The aim of the first part of this article is to demonstrate the potentialities of hybrids in the space program. These potentialities are applicable to all three main classes of chemical rockets currently in use, namely: (1) storable -propellant rockets, (2) cryogenic-propellant rockets, and (3) semistorable-propellant rockets, where the non-storable element is introduced at the time of firing. On the basis of these three categories, the properties of hybrid systems are discussed in relation to the specific impulse. The hybrid method of propulsion is compared with standard solid- and liquid-propellant propulsion systems. The second part of the article is concerned with the fundamental problems of combustion, the emphasis being placed on the rate of regression of the solid phase, which determines the performance of the system. Different theories of the regression rate are described and compared with various experimental results.
Hybrid Rocket Propulsion [La propulsion par fusees hybrides]
14th International Astronautical Congress ; 1963 ; Paris, FR
1964-02-01
Report
No indication
English
TIBKAT | 1964
|NTIS | 1993
|NTRS | 1993
|AA150R Hybrid Rocket Propulsion
NTRS | 2016
|