Designing integrated guidance law for aerodynamic missiles by hybrid multi-objective evolutionary algorithm and tabu search

In this paper, a strength Pareto evolutionary algorithm (SPEA) based approach is proposed for designing an integrated fuzzy guidance law which consists of three fuzzy controllers. Each of these controllers is activated in a region of the interception. The distribution of the membership functions and...

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Bibliographic Details
Published in:Aerospace science and technology Vol. 14; no. 5; pp. 356 - 363
Main Authors: Omar, Hanafy M., Abido, M.A.
Format: Journal Article
Language:English
Published: Issy-les-Moulineaux Elsevier SAS 01.07.2010
Elsevier
Subjects:
Algorithms
Construction
Evolutionary algorithm
Evolutionary algorithms
Exact sciences and technology
Fundamental areas of phenomenology (including applications)
Fuzzy
Guidance
Law
Missile
Missiles
Multi-objective optimization
Optimization
Physics
Solid dynamics (ballistics, collision, multibody system, stabilization...)
Solid mechanics
Tabu search
Tradeoffs
Guidance
Missile
Multi-objective optimization
Tabu search
Evolutionary algorithm
Energy consumption
Membership function
Pareto optimum
Hierarchical classification
Multiobjective programming
Solid dynamic
Aerodynamics
Constrained optimization
Fuzzy logic
Fuzzy control
Interception
Missile guidance
ISSN:1270-9638, 1626-3219
Online Access:Get full text
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Summary:In this paper, a strength Pareto evolutionary algorithm (SPEA) based approach is proposed for designing an integrated fuzzy guidance law which consists of three fuzzy controllers. Each of these controllers is activated in a region of the interception. The distribution of the membership functions and the rules are obtained by solving a nonlinear constrained multi-objective optimization problem where final time, energy consumption, and miss distance are treated as competing objectives. Tabu search is proposed to build a library of initial feasible solutions for the multi-objective optimization algorithm. In addition, a hierarchical clustering technique is implemented to provide the decision maker with a representative and manageable Pareto-optimal set without destroying the characteristics of the trade-off front. Moreover, a fuzzy-based mechanism is employed to extract the best compromise solution over the trade-off curve. The simulation results show that the proposed design technique was able to generate a missile guidance law with satisfactory performance with the existence of noisy measurements.
Bibliography:ObjectType-Article-2
SourceType-Scholarly Journals-1
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ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2010.03.001