Please use this identifier to cite or link to this item:
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
Citation: 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
ISSN: 01650114
Appears in Collections:Staff Publications

Show full item record
Files in This Item:
There are no files associated with this item.

Page view(s)

checked on Apr 20, 2019

Google ScholarTM


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.