卫星结构弹性碰撞减损的研究与仿真
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摘要
在飞行段卫星需要承受复杂的动力学载荷条件,是引起航天器结构受损或设备故障的主要阶段。多颗卫星地面力学环境试验表明,对于质量大或质心高的一类设备,时常由于很大的加速度响应而引起结构受损,对工程研制带来较大影响。提出一种不同以往的工程解决方法,即采用间隙弹性碰撞改变刚度和限幅的非线性方法,可以达到较好的减损效果。通过构建动力学模型和仿真分析表明,该方法能够减小连接部位蜂窝板的变形和载荷,在工程上提供了一种新的解决途径。
Usually satellite is under complex dynamic load during the launch phase,it's easy to cause satellitestructure damageto influence spacecraftmission. Mechanical environment tests show that spacecraftstructure damage always occurs because of larger acceleration response of equipment such as large mass or high center of mass,and affecttedthe project development.Difference from the usual engineering solutions,a method based on gap elastic impactting is studiedto reducing damage. By constructing mechanical model,simulation and analysis has been done to a designated parameter structurepanel and equipment,results show that the methed as one of solutions of lower damage is valid to reducing defomation and load located at connection between equipment andstructure.
Usually satellite is under complex dynamic load during the launch phase,it's easy to cause satellitestructure damageto influence spacecraftmission. Mechanical environment tests show that spacecraftstructure damage always occurs because of larger acceleration response of equipment such as large mass or high center of mass,and affecttedthe project development.Difference from the usual engineering solutions,a method based on gap elastic impactting is studiedto reducing damage. By constructing mechanical model,simulation and analysis has been done to a designated parameter structurepanel and equipment,results show that the methed as one of solutions of lower damage is valid to reducing defomation and load located at connection between equipment andstructure.
引文
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[2]刘天雄,范本尧,杨慧.卫星飞轮扰振控制技术[J].航天器工程,2009,18(1):53-60.LIU TianXiong,FAN BenYao,YANG Hui.Research on vibration disturbance control of momentum wheel[J].Spacecraft Engineerlng,2009,18(1):53-60(In Chinese).
[3]Warburton G B.Optimum absorber parameters for various combinations of response and excitation parameters[J].Journal of Earthquake Engineering and Structural Dynamics,1982,10(3):381-401.
[4]李运动,孙树旺.机载稳定框架减振特性设计与分析[J].机械强度.2014,36(1):030-034LI YunDong,SUN ShuWang.Vibration isolation and characterristic analysis for airborne stability platform[J].Journal of Mechanical Strength,2014,36(1):030-034(In Chinese).
[5]徐超,李瑞杰,游少雄.卫星飞轮支架的共固化阻尼减振设计[J].宇航学报,2010,31(3):907-911.XU Chao,LI Rui Jie,YOU ShaoXiong.Passive vibration control design、co-curing dampingcomposite for a satellite flywheel bracket[J].Journal of Astronautic,2010,31(3):907-911(In Chinese).
[6]LEEY,HAMILTON J W.The lumped parameter method for elastic impact problems[J].Applied Mechanics 1983,50(4),827-827.
[7]王晨升,苏芳.两自由度双边刚性约束碰撞系统的动力学分析[J].机械强度,2014,36(5):671-675.WANG ChenSheng,SU Fang.Analysis of dynamics of a two-degreeof-freedom impact system with two rigid constraints[J].Jourual of Mechanical Stength,2014,36(5):671-675(In Chinese).
[8]陈镇南,卢绪祥,李录平,等.基于ANSYS/LS-DYNA的带冠叶片碰撞振动特性的有限元分析[J].动力工程学报,2013,33(3):189-193.CHEN ZhenNan,LU XuXiang,LI LuPing,et al.Finiteelement analysis on collision-vibration characteristics ofshrouded blades basedon ANSYS/LS-DYNA[J].Journal of Chinese Society of Power Engineering,2013,33(3):189-193(In Chinese).
[9]武新华,李卫军.自带冠叶片冠间接触碰撞减振研究[J].汽轮机技术,2005,47(1):41-44.WU Xin Hua,LI Wei Jun.Research on damping of contract or impaction of blades’tips[J].Turbine Technology,2005,37(1):41-44(In Chinese).
[10]王建伟,徐晖,马宁.内嵌自主移动钢球欧拉梁自适应碰撞减振研究[J].西安交通大学学报,2010,44(11):103-108.WANG JianWei,XU Hui,MA Ning.Viberation suppression via adaptive impacts for eular beam with interior inlaid freedly moving steel ball[J].Journal of Xi’an Jiaotong University,2010,44(11):103-108(In Chinese).
[11]金栋平,胡海岩.碰撞振动与控制[M].北京:科学出版社,2005:75-87.JIN Dong Ping,HU Hai Yan.Impact vibration and control[M],Beijing:Science Press,2005:75-87(In Chinese).