MF-1模型飞行试验结构与热防护关键问题研究
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摘要
MF-1是我国首次以高超声速空气动力学基础问题研究为目的的航天模型飞行试验,试验模型为锥-柱-裙体,主要研究0°攻角圆锥边界层转捩和压缩拐角激波/边界层干扰现象。试验飞行器的结构与热防护系统,既要满足飞行安全的基本要求,又要满足转捩研究对表面精度的特殊要求。针对超大尾翼的变形控制要求,将"#"字形加强筋结构优化为"米"字形,有效抑制了尾翼的最大变形量和颤振的发生;针对4片尾翼安装偏角的控制要求,通过尾翼安装面工艺改进和安装偏角正负抵消的办法,确保了总安装偏角(代数和)小于7′,有效抑制了弹体滚转;针对表面精度控制要求,提出弹体结构/薄壁测温模块一体化设计与二次精加工方案,有效抑制了测温模块对边界层流动的干扰。地面测温组件热振联合试验、尾翼/尾段静力试验和试验模型振动试验结果表明,MF-1模型飞行试验结构与热防护系统安全可靠。飞行试验结果表明,MF-1模型飞行器结构与热防护关键问题的解决措施基本成功,但试验模型头锥与前舱连接同轴度偏差导致部分子午线出现台阶超差,从而诱导了部分子午面出现强制转捩现象,凸显了表面精度控制对边界层转捩研究的重要性。
The first aerospace modeling flight test named MF-1 in China was carried out aiming at studying fundamental problems in hypersonic aerodynamics.By employing a conecylinder-flare configuration in the payload modules,the main objective of this test is to investigate the boundary layer transition on the cone surface and the shock wave/boundary layer interaction at the compression corner.The structure and thermal protection system of experimental vehicle need to satisfy not only the basic requirements of flight safety,but also the special surface precision requirements regarding transition studies.According to the deformation control requirements of the tail fin,the cruciform strengthening structure was optimized to the shape of British ‘Union Jack',which effectively suppressed the maximum deformation and flutter of the tail fin.To satisfy the control requirements of the installation deflection of four tailfins,an improved method for the tail fin installation and positive and negative offset for the deflection installation were used to ensure the total installation deflection less than 7′and effective suppression of the projectile rolling.The integrated design of structure/thin wall temperature measurement module and a second precision machining scheme were proposed for the requirement of surface precision control.These methods effectively inhibit the interference of the temperature measurement module on the boundary layer flow.Thermal-vibrational joint test ofthe ground temperature measurement component,tail/tail-fin static test,and model vibration test show that the structure and thermal protection system for the MF-1 flight test are safe and reliable.Flight test results show that the structure and thermal protection of the MF-1 basically successfully resolve the key issues.However,the coaxality differences between the nose cone and the front cabin of test model lead to out-of-tolerance in meridian steps,further induce a forced transition phenomenon in the meridian plane.This behavior highlights the importance of surface accuracy control to the research on boundary layer transition.
The first aerospace modeling flight test named MF-1 in China was carried out aiming at studying fundamental problems in hypersonic aerodynamics.By employing a conecylinder-flare configuration in the payload modules,the main objective of this test is to investigate the boundary layer transition on the cone surface and the shock wave/boundary layer interaction at the compression corner.The structure and thermal protection system of experimental vehicle need to satisfy not only the basic requirements of flight safety,but also the special surface precision requirements regarding transition studies.According to the deformation control requirements of the tail fin,the cruciform strengthening structure was optimized to the shape of British ‘Union Jack',which effectively suppressed the maximum deformation and flutter of the tail fin.To satisfy the control requirements of the installation deflection of four tailfins,an improved method for the tail fin installation and positive and negative offset for the deflection installation were used to ensure the total installation deflection less than 7′and effective suppression of the projectile rolling.The integrated design of structure/thin wall temperature measurement module and a second precision machining scheme were proposed for the requirement of surface precision control.These methods effectively inhibit the interference of the temperature measurement module on the boundary layer flow.Thermal-vibrational joint test ofthe ground temperature measurement component,tail/tail-fin static test,and model vibration test show that the structure and thermal protection system for the MF-1 flight test are safe and reliable.Flight test results show that the structure and thermal protection of the MF-1 basically successfully resolve the key issues.However,the coaxality differences between the nose cone and the front cabin of test model lead to out-of-tolerance in meridian steps,further induce a forced transition phenomenon in the meridian plane.This behavior highlights the importance of surface accuracy control to the research on boundary layer transition.
