随动推力作用下柔性自旋飞行器横向振动响应及失稳分析  

Analysis of Transverse Vibration Response and Instability of Flexible Spinning Flight Vehicles under Follower Thrust

作　　者：荣吉利[1] 徐天富[1] 王玺[2] 殷新喆 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]北京航天发射技术研究所,北京100076

出　　处：《兵工学报》2015年第3期516-522,共7页Acta Armamentarii

基　　金：国家自然科学基金项目(10972033)

摘　　要：针对柔性自旋飞行器动力学问题,考虑结构自身旋转作用,建立计入陀螺力矩及随动推力影响的运动方程,研究系统的动力学响应问题。将柔性自旋飞行器简化为非均匀转子结构,采用剪切变形对轴向位移有影响的Timoshenko梁模型,计入了陀螺力矩及随动推力的影响,基于有限元方法建立了运动方程,分析了质量偏心力作用下转速和推力对系统动力响应的影响以及结构失稳的情况。分析结果表明:随动推力的增加会减小系统的刚度和临界转速;激振频率等于系统临界转速频率时系统发生共振;推力达到或超过临界推力将导致系统失稳;转速的增加会降低系统的临界推力值;结构的非均匀性对系统的临界转速和临界推力造成很大影响。The self-rotation of flexible spinning flight vehicles in the dynamic analysis is emphatically considered. The equations of motion are formulated and the dynamic stability is analyzed by taking into account gyroscopic moment and follower thrust. The flexible spinning flight vehicle is simplified as a non- uniform rotor structure. Timoshenko beam model, which assumes that the shear deformation influences axial displacement, is adopted with consideration of the effects of gyroscopic moment and follower thrust. The equations of motion are established based on the finite element method to analyze the effects of rota- ting speed and follower thrust on the dynamic response and structural instability under the action of mass eccentric force. The results show that system stiffness and critical spin speed decrease with the increase in follower thrust; the resonance of system occurs when the excitation frequency equals to the critical spin speed frequency; the follower thrust equaling to or being greater than the critical thrust results in system instability; the increase in spin speed will reduce the critical thrust of system; and the structural hetero-geneity greatly affects the critical spin speed and critical thrust.

关 键 词：振动与波 自旋飞行器 随动推力 TIMOSHENKO梁 

分 类 号：O326[理学—一般力学与力学基础] V214.33[理学—力学]