Control for motors such as are employed in ballistic missiles and space vehicles proposed and three systems presented; fundamental equations of burning rate and mass rate of flow from which control system will be derived; design offers increase in specific impulse at cold temperature, decrease in specific impulse at hot temperature, and increase in specific impulse with decreasing atmospheric pressure (increasing altitude). (See also SAE -- Paper n 59T for meeting Mar 31-Apr 3 1959 23 p)
Thrust magnitude control of solid-propellant rocket motors by mechanical means
SAE -- J
Society of Automotive Engineers -- Journal ; 67 , n 7
1959
4 pages
Article (Journal)
English
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Thrust magnitude control of solid-propellant rocket motors by mechanical means
Engineering Index Backfile | 1959
|THRUST MAGNITUDE CONTROL OF SOLID-PROPELLANT ROCKET MOTORS BY MECHANICAL MEANS
SAE Technical Papers | 1959
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Online Contents | 2007
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