引文
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[3]Adamczak D,Alesi H,Frost M.HIFiRE-1:payload design,manufacture,ground test,and lessons learned[R].AIAA2009-7294,2009.
[4]Kimmel R L,Adamczak D.Hifire-1background and lessons learned[R].AIAA 2012-1088,2012.
[5]Schneider S P.Flight data for boundary-layer transition at hypersonic and supersonic speeds[J].Journal of Spacecraft and Rockets,1999,36(1).
[6]Stetson K F.Nosetip bluntntess effects on cone frustum boundary layer transition in hypersonic flow[R].AIAA-83-1763,1983.
[7]Kimmel R L,Adamczak D,Gaitonde D,et al.HIFiRE-1boundary layer transition experiment design[R].AIAA 2007-0534,2007.
[8]Johnson H B,Alba C R,Candler G V,et al.Boundary layer stability analysis of the hypersonic international flight research transition experiments[J].AIAA Journal of Spacecraft and Rockets,2008,45(2).
[9]Stainback C P.Effect of unit reynolds number,nose bluntness,angle of attack,and roughness on transition on a 5°half-angle cone at Mach 8[R].NASA TN D-4961,January 1969.
[10]Liu Chuping,Yang Qingtao,et al.Heatflux measurement in aerothermodynamics and thermal protection tests[M].Beijing:National Defense Industry Press,2013.(in Chinese)刘初平,杨庆涛,等.气动热与热防护试验热流测量[M].北京:国防工业出版社,2013.
[11]Wu Dafang,Zhao Shougen,Yan Zhenqian,et al.Experimental study on thermal-vibration test of thermal insulating component for cruise missile[J].Journal of Aerospace Power,2009,24(07):7-11.(in Chinese)吴大方,赵寿根,晏震乾,等.巡航导弹防热部件热-振联合试验[J].航空动力学报,2009,24(07):7-11.
[12]Zhang Shouyan,Hui Yuxin,et al.Modeling free flight[M].Beijing:National Defense Industry Press,2002.(in Chinese)张守言,惠宇昕,等.模型自由飞试验[M].北京:国防工业出版社,2002.
[13]Zhang Zhijun,Cheng Zhu,Wang Qi,et al.Experimental technology study for thermo-vibration united environment[J].Journal of Experimental Mechanics,2013,28(04):30-35.(in Chinese).张治君,成竹,王琦,等.热振联合环境试验技术研究[J].实验力学,2013,28(04):30-35.
[14]Fan Huitao,Guo Qiangling.Research on free flight vibration environment of tactical missiles[J].Tactical Missile Technology,2015,02:17-22(in Chinese).樊会涛,郭强岭.战术导弹自主飞振动环境研究[J].战术导弹技术,2015,02:17-22.
[15]Liang Deli,Yu Kaiping,Han Jingyong.Advances in noise and vibration environment prediction of high speed spacecrafts[J].Noise and Vibration Control,2013,1006:58-62(in Chinese).梁德利,于开平,韩敬永.高速飞行器振动噪声环境预示技术[J].噪声与振动控制,2013,1006:58-62.
[16]Berger K T,Greene F A.Aerothermodynamic testing and boundary-layer trip sizing of the HIFiRE flight 1vehicle[J].Journal of Spacecraft and Rockets,2008,45(6).
[17]Kimmel R L,Adamczak D,Juliano T J.HIFiRE-5flight test preliminary results[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.Texas,USA:American Institute of Aeronautics and Astronautics,2013:1-16.
[18]Juliano T J,Adamczak D,Kimmel R L.HIFiRE-5flight test heating analysis[C]//52nd Aerospace Sciences Meeting.Maryland,USA:American Institute of Aeronautics and Astronautics,2014:1-17.