在轨发射有效载荷动力学仿真  

Dynamic Simulation of Payload On-orbit Launch

作　　者：张磊[1] 廖一寰[1] 唐国金[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《弹箭与制导学报》2008年第4期186-189,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金："863"课题资助

摘　　要：对有效载荷的在轨发射全过程进行了仿真。建立了发射装置的虚拟样机模型以及有效载荷与飞行器平台的动力学模型,将虚拟样机模型的计算结果输入动力学模型,分析了发射装置误差对有效载荷发射平稳性的影响,研究了发射后有效载荷的相对运动轨迹的安全性。仿真结果表明,发射装置弹簧推力偏斜与有效载荷质心偏移是有效载荷产生较大出筒角速度的主要原因;在不同飞行器平台发射方位角条件下,有效载荷的相对运动轨迹均符合安全要求。The whole process of payload on-orbit launch was simulated. Virtual prototyping model of separation mechanism was established. The analysis results of virtual prototyping model were imported into dynamic model which was built for payload and platform. The stability of on-orbit launch was analyzed considering the influence of separation mechanism error, and the safety of relative motion after launch was studied. The results show that the main factors causing separation angular velocity are spring error of, separation mechanism and centroid error of payload, and relative trajectory of payload is safe under different launching azimuth.

关 键 词：在轨发射 动力学 虚拟样机 仿真 

分 类 号：V412.42[航空宇航科学与技术—航空宇航推进理论与工程]