摘要
研究小卫星发射过程中最末级使用旋转固体火箭发动机时飞行器系统参数变化对其章动效果的影响。考虑了推进剂质量变化引起系统的能量耗散,在欧拉动力学方程的基础上,引入了由于飞行器系统质量变化引起的角动量变化率,得到了飞行器系统的角速度方程与章动方程。把实际飞行器工作过程的参数代入所推导的方程,得到了飞行器的章动放大过程,同时得到了飞行器系统参数变化对章动放大过程的影响规律。计算结果可为飞行器系统的设计提供指导。
The effect of spacecraft system parameter variation on its nutation process was researched in the last stage of launching small satellite using spinning solid rocket motor.The energy dissipation of spacecraft system due to solid propellant mass variation was taken into account.The angular momentum change rate due to spacecraft system mass variation was introduced in Euler dynamical equations.The angular velocity equations and nutation equation were obtained.The actual parameters in spacecraft working process were substituted into the deduced equations,and the nutation amplification of spacecraft was obtained.The influential law of the parameter of spacecraft system on nutation amplification was deduced at the same time.The calculation can provide guidance for the spacecraft system design.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第6期716-721,725,共7页
Journal of Solid Rocket Technology
基金
国家自然科学基金(10972063)
中央高校基本科研基金(HEUCF100203)
关键词
旋转飞行器
固体火箭发动机
能量耗散
章动放大
spinning spacecraft
solid rocket motor
energy dissipation
nutation amplification
