集成火星进入弹道的开伞过程动力学特性研究
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摘要
针对火星探测任务设计阶段的需求,提出集成再入弹道、开伞过程仿真一体化设计方法。首先,利用质点动力学模型,计算质点弹道,进行探测器进入过程的飞行轨迹仿真,获得开伞初始状态。其次,基于任意拉格朗日-欧拉(ALE)方法,建立开伞过程的流固耦合(FSI)动力学模型,进行典型工况开伞过程数值模拟,分析开伞动压和马赫数对降落伞充气过程的影响。数值模拟开伞过程伞衣几何外形变化和降落伞的流固耦合动力学行为,得到开伞过载变化曲线、伞衣阻力面积变化等典型特征参数。计算结果表明,降落伞开伞动力学的数值仿真方法为火星再入、减速和着陆(EDL)过程的概念设计提供了一定的参考依据。
Focusing on the demands of design stage for Mars exploration mission,a whole design method integrating with entry trajectory and opening simulation is proposed. Firstly,the particle dynamics model is built to solve and simulate the flight trajectory of entry body. Then the fluid-structure interactions( FSI) model is built based on the arbitrary Lagrangian Eulerian( ALE) method to numerically simulate the opening process of parachute in supersonic environment,and the influences of opening dynamics pressure and Mach number on inflation characteristics are analyzed. The 3D shape of canopy deformation during inflation is simulated,FSI behaviors of parachute are investigated,and the results of some typical inflation parameters like opening force and drag are obtained. The results show that this integrated numerical method can be applied to analyze the Mars entry,descent and landing( EDL) problems in mission design stage.
Focusing on the demands of design stage for Mars exploration mission,a whole design method integrating with entry trajectory and opening simulation is proposed. Firstly,the particle dynamics model is built to solve and simulate the flight trajectory of entry body. Then the fluid-structure interactions( FSI) model is built based on the arbitrary Lagrangian Eulerian( ALE) method to numerically simulate the opening process of parachute in supersonic environment,and the influences of opening dynamics pressure and Mach number on inflation characteristics are analyzed. The 3D shape of canopy deformation during inflation is simulated,FSI behaviors of parachute are investigated,and the results of some typical inflation parameters like opening force and drag are obtained. The results show that this integrated numerical method can be applied to analyze the Mars entry,descent and landing( EDL) problems in mission design stage.
引文
[1]Braun R D,Manning R M.Mars exploration entry,descent and landing challenges[J].Journal of Space&Rockets,2007,44(2):310-323.
[2]李爽,彭玉明,陆宇平.火星EDL导航、制导与控制技术综述与展望[J].宇航学报,2010,31(3):621-627.[Li Shuang,Peng Yu-ming,Lu Yu-ping.Review and prospect of mars EDL navigation guidance and control technologies[J].Journal of Astronautics,2010,31(3):621-627.]
[3]Prakash R,Burkhart P D,Chen A.Mars Science Laboratory entry,descent,and landing system overview[C].Aerospace Conference,2008 IEEE,Montana,America,March 1-8,2008.
[4]任高峰,崔平远,崔祜涛.一种新型火星定点着陆轨迹快速优化方法[J].宇航学报,2013,34(4):464-472.[Ren Gao-feng,Cui Ping-yuan,Cui Hu-tao.A new method of rapid trajectory optimization for Mars pin-point landing[J].Journal of Astronautics,2013,34(4):464-472.]
[5]鲁媛媛,荣伟,吴世通.火星探测器降落伞拉直过程中的“绳帆”现象研究[J].宇航学报,2014,35(11):1238-1244.[Lu Yuan-yuan,Rong Wei,Wu Shi-tong.Study on line sail during mars probe parachute deployment[J].Journal of Astronautics,2014,35(11):1238-1244.]
[6]侯黎强,李恒年,黄福铭.一种半解析方法火星再入探测器一体化设计模型[J].宇航学报,2011,32(11):2312-2318.[Hou Li-qiang,Li Heng-nian,Huang Fu-ming,A semianalytical integrated model for capsule entering mars atmosphere[J].Journal of Astronautics,2011,32(11):2312-2318.]
[7]杨肖峰,唐伟,桂业伟.MSL火星探测器高超声速流场预测及气动性分析[J].宇航学报,2015,36(4):383-389.[Yang Xiao-feng,Tang Wei,Gui Ye-wei.Hypersonic flow field prediction and aerodynamics analysis for MSL entry capsule[J].Journal of Astronautics,2015,36(4):383-389.]
