Results 191 to 200 of about 4,679 (234)

TURBULENT BOUNDARY LAYER COMBUSTION IN THE HYBRID ROCKET

Symposium (International) on Combustion, 1963
In this paper an effort has been made to survey recent theoretical and experimental work related to several aspects of the hybrid combustion process. It has been found that hybrid combustion is controlled by the rate at which heat can be delivered to the fuel surface, rather than by the surface reaction rates.
G. Marxman, M. Gilbert
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Hybrid rocket engine

2019
Предлагается новый гибридный (комбинированный) ракетный двигатель, на который получен патент Украины («Спосіб комбінування реактивного і прямоточного повітряно-реактивного двигунів». 25.08.2015 ¹100987). Обсуждаются некоторые аспекты его конструкции и работы в сравнении с аналогами.
Semenov, К, Kopiyka, A
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Internal ballistic considerations in hybrid rocket design

2nd Propulsion Joint Specialist Conference, 1966
This paper outlines methods for calculating the ballistic behavior of hybrid propellant combinations. The effects of scaling, pressure level, and internal geometric configuration are examined, utilizing a machine analysis that is based upon heat-transfer-limited theory.
C. E. WOOLDRIDGE, R. J. MUZZY
openaire   +1 more source

Assessment of Using Electric Pumps on Hybrid Rockets

AIAA Propulsion and Energy 2019 Forum, 2019
In small hybrid rockets, liquid oxidizer is fed into the combustion chamber by pressurizing the oxidizer tank to achieve the desired injector pressure. However, larger applications employ propellant pumps to keep the propellant tank mass at reasonable levels. Conventionally, pumps are implemented on rockets by means of turbopumps.
Gegeoglu, K., Kahraman, M., Üçler, Çağlar, Karabeyoglu, A.   +3 more
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Hybrid rocket motor experiments

1985
Aerospace ...
Timnat, Y.M. (author), Korting, P.A.O.G. (author)   +1 more
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Performance Additives for Hybrid Rockets

2016
Addition of performance-improving materials in the solid hydrocarbon fuels of hybrid rockets has been studied extensively both in academia and also in the industry. The primary motivation has been to improve the specific impulse, density impulse, and regression rate performance of the propulsion system.
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Model of Hybrid Rocket Combustion in Classical Hybrid Rocket Motors

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013
Takakazu Morita, Saburo Yuasa, Toru Shimada, Shigeru Yamaguchi   +3 more
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Hybrid rocket development at the American Rocket Company

26th Joint Propulsion Conference, 1990
R. KNIFFEN, BEVIN MCKINNEY, PAUL ESTEY
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Design and development of a hybrid rocket

A hybrid rocket is a propulsion system that uses a combination of solid fuel and liquid or gaseous oxidiser (Sutton 1992). Hybrids have many advantages, including their relative safety, minimal impact on the environment, low cost as compared to other forms of rockets, and their ability to be throttled.
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Hybrid Rocket Theory and Design

1968
A hybrid rocket is so named because one of the propellant components is liquid and the other solid. Normally the oxidizer is liquid and the fuel is solid. In a typical design (Fig. 7-1), the oxidizer is sprayed in at the head end of a solid cylindrical fuel grain. It is apparent that once the liquid oxidizer is injected, the combustion process proceeds
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