连续地月转移系统动力学研究与能量分析

doi:10.7527/S1000-6893.2015.0061

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连续地月转移系统动力学研究与能量分析

阳勇, 齐乃明, 黄盘兴, 徐喆垚

哈尔滨工业大学航天学院, 哈尔滨 150006

收稿日期:2014-07-14 修回日期:2014-09-10 出版日期:2015-06-15 发布日期:2015-03-06
通讯作者: 齐乃明 Tel.: 0451-86418119 E-mail: qinmok@163.com E-mail:qinmok@163.com
作者简介:阳勇男, 博士研究生。主要研究方向: 空间飞行器动力学与控制, 绳系卫星动力学。 Tel: 0451-86418119 E-mail: yangyong_hit@hit.edu.cn;齐乃明男, 博士, 教授, 博士生导师。主要研究方向: 飞行器动力学与控制, 机电一体化。 Tel: 0451-86418119 E-mail: qinmok@163.com
基金资助:
CAST重点创新基金 (CAST20090801)

Dynamics and energy analysis of continuous cislunar transfer system

YANG Yong, QI Naiming, HUANG Panxing, XU Zheyao

School of Astronautics, Harbin Institute of Technology, Harbin 150006, China

Received:2014-07-14 Revised:2014-09-10 Online:2015-06-15 Published:2015-03-06
Supported by:
China Academy of Space Technology Innovation Foundation (CAST20090801)

摘要/Abstract

摘要：

为了研究新型连续地月转移系统的动力学及能量需求,采用Lagrange方法,在系绳为刚性杆假设的前提下,同时忽略第三体引力、地球扁率和系绳轴向变形等扰动因素的影响,建立了驱动型动量交换绳系卫星(MMET)系统的三维刚性动力学模型。对所建立的动力学模型进行了数值仿真及对比分析,仿真结果验证了所建模型的正确性。研究表明,外力矩对系统轨道运动参数影响甚小,对姿态运动参数影响明显。采用MMET方式进行载荷转移,推导出了实现载荷地月轨道转移所需的入口速度条件以及时间周期条件,并求解出了载荷在2次任务之间的时间间隔。给定初始条件下,当MMET系统以0.231 6 rad/s的旋转角速度绕其质心旋转1 448.5圈,其绕地心刚好运行5圈时,载荷可顺利进入地月转移轨道。最后,对连续地月转移系统实现载荷的地月转移进行了能量对比分析,结果表明,相同条件下,MMET载荷转移方式相比于传统脉冲变轨方式在载荷转移过程中消耗更少的能量。

关键词: 绳系卫星, 动量交换, 地月转移, 载荷, 动力学, 能量分析

Abstract:

To study the dynamics and energy of continuous cislunar transfer system, under the conditions of rigid rod presumption and overlooking the perturbations of the third-body gravitation, the oblateness of the Earth and the axial deformation, by using the Lagrange method, a three-dimensional rigid dynamic model of motorized momentum exchange tether (MMET) is built, which has been verified under numerical simulation, comparison and analysis. Studies show that the external torque has less influence on the orbit movement but has evident influence on those attitude parameters. Entry velocity condition and time period condition, which ensure that payload enters the cislunar transferring trajectory successfully, of MMET have been deduced theoretically. Furthermore, the time interval between two payloads transferring missions is solved. Under the given initial conditions, if the rotational angular velocity of MMET is 0.231 6 rad/s, when MMET rotates around its center of mass by 1 448.5 circles and MMET orbits Earth for 5 circles simultaneously, the payload can enter cislunar transfer trajectory successfully. The analysis of energy requirement, which is needed by MMET way or traditional impulse transfer way when transferring payloads from Earth to Moon, has been studied. It is illustrated that under the same conditions, the way of MMET needs less energy.

Key words: tether, momentum exchange, cislunar transfer, payload, dynamics, energy analysis

中图分类号:

V476.5

阳勇, 齐乃明, 黄盘兴, 徐喆垚. 连续地月转移系统动力学研究与能量分析[J]. 航空学报, 2015, 36(6): 2005-2015.

YANG Yong, QI Naiming, HUANG Panxing, XU Zheyao. Dynamics and energy analysis of continuous cislunar transfer system[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 2005-2015.

