大型星载天线桁架式可折展机构的模态分析
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摘要
大型空间抛物柱面星载天线具有口径大、约束弱、刚度低、质量小等特点,其机构的空间稳定性直接决定天线的使用寿命和信息传输的可靠性。为准确获得大型空间星载天线在轨稳定性能参数,依据星载天线的高精度和长寿命的设计需求,提出一种新型抛物柱面星载天线结构形式,利用有限元仿真对该新型星载天线作模态分析,并分析相关参数。结果表明:采用Al7075材料的新型抛物柱面星载天线基频满足设计要求。同时,增加上下支杆和上下斜撑杆的截面尺寸可有效提高天线结构的固有频率。该研究为我国大型抛物柱面星载天线设计提供了理论支撑和技术参考。
The large space parabolic cylindrical satellite antenna is characterized by large diameter, weak constraint, low stiffness and small mass. The space stability of its mechanism directly determines the service life of the antenna and the reliability of information communication. To obtain the on-orbit stability performance of the large satellite antenna, a new parabolic cylindrical satellite antenna structure is proposed in this paper according to design requirements on high precision and long life of the satellite antenna. Modal analysis of the new satellite antenna is carried out by finite element simulation and related parameters are studied. The results show that the minimal frequency of the new parabolic cylindrical satellite antenna using Al7075 material meets design requirements. Meanwhile, the natural frequency of the antenna structure can be effectively improved by increasing cross section sizes of upper and lower support bars as well as upper and lower inclined support bars. The above research provides theoretical support and technical reference for the design of large-scale parabolic cylindrical satellite antennas in China.
The large space parabolic cylindrical satellite antenna is characterized by large diameter, weak constraint, low stiffness and small mass. The space stability of its mechanism directly determines the service life of the antenna and the reliability of information communication. To obtain the on-orbit stability performance of the large satellite antenna, a new parabolic cylindrical satellite antenna structure is proposed in this paper according to design requirements on high precision and long life of the satellite antenna. Modal analysis of the new satellite antenna is carried out by finite element simulation and related parameters are studied. The results show that the minimal frequency of the new parabolic cylindrical satellite antenna using Al7075 material meets design requirements. Meanwhile, the natural frequency of the antenna structure can be effectively improved by increasing cross section sizes of upper and lower support bars as well as upper and lower inclined support bars. The above research provides theoretical support and technical reference for the design of large-scale parabolic cylindrical satellite antennas in China.
引文
[1] 胡海岩,田强,张伟,等.大型网架式可展开空间结构的非线性动力学与控制[J].力学进展,2013,43(4):390-414.
[2] MISAWA M. Natural frequency prediction of deployable satellite antennas in orbit[J]. Transactions of the Japan Society of Mechanical Engineers, 1996, 62(603): 4198-4204.
[3] MISAWA M, OHKAMI Y. Stiffness design of deployable satellite antennas in deployed configuration[J]. Journal of Spacecraft and Rockets, 2012, 35(3): 380-386.
[4] BALAJI K, NAGARAJ B P, RAI V S, et al. Parametric study of sensitivity of deployed frequency for large cable net antenna[J]. Journal of Aerospace Engineering, 2014, 228(5): 727-739.
[5] SATISH T N, MURTHY R, SINGH A K. Analysis of uncertainties in measurement of rotor blade tip clearance in gas turbine engine under dynamic condition[J]. Journal of Aerospace Engineering, 2014, 228(5): 652-670.
[6] MIURA K, FURUYA H, SUZUKI K. Variable geometry truss and its application to deployable truss and space crane arm[J]. Acta Astronautica, 1985, 12(7/8): 599-607.
[7] HOOKER W W, MARGULIES G. The dynamical attitude equations for n-body satellite[J]. Journal of the Astronautical Sciences, 1965, 12(4): 123-128.
[8] IDER S K. Finite-element based recursive formulation for real time dynamic simulation of flexible multibody systems[J]. Computers & Structures, 1991, 40(4): 939-945.
[9] CUADRADO J, GUTIéRREZ R, NAYA M A, et al. Experimental validation of a flexible MBS dynamic formulation through comparison between measured and calculated stresses on a prototype car[J]. Multibody System Dynamics, 2004, 11(2): 147-166.
[10] CONWAY B A, WIDHALM J W. Equations of attitude motion for an N-body satellite with moving joints[J]. Journal of Guidance Control and Dynamics, 2015, 8(4): 537-539.
[11] BAE D S, HAN J M, CHOI J H, et al. A generalized recursive formulation for constrained flexible multibody dynamics[J]. International Journal for Numerical Methods in Engineering, 2001, 50(8): 1841-1859.
[12] 赵孟良,关富玲. 考虑摩擦的周边桁架式可展天线展开动力学分析[J]. 空间科学学报, 2006, 26(3): 220-226.
[13] 李团结, 张琰,李涛. 周边桁架可展天线展开过程动力学分析及控制[J]. 航空学报, 2009, 30(3): 444-449.
[14] 周志成, 曲广吉. 星载大型网状天线非线性结构系统有限元分析[J]. 航天器工程, 2008, 17(6): 33-38.
[2] MISAWA M. Natural frequency prediction of deployable satellite antennas in orbit[J]. Transactions of the Japan Society of Mechanical Engineers, 1996, 62(603): 4198-4204.
[3] MISAWA M, OHKAMI Y. Stiffness design of deployable satellite antennas in deployed configuration[J]. Journal of Spacecraft and Rockets, 2012, 35(3): 380-386.
[4] BALAJI K, NAGARAJ B P, RAI V S, et al. Parametric study of sensitivity of deployed frequency for large cable net antenna[J]. Journal of Aerospace Engineering, 2014, 228(5): 727-739.
[5] SATISH T N, MURTHY R, SINGH A K. Analysis of uncertainties in measurement of rotor blade tip clearance in gas turbine engine under dynamic condition[J]. Journal of Aerospace Engineering, 2014, 228(5): 652-670.
[6] MIURA K, FURUYA H, SUZUKI K. Variable geometry truss and its application to deployable truss and space crane arm[J]. Acta Astronautica, 1985, 12(7/8): 599-607.
[7] HOOKER W W, MARGULIES G. The dynamical attitude equations for n-body satellite[J]. Journal of the Astronautical Sciences, 1965, 12(4): 123-128.
[8] IDER S K. Finite-element based recursive formulation for real time dynamic simulation of flexible multibody systems[J]. Computers & Structures, 1991, 40(4): 939-945.
[9] CUADRADO J, GUTIéRREZ R, NAYA M A, et al. Experimental validation of a flexible MBS dynamic formulation through comparison between measured and calculated stresses on a prototype car[J]. Multibody System Dynamics, 2004, 11(2): 147-166.
[10] CONWAY B A, WIDHALM J W. Equations of attitude motion for an N-body satellite with moving joints[J]. Journal of Guidance Control and Dynamics, 2015, 8(4): 537-539.
[11] BAE D S, HAN J M, CHOI J H, et al. A generalized recursive formulation for constrained flexible multibody dynamics[J]. International Journal for Numerical Methods in Engineering, 2001, 50(8): 1841-1859.
[12] 赵孟良,关富玲. 考虑摩擦的周边桁架式可展天线展开动力学分析[J]. 空间科学学报, 2006, 26(3): 220-226.
[13] 李团结, 张琰,李涛. 周边桁架可展天线展开过程动力学分析及控制[J]. 航空学报, 2009, 30(3): 444-449.
[14] 周志成, 曲广吉. 星载大型网状天线非线性结构系统有限元分析[J]. 航天器工程, 2008, 17(6): 33-38.