Fuzzy logic and guidance algorithm design

Conference · Sat Dec 31 00:00:00 EST 1994

OSTI ID:482015

Leng, G ^[1]

---

1. 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-; TRN: 97:002904-0047
• Resource Relation: Conference: 1. international conference on nonlinear problems in aviation and aerospace, Daytona Beach, FL (United States), 9-11 May 1996; Other Information: PBD: 1994; Related Information: Is Part Of First international conference on nonlinear problems in aviation & aerospace; Sivasundaram, S. [ed.]; PB: 729 p.
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES
99 MATHEMATICS
COMPUTERS
INFORMATION SCIENCE
MANAGEMENT
LAW
MISCELLANEOUS
INERTIAL GUIDANCE
COMPUTER-AIDED DESIGN
FUZZY LOGIC
MISSILES
ALGORITHMS
NAVIGATION