Fuzzy logic and guidance algorithm design
Conference
·
OSTI ID:482015
- National Univ. of Singapore (Singapore)
This paper explores the use of fuzzy logic for the design of a terminal guidance algorithm for an air to surface missile against a stationary target. The design objectives are (1) a smooth transition, at lock-on, (2) large impact angles and (3) self-limiting acceleration commands. The method of reverse kinematics is used in the design of the membership functions and the rule base. Simulation results for a Mach 0.8 missile with a 6g acceleration limit are compared with a traditional proportional navigation scheme.
- OSTI ID:
- 482015
- Report Number(s):
- CONF-960503--
- Country of Publication:
- United States
- Language:
- English
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