A method of designing a self-adaptive missile guidance system is presented. The system inputs are assumed to be known in a statistical sense only. Newton's modified Wiener theory is utilized in the design of the system and to establish the performance criterion. The missile is assumed to be a beam rider, to have a g limiter, and to operate over a flight envelope where the open-loop gain varies by a factor of 20. It is shown that the percent of time that missile acceleration limiting occurs can be used effectively to adjust the coefficients of the Wiener filter. The result is a guidance system which adapts itself to a changing environment and gives essentially optimum filtering and minimum miss distance.
Self-Adaptive Missile Guidance System for Statistical Inputs
1960
34 pages
Report
No indication
English
Self-adaptive missile guidance system for statistical inputs
Engineering Index Backfile | 1960
|A self-adaptive missile guidance system for statistical inputs
TIBKAT | 1960
|Synthesis of optimum homing missile guidance systems with statistical inputs
Engineering Index Backfile | 1959
|Engineering Index Backfile | 1959
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