| 引用本文: | 王建华,刘鲁华,王鹏,等.高超声速飞行器纵向平面滑翔飞行制导控制方法.[J].国防科技大学学报,2017,39(1):58-66.[点击复制] |
| WANG Jianhua,LIU Luhua,WANG Peng,et al.Longitudinal integrated guidance and control scheme for hypersonic vehicle in glide phase[J].Journal of National University of Defense Technology,2017,39(1):58-66[点击复制] |
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| 高超声速飞行器纵向平面滑翔飞行制导控制方法 |
| 王建华, 刘鲁华, 王鹏, 汤国建 |
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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纵向平面内准平衡滑翔制导控制问题，提出一种基于动态面控制和滑模控制的制导与姿态控制系统设计方法。建立高超声速飞行器纵向平面质心和绕质心运动模型，以航程预测-校正控制为出发点得到期望速度倾角并结合飞行器纵向模型中速度倾角、攻角和俯仰角速率间的关系，利用动态面控制方法、终端滑模控制和二阶滑模控制方法完成高超声速飞行器纵向平面内制导与姿控系统设计。基于偏导系数矩阵形式的通用高超声速飞行器气动模型，完成期望攻角和左右升降舵偏角指令的解析计算。通过高超声速飞行器对该制导控制系统设计方法的有效性和鲁棒性进行仿真验证。根据数值仿真结果，系统阐述了高超声速飞行器进入准平衡滑翔飞行前后制导控制系统工作的特点，进而总结了从初始下降段到准平衡滑翔段交班飞行阶段制导控制系统设计需要注意的问题。 |
| 关键词: 高超声速飞行器 制导控制系统 动态面控制 准平衡滑翔 纵向平面 |
| DOI：10.11887/j.cn.201701010 |
| 投稿日期：2015-12-11 |
| 基金项目:国家自然科学基金资助项目（61104200） |
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| Longitudinal integrated guidance and control scheme for hypersonic vehicle in glide phase |
| WANG Jianhua, LIU Luhua, WANG Peng, TANG Guojian |
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(College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| A longitudinal integrated guidance and control scheme for the hypersonic vehicle in glide phase was designed based on the dynamic surface control method and the sliding mode control theory. The translational rotational dynamic and kinematical equations in the longitudinal plane were denoted; the desired velocity slope angle was derived based on the predictor corrector of the longitudinal range; the relations of the velocity slope angle, angle of attack, and the pitch rate were established. The dynamic surface control, the terminal sliding model and the second-order sliding mode control methods were adopted to implement the longitudinal integrated guidance and control scheme; the commanded angle of attack and elevon fins were analytically solved by using the GHV’s aerodynamic model having partial derivative matrix forms. The effectiveness and robustness of the newly proposed longitudinal integrated guidance and control scheme was validated. Moreover, the characteristics of flight phases before and after the quasi equilibrium glide phase were discussed and the problems with respect to the guidance and control system design were analyzed. |
| Keywords: hypersonic vehicle guidance and control system dynamic surface control quasi equilibrium glide longitudinal plane |
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