适于高超声速飞行器的三维非线性滑模制导律

综合考虑高超声速飞行器末制导过程中的运动耦合和参数扰动问题,设计了一种适于高超声速飞行器的三维非线性伪最优滑模制导律。首先,针对运动耦合问题,定义视线旋量和视线旋量速度,构建了基于视线旋量和视线旋量速度的高超声速飞行器三维非线性制导参考模型;然后,针对参数扰动问题,基于变结构控制理论,推导出一种适于多约束制导要求的三维非线性滑模制导律,并通过理论推导证明了该制导律的稳定性;最后,引入伪控制变量,完成了制导参数的优化,从而完成三维非线性伪最优滑模制导律的设计。该制导律能够从理论上克服运动耦合和参数扰动问题,其制导参数又满足一定物理意义下的最优性。仿真结果验证了制导律的有效性。

Three dimensional nonlinear sliding mode guidance law for hypersonic vehicle

A novel three dimensional (3D) nonlinear pseudo optimal sliding mode guidance law for hypersonic vehicle is proposed to resolve the motion coupling and parameter perturbation problems. Firstly, aiming at the motion coupling problem, a 3D nonlinear reference guidance model of hypersonic vehicle is constructed based on line of sight (LOS) twist and its rate after their concepts is defined. Secondly, in order to depress the influence of parameter perturbation, a 3D nonlinear sliding mode guidance law adapted to multi constraint guidance is deduced based on variable structure control theory. Moreover, the stability of this guidance law is proved through theory deduction. Finally, a novel 3D nonlinear pseudo optimal sliding mode guidance law is designed, after its parameters are optimized by introducing pseudo control variable. With the novel guidance law, the motion coupling and parameter perturbation problems can be well avoided and optimal characteristic of guidance parameters is ensured as well. The validity of the guidance law is also validated through simulation experiments.