火箭助推器翼伞回收动力学仿真与试验分析
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摘要
翼伞具有良好的滑翔性、操纵性和稳定性,能够解决火箭助推器落点散布大导致的安全性问题。为对翼伞回收系统和控制系统进行优化设计,以基于可控翼伞回收技术的火箭助推器–控制平台—翼伞多体飞行系统为研究对象,采用拉格朗日乘子法建立了三体组合10自由度多体动力学仿真模型,考虑了翼伞的表观质量特性和火箭助推器的气动力影响,对某次空投飞行试验进行了动力学过程仿真重建,通过仿真与试验的对比分析飞行机理和系统性能。分析结果表明,翼伞系统间存在多体相对运动,必须采用多体动力学模型进行研究;机动飞行时,火箭助推器与翼伞间的相对运动角度并不大,而且火箭助推器的大尺寸对相对偏航运动的影响也并不显著;航向跟踪误差主要来自操纵效率低,在小角度航向跟踪误差时,需提高操纵控制增益。研究成果可以为翼伞系统的工程设计与应用提供参考。
Controllable parafoil system could solve the security problem resulted from large dispersion of deserted boosters with its favorable gliding, manueverability and stability. To optimize the parafoil recovery system and its control system, taking a multibody dynamic system of booster-controller-parafoil based on parafoil recovery technology as a researching object, a three-body simulation model with 10-degree-of-freedom is established with Lagrange multiplier method, which considers the apparent mass characteristics of parafoil and aerodynamic impact of the booster. The process of an airdrop test is reconstructed with this model, and flight mechanism and performances are analyzed. The results show that multibody relative motion does exist among parafoil-payload systems, thus it is essential to establish a mutltibody model for simulation. While in maneuvering, the relative attitudes are not so large, and the aerodynamic of large size of rocket on parafoil system is not so profound. The tracking errors mainly come from low steering efficiency of parafoil, thus it is necessary to increase the gain of steering. The results provide a reference for the parafoil system engineering and application.
Controllable parafoil system could solve the security problem resulted from large dispersion of deserted boosters with its favorable gliding, manueverability and stability. To optimize the parafoil recovery system and its control system, taking a multibody dynamic system of booster-controller-parafoil based on parafoil recovery technology as a researching object, a three-body simulation model with 10-degree-of-freedom is established with Lagrange multiplier method, which considers the apparent mass characteristics of parafoil and aerodynamic impact of the booster. The process of an airdrop test is reconstructed with this model, and flight mechanism and performances are analyzed. The results show that multibody relative motion does exist among parafoil-payload systems, thus it is essential to establish a mutltibody model for simulation. While in maneuvering, the relative attitudes are not so large, and the aerodynamic of large size of rocket on parafoil system is not so profound. The tracking errors mainly come from low steering efficiency of parafoil, thus it is necessary to increase the gain of steering. The results provide a reference for the parafoil system engineering and application.
引文
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[18]蒋万松,荣伟,滕海山,等.翼伞载荷系统多体动力学仿真分析[J].南京航空航天大学学报,2016,48(4):474-481.JIANG Wansong,RONG Wei,TENG Haishan,et al.Multibody Dynamical Simulation Analysis for Parafoil-payload System[J].Journal of Nanjing University of Aeronautics&Astronautics,2016,48(4):474-481.(in Chinese)
[19]赵育善,师鹏.航天器飞行动力学建模理论与方法[M].北京:北京航空航天大学出版社,2012.ZHAO Yushan,SHI Peng.Spacecraft Flight Dynamics Modeling Theory and Methods[M].Beijing:Beijing University of Aeronautics&Astronautics Press,2012.(in Chinese)
[20]LINGARD J S.Ram Airparachute Design[C]//13th AIAA Aerodynamic Decelerator Systems Technology Conference,Clearwater Beach.AIAA 1995.
[21]IACOMINI C S,CERIMELE C J.Lateral-directional Aerodynamics from a Large Scale Parafoil Test Program[C]//15th Aerodynamic Decelerator Systems Technology Conference,Toulouse,France.AIAA 99-1731.
[22]夏雪湔,邓学蓥.工程分离流动力学[M].北京:北京航空航天大学出版社,1991.XIA Xuejian,DENG Xueying.Engineering Separation Flow Dynamics[M].Beijing:Beijing University of Aeronautics&Astronautics Press,1991.(in Chinese)
[2]熊菁.翼伞系统动力学与归航方案研究[D].长沙:国防科技大学博士学位论文,2005.XIONG Jing.Research on Dynamics and Homming Control of Parafoil System[D].Changsha:National University of Defense Technology,2005.(in Chinese)
[3]熊菁,宋旭民,秦子增.翼伞系统两体相对运动分析[J].航天返回与遥感,2004,25(2):10-16.XIONG Jing,SONG Xuming,QIN Zizeng.Study on Relative Motion of Two-body Parafoil System[J].Spacecraft Recovery&Remote Sensing,2004,25(2):10-16.(in Chinese)
[4]YAKIMENKO O A.On the Development of a Scalable 8-DOF Model for a Generic Parafoil-payload Delivery System[C]//18th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar,Munich,Germany.AIAA 2005-1665.