[8]彭勇,张青斌,秦子增.降落伞主充气阶段数值模拟[J].国防科技大学学报,2004,26(2):13-16.[Peng Yong,Zhang Qing-bin,Qin Zi-zeng,Simulation of parachute final inflation phase[J].Journal of National University of Defense Technology,2004,26(2):13-16.]
[9]高兴龙,唐乾刚,张青斌,等.开缝伞充气过程流固耦合数值研究[J].航空学报,2013,34(10):1-12.[Gao Xinglong,Tang Qian-gang,Zhang Qing-bin,et al.Numerical study on fluid-structure interaction of slot-parachute's inflation process[J].Acta Aeronautica et Astronautica Sinica,2013,34(10):1-12.]
[10]余莉,史献林,明晓.降落伞充气过程的数值模拟[J].航空学报,2007,28(1):52-57.[Yu Li,Shi Xian-lin,Ming Xiao.Numerical simulation of parachute during opening process[J].Acta Aeronautica et Astronautica Sinica,2007,28(1):52-57.]
[11]Gao X L,Zhang Q B,Tang Q G.Transient dynamic modeling and analysis of complex parachute inflation with fixed payload[J].Journal of Aerospace Engineering,2014,28(4):1-15.
[12]赵汉元.飞行器再入动力学和制导[M].长沙:国防科技大学出版社,1997.
[13]丰志伟,张青斌,高兴龙.火星探测器气动外形/弹道一体化多目标优化[J].航空学报,2014,35(9):2461-2471.[Feng Zhi-wei,Zhang Qing-bin,Gao Xing-long.Aerodynamic shape and trajectory integrated multiobjective optimization for mars explorer[J].Acta Aeronautica et Astronautica Sinica,2014,35(9):2461-2471.]
[14]程晓丽,李俊红,王强.空间飞行器在火星再入环境下的气动力特性[J].宇航学报,2010,31(4):967-972.[Cheng Xiao-li,Li Jun-hong,Wang Qiang.Aerodynamic force characteristics of Mars entry vehicles[J].Journal of Astronautics,2010,31(4):967-972.]
[15]Sutton K,Graves R A.A general stagnation-point convectiveheating equation for arbitrary gas mixtures[R].National Aeronautics and Space Administration,1971.
[16]Shen H J,Seywald H,Powell R.Desensitizing the pin-point landing trajectory on Mars[C].AIAA/AAS Astrodynamics Specialist Conference and Exhibit,Honolulu,Hawaii,August 18-21,2008.
[17]黄飞,吕俊明,程晓丽.火星稀薄大气参数对进入器气动特性的影响[J].宇航学报,2015,36(10):1093-1100.[Huang Fei,Lv Jun-ming,Cheng Xiao-li.Impact of martian rarefied atmosphere parameters on entry vehicle aerodynamics under hypersonic conditions[J].Journal of Astronautics,2015,36(10):1093-1100.]
[18]Aquelet N,Tutt B.Euler-Lagrange coupling for porous parachute canopy analysis[J].The International Journal of Multiphysics,2007,1(1):53-68.
[19]Benson D J.A mixture theory for contact in multi-material Eulerian formulations[J].Computer Methods in Applied Mechanics and Engineering,1997,140(1):59-86.
[20]崔平远,胡海静,朱圣英.火星精确着陆制导问题分析与展望[J].宇航学报,2014,35(3):245-253.[Cui Pingyuan,Hu Hai-jing,Zhu Sheng-ying.Analysis and prospect of guidance aspects for Mars precision landing[J].Journal of Astronautics,2014,35(3):245-253.]
[21]Knacke T W.Parachute recovery systems design manual[M].Santa Barbara,United States of America:Para Publishing,1992.
[2]李爽,彭玉明,陆宇平.火星EDL导航、制导与控制技术综述与展望[J].宇航学报,2010,31(3):621-627.[Li Shuang,Peng Yu-ming,Lu Yu-ping.Review and prospect of mars EDL navigation guidance and control technologies[J].Journal of Astronautics,2010,31(3):621-627.]
[3]Prakash R,Burkhart P D,Chen A.Mars Science Laboratory entry,descent,and landing system overview[C].Aerospace Conference,2008 IEEE,Montana,America,March 1-8,2008.
[4]任高峰,崔平远,崔祜涛.一种新型火星定点着陆轨迹快速优化方法[J].宇航学报,2013,34(4):464-472.[Ren Gao-feng,Cui Ping-yuan,Cui Hu-tao.A new method of rapid trajectory optimization for Mars pin-point landing[J].Journal of Astronautics,2013,34(4):464-472.]
