航天设备力限振动试验复杂二自由度方法研究
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摘要
在航天产品振动试验领域,力限方法采用力和加速度条件双控策略可缓解传统振动试验中的过试验,但力条件的确定困难,尤其对于设备级产品的试验存在源的界定问题。针对固定边界的设备级产品,介绍了复杂二自由度法用于获取固定边界下力条件的修正方法,对于其中关键的源和负载的质量参数给出获取方法,并应用于试验实例,为工程中力限条件的合理制定提供了参考。
Force limit method can reduce the over-testing problem associated with traditional vibration testing by dual control of the force and acceleration.However,the force specification is difficult to estimate,especially for the equipment vibration test in which the source definition problem exists.This paper demonstrates a modified complex two-degree-of-freedom method adapted to fixed boundary conditions of the mounting structure.Some methods are also given to acquire the mass parameters of source and load,which are critical to the reasonably conservative force specification.Practical examples have been performed with the modified method to verify its validity,which provides reference for force specification determination.
Force limit method can reduce the over-testing problem associated with traditional vibration testing by dual control of the force and acceleration.However,the force specification is difficult to estimate,especially for the equipment vibration test in which the source definition problem exists.This paper demonstrates a modified complex two-degree-of-freedom method adapted to fixed boundary conditions of the mounting structure.Some methods are also given to acquire the mass parameters of source and load,which are critical to the reasonably conservative force specification.Practical examples have been performed with the modified method to verify its validity,which provides reference for force specification determination.
引文
[1]马兴瑞,韩增尧,邹元杰,等.航天器力学环境分析与条件设计研究进展[J].宇航学报,2012,33(1):1-12.
[2]黄波,张正平,李海波,等.力限振动试验技术进展综述[J].强度与环境,2012,39(5):18-27.
[3]Force Limited Vibration Testing[M].NASA Technical Handbook 7004C,2012.
[4]周莹,宋汉文.力控振动试验与过试验现象分析[J].振动与冲击,2008,27(4):82-84.
[5]Chad E R,Ralph D B.Validation of Force Limited Vibration Testing at NASA Langley Research Center[R].Langley Research Center,Hampton,Virginia,2003.
[6]Cote A,Sedaghati R,Soucy Y.Force-limited Vibration Complex Two-degree-of-freedom System Method[J].AIAA Journal2004,42(6):1208-1218.
[7]Wada B K,Bamford R,Garba J A.Equivalent Spring-Mass System:A Physical Interpretation[J].Shock and Vibration Bulletin,1972(42):215-225.
[8]Sedaghati R,Soucy Y,Etienne N.Experiential Estimation of Effective Mass for Structural Dynamics and Vibration Application[C]∥Proceeding of the 21th International Modal Analysis Conference.Kissimmee(FL),USA:2003
[9]Piersol A G,White P H,Wilby E G,et al.Vibration Test Procedures for Orbiter Sidewall Mounted Payloads-Phase IIFinal Report[R].Astron Research and Engineering,HQ Space Division,Los Angeles,CA,1989.
[2]黄波,张正平,李海波,等.力限振动试验技术进展综述[J].强度与环境,2012,39(5):18-27.
[3]Force Limited Vibration Testing[M].NASA Technical Handbook 7004C,2012.
[4]周莹,宋汉文.力控振动试验与过试验现象分析[J].振动与冲击,2008,27(4):82-84.
[5]Chad E R,Ralph D B.Validation of Force Limited Vibration Testing at NASA Langley Research Center[R].Langley Research Center,Hampton,Virginia,2003.
[6]Cote A,Sedaghati R,Soucy Y.Force-limited Vibration Complex Two-degree-of-freedom System Method[J].AIAA Journal2004,42(6):1208-1218.
[7]Wada B K,Bamford R,Garba J A.Equivalent Spring-Mass System:A Physical Interpretation[J].Shock and Vibration Bulletin,1972(42):215-225.
[8]Sedaghati R,Soucy Y,Etienne N.Experiential Estimation of Effective Mass for Structural Dynamics and Vibration Application[C]∥Proceeding of the 21th International Modal Analysis Conference.Kissimmee(FL),USA:2003
[9]Piersol A G,White P H,Wilby E G,et al.Vibration Test Procedures for Orbiter Sidewall Mounted Payloads-Phase IIFinal Report[R].Astron Research and Engineering,HQ Space Division,Los Angeles,CA,1989.