上海航天
上海航天
상해항천
AEROSPACE SHANGHAI
2012年
4期
27-30,72
,共5页
近地轨道卫星%变结构控制%大气阻力%编队构型
近地軌道衛星%變結構控製%大氣阻力%編隊構型
근지궤도위성%변결구공제%대기조력%편대구형
Low earth satellite%Variable structure control%Atmosphere drag%Formation configuration
分析了大气阻力对近地轨道卫星轨道参数的影响,用变结构控制设计了基于大气阻力的编队构型沿航迹方向的控制。将中心的漂移距离和编队卫星的面质比之差作为输入量,设计滑模面进行编队控制,用极限环方式消除了在滑膜面附近的频繁切换。仿真结果验证了该控制律的正确性。
分析瞭大氣阻力對近地軌道衛星軌道參數的影響,用變結構控製設計瞭基于大氣阻力的編隊構型沿航跡方嚮的控製。將中心的漂移距離和編隊衛星的麵質比之差作為輸入量,設計滑模麵進行編隊控製,用極限環方式消除瞭在滑膜麵附近的頻繁切換。倣真結果驗證瞭該控製律的正確性。
분석료대기조력대근지궤도위성궤도삼수적영향,용변결구공제설계료기우대기조력적편대구형연항적방향적공제。장중심적표이거리화편대위성적면질비지차작위수입량,설계활모면진행편대공제,용겁한배방식소제료재활막면부근적빈번절환。방진결과험증료해공제률적정학성。
The effect of the atmosphere drag on the orbit parameters of the low earth satellite was analyzed in this paper. The control of the in-track drift of the formation configuration was designed by using various control method based on the atmosphere drag. The drift if the center and the difference of the area-mass ratio between the formation satellites were served as the input to design the sliding mode for controlling the formation. The problem that the structure switched frequently was solved by designing margin circle： The simulation results showed that this control law was correct.
