spacecraft maneuver 中文意思是什麼
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The basis of dynamics and simulation includes the iterative flyout angle algorithm to the solutions to lambert problem and battin ' s universal conic section state extrapolate method. then spacecraft ' s orbit roots, maneuver impulse and maneuver time are discussed as the following four part : first of all, the chaser ' s one orbit roots is selected as a variable to simulate its influence to the large scale orbital maneuver. the research reveals fact that the orbit roots both of chaser and target should be close to each other to achieve better maneuver and rendezvous " ability, moreover, the best orbit maneuver and rendezvous occurs when both chaser and target ' s initial phase angle are equal
為了研究了交會機動中追蹤器和目標器的軌道根數、機動時限和機動能耗等因素對交會機動的影響，模擬和分析分為以下四個部分:首先，研究了追蹤器軌道單個參數為變量情況下兩航天器大范圍交會機動問題，研究表明，追蹤器的變化參量與目標器相應的參量在接近的情況下可以獲得良好的交會機動特性，而對于兩航天器軌道共面的情況下，初始相位角相等時則獲得最佳的機動效果。 -
This paper mainly discuss the problem of method and policy of spacecraft ' s large scale orbital maneuver
論文研究了航天器大范圍軌道機動的方法與策略。 -
Aiming at the fact that more debris collision risks are to the low earth orbit spacecraft in the getting worse debris environment, this paper gives a set of feasible debris early warning method and maneuver strategy, by means of which spacecraft can adopt orbit maneuver, evade dangerous objects so as to improve viability under the control of ground command and control center
本論文的研究是應對日益惡化的空間碎片環境對近地航天器造成的碰撞風險，提出一套可行的碎片預警方法和規避策略，使航天器在必要時刻，通過地面的指控，採取主動的軌道機動，躲避危險物體，從而提高生存能力。 -
Active vibration control of flexible spacecraft during attitude maneuver
撓性航天器姿態機動的主動振動控制 -
By means of confirming the geometry relation between the spacecraft and dangerous object, estimated the collisional velocity, the location of collisional point, collisional degree, established the maneuver rule
通過確定航天器與危險目標的幾何關系，估算碰撞速度、碰撞點的位置、碰撞程度，制定了規避準則。 -
Under the requirement of multi - maneuver flight mission, spacecraft sometimes has to perform autonomous navigation by using on - board sensors in a short time
未來多任務航天器往往要執行多次機動飛行，由於地面導航的局限性，需要在較短的時間內對航天器進行自主導航。
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