无筒空射运载火箭重力出舱机箭耦合动力学  

Aircraft⁃Rocket Coupling Dynamics for Gravity Air⁃Launch Without Launching Tube

作　　者：韩艳铧 尹文博 张勇 HAN Yanhua;YIN Wenbo;ZHANG Yong(College of Astronautics,Nanjing University of Aeronautics&Astronautics,Nanjing 211106,China;UAV Research Institute,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航天学院,南京211106 [2]南京航空航天大学无人机研究院,南京210016

出　　处：《南京航空航天大学学报》2022年第2期311-320,共10页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：研究了以运输机为平台的内装式空射运载火箭重力出舱载机⁃火箭两体动力学。根据火箭受力条件和相对运动自由度,将其出舱运动顺次分为5个阶段。给出了各阶段过渡的力学条件,基于牛顿⁃欧拉法分别建立了前4个阶段的机⁃箭两体动力学模型。定义了火箭出舱过程可能发生危险的多种异常情况,给出了发生异常的力学或几何条件。然后对火箭出舱全程作了数值仿真。若发射初始条件合理,仿真将顺次经历前4个或3个正常阶段,直至火箭离舱。如果异常情况的条件满足,火箭出舱将发生危险,仿真失去意义,故中止,需要调整发射初始条件后进一步仿真验证。本文给出的系统动力学模型和仿真数据可为工程部门设计空射型火箭的本体参数,以及设置空射初始条件提供参考。The two⁃body system dynamics of the aircraft⁃rocket during the built⁃in gravity air⁃launch process is studied.And the transport aircraft is taken as the platform.According to the mechanical conditions of the rocket and the degree of freedom of the relative movement,the rocket’s exit⁃movement is divided into five stages in sequence.The mechanical conditions for the transfer of the stages are provided.Based on the Newton⁃Euler method,the aircraft⁃rocket coupling dynamics models for the first four stages are established.It defines a variety of dangerous abnormal situations that may occur when the rocket exits the cabin,and the mechanical or geometric conditions under which the abnormal situation occurs are provided.Then a numerical simulation is carried out for the whole process.If the initial launch conditions are reasonable,the simulation will go through the first four or three normal stages in sequence until the rocket leaves the cabin.If the trigger conditions of the abnormal situation are met,the rocket will be dangerous when it exits the cabin,and the simulation is meaningless.So the simulation is aborted and the initial launch conditions need to be adjusted,and further simulation verification is required.The system dynamics model and simulation data obtained in this paper may provide references for the engineering design of parameters of the air⁃launched rocket,as well as the practical settings of the initial conditions of the air⁃launch.

关 键 词：内装式空射运载火箭 重力出舱 多体耦合动力学 牛顿⁃欧拉法 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]