摘要
针对助推段固体捆绑火箭纵-横-扭强耦合的模态特征,在小变形假设下推导了某型固体捆绑火箭姿态动力学模型,系统分析了模态纵向分量对箭体姿态运动和弹性变形的影响。研究表明,模态纵向分量对箭体姿态运动影响较小,但会加大速率陀螺特别是滚动通道速率陀螺输出信号的高频抖振,这一现象是捆绑火箭因助推器的存在所固有的。模态纵向分量容易和部分"呼吸"模态和扭转模态发生耦合,但对横向弯曲模态基本无影响。
In view of distinct characteristics of coupling between longitudinal,lateral and torsional vibration during the phase of boost,the attitude dynamic model of a solid strap-on launch vehicle is derived under the hypothesis of small deformation,and effect of the longitudinal component of modes on attitude motion and flexible deformation of the strap-on launch vehicle is analyzed comprehensively.It is shown that the longitudinal component of modes have a marginal impact on the vehicle＇s attitude motion,but will enhance the high frequency oscillation of rate gyro＇s output signal especially in roll channel,this is a common phenomena of strap-on launch vehicle in the presence of boosters.The vehicle＇s longitudinal component of modes can be easily coupled with some ＂breath＂ modes and torsional modes,but have little or no impact on lateral bending modes.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2010年第5期1390-1397,共8页
Journal of Astronautics
关键词
捆绑火箭
纵向模态
纵向振动
扭转振动
姿态控制
Strap-on launch vehicle
Longitudinal mode
Longitudinal vibration
Torsional vibration
Attitude control
