| 引用本文: | 彭双春,朱建文,汤国建,等.基于旋量方法的高超声速飞行器三维非线性伪最优制导律设计.[J].国防科技大学学报,2015,37(6):84-90.[点击复制] |
| PENG Shuangchun,ZHU Jianwen,TANG Guojian,et al.Three-dimensional nonlinear pseudo optimal guidance law for hypersonic vehicle based on twist technology[J].Journal of National University of Defense Technology,2015,37(6):84-90[点击复制] |
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| 基于旋量方法的高超声速飞行器三维非线性伪最优制导律设计 |
| 彭双春, 朱建文, 汤国建, 陈克俊 |
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(国防科技大学 航天科学与工程学院， 湖南 长沙 410073)
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| 摘要: |
| 针对高超声速飞行器制导过程中的通道耦合问题, 设计一种基于旋量方法的三维非线性伪最优制导律。引入角度矢量、视线旋量、视线旋量速度等概念，通过等价性证明，得出视线旋量、视线旋量速度控制分别与视线方位、视线角速度控制具有一致性的结论，从而将制导问题转化为视线旋量和旋量速度的控制问题；基于旋量方法构建弹目视线旋量、视线旋量速度模型, 构建得到飞行器制导的三维非线性模型；为避免直接求解Riccati微分方程过程的复杂性，引入伪控制变量，将三维非线性制导模型转化为线性制导模型；分别针对无终端约束和有终端约束情况, 基于二次型最优方法得到三维非线性伪最优制导律。该制导律避免了通道解耦, 其制导参数又满足一定物理意义下的最优性。仿真结果验证了所设计制导律的有效性。 |
| 关键词: 高超声速飞行器 伪最优制导律 旋量方法 三维制导 通道耦合 |
| DOI：10.11887/j.cn.201506017 |
| 投稿日期：2015-01-19 |
| 基金项目:国家自然科学基金资助项目（61304229）；中国博士后科学基金资助项目（2013M542562） |
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| Three-dimensional nonlinear pseudo optimal guidance law for hypersonic vehicle based on twist technology |
| PENG Shuangchun, ZHU Jianwen, TANG Guojian, CHEN Kejun |
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(College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| A new three-dimensional (3D) nonlinear pseudo optimal guidance law based on twist technology was proposed to resolve the coupling problem between different channels for the guidance of hypersonic vehicle. The basic concepts of angle vector, line-of-sight (LOS) twist and its rate were introduced, and through equivalence certification, the guidance problem was converted into control problem of LOS twist and twist rate, with the conclusion that the LOS twist and its rate control equals to the LOS orientation and LOS angle rate control. A 3D nonlinear guidance model was constructed on the basis of LOS twist and the rate models through twist technology. In addition, the 3D nonlinear model was decoupled into the linear one by introducing pseudo control variable to reduce the complicate resolution of differential Riccati equation. The 3D nonlinear pseudo optimal guidance laws were derived using linear quadratic regulator (LQR) corresponding to no ending constraint and ending constraints respectively. With these novel guidance laws, the decoupling process can be well avoided and the optimal characteristics of guidance parameters were ensured as well. The validity of these guidance laws was also validated through simulation experiments. |
| Keywords: hypersonic vehicle pseudo optimal guidance law twist technology 3D guidance channels coupling |
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