内装式空射运载火箭重力出舱机箭耦合动力学分析  

Aircraft-Rocket Coupling Dynamics for Internally Carried Gravity Air-Launch Method

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》2020年第6期963-971,共9页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：中央高校基本科研业务费青年科技创新基金(NT2020025)资助项目。

摘　　要：研究了以运输机为平台的内装式运载火箭空射过程载机和火箭的耦合动力学建模。建模针对两个阶段:第一阶段,火箭固定于载机机舱内,两者构成一个整体,按照普通刚体的力学方法处理;第二阶段,火箭解锁后,沿着舱内的发射筒向外滑行,载机和火箭形成两刚体相互作用的耦合系统,基于牛顿⁃欧拉法建立系统动力学模型。载机在空射火箭过程中,油门和升降舵满偏,在加速前飞的同时拉大姿态俯仰角,火箭在自身重力分量和惯性力的作用下,沿着机舱内的发射筒加速向外滑行,直至与载机分离。数值仿真分析了空射过程载机的重要力学参数的变化过程,验证了载机操控策略的可行性和安全性,可为未来中国空射运载火箭技术设计提供数据参考。The paper studies the modeling of the aircraft-rocket coupling dynamics during air launch of the transporter-mounted rocket. The modeling aims at two stages. In the first stage,the rocket is fixed in the cabin of the aircraft,so they constitute a whole,which is treated by single rigid body mechanics. In the second stage,after the rocket is unlocked,it moves along the launch tube in the cabin. While sliding outside,the aircraft and rocket constitute a coupled system of two interacting rigid bodies. A dynamics model is established using Newton-Euler method for the two rigid body systems. When the aircraft launches the rocket,the throttle and elevator are fully deflected,so its pitch angle is increased while accelerating forward.The rocket will slide outward along the launch tube in the cabin under the action of its own gravity component and inertial force till separating from the aircraft. Finally,through numerical simulation,the paper analyzes the change of some important mechanical variables of the aircraft during air-launch,verifying the feasibility and safety of the aircraft’s control strategy. The analysis results provide the data references for China’s air-launch rocket technology in the future.

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 飞行控制 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]