Results 81 to 90 of about 10,741 (228)

Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles [PDF]

A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced Earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus ...
Andreev T., Bolieau C.W., Figure, Gordon S., Loh W.H.T., PrimeEquipmentContraclEnd, Sutton G.P., Zurawski R.L.   +7 more
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The problem of combustion instability in liquid rocket engines

Challenges and Issues of Modern Science
The purpose of this work is to carry out an overview on combustion instability in liquid propellant rocket engines, its classification, the main principles of occurrence as well as ways to prevent the phenomena while designing of the prospective engine.
Samir Vekilov, Volodymyr Lipovskyi, Roman Pustovyi   +2 more
doaj  

Three stage rocket vehicle with parallel staging [PDF]

, 1984
A three stage rocket vehicle has a large forward propellant tank and a small aft propellant tank axially aligned. Secured to the rear end of the aft propellant tank is an engine mount structure carrying rocket engines.
Marshall, W. R.
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A novel heat transfer modeling methodology for regenerative cooling in liquid propellant rocket engines

Case Studies in Thermal Engineering
Liquid propellant rocket engines operate at extremely high temperatures and commonly rely on regenerative cooling to protect chamber walls and maintain structural integrity.
T. Gândara, V. Costa, J. Dias
doaj   +1 more source

Analysis of the Combustion Process in the Engine Zamstic [PDF]

فناوری در مهندسی هوافضا, 2017
In liquid rocket engine design, because of the combustion due to the high temperatures and high rates of heat transfer (1MW/m2 to about 160MW/m2) of hot gases to the chamber walls, the cooling thrustchamber is of utmost importance.
Koros nekofar, Andisheh Tiregar, seyed Amir Hosseini   +2 more
doaj  

The alleged contributions of Pedro E. Paulet to liquid-propellant rocketry [PDF]

The first practical working liquid propellant rocket motor was claimed by Pedro E. Paulet, a South American engineer from Peru (1895). He operated a conical motor, 10 centimeters in diameter, using nitrogen peroxide and gasoline as propellants and ...
Ordway, F. I., III
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Chemistry: Space resources for teachers including suggestions for classroom activities and laboratory experiments [PDF]

, 1971
Curriculum supplement to assist general chemistry teachers in updating instruction materials with aerospace ...
Bowman, W. H., Lawrence, R. M.
core   +1 more source

Development of Solid Gas Generating Compositions to Ensure Non Explosiveness of Spent Orbital Stages of Liquid Rocket of Space Launch Vehicles

Eurasian Chemico-Technological Journal, 2017
The choice is discussed of solid gas generating compositions for venting by hot combustion products a fuel tank of the spent orbital stage of a space launch vehicle with a main liquid rocket engine.
V. I. Trushlyakov, K. I. Zharikov, D. B. Lempert   +2 more
doaj   +1 more source

In-situ propellant rocket engines for Mars mission ascent vehicle [PDF]

When comtemplating the human exploration of Mars, many scenarios using various propulsion systems have been considered. One propulsion option among them is a vehicle stage with multiple, pump fed rocket engines capable of operating on propellants ...
Roncace, Elizabeth A.
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Supercharged topping rocket propellant feed system [PDF]

, 1979
A rocket propellant feed system utilizing a bleed turbopump to supercharge a topping turbopump is presented. The bleed turbopump is of a low pressure type to meet the cavitation requirements imposed by the propellant storage tanks.
Ginsburg, A., Hartmann, M. J., Stewart, W. L.   +2 more
core   +1 more source