Please use this identifier to cite or link to this item: http://scholarbank.nus.edu.sg/handle/10635/58488
Title: Missile guidance algorithm design using inverse kinematics and fuzzy logic
Authors: Leng, G. 
Keywords: Aerospace engineering
Guidance algorithm design
Inverse kinematics
Issue Date: 1996
Source: Leng, G. (1996). Missile guidance algorithm design using inverse kinematics and fuzzy logic. Fuzzy Sets and Systems 79 (3) : 287-295. ScholarBank@NUS Repository.
Abstract: This is a feasibility study of using fuzzy logic to guide an air-to-surface missile against a stationary target. The guidance algorithm design specifications are (1) a smooth transition at lock-on, (2) inherent acceleration command limits and (3) large impact angles. Inverse kinematics is used to design the fuzzy guidance algorithm so that all three requirements are satisfied. A comparison with proportional navigation (PN) guidance is made with respect to impact angle, intercept time and command limits. It is shown that, unlike PN guidance, the combined inverse kinematics/fuzzy logic guidance scheme is able to satisfy the conflicting design requirements. © 1996 - Elsevier Science B.V. All rights reserved.
Source Title: Fuzzy Sets and Systems
URI: http://scholarbank.nus.edu.sg/handle/10635/58488
ISSN: 01650114
Appears in Collections:Staff Publications

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