| 基于SQP法的助推-滑翔导弹助推段弹道优化研究 |
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| 引用本文： | 杨铮,岳瑞华,李冰,徐中英. 基于SQP法的助推-滑翔导弹助推段弹道优化研究[J]. 指挥控制与仿真, 2014, 36(5) |
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| 作者姓名： | 杨铮 岳瑞华 李冰 徐中英 |
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| 作者单位： | 第二炮兵工程大学,第二炮兵工程大学,第二炮兵驻第四研究院军事代表室,第二炮兵工程大学 |
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| 摘 要： | 轨迹优化是飞行器总体优化设计中的重要组成部分，它贯穿于飞行器的整个设计过程。高超声速助推-滑翔导弹的弹道优化问题涉及攻角、法向过载、最大动压等多种约束条件，是一种复杂的最优控制问题。序列二次规划法（SQP）是解决该类问题行之有效的数值优化方法。本文利用SQP算法对助推-滑翔导弹助推段进行弹道优化，为这一高超声速飞行器的整体结构设计提供了有益的参考。
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| 关 键 词： | 弹道优化 SQP 约束条件 数学模型 |
| 修稿时间： | 2014-05-07 |
The Research About Trajectory Optimization of The Booster Trajectory of The Booster - Gliding Missile Based On the SQP Method |
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| yangzheng,yueruihu,libing and xuzhongying. The Research About Trajectory Optimization of The Booster Trajectory of The Booster - Gliding Missile Based On the SQP Method[J]. Command Control & Simulation, 2014, 36(5) |
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| Authors: | yangzheng yueruihu libing xuzhongying |
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| Affiliation: | The Sencond Artillery Engineering University,The Sencond Artillery Engineering University,The second artillery in the fourth institute military agent's room,The Sencond Artillery Engineering University |
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| Abstract: | Trajectory optimization, which runs through the whole design process of the craft, is an important part of the craft overall optimizationdesign. The trajectory optimization of thehypersonic booster - gliding missile isa kind of complex optimal control problem.Itinvolves a variety of constraint limits,such as attackangle, normal overload, the maximum dynamic pressure and so on.The Sequential quadratic programming method (SQP) is an effective numerical optimization methodto solve the problem. In this paper, the SQP is applied to optimize the booster trajectory of the booster - gliding missile,providing the beneficial reference for the integral structure designof such kind of high supersonic aircraft. |
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| Keywords: | trajectory optimization SQP constraint limit mathematic model |
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