A guidance strategy is proposed for reducing target miss produced by performance uncertainty in the final stage of ballistic missile systems that do not have thrust termination or other velocity control capability. The approach taken here is to turn the thrusting missile onto a null range direction such that performance uncertainty contributions to target miss are reduced. The guidance algorithm proposed here does not constrain time-of-flight. Since time-of-flight normally varies with thrusting flight along a null range direction, the result is a guidance solution that does not change rapidly near the end of the motor burn. This guidance procedure is a variation of an iterative Lambert guidance scheme that can be used to provide a position constraint with a nearly constant bum attitude by allowing a variable time-of-flight.
Cut-off insensitive guidance with variable time of flight
1993
9 pages
Report
Keine Angabe
Englisch
93-3785 Cut-Off Insensitive Guidance with Variable Time of Flight
British Library Conference Proceedings | 1993
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Online Contents | 2015
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