Onboard computer equations for rocket vehicle guidance to elliptical orbit are developed; computational requirements are held to minimum, consistent with accurate orbital injection, near optimum fuel consumption, and explicit formulation; digital simulation results are shown for circular orbit injection with Saturn V vehicle; guidance scheme errors are less than 1 1/10 m/sec for disturbances caused by wind and variations in rocket engine parameters; payload loss caused by simplified guidance law is less than 1/10% of gross weight delivered to orbit. (17709)
Simplified explicit guidance scheme for orbital injection
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 11
1968
3 pages
Article (Journal)
English
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