| 引用本文: | 宫梓丰,刘刚,宋睿,等.考虑禁飞区的高超声速飞行器再入跟踪控制.[J].国防科技大学学报,2020,42(1):66-72.[点击复制] |
| GONG Zifeng,LIU Gang,SONG Rui,et al.Reentry tracking control of hypersonic vehicle with fly zone constraints[J].Journal of National University of Defense Technology,2020,42(1):66-72[点击复制] |
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| 考虑禁飞区的高超声速飞行器再入跟踪控制 |
| 宫梓丰1,刘刚1,宋睿2,吴玉彬1,蔡光斌1 |
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(1. 火箭军工程大学 核工程学院, 陕西 西安 710025;2. 火箭军士官学校 测试控制系, 山东 青州 262500)
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| 摘要: |
| 为确立高超声速飞行器再入精确模型,参考NASA的研究数据对动力学方程中的气动参数进行拟合。基于飞行器结构的相关性质及战略应用背景,加入热流密度、动压、过载和禁飞区等参考约束的限制,融合成强非线性、复杂耦合的最优控制问题。采用改进自适应伪谱法求解模型所构建的微分方程组,通过设置自适应网格细化与配点,使单位时间内状态变量和控制变量波动过大的时间区间被进一步细划,并利用SNOPT求解器解算出符合条件的最优轨迹。设计闭环控制器,实现对最优轨迹的姿态变化的跟踪,测试系统的性能并进行评估。仿真结果表明:整个再入过程中,飞行器速度下降过程偏于平稳,再入轨迹可以满足约束条件,在避开禁飞区的同时取得最大横向航程；三通道角速度收敛可控,对姿态的跟踪较理想,控制器基本可以实现精确调姿。 |
| 关键词: 高超声速飞行器 再入段 最优控制 自适应伪谱法 姿态跟踪 |
| DOI：10.11887/j.cn.202001010 |
| 投稿日期：2018-07-05 |
| 基金项目:国家自然科学基金资助项目(61773387) |
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| Reentry tracking control of hypersonic vehicle with fly zone constraints |
| GONG Zifeng1, LIU Gang1, SONG Rui2, WU Yubin1, CAI Guangbin1 |
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(1. School of Nuclear Engineering, Rocket Force University of Engineering, Xi′ an 710025, China;2. Department of Test Control, Rocket Force Sergeant School, Qingzhou 262500, China)
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| Abstract: |
| In order to establish the accurate reentry model of hypersonic vehicle, the aerodynamic parameters of the dynamic equation were fitted according to NASA′ s research data. Based on the physical properties and the practical application of the aircraft material, the constraints of heat flow, overload, dynamic pressure and fly zone constraints were set up, and the nonlinear multi-coupling optimal control problem was formed. The hp-adaptive pseudospectral method was used to transform the model. Through the mesh refinement process, the time interval of the larger change of state was further subdivided, and the optimal trajectory of the condition was calculated by using the SNOPT solver solution. A closed loop controller was designed to track the trajectory changes of the optimal trajectory, and to test the performance of the system and to evaluate it. The simulation results showed that during the whole reentry process, the speed decline process of the aircraft is stationary, the reentry trajectory can satisfy the constraint conditions, and the maximum transverse range is obtained while avoiding the no flight area. The angular velocity of the three channels is convergent and controllable, and the tracking of the attitudes is ideal. Above all, the controller can basically adjust the posture. |
| Keywords: hypersonic vehicle reentry stage optimal control adaptive pseudospectral method attitude tracking |
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