高超声速飞行器俯冲段制导控制一体化设计方法
收稿日期: 2016-04-18
修回日期: 2016-07-26
网络出版日期: 2016-08-17
基金资助
国家自然科学基金（61104200）；国防科学技术大学科研计划项目重大应用基础研究（ZDYYJCYJ20140101）
Integrated guidance and control scheme for hypersonic vehicles in dive phase
Received date: 2016-04-18
Revised date: 2016-07-26
Online published: 2016-08-17
Supported by
National Natural Science Foundation of China (61104200); National University of Defense Technology Scientific Research Projects (ZDYYJCYJ20140101)
针对高超声速飞行器高速俯冲飞行段制导控制系统设计问题，建立了俯冲飞行段制导控制一体化低阶设计模型，提出了一种新颖的六自由度（6DoF）制导控制系统设计方法。基于目标-飞行器三维空间相对运动模型和坐标系转移关系建立了三维全耦合俯冲相对运动模型，推导得到了飞行器加速度在弹道坐标系三轴的分量与飞行器三通道角速率间的解析模型，进而结合飞行器绕质心动力学模型建立了以气动舵偏角为控制输入的俯冲飞行段制导控制一体化低阶设计模型。该制导控制一体化低阶设计模型降低了俯冲飞行段制导控制系统的模型阶数，减少了六自由度制导控制系统的设计参数，省略了传统设计方法中根据期望过载反求气动欧拉角的过程；同时利用解析模型替代了传统方法中姿态控制环路的跟踪控制过程，简化了制导控制系统的设计流程，为制导控制一体化设计提供了一种新的分析思路。数值仿真结果验证了本文提出的制导控制一体化设计方法的有效性和鲁棒性。
王建华 , 刘鲁华 , 王鹏 , 汤国建 . 高超声速飞行器俯冲段制导控制一体化设计方法[J]. 航空学报, 2017 , 38(3) : 320328 -320328 . DOI: 10.7527/S1000-6893.2016.0223
A reduced-order model for the design of guidance and control system of hypersonic vehicles in dive flight phase is developed, and a novel design approach of six-degree-of-freedom (6DoF) guidance and control system is proposed. The 3D coupling relative dynamics between the target and the hypersonic vehicle are derived based on accurate transitions of coordinate systems. An analytical model for components of acceleration of the hypersonic vehicle in the ballistic frame and the three-channel body rates is obtained. The 3D diving relative model, with the control surface fin deflections being the inputs, is denoted as the 6DoF integrated guidance and control design model. The system order and the tuning parameters of the 6DoF guidance and control system are reduced. The process of calculating the angle of attack and sideslip angle based on the desired overloads is omitted. In addition, the novel analytical model is applied to substitute the compensated dynamics for the traditional tracking processes of the rotational control loops. A novel design approach of 6DoF guidance and control system is proposed. The effectiveness and robustness of the proposed integrated guidance and control scheme are investigated and verified using an air-breathing generic hypersonic vehicle.
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