参考文献

[1] Cartmell M P. Generating velocity increments by means of a spinning motorized tether, AIAA-1998-3739[R]. Reston: AIAA, 1998.
[2] Cartmell M P, McKenzie D J. A review of space tether research[J]. Progress in Aerospace Sciences, 2008(44): 1-22.
[3] Cartmell M P, Ziegler S W, Neill D S. On the performance prediction and scale modelling of a motorised momentum exchange propulsion tether[C]//Proceedings of the Space Technology and Applications International Forum. Maryland: American Institute of Physics, 2003: 571-579.
[4] Ziegler S W, Cartmell M P. Investigating the use of motorised tethers for payload orbital transfer, AIAA-2000-4529[R]. Reston: AIAA, 2000.
[5] Cartmell M P, Ziegler S W. Symmetrically laden motorised tethers for continuous two-way interplanetary payload exchange, AIAA-1999-2840[R]. Reston: AIAA, 1999.
[6] Ziegler S W. The rigid body dynamic of tethers in space[D]. Glasgow, Scotland: University of Glasgow, 2003.
[7] Ziegler S W, Cartmell M P. Using motorized tethers for payload orbital transfer[J]. Journal of Spacecraft and Rockets, 2001, 38(6): 904-913.
[8] Chen Y, Cartmell M P. Dynamical modelling of the motorised momentum exchange tether incorporating axial elastic effects[C]//Proceedings of Advanced Problems in Mechanics. St. Petersburg, Russian: Russian Academy of Sciences, 2007: 1-13.
[9] Li Z, Peter M B. Momentum exchange-feedback control of flexible spacecraft maneuvers and vibration[J]. Journal of Guidance, Control and Dynamics, 1992, 15(6): 1354-1361.
[10] Kim E,Vadali R S. Modeling issues related to retrieval of flexible tethered satellite systems[J]. Journal of Gui-dance, Control and Dynamics, 1995, 18(5): 1169-1176.
[11] Ismail N A. The dynamics of a flexible motorised momentum exchange tether (MMET)[D]. Glasgow, Scotland: University of Glasgow, 2012.
[12] Mouterde E, Cartmell M P, Wang Y. Computational simulation of feedback linearised control of a motorised momentum exchange tether on a circular earth orbit[C]//Computational Mechanics WCCM VI in Conjunction with APCOM'04. Beijing: Tsinghua University, 2004: 498-505.
[13] Liu L D,Bainum P M. Effect of tether flexibility on the tethered shuttle subsatellite stability and control[J]. Journal of Guidance, Control and Dynamics, 1989, 12(6): 866-873.
[14] Chen Y, Cartmell M P. Hybrid sliding mode control for motorised space tether spin-up when coupled with axial oscillation[C]//Proceedings of Advanced Problems in Mechanics. St. Petersburg, Russian: Russian Academy of Sciences, 2009: 1-16.
[15] Chen Y, Cartmell M P. Hybrid fuzzy sliding mode control for motorised space tether spin-up when coupled with axial and torsional oscillation[J]. Astrophysics and Space Science, 2010(326): 105-118.
[16] Chen Y. Dynamical modelling of a flexible motorised momentum exchange tether and hybrid fuzzy sliding mode control for spin-up[D]. Glasgow, Scotland: University of Glasgow, 2009.
[17] Murray C. Continuous earth-moon payload exchange using motorised tethers with associated dynamics[D]. Glasgow, Scotland: University of Glasgow, 2011.
[18] Murray C, Cartmell M P. Moon-tracking orbits using motorized tethers for continuous earth-moon payload exchanges[J]. Journal of Guidance, Control and Dynamics, 2013, 36(2): 567-576.
[19] Liu D, Zhao J. Aero spacecraft dynamics[M]. Harbin: Harbin Institute of Technology Press, 2003: 62-68 (in Chinese). 刘暾, 赵钧. 空间飞行器动力学[M]. 哈尔滨: 哈尔滨工业大学出版社, 2003: 62-68.
[20] Zhao J. Orbital dynamics of spacecraft[M]. Harbin: Harbin Institute of Technology Press, 2011: 42-87 (in Chinese). 赵钧. 航天器轨道动力学[M]. 哈尔滨: 哈尔滨工业大学出版社, 2011: 42-87.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

连续地月转移系统动力学研究与能量分析

Dynamics and energy analysis of continuous cislunar transfer system

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