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.
出处
《弹箭与制导学报》
CSCD
北大核心
2008年第4期186-189,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
"863"课题资助
关键词
在轨发射
动力学
虚拟样机
仿真
on-orbit launch
dynamics
virtual prototyping
simulation
