Hybrid rockets

F) Anon, Experimental Analysis of Hybrid Rocket Fuels for MHD Pulse Power Generation Interim Tech Rept No 3, 2 Mar—2 Nov 66,... 

Rastogi, R. P. et al., Indian J. Chem., Sect. A, 1980, 19 A, 317-321 Reaction in this hybrid rocket propellant system is enhanced by presence of ammonium vanadate. 

Fineman, S., Some Analytical Considerations of the Hybrid Rocket Combustion Problem, M. S. E. Thesis, Department of Aeronautical Engineering, Princeton University, Princeton,... 

Hybrid rockets are intermediate between solid rockets and hquid rockets in terms of the nature of the combination of solid fuel and hquid oxidizer. Since the fuel and oxidizer components of a Hquid rocket are physically separated, two mechanical systems are needed to feed these components into the combustion chamber. On the other hand, a hybrid rocket uses a polymeric inert material as a fuel and a Hquid oxidizer, and so only one mechanical system is needed to feed this Hquid oxidizer into the combusHon chamber. 

In order to improve the combustion performance of hybrid rockets, a new concept of a hybrid rocket is proposed the gas-hybrid rocket.l ] Fig. 14.23 shows a schemafic drawing of a gas-hybrid rocket composed of a combustion chamber, a gas generator, a Hquid oxidizer tank, and oxidizer feeding pipes and a valve. UnHke conventional hybrid rockets, the gas-hybrid rocket is a two-stage combusHon sys-... 

Fig. 14.24 Two types of gas-hybrid rocket gas-pressurized system and turbo pump operation system.

Though the pyrolants used in gas-hybrid rockets burn in a similar manner as rocket propellants, their chemical compositions are fuel-rich. The pyrolants burn incompletely and the combustion temperature is below about 1000 K. When an atomized oxidizer is mixed with the fuel-rich gas in the secondary combustor, the mixture reacts to generate high-temperature combustion products. The combushon performance designated by specific impulse, is dependent on the combinahon of pyrolant and oxidizer. 

Fig. 14.25 Specific impulse of an N204/pyrolant gas-hybrid rocket as a function of oxidizer/fuel ratio.

Kuwahara, T, Mitsuno, M., Odajima, H., Kubozuka, S., and Kubota, N., Combustion Characteristics of Gas-Hybrid Rockets, AlAA-94-2880, New York (1994). 

Q3) V. Lindner, pp 716-17 in Kirk Othmer s Encycl, Vol 8(1965) (Burning rate detn of rocket proplnts by strand burning method ) R ) R.J. Zabelka, "Combustion of Several Hybrid Rocket Fuels , UnivMicrofilms, Ann Arbor, Michigan, Order No 65-2668, 247 pp. Dissertation Abstract 26(4), 2091-92(1965) (Engl) CA 64, 3273 (1966) K2) F. Solimosi... 

WWII. Hybrid Rocket Propellants are described in this Vol... 

Hybrid Rocket Propellants. A special proplnt combination of unlike materials, particularly of unlike physical characteristics. Typical hybrid proplnt combinations are a solid fuel (or oxidizer) in combination with a liquid oxidizer (or fuel) in tjiat order. Sometimes a grain of solid fuel is encased in the combustion chamber of a rocket engine and burned in combination with liq oxygen. Similarly, a liq fuel may be injected into a combustion chamber in contact with a solid oxidizer. Another example is the use of concentrated hydrogen peroxide and a hydrocarbon fuel. In this case, the hydrogen peroxide is converted by decompn into a hot gas contg oxygen. The fuel is injected downstream of the first reaction, mixed with the hot oxidizer-rich gas, and burns (Ref 1)... 

Hybrid rocket proplnts hybrid technology provide a number of propulsion-system capabilities in combinations not readily achievable with all-solid or all-liq systems. Foremost among... 

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