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 -- J v 67 n 7 July 1959 p 66-9)
Thrust magnitude control of solid-propellant rocket motors by mechanical means
SAE -- Paper
SAE Meeting ; 1959 Control
1959
23 pages
Conference paper
English
© Metadata Copyright Elsevier B. V. All rights reserved.
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
|TECHNICAL NOTES - Thrust Termination Dynamics of Solid Propellant Rocket Motors
Online Contents | 2007
|