基于伪谱法的空间绳系组合体最优燃耗离轨研究
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摘要
为了优化空间绳系组合体轨道转移的燃耗,提出一种基于伪谱法求解的包含拖拽、平衡、甩摆三个阶段的绳系组合体最优燃耗离轨方案.首先将全过程离轨的燃耗作为性能指标,采用简化的绳系组合体动力学模型,利用高斯伪谱法求解出拖拽阶段系统状态最优轨迹;其次考虑较复杂的绳系组合体动力学模型,使用模型预测控制方法跟踪拖拽阶段系统状态最优轨迹.仿真结果表明该方法能实现主动星安全、高效,并以最低燃耗地将目标星转移到目标轨道.
To optimize the fuel consumption of deorbit of space tethered system( TSS),a TSS deorbit scheme based on pseudo-spectral method with minimal fuel consumption is proposed,which concludes three phases called dragging,equilibrium and swinging. Firstly,the fuel consumption of the whole process is taken as the cost function. A simplified TSS dynamic model is used to derive the optimal state trajectories of the TSS in the dragging phase based on Gauss pseudo-spectral method. Secondly,a more accurate TSS dynamic model is adopted and the model predictive control method is used to track the reference optimal state trajectories. Numerical simulation results show that the scheme can make the tug transfer the target satellite to the target orbit safely,efficiently and with minimum fuel consumption.
To optimize the fuel consumption of deorbit of space tethered system( TSS),a TSS deorbit scheme based on pseudo-spectral method with minimal fuel consumption is proposed,which concludes three phases called dragging,equilibrium and swinging. Firstly,the fuel consumption of the whole process is taken as the cost function. A simplified TSS dynamic model is used to derive the optimal state trajectories of the TSS in the dragging phase based on Gauss pseudo-spectral method. Secondly,a more accurate TSS dynamic model is adopted and the model predictive control method is used to track the reference optimal state trajectories. Numerical simulation results show that the scheme can make the tug transfer the target satellite to the target orbit safely,efficiently and with minimum fuel consumption.
引文
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[10]RAO A V,BENSON D A,DARBY C.Algorithm 902:Gpops,a matlab software for solving multiple-phase optimal control problems using the Gauss Pseudospectral method[J].ACM Transactions on Mathematical Software(TOMS),2010,37(2).
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[12]ZHONG R,XU S J.Orbit-transfer control for TSS using Direct collocation method[J].Acta Aeronautica et Astronautica Sinica,2010,31(3):572-578.
[2]BREMEN A S.Robotic geostationary orbit restorer(ROGER)phase:a final report[J].ESA,2003:56-69.
[3]LIU H T,YANG L P,ZHANG Q B,et al.An investigation on tether-tugging de-orbit of defunct geostationary satellites[J].Science China Technological Science,2012,55(7):2017-2019.
[4]ZHONG R,ZHU Z H.Optimal control of nanosatellite fast deorbit using electrodynamics tether[J].Journal of Guidance,Control,and Dynamics,2014,37(4):1182-1194.
[5]VALLADO D A.Fundamentals of astrodynamics and applications[M].Springer Science&Business Media,2001:572-578.
[6]ZHONG R,ZHU Z H.Long-term libration dynamics and stability analysis of electrodynamic tethers in spacecraft deorbit[J].Journal of aerospace engineering,2014,27(5):13.
[7]Inter-Agency Space Debris Coordination Committee.IADC space debris mitigation guidelines[J].IADC-02-01 Revision,2007,1.
[8]JOSSELYN S,ROSS I M.Rapid verification method for the trajectory optimization of reentry vehicles[J].Journal of Guidance,Control,and Dynamics,2003,26(3):505-508.
[9]HUNTINGTON G T,RAO A V.Optimal reconfiguration of spacecraft formations using the Gauss pseudospectral method[J].Journal of Guidance,Control,and Dynamics,2008,31(3):689-698.
[10]RAO A V,BENSON D A,DARBY C.Algorithm 902:Gpops,a matlab software for solving multiple-phase optimal control problems using the Gauss Pseudospectral method[J].ACM Transactions on Mathematical Software(TOMS),2010,37(2).
[11]BENSON D.A Gauss Pseudospectral transcription for optimal control[D].USA:Massachusetts Institute of Technology,2005.
[12]ZHONG R,XU S J.Orbit-transfer control for TSS using Direct collocation method[J].Acta Aeronautica et Astronautica Sinica,2010,31(3):572-578.