综合载荷环境下高超声速飞行器结构多场联合强度试验技术
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摘要
针对当前高超声速飞行器结构综合环境强度验证技术的迫切需求,开展考虑气动力、高温、噪声及机械振动等载荷的多场联合强度试验设计,提出了多系统集成方法,给出了多载荷联合加载解耦方法与控制策略,基于行波管建立了多场联合试验平台,对平台关键环境影响因素进行了分析,给出了具体的解决途径,最后基于该试验平台完成了某舵面构件的气动力/高温/噪声/振动多场联合试验,得到了联合载荷作用下结构应变、加速度及位移等响应的时域与频域变化特征,试验表明,多场联合环境下结构的响应水平较高,结构更容易发生破坏,通过该试验验证了多场联合试验技术的可行性及有效性,可为复杂载荷环境下高超声速飞行器结构的地面强度试验验证提供有力的技术支撑。
Aimed at the urgent requirements of the combined load test for current hypersonic vehicle structures,a multi-load combined test design considering aerodynamic force,high temperature,acoustic,and mechanical vibration is carried out.First,a multi-system integration method is proposed,and the decoupling method and the control strategy are proposed for multi-load combined loadings.Then,based on the progressive wave tube,a multi-load combined platform is built.Moreover,the key factors that affect the performance of the platform are analyzed and the corresponding solutions are provided.Finally,a multi-field test combined with the aerodynamic force/high temperature/acoustic/mechanical vibration of a rudder surface component is completed based on this test platform,obtaining the time-domain and frequency-domain characteristics of the responses such as strain,acceleration and displacement.The test results show that the response level of the structure in a combined load environment is relatively high and the structure is more prone to damage.The feasibility and effectiveness of the multi-load combined test technique are verified through this test,indicating apowerful technical support for the verification of the ground strength of the hypersonic vehicle structure in a complex load environment.
Aimed at the urgent requirements of the combined load test for current hypersonic vehicle structures,a multi-load combined test design considering aerodynamic force,high temperature,acoustic,and mechanical vibration is carried out.First,a multi-system integration method is proposed,and the decoupling method and the control strategy are proposed for multi-load combined loadings.Then,based on the progressive wave tube,a multi-load combined platform is built.Moreover,the key factors that affect the performance of the platform are analyzed and the corresponding solutions are provided.Finally,a multi-field test combined with the aerodynamic force/high temperature/acoustic/mechanical vibration of a rudder surface component is completed based on this test platform,obtaining the time-domain and frequency-domain characteristics of the responses such as strain,acceleration and displacement.The test results show that the response level of the structure in a combined load environment is relatively high and the structure is more prone to damage.The feasibility and effectiveness of the multi-load combined test technique are verified through this test,indicating apowerful technical support for the verification of the ground strength of the hypersonic vehicle structure in a complex load environment.
引文
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[2]杨炳渊,史晓鸣,梁强.高超声速有翼导弹多场耦合动力学的研究和进展[J].强度与环境,2008,35(6):55-62.YANG B Y,SHI X M,LIANG Q.Investigation and development of the multi-physics coupling dynamics on the hypersonic winged missiles[J].Structure&Environment Engineering,2008,35(6):55-62(in Chinese).
[3]许斌,梅睿,马建敏,等.高速柔性飞行器耦合动力学研究进展[J].飞行力学,2016,34(3):1-6.XU B,MEI R,MA J M,et al.Development in coupling dynamics of flexible high-speed aircraft[J].Flight Dynamics,2016,34(3):1-6(in Chinese).
[4]谭光辉,李秋彦,邓俊.热环境下结构固有振动特性试验及分析[J].航空学报,2016,37(1):32-37.TAN G H,LI Q Y,DENG J.Test and analysis of natural modal characteristics of a wing model with thermal effect[J].Acta Aeronautica et Astronautica Sinica,2016,37(1):32-37(in Chinese).
[5]沙云东,魏静,高志军,等.热声载荷作用下薄壁结构的非线性响应特性[J].航空学报,2013,34(6):1336-1346.SHA Y D,WEI J,GAO Z J,et al.Nonlinear response characteristics of thin-walled structure under thermoacoustic loadings[J].Acta Aeronautica et AstronauticaSinica,2013,34(6):1336-1346(in Chinese).
[6] XU G H,HE W,SHEN R J.Design of temperature testing system in multi-parameter combined environmental test[J].Applied Mechanics and Materials,2012,157(158):127-131.
