摘要
借助于变质量陀螺方程,分析在主动段发动机尾喷口直径的变化对旋转固体火箭自旋速度的影响,得出对于双推力发动机在助推段向巡航段过渡时,由于发动机质量流量的改变,会使静稳定旋转固体火箭自旋速度以及弹体升力系数发生改变,导致弹道波动,进而得出为使旋转固体火箭自旋速度和弹道稳定,发动机尾喷口直径应与燃烧室内径相等的结论。利用Bendixson-Dulac定理,从微分方程理论给出了主动段飞行的旋转固体火箭,要么不发生锥形运动,要么仅发生一种稳定的锥形运动的理论证明,并得出气动阻尼不利于弹体姿态的结论。最后推导出旋转固体火箭变质量特性对弹体的章动阻尼作用的解析公式。
Based on the gyroscopic equation of mass changing,the effect of the diameter of tail nozzle on the rotational velocity was analyzed.The research shows that the change of spin rate of a statically stable spinning solid rocket and the change of its lift coefficient lead to the trajectory fluctuations as a result of large variations in mass flow of dual-thrust rocket engine in the transition period from the boost phase to the cruising phase,and then the diameter of tail nozzle would be equal to the diameter of rocket chamber for the sake of the stable spin rate.Through the Bendixson-Dulac theorem in differential equation theory,the conclusion that a spinning solid rocket in powered-flight phase is in a stable condition of coning motion or not in the condition was deduced in the theory.An analytic formula of the characteristics of mass changing on the nutation damping was achieved.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第6期711-715,共5页
Journal of Solid Rocket Technology
关键词
旋转固体火箭
发动机尾端
锥形运动
章动阻尼
spinning solid rocket
afterbody nozzle
coning motion
nutation damping
