Gas-Hybrid Rockets

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). 

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)... 

The moment at which emission of the gas jet by a rocket ends. In solid propellant rockets this moment corresponds to a complete burnout of the propellant in liquid fuel and hybrid rockets, reignition can take place. 

The hybrid metal phthalocyanine complexes may find application for specific pollution control processes such as S02 stack-gas scrubbing, post-Klaus plant scrubbing of H2S and S02, sweetening of sour oil-refinery wastes, odor and corrosion control in wastewater facilities, and the elimination of excess rocket fuel wastes. 

---