[5]鲁媛媛,荣伟,吴世通.火星探测器降落伞拉直过程中的“绳帆”现象研究[J].宇航学报,2014,35(11):1238-1244.[Lu Yuan-yuan,Rong Wei,Wu Shi-tong.Study on line sail during mars probe parachute deployment[J].Journal of Astronautics,2014,35(11):1238-1244.]
[6]侯黎强,李恒年,黄福铭.一种半解析方法火星再入探测器一体化设计模型[J].宇航学报,2011,32(11):2312-2318.[Hou Li-qiang,Li Heng-nian,Huang Fu-ming,A semianalytical integrated model for capsule entering mars atmosphere[J].Journal of Astronautics,2011,32(11):2312-2318.]
[7]杨肖峰,唐伟,桂业伟.MSL火星探测器高超声速流场预测及气动性分析[J].宇航学报,2015,36(4):383-389.[Yang Xiao-feng,Tang Wei,Gui Ye-wei.Hypersonic flow field prediction and aerodynamics analysis for MSL entry capsule[J].Journal of Astronautics,2015,36(4):383-389.]
[8]彭勇,张青斌,秦子增.降落伞主充气阶段数值模拟[J].国防科技大学学报,2004,26(2):13-16.[Peng Yong,Zhang Qing-bin,Qin Zi-zeng,Simulation of parachute final inflation phase[J].Journal of National University of Defense Technology,2004,26(2):13-16.]
[9]高兴龙,唐乾刚,张青斌,等.开缝伞充气过程流固耦合数值研究[J].航空学报,2013,34(10):1-12.[Gao Xinglong,Tang Qian-gang,Zhang Qing-bin,et al.Numerical study on fluid-structure interaction of slot-parachute's inflation process[J].Acta Aeronautica et Astronautica Sinica,2013,34(10):1-12.]
[10]余莉,史献林,明晓.降落伞充气过程的数值模拟[J].航空学报,2007,28(1):52-57.[Yu Li,Shi Xian-lin,Ming Xiao.Numerical simulation of parachute during opening process[J].Acta Aeronautica et Astronautica Sinica,2007,28(1):52-57.]
[11]Gao X L,Zhang Q B,Tang Q G.Transient dynamic modeling and analysis of complex parachute inflation with fixed payload[J].Journal of Aerospace Engineering,2014,28(4):1-15.
[12]赵汉元.飞行器再入动力学和制导[M].长沙:国防科技大学出版社,1997.
[13]丰志伟,张青斌,高兴龙.火星探测器气动外形/弹道一体化多目标优化[J].航空学报,2014,35(9):2461-2471.[Feng Zhi-wei,Zhang Qing-bin,Gao Xing-long.Aerodynamic shape and trajectory integrated multiobjective optimization for mars explorer[J].Acta Aeronautica et Astronautica Sinica,2014,35(9):2461-2471.]
[14]程晓丽,李俊红,王强.空间飞行器在火星再入环境下的气动力特性[J].宇航学报,2010,31(4):967-972.[Cheng Xiao-li,Li Jun-hong,Wang Qiang.Aerodynamic force characteristics of Mars entry vehicles[J].Journal of Astronautics,2010,31(4):967-972.]
[15]Sutton K,Graves R A.A general stagnation-point convectiveheating equation for arbitrary gas mixtures[R].National Aeronautics and Space Administration,1971.
[16]Shen H J,Seywald H,Powell R.Desensitizing the pin-point landing trajectory on Mars[C].AIAA/AAS Astrodynamics Specialist Conference and Exhibit,Honolulu,Hawaii,August 18-21,2008.
[17]黄飞,吕俊明,程晓丽.火星稀薄大气参数对进入器气动特性的影响[J].宇航学报,2015,36(10):1093-1100.[Huang Fei,Lv Jun-ming,Cheng Xiao-li.Impact of martian rarefied atmosphere parameters on entry vehicle aerodynamics under hypersonic conditions[J].Journal of Astronautics,2015,36(10):1093-1100.]
[18]Aquelet N,Tutt B.Euler-Lagrange coupling for porous parachute canopy analysis[J].The International Journal of Multiphysics,2007,1(1):53-68.
[19]Benson D J.A mixture theory for contact in multi-material Eulerian formulations[J].Computer Methods in Applied Mechanics and Engineering,1997,140(1):59-86.
[20]崔平远,胡海静,朱圣英.火星精确着陆制导问题分析与展望[J].宇航学报,2014,35(3):245-253.[Cui Pingyuan,Hu Hai-jing,Zhu Sheng-ying.Analysis and prospect of guidance aspects for Mars precision landing[J].Journal of Astronautics,2014,35(3):245-253.]
[21]Knacke T W.Parachute recovery systems design manual[M].Santa Barbara,United States of America:Para Publishing,1992.