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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
引用本文:彭双春,朱建文,汤国建,陈克俊.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.
作者姓名:彭双春  朱建文  汤国建  陈克俊
作者单位:国防科学技术大学 航天科学与工程学院,国防科学技术大学 航天科学与工程学院,1. 国防科学技术大学 航天科学与工程学院,1. 国防科学技术大学 航天科学与工程学院
基金项目:青年自然科学(61304229),中国博士后科学基金(2013M542562);
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
收稿时间:2015/1/19 0:00:00

Three-dimensional nonlinear pseudo optimal guidance for hypersonic vehicle based on twist technology
PENG Shuangchun,ZHU Jianwen,TANG Guojian and CHEN Kejun.Three-dimensional nonlinear pseudo optimal guidance for hypersonic vehicle based on twist technology[J].Journal of National University of Defense Technology,2015,37(6):84-90.
Authors:PENG Shuangchun  ZHU Jianwen  TANG Guojian and CHEN Kejun
Institution:College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China and College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
Abstract:A novel three-dimensional (3D) nonlinear pseudo optimal guidance law based on twist technology is proposed to resolve the coupling problem between different channels for the guidance of hypersonic vehicle. First, it introduces the basic concepts of angle vector, line-of-sight (LOS) twist and its rate, and converts guidance problem into LOS twists and the rate control problem with the conclusion that the LOS twists and the rate control equals to the LOS orientation and LOS angle rate control. Second, 3D nonlinear guidance model is constructed based on LOS twist and the rate through twist technology. In addition, 3D nonlinear model is decoupled into the linear one by introducing pseudo control variable to avoid the complicate resolution of differential Riccati equation. Moreover, 3D nonlinear pseudo optimal guidance laws are derived using linear quadratic regulator (LQR) corresponding to no ending constraints and ending constraints respectively. With this novel guidance law, the decoupling process can be well avoided and optimal characteristic of guidance parameters is ensured as well. The validity of this guidance is also validated through simulation experiments.
Keywords:hypersonic  vehicle  pseudo  optimal guidance  law  twist  technology  3D  guidance  channels  coupling
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