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

doi:10.3969/j.issn.1000-1093.2015.03.020

兵工学报 ›› 2015, Vol. 36 ›› Issue (3): 516-522.doi: 10.3969/j.issn.1000-1093.2015.03.020

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

荣吉利¹，徐天富¹，王玺²，殷新喆¹

(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)

收稿日期:2014-02-20 修回日期:2014-02-20 上线日期:2015-05-01
通讯作者: 荣吉利 E-mail:rongjili@bit.edu.cn
作者简介:荣吉利（1964—），男，教授，博士生导师
基金资助:
国家自然科学基金项目（10972033）

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

RONG Ji-li¹, XU Tian-fu¹, WANG Xi², YIN Xin-zhe¹

(1.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2.Beijing Aerospace Launch Technology Institute, Beijing 100076, China)

Received:2014-02-20 Revised:2014-02-20 Online:2015-05-01
Contact: RONG Ji-li E-mail:rongjili@bit.edu.cn

摘要/Abstract

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。

关键词: 振动与波, 自旋飞行器, 随动推力, Timoshenko梁

Abstract: 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 rotating 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 heterogeneity greatly affects the critical spin speed and critical thrust.

Key words: vibration and wave, spinning flight vehicle, follower thrust, Timoshenko beam

荣吉利，徐天富，王玺，殷新喆. 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[J]. 兵工学报, 2015, 36(3): 516-522.

RONG Ji-li, XU Tian-fu, WANG Xi, YIN Xin-zhe. Analysis of Transverse Vibration Response and Instability of Flexible Spinning Flight Vehicles under Follower Thrust[J]. Acta Armamentarii, 2015, 36(3): 516-522.

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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

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