301)

Liquid Propellant Rocket Development

Journal of the American Rocket Society, 1946
Liquid Propellant Rocket Development" By M. W. NESBITT Chief Engineer, Reaction The subject of liquid propellant rocket development is one which has become greatly broadened in the past three years. In order to cover each phase of liquid rocket development in detail it would be necessary to spend considerably more time than is presently available ...
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Liquid-Propellant Rocket Power Plants

Journal of Fluids Engineering, 1947
Abstract This paper discusses some of the general features of liquid-propellant rocket power plants, and the propellant systems which have been developed. The object of the discussion is to call attention to problems requiring solution in order to improve the reliability and performance of liquid-propellant rocket power plants.
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On porous liquid propellant rocket engine injectors

Aerospace Science and Technology, 2008
A novel injection concept for cryogenic liquid propellant rocket engines has been tested and verified successfully using an optically accessible combustion chamber. The injector consists of a porous faceplate made from sinter metal and five LOX posts arranged in a classical parallel showerhead configuration.
Lux, Johannes, Suslov, Dmitry, Haidn, Oskar   +2 more
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Simulation of liquid propellant rocket engine combustion instabilities

17th Aerospace Sciences Meeting, 1979
A simulation technique for studying the high frequency combustion instabilities of liquid propellant rocket engines has been developed and used to investigate various aspects of instability phenomena. Of importance was investigation of the significance of the method of coupling the combustion and the gas dynamics of the system.
M. B. Ventrice, J. C. Fang, K. R. Purdy
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Design of liquid-propellant rocket engines

Journal of Machinery Manufacture and Reliability, 2012
A design method for liquid-propellant rocket engines is proposed, on the basis of models adjusted in response to test results. This method increases the reliability of the results and reduces ground testing of the motors. The effectiveness of the method is confirmed by ground testing and flight experience with the motors developed by Salyut Design ...
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Liquid-propellant rocket abort fire model.

Journal of Spacecraft and Rockets, 1971
During a rocket launch pad abort, a hazardous payload material can be subjected to a severe thermal environment from the resulting fireball. A model has been developed which specifies heat flux from the fireball as a function of time for any initial propellant quantity.
H. C. Hardee, B. E. Bader, A.B. Donaldson   +2 more
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Numerical simulation of a liquid propellant rocket motor

Journal of Thermal Science, 2001
This work presents a numerical simulation of the flow field in a liquid propellant rocket engine chamber and exit nozzle using techniques to allow the results to be taken as starting points for designing those propulsive systems. This was done using a Finite Volume method simulating the different flow regimes which usually take place in those systems ...
Carlos E. S. S. Migueis, Nicolas Moisés Cruz Salvador, Demétrio Bastos-Netto, Marcelo M. Morales   +3 more
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Liquid propellant rocket engines - Their status and future.

Journal of Spacecraft and Rockets, 1967
Performance, weight, design, flexibility, engine cycles and reliability of liquid propellant rocket engines used in NASA and USAF ...
V. R. Larson, R. V. Burry, S. F. Iacobellis   +2 more
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Liquid-Propellant Rocket Engine Injector Dynamics

Journal of Propulsion and Power, 1998
The dynamic characteristics of liquid-rocket injectors in the presence of intense combustion-chamber and propellant feed-line oscillations are discussed. Liquid-propellant injectors always function in nonsteady e ow environments and are therefore considered as a dynamic component of an engine.
Vladimir G. Bazarov, Vigor Yang
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Liquid-Propellant Rocket Engines

2012
The liquid-propellant rocket engine has the characteristics that allow it to deliver thrust at a high-performance level, with an efficiency and operational flexibility that enables a number of mission applications to go forward. Monopropellant and bipropellant versions of this category of engine are discussed in some detail in this chapter.
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