基于重力转弯解析解的动力减速制导方法  

Powered deceleration guidance method based on gravity-turn analytical solutions

作　　者：张智[1] 袁晗 张晚晴 ZHANG Zhi;YUAN Han;ZHANG Wanqing(China Academy of Launch Vehicle Technology,Beijing 100076,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京宇航系统工程研究所,北京100076

出　　处：《航空学报》2023年第23期110-127,共18页Acta Aeronautica et Astronautica Sinica

摘　　要：火箭垂直回收的一项关键技术是动力减速段的制导技术。本文针对垂直回收过程,分析了返回过程中动力减速段对制导系统的需求和约束条件,研究了一种基于变轴向视加速度重力转弯解析解的动力减速段制导方法。针对动力减速段中存在推进剂消耗的情况,将火箭在飞行过程中的质量在初始质量附近进行一阶泰勒展开,进而得到了轴向视加速度变化的一阶重力转弯解析解,并通过仿真验证了其优越性。利用该解析解,设计了基于待飞航程的自适应启动方案,能够更好的修正落点航程偏差。在得到解析预测的基础上,通过落点预测与虚拟目标点之差反馈修正攻角和侧滑角,从而同时满足航程、关机点比机械能和关机点姿态约束。仿真结果表明,自适应启动方法具有降低动力减速飞行过程的攻角需求、提高位置修正能力的优势;所设计的制导方法能够在满足终端位置、比机械能约束的同时满足了终端攻角约束,且不同轨迹中气动减速段的热流变化较小。One of the key technologies of rocket vertical recovery is the guidance technology in the powered deceleration phase.The requirements and constraints in the powered deceleration phase for the guidance system in the return process are analyzed,and a powered deceleration guidance method based on the gravity-turn analytical solution with variable axial apparent acceleration is studied.Considering the existence of propellent consumption in the powered deceleration phase,the mass lost in the flight process of the rocket is expanded by the first-order Taylor expansion at the initial mass,and then the first-order gravity-turn analytical solution of the variable axial apparent acceleration is obtained,and the superiority of the analytical solution is verified by simulation.Using this analytical solution,an adaptive handover method based on the range to be flown is designed,which can better correct the range deviation of the landing point.Based on the analytical prediction,the angle of attack and sideslip angle are corrected by the deviation between the landing point prediction and the virtual target point feedback,so as to meet the constraints of range,shutdown point speed and shutdown point attitude at the same time.The simulation results show that the adaptive handover method has the advantages of reducing the angle of attack and improving the position correction capability during dynamic deceleration flight.The guidance method proposed can meet the terminal position and specific mechanical energy constraints as well as the constraint of the terminal angle of attack,causing only slight change in the heat flow in the aerodynamic deceleration section of different trajectories.

关 键 词：可重复使用运载火箭 垂直起飞垂直着陆 动力减速段制导 重力转弯解析解 自适应启动 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]