Results 81 to 90 of about 9,371 (228)
LOX/Hydrogen Coaxial Injector Atomization Test Program [PDF]
Quantitative information about the atomization of injector sprays is needed to improve the accuracy of computational models that predict the performance and stability margin of liquid propellant rocket engines.
Zaller, M.
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Technical Assessments of Future European Space Transportation Options [PDF]
, 2007 The paper describes some of the most recent activities in Germany in the technical assessment of future European launcher architecture. In focus is a joint effort of DLR-SART with German launcher industry in the definition of a next generation upper ...
Dutheil, Jean-Philippe +3 more
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Determination of the effects of nozzle nonlinearities upon nonlinear stability of liquid propellant rocket motors [PDF]
The research is reported concerning the development of a three-dimensional nonlinear nozzle admittance relation to be used as a boundary condition in the nonlinear combustion instability theories for liquid propellant rocket engines.
Padmanabhan, M. S. +2 more
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Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение, 2016 The article presents the results of theoretical and experimental studies of the peculiarities of the working process of low-thrust hypergolic- propellant liquid rocket engines (LTLRE) with the thrust of less than 1 N.
V. E. Nigodjuk, A. V. Sulinov
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Performance of a circular body earth-to-orbit winged transport with various strap-on boosters [PDF]
Various types of twin strap-on boosters were evaluated by applying them to a core vehicle. The core vehicle has a clipped delta wing and a simple circular body, and is equipped with five Space Shuttle main engines.
Macconochie, Ian O. +2 more
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Passively regulated water electrolysis rocket engine Patent [PDF]
, 1970 Water electrolysis rocket engine with self- regulating stoichiometric fuel mixing ...
Grant, D. J.
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Mehran University Research Journal of Engineering and Technology, 2019 Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants. Characteristic length is defined by the time required for complete burning of fuel.
Tajwali Khan, Ihtzaz Qamar
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High energy-density liquid rocket fuel performance [PDF]
A fuel performance database of liquid hydrocarbons and aluminum-hydrocarbon fuels was compiled using engine parametrics from the Space Transportation Engine Program as a baseline. Propellant performance parameters are introduced. General hydrocarbon fuel
Rapp, Douglas C.
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AN OPTIMIZED HYBRID ROCKET MOTOR FOR THE SARA PLATFORM REENTRY SYSTEM DOI 10.5028/jatm.2012.04032312
Journal of Aerospace Technology and Management, 2012 This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the
Pedro Luiz Kaled Da Cás +3 more
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Launch Vehicle Description [PDF]
, 1970 The Thorad-Agena is a two-stage launch vehicle consisting of a Thorad first-stage and an Agena second-stage, connected by a booster adapter. The composite vehicle, including the shroud and the booster adapter, is about 33 meters (109 ft) long.
Coffey, E. E., Geye, R. P.
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