【摘要】：提出了利用太陽帆進(jìn)行大偏心率伴飛衛(wèi)星軌道控制的方法.伴飛衛(wèi)星圍繞其慣量主軸做角速度恒定的自轉(zhuǎn),其慣量主軸在慣性系內(nèi)指向保持不變.對伴飛衛(wèi)星的控制分為軌道面的控制和軌道面內(nèi)控制兩部分.在控制過程中,優(yōu)先考慮軌道面內(nèi)的控制,在軌道面內(nèi)控制不能進(jìn)行(或者因為幾何原因不能進(jìn)行軌道面內(nèi)控制)時,進(jìn)行軌道面的控制.通過滑膜控制方法(Sliding Mode Control)計算軌道面內(nèi)控制需要的控制力的方向和大小.得到需求的控制力要求后,推算出在控制過程中太陽帆相對于伴飛衛(wèi)星主體的角度解析表達(dá)式.通過控制太陽帆的方向得到所需的不同的控制力.整個控制過程只針對伴飛衛(wèi)星,主星處于自然飛行狀態(tài).最后對于這種控制方法進(jìn)行數(shù)值驗證.在無攝運動狀態(tài)下通過控制系統(tǒng)進(jìn)行伴飛軌道的軌道調(diào)整和誤差消除,在考慮4階非球形引力和第三體引力攝動情況下進(jìn)行伴飛軌道的軌道維持.數(shù)值結(jié)果表明通過這種控制方法伴飛軌道能夠保持軌道誤差小于5 m.
[Abstract]:A method for orbit control of satellite with large eccentricity by using solar sail is presented. The satellite has a constant rotation of angular velocity around its inertial spindle, and the direction of the inertial spindle remains unchanged. The control of the satellite is divided into two parts: the control of orbit surface and the control of orbit plane. In the control process, priority is given to the in-plane control of the track, and when the in-plane control of the track cannot be carried out (or can not be controlled in the track for geometric reasons), the control of the track surface is carried out. The direction and magnitude of the control force needed for the in-plane control of the track are calculated by the synovial control method (Sliding Mode Control). After the required control force is obtained, the analytical expression of the angle of the solar sail relative to the satellite body during the control process is deduced. Different control forces are obtained by controlling the direction of the solar sail. The whole control process is only for the companion satellite, and the host satellite is in a natural flight state. Finally, the numerical verification of the control method is carried out. The orbit adjustment and error elimination of the tracking orbit are carried out by the control system in the state of non-perturbation motion, and the orbit maintenance of the tracking orbit is carried out considering the perturbation of the fourth order non-spherical gravity and the third body gravity. The numerical results show that the trajectory error can be kept less than 5 m by this control method.
【作者單位】： 中國科學(xué)院紫金山天文臺;中國科學(xué)院空間目標(biāo)與碎片觀測重點實驗室;中國科學(xué)院大學(xué);
【基金】：國家自然科學(xué)基金項目(11125315,11173056)資助
【分類號】：P173.1

【參考文獻(xiàn)】

相關(guān)期刊論文 前1條

1 胡壽村;趙玉暉;季江徽;侯錫云;;攝動分析法在小推力軌道優(yōu)化中的應(yīng)用[J];天文學(xué)報;2015年02期

【二級參考文獻(xiàn)】

相關(guān)期刊論文 前7條

1 李俊峰;蔣方華;;連續(xù)小推力航天器的深空探測軌道優(yōu)化方法綜述[J];力學(xué)與實踐;2011年03期

2 蔣方華;陳楊;劉躍聰;寶音賀西;李俊峰;;2010年國際深空探測軌道優(yōu)化競賽的清華大學(xué)解法[J];力學(xué)與實踐;2011年03期

3 沈紅新;羅亞中;李海陽;;第四屆全國空間軌道設(shè)計競賽冠軍團(tuán)隊解法[J];力學(xué)與實踐;2013年01期

4 路毅;李濟(jì)生;李恒年;車征;;基于星歷匹配法的載人小行星探測軌跡優(yōu)化問題求解[J];力學(xué)與實踐;2014年02期

5 彭超;高揚;;近圓參考軌道衛(wèi)星編隊洛侖茲力控制[J];力學(xué)學(xué)報;2012年05期

6 林厚源;趙長印;;無需初值猜測的間接法小推力軌道設(shè)計[J];天文學(xué)報;2012年03期

7 季江徽;;開展小行星彗星深空探測的科學(xué)意義和啟示[J];國防科技工業(yè);2011年04期

，

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