摘要
研究了喷气阻尼和推力偏斜对旋转导弹锥形运动的影响。建立了考虑变质量特性和喷流影响的旋转导弹姿态动力学模型。将旋转弹姿态动力学方程分为自旋运动和锥形运动两组,用复攻角简化锥形运动的微分方程,分析了自旋转速和锥形运动,推导出准攻角和准侧滑角的解析解,讨论了陀螺力矩、气动力矩、喷气阻尼力矩和推力偏斜对锥形运动的影响,获得了锥形运动稳定的条件。仿真结果验证了理论分析的正确性。研究表明:喷气阻尼效应增大了锥形运动的阻尼,利于锥形运动的稳定,但对锥形运动的频率无影响;推力偏斜使锥形运动中增加了与自旋同频的受迫振动,为限制受迫振动的幅度应使自旋转速避开慢圆运动和快圆运动的频率,并增大锥形运动的阻尼。研究对旋转弹的喷气阻尼力矩影响分析和总体设计有较大的参考价值。
The influence of jet damping and thrust misalignment on coning motion of rolling airframe missile was studied in this paper.The attitude dynamic equations of rolling airframe missiles considering the variable mass characteristic and jet were established.The dynamic equations were divided into two parts which were spinning motion and coning motion.The derivative equation of coning motion was simplified by complex angle of attack.The rotational speed of spinning and coning motion were analyzed.The analytic solution of quasi attack angle and quasi sideslip angle was deduced.The influence of the gyro moment,aerodynamic moment,jet damping moment and thrust misalignment on cone motion was analyzed respectively.The condition of stable coning motion was obtained.The simulation results verified the theoretical analysis results.It showes that the jet damping effect increases the damping of coning motion and stabilizes it but has no influence on coning motion.The thrust deflection causes the forced vibration at the same frequency with the spin.To avoid the amplitude of forced vibration becoming too large,the spinning speed shall keep away from the frequency of slow circular motion and fast circular motion.The research is valuable for analyzing the influence of jet damping motion and overall designing for rolling airframe missiles.
出处
《上海航天》
CSCD
2017年第S1期29-35,共7页
Aerospace Shanghai
关键词
旋转导弹
姿态动力学
锥形运动
喷气阻尼
推力偏斜
陀螺效应
马格努斯效应
复攻角
rolling airframe missile
attitude dynamics
coning motion
jet damping
thrust misalignment
gyroscopic effect
Magnus effect
complex angle of attack
