给出了形成星座的脉冲式变轨的基本原理；
The paper gives the principle of impulse transfer for making constellation.
导出了空间交会中多脉冲变轨的一般算法。
A general solution for multi impulse maneuvers in space rendezvous is derived.
最后对多脉冲变轨与双脉冲变轨进行了比较。
Finally, a comparison between two impulse and multi impulse maneuvers is introduced.
并且它的变轨周期是10万年，从近似的圆变得更椭圆。
And it shifts its orbit from being roughly circular to more elliptical on a 100,000-year cycle.
针对小卫星星座，进行星座发射中的最优脉冲式变轨研究。
In this paper, thinking of small satellite constellation, optimal impulse orbit transfer is studied for constellation launching.
从卫星系统的角度看，主要风险在于变轨能否精确和迅速地完成。
Judging from the satellite system, the major risk is whether the orbit changes can be completed precisely and promptly.
基于最优控制理论，将一个最优变轨问题转化成一个两点边值问题。
The optimal transfer problem is converted into Two-Point Boundary Value problem based on optimal control theory.
由搭载方式发射的小卫星，通常需要变轨才能进入自己的工作轨道。
Small satellite launched together with a main satellite often needs orbital maneuvers to enter its working orbit.
同时，它可以取代化学燃料火箭来帮助卫星从近地轨道变轨至静止轨道。
In the meantime, it could replace chemical rockets for pushing satellites from low Earth orbit to geostationary orbit.
根据相对轨道要素的变轨机动控制，进行编队飞行卫星群构型的初始化。
The configuration initialization of satellite formations is carried out based on orbit maneuver control...
特别是由推力协同变轨所导致的奇异最优控制问题到目前尚没有完全解决。
Up to now the singular optimal control problems in the thrust synergetic orbital transfer have not been completely solved.
基于虚拟目标点和椭圆弹道理论，提出了一种在自由段机动变轨的新方法。
Based on the virtual target point and the ellipse trajectory theory, a new maneuver method in the free - flight phase is presented.
文中基于卫星相对运动状态转移方程，推出了星座双脉冲式变轨控制的理论解；
In this paper, thinking of three-satellite constellation, optimal impulse orbit transfer is studied for constellation launching.
文章研究了空间交会远程导引阶段综合变轨问题的变轨策略方法和实用理论模型。
This paper presents the approaches and practical theoretical models on synthetic orbit maneuver during long distance guidance stage of space rendezvous.
推力有限时，地球同步轨道卫星在远地点变轨的弧段很长，会导致较多的燃料消耗。
In the case of finite thrust apogee maneuver for the geostationary satellite, the fuel consumption increases due to the long burn arc.
分别利用了共轭函数法与直接配置和非线性规划方法对异面最优变轨问题进行了求解。
Adjoint function algorithms and direct collocation and nonlinear programming methods are applied to resolve the non-coplanar optimal orbit transfers problem.
该导引律能同时满足脱靶量要求和末端落角要求，保证了大空域变轨弹道的各段弹道平滑衔接。
This guidance law can satisfy the requirements of miss distance and terminal Angle, thus it guarantees that all phases of the large-space variable trajectory smoothly link.
在把MUOS卫星变轨到最终位置以及执行任务寿命期内的在轨机动性重新配置上，该推进系统是很关键的。
The propulsion subsystem is essential for maneuvering the MUOS satellite during transfer orbit to its final location as well as conducting on-orbit repositioning maneuvers throughout its mission life.
不管怎样，那样的一次变轨只能把地球的生命延长仅几十亿年。之后，这颗行星最终还会处于冰冷和阴暗之中。
Anyway, such a maneuver would prolong the viability of the Earth for only a few billion years. After that, the planet would be stranded in the cold and dim.
研究者发现司机把车撞进路灯杆或变轨时与其他汽车相撞这种事故在夏天的发生率更高，因为夏天穿的比较少。
Researchers found drivers crash their cars into lamp posts or shunt other vehicles more in the summer when men and women are wearing less clothing.
结合气动谐振点火器进行头部设计的氢氧变轨火箭发动机是一项新颖化学火箭推进技术，尤其适于空间站应用。
Orbit maneuver hydrogen-oxygen thruster based on gas dynamic resonance igniter is a novel chemical propulsion technology especially prospective in space station application.
通过美军收集的跟踪数据显示，SJ-12自6月发射升空后进行了多次变轨，并逐渐的调整到SJ-06F的轨道上。
According to tracking data collected by the US military, SJ-12 has performed multiple manoeuvres since its launch in June, slowly shifting its orbit to match that of SJ-06F.
为研究轻型、可靠、环保的空间站机动变轨发动机，在氢氧液体火箭发动机头部设计中引入了新型气动谐振点火技术。
To develop light, reliable, sanitary space station maneuverable orbital transfer thruster, the novel gas dynamic resonance ignition method was applied.
利用该算法进一步考虑初始时刻反卫星武器与目标卫星的位置关系和变轨消耗能量之间的关系，同时给出了发射窗口的求解算法。
Moreover, the relation of initial launch condition and energy consumption is discussed in this paper, and the determination of launch window is given.
为了实现反舰导弹的大空域变轨，提出了一种三维虚拟目标比例导引律。该导引律利用简单的控制指令就能控制导弹完成复杂的大空域变轨。
In order to realize large airspace transfer orbital trajectory of an anti-ship missile, a 3-dimensional virtual target's proportional navigation guidance (PNG) law is proposed.
本文论述了车桥及车轨时变系统横向振动计算中存在的根本问题。
In this paper, the fundamental problems in the calculation of transverse vibration of train bridge and train track time varying system are expounded.
本文论述了车桥及车轨时变系统横向振动计算中存在的根本问题。
In this paper, the fundamental problems in the calculation of transverse vibration of train bridge and train track time varying system are expounded.
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