MF-1弹道设计与蒙特卡罗飞行仿真
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摘要
MF-1是我国的首次高超声速空气动力学基础问题研究模型飞行试验。本文研究建立了MF-1试验飞行器弹道设计与拉偏仿真数学模型,开展了MF-1弹道设计和拉偏仿真计算。对结果分析表明,对于MF-1这类无控飞行器,某些条件下可能在飞行过程中发生滚转共振现象,导致飞行总迎角迅速发散,气动过载显著增加,飞行弹道严重偏离设计弹道,甚至可能出现解体风险。通过严格控制飞行器加工和安装偏差,有助于降低滚转共振发生概率。
MF-1 is the first modeling flight test in China aiming at fundamental hypersonic aerodynamics problems.In this paper,the models of trajectory design and Monte Carlo flight simulation for MF-1 are established,and the results of designed trajectory and Monte Carlo flight simulations are presented.Results analysis shows that,for MF-1-like flight vehicles,the roll resonance phenomena may happen in some circumstances.These phenomena can produce unstable total flight angle of attack and increasing aerodynamic overloads,leading to trajectory parameters deviating from designed values,and risks of structural collapse.Moreover,the roll resonance can be suppressed by strictly limiting the errors and bias during producing and manufacturing procedures.
MF-1 is the first modeling flight test in China aiming at fundamental hypersonic aerodynamics problems.In this paper,the models of trajectory design and Monte Carlo flight simulation for MF-1 are established,and the results of designed trajectory and Monte Carlo flight simulations are presented.Results analysis shows that,for MF-1-like flight vehicles,the roll resonance phenomena may happen in some circumstances.These phenomena can produce unstable total flight angle of attack and increasing aerodynamic overloads,leading to trajectory parameters deviating from designed values,and risks of structural collapse.Moreover,the roll resonance can be suppressed by strictly limiting the errors and bias during producing and manufacturing procedures.
引文
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[6]SMART M K,SUARWEERA M V.HIFiRE7-development of a 3-D scramjet for flight testing[R].AAIA 2009-7259,2009.
[7]GURBER M,JACKSON K,EKULND D.Instrumentation and performance analysis plans for the HIFiRE flight 2experiment[R].AIAA 2009-5032,2009.
[8]NEUENHAHN T,OLIVIER H,PAULL A.Development of the HyShot stability demonstrator[R].AIAA 2006-2960,2006.
[9]CHEN F J(FRANK),BERRY S A.HyBoLT flight experiment[R].NASA/TM-2010-216725.
[10]WALKER S,RODGERS F,PAULL A,et al.HyCAUSEflight test program[R].AIAA 2008-2580,2008.
[11]MUYLAERT J,CIPOLLIN F,WALPOT L,et al.Flight experiments for hypersonic vehicle development expert[R].RTO-EN-AVT-130.
[12]BARRIO A M,SUDARS M,GAVIRA J,et al.EXPERT-The ESA experimental re-entry test-bed.trajectory and mission design[R].AIAA 2011-6342,2011.
[13]文苏丽,时兆峰.SHEFEX-全新的高超声速技术试验平台[J].飞航导弹,2010(9):24-28.WEN S L,SHI Z F.SHEFEX-,an new hypersonic technology test platform[J].Aerodynamic Missile Journal,2010(9):24-28.(in Chinese)
[14]BAIOCCOP.Pre-X experimental re-entry lifting body-design of flight test experiments for critical aerothermal phenomena[R].ADA476581.
[15]和争春.飞船返回舱气动参数辨识及其有关问题研究[D].西安:西北工业大学,2004.HE Z C.Research on aerodynamic parameters identification and related problems for spaceship re-entry capsule[D].Xi’an:Northwestern polytechnical University,2004.
[16]蔡金狮,董能力.再入弹头滚转共振概率估算[J].宇航学报,1995,16(1):1-7.CAI J S,DONG N L.Roll resonance probability estimation of reentry warhead[J].Journal of Astronautics,1995,16(1):1-7.(in Chinese)