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
|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||URI:||http://scholarbank.nus.edu.sg/handle/10635/58488||ISSN:||01650114|
|Appears in Collections:||Staff Publications|
Show full item record
Files in This Item:
There are no files associated with this item.
checked on Apr 20, 2019
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.