本文關(guān)鍵詞： 繩系系統(tǒng) 軌道轉(zhuǎn)移 擺動(dòng)特性 動(dòng)力學(xué) 張力控制　出處：《北京航空航天大學(xué)學(xué)報(bào)》2016年04期 　論文類型：期刊論文

【摘要】：考慮了任務(wù)星與廢星的姿態(tài)運(yùn)動(dòng)以及系統(tǒng)組合體的面內(nèi)外姿態(tài)運(yùn)動(dòng),建立了繩系拖拽離軌系統(tǒng)動(dòng)力學(xué)與控制模型,以切向常值推力下繩系拖拽軌道轉(zhuǎn)移為任務(wù)過程,分析了任務(wù)星在噴氣和零動(dòng)量輪的限制姿態(tài)反饋控制條件下飛行時(shí),廢星姿態(tài)擺動(dòng)、系統(tǒng)組合體面內(nèi)外擺動(dòng)和任務(wù)星姿態(tài)運(yùn)動(dòng)的規(guī)律及相互影響關(guān)系。采用留位和阻尼控制相結(jié)合的系繩張力復(fù)合控制方法,并結(jié)合任務(wù)星姿態(tài)控制,確保繩系拖拽轉(zhuǎn)移安全平穩(wěn)進(jìn)行。仿真結(jié)果表明:常值推力下繩系拖拽軌道轉(zhuǎn)移時(shí),牽掛點(diǎn)偏置誘發(fā)的廢星姿態(tài)周期性擺動(dòng)會(huì)激發(fā)繩系組合體的面內(nèi)外同頻率高階擺動(dòng),星體姿態(tài)運(yùn)動(dòng)是任務(wù)星姿態(tài)擾動(dòng)力矩產(chǎn)生的主要因素;采用張力復(fù)合控制可有效消除廢星姿態(tài)擺動(dòng)并保持星間相對距離,結(jié)合任務(wù)星姿態(tài)控制,可實(shí)現(xiàn)離軌過程的平穩(wěn)與安全,大幅減少任務(wù)星的姿控能耗。
[Abstract]:Considering the attitude motion of the mission star and the spent star, as well as the in-plane attitude motion of the system combination, the dynamics and control model of the towing and deorbiting system of the rope system is established. With tangential constant thrust drag and drop orbit transfer as the mission process, the wobble of the spent satellite attitude is analyzed when the mission star is flying under the condition of limited attitude feedback control of jet and zero momentum wheel. The system combines the law and the mutual influence relation of the decent internal and external swing and the attitude motion of the mission star. The compound control method of the tether tension combined with the stay and damping control is adopted and the attitude control of the mission star is combined with the control of the attitude of the mission star. The simulation results show that the transfer of towing track under constant thrust is carried out safely and smoothly. The periodic wobble of the attitude of the abandoned star induced by the bias of the concern point will excite the high-order oscillations in and out of the plane of the rope system assembly, and the attitude motion of the star is the main factor to produce the disturbance torque of the attitude of the mission star. Combined with the attitude control of the mission star, the stability and safety of the deorbiting process can be realized, and the energy consumption of the attitude control of the mission star can be greatly reduced by using the tension compound control method to effectively eliminate the wobble of the spent star attitude and maintain the relative distance between the satellites.
【作者單位】： 北京航空航天大學(xué)宇航學(xué)院;
【基金】：國家自然科學(xué)基金(11572016)~~
【分類號】：V412.4;V414
【正文快照】： 網(wǎng)絡(luò)出版地址:www.cnki.net/kcms/detail/11.2625.V.20151009.1547.006.html引用格式:趙國偉,張興民,唐斌,等.空間繩系拖拽系統(tǒng)擺動(dòng)特性與平穩(wěn)控制[J].北京航空航天大學(xué)學(xué)報(bào),2016,42(4):694-702.ZHAO G W,ZHANG X M,TANG B,et al.Properties of pendulum motion of tether tug

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