[7]孟光,周徐斌,苗军.航天重大工程中的力学问题[J].力学进展,2016,46(6):267-322.MENG G,ZHOU X B,MIAO J.Mechanical problems in momentous projects of aerospace engineering[J].Advances in Mechanics,2016,46(6):267-322(in Chinese).
[8]吴建国,李海波,张琪.综合离心环境试验技术研究进展[J].强度与环境,2014,41(1):1-9.WU J G,LI H B,ZHANG Q.Advances in synthesis centrifugal environment test[J].Structure&Environment Engineering,2014,41(1):1-9(in Chinese).
[9]军用飞机结构强度规范:GJB 67A.8—2008[S].北京:中国标准出版社,2008.Military airplane structural strength specification:GJB67A.8—2008[S].Beijing:Standards Press of China,2008.(in Chinese).
[10] BLEVINS R D,BOFILIOS D,HOLEHOUSE I,et al.Thermo-vibro-acoustic loads and fatigue of hypersonic flight vehicle structure:AFRL-RB-WP-TR-2009-3139[R].OH:Wright Patterson AFB,2009.
[11] BRIAN Z.Predictive capability for hypersonic structural response and life-prediction:Phase 2—Details design of hypersonic cruise vehicle hot-structure:AFRL-RQ-WPTR-2012-0280[R].Seal Beach,CA:Boeing Company,2012.
[12] BLADES E.L,MISKOVISH R S,NUCCI M.Towards a coupled mutliphysics analysis capability for hypersonic vehicle structures:AIAA-2011-1962[R].Reston,VA:AIAA,2011.
[13] ANDREW K M,MARC P M.Thermal reduced order model adaptation to aero-thermo-structural interactions:AIAA-2014-049[R].Reston,VA:AIAA,2014.
[14] ANDREAS.Materials with complex behavior:Modeling,simulation,testing,and application[M].Berlin Heidelberg:Springer-Verlag,2010:193-211.
[15] BROWN A M.Temperature dependent modal test/analysis correlation of X34 Fastrac composite rocket nozzle:AIAA-2000-1741[R].Reston,VA:AIAA,2000.
[16] GLASS D E.Airframe technology develops for next generation launch vehicles:AIAA-2003-6916[R].Reston,VA:AIAA,2003.
[17] STEPHENS C A,HUDSON L D,PIAZZA A.Overview of an advanced hypersonic structural concept test program:NASA-2008-561[R].Washington,D.C.:NASA,2008.
[18] HUDSON L.Thermal-mechanical testing of hypersonic vehicle structures:NASA-2008-13159[R].Washington,D.C.:NASA,2008.
[19]陈晓冬,杜向辉,徐宁.空空导弹发射装置组合振动试验方法研究[J].装备环境工程,2014,11(6):153-158.CHEN X D,DU X H,XU N.Research on combined vibration test method for the launcher equipment of airborne missile[J].Equipment Environment Engineering,2014,11(6):153-158(in Chinese).
[20]吴振强,张伟,孔凡金.热噪声复合环境试验装置研制及其能力验证[J].导弹与航天运载技术,2014,335(5):60-67.WU Z Q,ZHANG W,KONG F J.Research and capability verification of the test apparatus simulating combined thermal and acoustic environment[J].Missiles and Space Vehicles,2014,335(5):60-67(in Chinese).
[21]刘磊,代光月,曾磊,等.气动力/热与结构多场耦合试验模型方案初步设计[J].航空学报,2017,38(11):221165.LIU L,DAI G Y,ZENG L,et al.Preliminary test model design of fluid-thermal-structural interaction problems[J].Acta Aeronautica et Astronautica Sinica,2017,38(11):221165(in Chinese).
[22]吴大方,王岳武,商兰,等.1 200℃高温环境下板结构热模态试验研究与数值模拟[J].航空学报,2016,37(6):1861-1875.WU D F,WANG Y W,SHANG L,et al.Test research and numerical simulation on thermal modal of plate structure in 1 200℃high temperature environments[J].Acta Aeronautica et Astronautica Sinica,2016,37(6):1861-1875(in Chinese).
[23] GENG Q,LI H,LI Y M.Dynamic and acoustic response of a clamped rectangular platein thermal environments:Experiment and numerical simulation[J].Acoustical Society of America,2014,135(5):2674-2682.
[24] MARLANA N B,ANURAG S,ADAM P,et al.Thermal-acoustic analysis of a metallic integrated thermal protection system structure:AIAA-2010-3121[R].Reston,VA:AIAA,2010.