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With regard to the maneuverability insufficiency encountered by missiles with large static margin when achieving large impact angle constraint,the minimax acceleration guidance law with impact angle constraint is proposed to reduce the missile 's required acceleration and avoid control saturation.First,the minimax problem is transformed to a conventional optimal control problem by introducing an auxiliary state into the dynamic equations. Then the analytic solution for lag-free system is deduced through trial and error,while the numerical solutions for lag-free and first-order lag systems are obtained by Gauss pseudospectral method. The effectiveness of these two approaches is validated through numerical simulations. It is shown that the optimal trajectories for lag-free and first-order lag systems are respectively accurate and approximate combinations of circular arc and line segment.
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Basic Information:
DOI：10.16358/j.issn.1009-1300.2017.06.13
China Classification Code:TJ765.3
Citation Information:
[1]Guo Kun,Yang Shuxing.Minimax Acceleration Guidance Law Design with Impact Angle Constraint[J].Tactical Missile Technology,2017,No.186(06):76-82.DOI:10.16358/j.issn.1009-1300.2017.06.13.
Fund Information:
国家自然科学基金(11532002)
2017-11-15
2017-11-15