载机干扰流场下的内装式空射火箭分离过程仿真

为精确模拟载机干扰流场下的箭机分离过程，综合运用多体动力学和计算流体力学的基本理论，提出了一种基于动力学仿真和数值模拟的仿真方法. 该方法通过建立载机、火箭和稳定伞的全尺寸实体模型，并在ADAMS中施加约束和驱动后进行可视化仿真. 火箭在载机干扰流场中的非定常气动力利用计算流体力学和动网格技术进行仿真计算，稳定伞的气动力通过克希霍夫运动方程进行推导. 针对影响箭机分离的关键因素进行仿真对比分析，结果表明该方法较准确地模拟了载机干扰流场下的分离过程，从而为内装式空射火箭的整体方案设计提供了重要的依据.

Simulation of Internally Carried Air-Launched Launch Vehicle Separation from the Aircraft in the Aircraft Wake

In order to simulate the separation of launch vehicle from the aircraft in the aircraft wake exactly, A simulation method based on dynamics simulation and numerical simulation was proposed according to multi-body system dynamics and computational fluid dynamics. It is such a method, the full-scale model of aircraft, vehicle and parachute were built firstly and then imported into ADAMS software to add constraints solution and driving forces for visual dynamic simulation. The unsteady aerodynamic forces of vehicle under the aircraft wake were calculated by CFD and moving grid technique as well as the parachute's were derived from Kirchhoff motion equation. Through comparing and analyzing the simulation results under different launch conditions, it has been proved that this method can simulate the separation of launch vehicle from aircraft under the aircraft wake accurately. It provides foundation for the aggregate project of internally carried air-launch vehicle.