面向可打击区域的高超声速飞行器制导控制一体化方法研究

Research on Integrated Guidance and Control Method for Hypersonic Vehicles for Striking Area

针对高超声速飞行器制导和控制系统分离设计方法的不足,提出通过制导控制一体化设计提升其可打击区域的方法。首先,在建立高超声速制导控制一体化模型的基础上,揭示了其通过控制弹体坐标系与地面坐标系的牵连加速度来跟踪制导指令的工作原理。其次,通过典型弹道的数值仿真,对比分析了制导控制一体化设计相较于分离设计的控制信号差异。最后,通过确定制导控制分离设计及一体化设计的高超声速飞行器可打击区域的方式,从大样本仿真角度体现制导控制一体化的优势。结果表明,制导控制一体化设计可以放宽对可用过载的需求且有助于提升高超声飞行器的可打击区域。

Aiming at the shortcomings of the separation design of guidance and control systems,a method of improving the striking area through integrated design of guidance and control is proposed.Firstly,based on the establishment of an integrated guidance and control model for hypersonic vehicle,the working principle which tracks acceleration commands by controlling the implicated acceleration between the body coordinate system and the ground coordinate system is revealed.Secondly,through numerical simulation of typical trajectories,the ability of integrated guidance and control design to reduce required overload compared to separate design is compared and analyzed.Finally,by determining the separation and integration design of guidance and control in the striking area of hypersonic vehicle,the advantages of integrated guidance and control are reflected from the perspective of large-scale simulation.The results indicate that the integrated guidance and control can relax the demand for available overload and improve the striking area of hypersonic vehicle.