航天控制
航天控製
항천공제
AEROSPACE CONTROL
2010年
1期
17-20,69
,共5页
近地轨道%卫星编队飞行%平均轨道根数%J_2摄动%大气阻力摄动
近地軌道%衛星編隊飛行%平均軌道根數%J_2攝動%大氣阻力攝動
근지궤도%위성편대비행%평균궤도근수%J_2섭동%대기조력섭동
Low earth orbit%SateUite formation flying%Mean orbit element%J_2 perturbation%Drag pertur-bation
针对J_2摄动和大气摄动导致低轨编队卫星构型破坏的情况,基于高斯摄动方程给出了以平均轨道根数为被控制量的脉冲控制模型.利用法向脉冲调整轨道倾角和升交点赤经偏差,在轨道上2个位置施加径向和切向脉冲调整其余轨道根数偏差从而修正卫星编队构形.最后通过数值仿真验证了算法的简单性、有效性.
針對J_2攝動和大氣攝動導緻低軌編隊衛星構型破壞的情況,基于高斯攝動方程給齣瞭以平均軌道根數為被控製量的脈遲控製模型.利用法嚮脈遲調整軌道傾角和升交點赤經偏差,在軌道上2箇位置施加徑嚮和切嚮脈遲調整其餘軌道根數偏差從而脩正衛星編隊構形.最後通過數值倣真驗證瞭算法的簡單性、有效性.
침대J_2섭동화대기섭동도치저궤편대위성구형파배적정황,기우고사섭동방정급출료이평균궤도근수위피공제량적맥충공제모형.이용법향맥충조정궤도경각화승교점적경편차,재궤도상2개위치시가경향화절향맥충조정기여궤도근수편차종이수정위성편대구형.최후통과수치방진험증료산법적간단성、유효성.
Based on Gauss perturbation, impulsive control model for formation keeping is put forward with regard to the problem that LEO satellites formation could be destroyed under J_2 perturbation and atmospheric drag perturbation. In order to correct errors of formation keeping, firstly, the inclination and longitude as-cending node is adjusted by exerting an impulsive control effort along the normal direction. Then, the other elements errors are amended by exerting impulsive control efforts from two positions along tangent and radial directions simultaneously. Finally, the simplicity and effectiveness of the impulsive control algorithm is veri-fied by mathematical simulation results.
