Thrust, rocket

The ratio of rocket thrust to propellant mass flow, commonly called the specific impulse (/9p) of the propellant, represents a measure of the force developed per unit mass flow of propellant. From Eq. (2), it is apparent that high propellant-flame temperatures and low molecular-weight combustion products are required to produce high 7sp. 

The main component of a modem liquid-propellant rocket thrust-chamber assembly is called the coolant jacket. There are many jacket designs but, in nearly all cases, the jacket structure extends thru the throat region as well as the combustion chamber Ref J.W. Herrick E. Burgess, Rocket Encyclopedia Illustrated , Aero Publ, Los Angeles, Calif (1959), p 240... 

Blow. The slang word for an expin, a severe deton or any expl type malfunction that occurs when testing a rocket thrust chamber or similar rocket component... 

In rocketry, the term might mean the consumption of a solid proplnt chge in a rocket thrust chamber in a manner that results in the gas pressure remaining constant Refs l)Ohart(1946), 23 2)Glossary of Ord(1959), 194 3)RocketEncycl(1959)-not found... 

II. A. 5. Variation of rocket thrust coefficient with nozzle... 

Fig. II. A. 5 Variation of rocket thrust coefficient with nozzle area ratio and pressure ratio Pc/Pa for Y = 1.2...

Fig. 6 Rhenium rocket thrust chamber fabricated using CVD. Photo courtesy of B. H. Tuffias, Uitramet. ...

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