推力和阻力作用下柔性自旋飞行器稳定性分析

doi:10.3969/j.issn.1000-1093.2019.10.005

兵工学报 ›› 2019, Vol. 40 ›› Issue (10): 2005-2013.doi: 10.3969/j.issn.1000-1093.2019.10.005

推力和阻力作用下柔性自旋飞行器稳定性分析

潘成龙¹，荣吉利¹，徐天富²，项大林³

(1.北京理工大学宇航学院，北京 100081； 2.中国兵器工业集团航空弹药研究院，黑龙江哈尔滨 150030；3.北京宇航系统工程研究所，北京 100076)

收稿日期:2018-12-27 修回日期:2018-12-27 上线日期:2019-12-18
通讯作者: 荣吉利(1964—)，男，教授，博士生导师 E-mail:rongjili@bit.edu.cn
作者简介:潘成龙(1987—)，男，博士研究生。E-mail: jiaonan88@bit.edu.cn
基金资助:
国家自然科学基金项目(10972033)

Analysis about the Dynamic Stability of Flexible Spinning Vehicle under Thrust and Drag Load

PAN Chenglong¹, RONG Jili¹, XU Tianfu², XIANG Dalin³

(1.School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;2.NORINCO Group Aviation Ammunition Research Institute, Harbin 150030, Heilongjiang, China;3.Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China)

Received:2018-12-27 Revised:2018-12-27 Online:2019-12-18

摘要/Abstract

摘要： 针对柔性自旋飞行器动力学问题，开展了在推力和阻力作用下动力稳定性研究。柔性自旋飞行器简化为非均匀、自由-自由的Timoshenko回转梁模型，基于转子动力学理论和有限元方法，考虑陀螺效应，在瞬态坐标系下建立了推力和阻力作用柔性自旋飞行器的横向振动方程。在平均轴系和瞬态坐标系下分别从自旋转速、推力和阻力3个方面，分析了自旋飞行器动力稳定性和横向振动响应效应。研究结果表明：在瞬态坐标系下，阻力能够提高自旋飞行器稳定性，自旋转速不改变失稳区域;与之相反，在平均轴系下，阻力能够降低自旋飞行器稳定性，使临界推力和临界转速减小；自旋转速能够增大失稳区域，使静态失稳变为动态失稳；转动惯量和剪切效应能降低系统稳定性，相比于转动惯量，剪切效应影响更大，特别是对2阶频率影响。

关键词: 自旋飞行器, Timoshenko梁, 横向振动, 振动响应

Abstract: The dynamics stability under thrust and drag load is researched for dynamics stability of a flexible spinning vehicle. Spinning vehicle is simplified as a non-uniform free-free Timoshenko beam model considering gyroscopic effect. The transverse vibration equation of spinning vehicle in the transient coordinate system is derived using rotor dynamics theory and finite element method. Dynamic stability and transverse vibration response effect of flexible spinning vehicle in the mean axis system and the transient coordinate system are analyzed from spinning speed, thrust and drag. Results show that the drag can be used to improve the stability of spinning vehicle, and the spinning speed has no effect on the instability region in the transient coordinate system; in the mean axis system, the drag leads to the reduction in the stability of vehicle and the decrease in critical thrust and critical speed, and the spinning speed can result in the increase in instability region and make the static instability become the dynamic instability. The moment of inertia and shear effect reduce the system stability. The shear effect has a greater influence especially on the second-order frequency compared with the moment of inertia of transient coordinate system.Key

Key words: spinningvehicle, Timoshenkobeam, transversevibration, vibrationresponse

中图分类号:

潘成龙，荣吉利，徐天富，项大林. 推力和阻力作用下柔性自旋飞行器稳定性分析[J]. 兵工学报, 2019, 40(10): 2005-2013.

PAN Chenglong, RONG Jili, XU Tianfu, XIANG Dalin. Analysis about the Dynamic Stability of Flexible Spinning Vehicle under Thrust and Drag Load[J]. Acta Armamentarii, 2019, 40(10): 2005-2013.

参考文献

［1］ BEAL T R. Dynamic stability of flexible missile under constant and pulsating thrusts［J］. AIAA Journal, 1965, 3(3): 486-494.
［2］ WU J J. Missile stability using finite elements-an unconstrained variational approach［J］. AIAA Journal, 1976, 14(3): 313-319.
［3］宋健. 在推力和阻力作用下飞行器横向振动分析［J］. 中国工程科学, 2000, 2(10): 63-72.
SONG J. Lateral vibration analyses of flying vehicle under thrust and drag［J］. Engineering Science, 2000, 2(10):63-72. (in Chinese)
［4］ XU Y, XIE C C, YANG C. Effect of thrust on aeroelastic stability of a slender missile［C］∥Proceedings of 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Schaumburg, IL,US:AIAA, 2008.
［5］许赟, 谢长川, 杨超. 推力作用下细长弹箭横向振动及稳定性分析［J］. 工程力学, 2009, 26(12): 211-215.
XU Y, XIE C C, YANG C. Transverse vibration and dynamic stability analysis of slender projects under thrust［J］. Engineering Mechanics, 2009, 26(12):211-215. (in Chinese)
［6］张雷, 王永. 尾部有推力自由梁的振动分析［J］. 弹道学报, 2010, 22(1): 83-86.
ZHANG L, WANG Y. Vibration analysis of free-free beam with end rocket thrust［J］. Journal of Ballistics, 2010, 22(1):83-86. (in Chinese)
［7］ WU L, XIE C C, YANG C. Aeroelastic stability of a slender missile with constant thrust［J］. Procedia Engineering, 2012, 31(1): 128-135.
［8］全景阁, 叶正寅, 张伟伟. 轴向载荷对大长细比导弹稳定性的影响研究［J］. 兵工学报, 2015, 36(1): 94-102.
QUAN J G, YE Z Y, ZHANG W W. Analysis on stability of a slender missile under axial loads［J］. Acta Armamentarii, 2015, 36(1): 94-102. (in Chinese)
［9］陈红永, 陈海波. 轴压作用下自由-自由运动梁振动特性研究［J］. 工程力学, 2015, 32(3):233-240.
CHEN H Y, CHEN H B. Vibration characteristics of free-free moving beam under axial compressive loads［J］. Engineering Mechanics, 2015, 32(3):233-240. (in Chinese)

