某飞行器级间分离气动力/约束力/飞力综合建模与仿真  

Modeling and Simulation Coupled Aerodynamics,Constraint Force and Flight Dynamics for Stage Separation of Aircraft

作　　者：张科南[1] 李鹏飞[2] 陈万春[1] 吴颂平[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《系统仿真学报》2012年第10期2227-2231,2235,共6页Journal of System Simulation

摘　　要：飞行力学模块、约束力模块和气动力模块是构成飞行器级间分离建模仿真的三个主要部分。这三个部分相互耦合,给求解带来困难。为解决这类仿真问题,提出一种综合建模方法。该方法包括:飞行力学运动方程;CFE(Constraint Force Equation)方法求解约束力;CFD(Computational Fluid Dynamics)方法求解气动力和碰撞分析。其中,气动力模块计算得到气动载荷,输入到约束力的计算中;约束力模块得到的飞行器速度和角速度输入到飞行力学模块,经积分得到位置和姿态信息;而这些速度、位置和姿态信息又反馈到气动力模块中,构成一个回路。碰撞分析模块用来计算仿真终值条件。Modeling and simulation for stage separation of an aircraft mainly contains three parts： flight dynamics module, constraint force module and aerodynamics module. The three parts are coupled, and make the problem difficult to solve. To address this problem, a coupling modeling method was proposed. This method includes： flight dynamics equations of motion, using constraint force equation （CFE） method to solve constraint forces, using computational fluid dynamics （CFD） method to solve aerodynamics load, and impact analysis. The aerodynamics load calculated by aerodynamics module enters the constraint force module as input, the velocity and angular velocity of the vehicle can be obtained from the constraint force module, and input the flight dynamics module. Then the location and attitude can be determined. After that, the velocity, location and attitude information rettLrn to the aerodynamics module as feedback to complete a loop. The impact analysis module gives the order when to stop the simulation.

关 键 词：级间分离 飞行力学 约束力 建模仿真 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]