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Overview of Hybrid Sounding Rocket Program [PDF]

33rd Joint Propulsion Conference and Exhibit, 1997
A series of four hybrid sounding rockets were successfully launched as part of the Hybrid Propulsion Demonstration Program (HPDP). These flights demonstrated a safe non-pyrophoric/nonpyrotechnic ignition system, inexpensive component manufacturing techniques, simple launch operations, and a quick launch turn-around time. This paper gives an overview of
J. Arves, H. Jones, K. Kline, K. Smith, Ted Slack, T. Bales, J. Arves, H. Jones, K. Kline, K. Smith, Ted Slack, T. Bales   +11 more
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Optimization of Hybrid Sounding Rockets for Hypersonic Testing

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009
The use of ground-launched hybrid rockets to bring subscale models to flight conditions within the hypersonic flight corridor is investigated. The analysis is based on a multidisciplinary optimization procedure that couples the direct optimizations of the parameters that rule the engine geometry and operation and the indirect optimization of the ...
CASALINO, LORENZO, PASTRONE, Dario Giuseppe   +1 more
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Hybrid Rocket Engines

2012
The hybrid rocket engine utilizes a combination of solid rocket and liquid rocket technology to meet some flight mission applications. In terms of performance, cost, availability of materials and safety, the hybrid approach does potentially have some advantages.
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Optimal propellant control in hybrid rocket engines

31st Joint Propulsion Conference and Exhibit, 1995
Paper AIAA 95 ...
COLASURDO, GUIDO, PASTRONE, Dario Giuseppe, CASALINO, LORENZO   +2 more
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Enhancement of Regression Rate in Hybrid Rockets

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2011
This study has identified a potential HTPB based propellant that gives a very good density specific impulse but yet does not burn like a solid propellant. Due to low solid loading in this propellant, pre-curing of the HTPB and IPDI mixture is a necessity to get uniform density across the length of the grain.
Kumar Rajiv, P. A. Ramakrishna, Marothiya Gaurav   +2 more
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Model of Hybrid Rocket Combustion in Classical Hybrid Rocket Motors [PDF]

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013
Toru Shimada, Saburo Yuasa, Shigeru Yamaguchi, Takakazu Morita   +3 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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Hybrid rocket motor fuel studies

33rd Joint Propulsion Conference and Exhibit, 1997
Results from four fuel characterization studies are reported. The first study was a premix (complete fuel except for curative) hold time determination which concluded that a full-scale 600-gal premix could be held for at least 3 weeks without any harmful degradation of the cured final fuel.
H. Weyland, H. Weyland
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Hybrid Gas Generator for a Staged Hybrid Rocket Engine

Journal of Propulsion and Power, 2017
The two-stage combustion hybrid rocket engine with a hybrid gas generator method offers numerous advantages over a solid-propellant gas generator and classical hybrid rocket engines. These advantages include a higher specific impulse in operation, lower lifecycle costs, and lower sensitivity to combustion pressure.
Dong Eun Lee, Changjin Lee
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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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