［10］陈强, 杨国来, 王晓锋. 轴向变速运动弯曲梁的固有频率分析［J］. 工程力学, 2015, 32(2):37-44.
CHEN Q, YANG G L, WANG X F. Analysis of the natural frequency of an axially moving beam with non-uniform velocity［J］. Engineering Mechanics, 2015, 32(2): 37-44. (in Chinese)
［11］王乐, 余慕春. 轴力对自由边界Timoshenko梁横向动特性影响研究［J］. 兵器装备工程学报, 2018,39(3): 36-39.
WANG L, YU M C. Effect of axial force on the lateral vibration characteristics of Timoshenko beam under free boundary condition［J］. Journal of Ordnance Equipment Engineering,2018,39(3):36-39. (in Chinese)
［12］ ZHU H L, YU L, LIANG S H, et al. Dynamic simulation of a flexible spinning vehicle with the periodic varing thrust［J］. Journal of Shanghai University (English Edition), 2008, 12(2): 115-119.
［13］荣吉利, 徐天富, 李健. 基于Timoshenko梁模型的旋转弹箭横向振动模态分析［J］. 北京理工大学学报, 2012, 32(6): 551-555.
RONG J L, XU T F, LI J. Modal analysis of transverse vibration of a spinning rocket based on Timoshenko beam［J］. Transactions of Beijing Institute of Technology, 2012, 32(6):551-555. (in Chinese)
［14］荣吉利, 徐天富, 王玺, 等. 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 J L, XU T F, WANG X, et al. Analysis of transverse vibration response and instability of flexible spinning flight vehicles under follower thrust［J］. Acta Armamentarii, 2015, 36(3): 516-522. (in Chinese)
［15］荣吉利, 徐天富, 王玺, 等. 随动推力作用下柔性旋转飞行器稳定性分析［J］. 宇航学报, 2015, 36(1): 18-24.
RONG J L, XU T F, WANG X, et al. Dynamic stability analysis of slender spinning flight vehicles under follower thrust［J］. Journal of Astronautics, 2015, 36(1): 18-24. (in Chinese)
［16］ XU T F, RONG J L, XIANG D L, et al. Dynamic modeling and stability analysis of a flexible spinning missile under thrust［J］. International Journal of Mechanical Sciences, 2016,119:144-154.
［17］郭东, 徐敏, 陈士橹. 弹性飞行器飞行动力学建模研究［J］. 空气动力学学报, 2013, 31(4):413-419.
GUO D, XU M, CHEN S L. Research on flight dynamic modeling of highly flexible aircrafts［J］. Acta Aerodynamica Sinica, 2013, 31(4): 413-419. (in Chinese)
［18］陈尔康, 廖欣, 高长生, 等. 考虑刚体运动与弹体变形耦合效应的旋转导弹动力学建模［J］. 兵工学报, 2018, 39(11): 2159-2171.
CHEN E K, LIAO X, GAO C S, et al. Analysis of transverse vibration response and instability of flexible spinning flight vehicles under follower thrust［J］. Acta Armamentarii, 2018, 39(11): 2159-2171. (in Chinese)
［19］徐天富. 柔性自旋飞行器动力学分析与稳定性研究［D］. 北京: 北京理工大学, 2015.
XU T F. Dynamics and stability analysis of flexible spinning flight vehicles［D］. Beijing: Beijing Institute of Technology, 2015. (in Chinese)

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[7]	刘辉, 蔡仲昌, 曹华夏, 项昌乐. 车辆动力传动系统扭转强迫振动响应灵敏度研究[J]. 兵工学报, 2011, 32(8): 939-944.
[8]	裴譞，张宇文，袁绪龙，张纪华. 潜载导弹垂直发射横向振动特性仿真分析[J]. 兵工学报, 2009, 30(8): 1056-1060.
[9]	1:荣吉利;2:李瑞英. 大长径比自旋弹箭横向自振特性的有限元计算方法与结果分析[J]. 兵工学报, 2002, 23(1): 79-82.
[10]	1:臧涛成;2:胡焕性. 大长径比脱壳穿甲弹飞行时的横向振动[J]. 兵工学报, 1999, 20(3): 208-211.
[11]	何永清、张家泰、杨波、陈其廉. 炮身的双时变横向振动分析[J]. 兵工学报, 1995, 16(2): 13-18.
[12]	樊黎霞. 武器构件回转弯曲撞击瞬态响应分析[J]. 兵工学报, 1994, 15(3): 1-7.

推力和阻力作用下柔性自旋飞行器稳定性分析

Analysis about the Dynamic Stability of Flexible Spinning Vehicle under Thrust and Drag Load

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