组合动力原型机吸气爬升段纵向控制器设计  

Longitudinal Controller Design for Climb Phase of Combined-cycle Vehicle

作　　者：牧童 黄一敏[1] 王浩鑫 MU Tong;HUANG Yimin;WANG Haoxin(College of Automation Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China)

机构地区：[1]南京航空航天大学自动化学院,江苏南京211106

出　　处：《机械制造与自动化》2024年第2期252-257,共6页Machine Building & Automation

摘　　要：针对飞行器的飞行特点和自身的气动结构,建立复杂的非线性数学模型,进行静稳定性和模态特性的分析。为解决高超声速飞行器在吸气爬升段纵向的姿态角抖动问题,提出控制系统在吸气爬升段要使得对象飞行器保持低动态特性的理念。设计基于角速率阻尼内回路的纵向控制律,从时域、频域两个方面进行分析,并进行不确定性仿真,验证了其鲁棒性,最终得出阻尼内回路适用于对象无人机吸气爬升段纵向控制的结论。According to the flight characteristics of the aircraft and its own aerodynamic structure,a complex nonlinear mathematical model is established,and the static stability and modal characteristics are analyzed.To cope with the longitudinal attitude angle jitter of hypersonic vehicle in inspiratory climb phase,the idea that the control system should keep the target vehicle low dynamic characteristics in the inspiratory climb phase is proposed.The longitudinal control law based on angular rate damping inner loop is designed and analyzed from time domain and frequency domain,and its robustness is verified by uncertainty simulation.The final conclusion is that the damping inner loop is suitable for the longitudinal control of the object UAV in the suction climb phase.

关 键 词：吸气爬升段 高超声速飞行器 低动态 阻尼内回路 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]