机载导弹弹射式发射建模与仿真  

Modeling and Simulation of Eject Launcher for Airborne Missile

作　　者：许斌[1,2] 杨积东[2] 刘广[1,2] 张文[1] 

机构地区：[1]复旦大学力学与工程科学系,上海200433 [2]上海航天技术研究院第八设计部,上海200233

出　　处：《系统仿真学报》2011年第B07期51-54,共4页Journal of System Simulation

摘　　要：对机载导弹采用气压传动系统进行弹射式发射进行动力学建模与仿真。通过建立气压传动各元件的数学方程,在MATLAB/Simulink软件中建立气压传动系统仿真模型。同时在多体系统动力学仿真分析软件ADAMS中建立机载导弹动力学模型,并在Simulink中对弹射发射过程中作动筒与弹体分离过程进行控制。采用Simulink与ADAMS开展联合仿真,研究机载导弹弹射式发射动力学行为。The modeling and simulation of a launcher for airborne missile was performed,which used a pneumatic system to eject the missile from a combat aircraft.Based on the mathematical models of the pneumatic elements,a model for the pneumatic system of the eject launcher was built by the software MATLAB/Simulink.The software ADAMS which was a tool for simulation of multibody system dynamics was used to model the missile.To express the separating procedure between the airborne missile and the ejecting actuator,blocks of condition selection and judgment were introduced in Simulink.A physics-based co-simulation of Simulink and ADAMS was conducted to evaluate the separation dynamics while accounting for all the physics and body dynamics.

关 键 词：机载导弹 弹射式发射 气压传动 发射动力学 联合仿真 

分 类 号：O242[理学—计算数学]