[5]PILLASCH D W,SHEN Y C,VALERO N.Parachute/Submunition System Coupled Dynamics[C]//8th Aerodynamic Decelerator and Balloon Technology Conference,Hyannis,MA,U.S.A.AIAA 84-0784.
[6]WISE K A.Dynamics of a UAV with Parafoil under Powered Flight[C]//AIAA Guidance,Navigation,and Control Conference and Exhibit,Keystone,Colorado.AIAA 2006-6795.
[7]STRICKER G,WITTE L.Analysis of the Relative Motion in a Parafoil-load System[C]//16th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar,Boston,MA,U.S.A.AIAA 2001-2013.
[8]CHRISTIAAN R.A Flight Simulation Algorithm for a Parafoil Suspending an Air Vehicle[J].Journal of Guidance,Control and Dynamics,2007,30(3):791-803.
[9]MOOIJ E,WIJNANDS Q G,et al.9 DOF Parafoil/Payload Simulator Development and Validation[C]//AIAA Modeling and Simulation Technologies Conference and Exhibit,Austin,Texas.AIAA 2003-5459.
[10]陈建平,宁雷鸣,张红英,等.基于多体动力学的大型翼伞系统飞行仿真分析[J].飞行力学,2015,33(6):486-490.CHEN Jianping,NING Leiming,ZHANG Hongying,et al.Flight Simulation and Analysis of Large Parafoil System Based on Multibody Dynamics[J].Flight Dynamics,2015,33(6):486-490.(in Chinese)
[11]陈建平,张红英,童明波,等.翼伞系统纵向飞行性能仿真[J].中国空间科学技术,2015,35(2):25-32.CHEN Jianping,ZHANG Hongying,TONG Mingbo,et al.Longitudinal Flight Performances Simulation for Parafoil System[J].Chinese Space Science and Technology,2015,35(2):25-32.(in Chinese)
[12]BARROWS T M.Multibody Parafoil Model[C]//20th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar,Seattle,Washington.AIAA 2009-2945.
[13]PRAKASH O,ANANTHKRISHNAN N.Modeling and Simulation of 9-DOF Parafoil-payload System Flight Dynamics[C]//AIAA Atmospheric Flight Mechanics Conference and Exhibit,Keystone,Colorado.AIAA 2006-6130.
[14]MULLER S,WAGNER O,SACHS G.A High-fidelity Nonlinear Multibody Simulation Model for Parafoil System[C]//17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar,Monterey,California.AIAA 2003-2120.
[15]GORMAN C M,SLEGERS N J.Comparison and Analysis of Multi-body Parafoil Models with Varying Degrees of Freedom[C]//21st AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar,Dublin,Ireland.AIAA2011-2615.
[16]BARROWS T M.Apparent Mass of Parafoils with Spanwise Camber[C]//16th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar,Boston,MA,U.S.A.AIAA 2001-2006.
[17]LISSAMAN B S,BROWN G J.Apparent Mass Effects on Parafoil Dynamics[C]//Aerospace Design Conference,Irvine,CA,U.S.A.AIAA 93-1236.
[18]蒋万松,荣伟,滕海山,等.翼伞载荷系统多体动力学仿真分析[J].南京航空航天大学学报,2016,48(4):474-481.JIANG Wansong,RONG Wei,TENG Haishan,et al.Multibody Dynamical Simulation Analysis for Parafoil-payload System[J].Journal of Nanjing University of Aeronautics&Astronautics,2016,48(4):474-481.(in Chinese)
[19]赵育善,师鹏.航天器飞行动力学建模理论与方法[M].北京:北京航空航天大学出版社,2012.ZHAO Yushan,SHI Peng.Spacecraft Flight Dynamics Modeling Theory and Methods[M].Beijing:Beijing University of Aeronautics&Astronautics Press,2012.(in Chinese)
[20]LINGARD J S.Ram Airparachute Design[C]//13th AIAA Aerodynamic Decelerator Systems Technology Conference,Clearwater Beach.AIAA 1995.
[21]IACOMINI C S,CERIMELE C J.Lateral-directional Aerodynamics from a Large Scale Parafoil Test Program[C]//15th Aerodynamic Decelerator Systems Technology Conference,Toulouse,France.AIAA 99-1731.
[22]夏雪湔,邓学蓥.工程分离流动力学[M].北京:北京航空航天大学出版社,1991.XIA Xuejian,DENG Xueying.Engineering Separation Flow Dynamics[M].Beijing:Beijing University of Aeronautics&Astronautics Press,1991.(in Chinese)