spacecraft transfer

Application of the Multi-objective Evolutionary Algorithm in Midcourse Correction of Spacecraft Transfer Orbit

多目标进化算法在航天器转移轨道中途修正中的应用

By building the LEO satellite network, it is easy for spacecraft to transfer and share data. However the network access method is one of challenges of the LEO satellite network.

通过建设LEO卫星网，容易实现航天器的数据传输与共享，但是航天器的网络接入是研究难点之一。

Spacecraft needs not only transfer data to the ground, but also share the information with each other.

航天器不仅需要将数据实时地传输到地面，而且需要与其他航天器实现信息共享。

Robust Attitude Control of Flexible Liquid Spacecraft under Fast Orbit Transfer

轨道快速机动期间的姿态鲁棒稳定控制方法研究

Study on the Minimal Energy Maneuvering Control of a Rigid Spacecraft with Momentum Transfer

刚体航天器的最小能量姿态机动最优控制研究

Long March 3 ( LM-3) is a three-stage launch vehicle, primarily intended for sending spacecraft into Geosynchronous Transfer Orbit with the GTO capacity of l.

“长征三号”运载火箭是三级火箭，主要用于发射地球同步轨道有效载荷，运载能力为1.5吨。

spacecraft Into the geosynchronous transfer orbit speed of 10.25 kilometers requirements/ s;

航天器进入地球同步转移轨道运行所需速度为10.25公里／秒；

Based on the current state of the spacecraft, make the transfer nominal terminal as control target, the Lambert algorithm was used to re-plan the transfer orbit, and impose appropriate controls make the spacecraft entering the transfer orbit.

该方法根据航天器当前状态，以转移终端标称状态为控制目标，采用Lambert算法重新规划转移轨道，并施加合适控制使其进入转移轨道。

Nonlinear control of large-angle attitude maneuvers for flexible spacecraft with angular momentum transfer

具有角动量存贮挠性飞行器大角度姿态机动的非线性控制

Because of the complexity of heat transfer in spacecraft and uncertainty of some input parameters in thermal analysis model, the spacecraft thermal model often requires correction in order to make accurate evaluation of thermal design level and work characteristics of spacecraft.

由于航天器内部换热的复杂性以及热分析模型某些输入参数的不确定性，往往需要对航天器热模型进行修正，以使热分析计算能够较准确地对航天器的运行特性和热设计水平进行评估。

Objective To apply the ground-based transfer experimental results to the spacecraft in micro-gravity.

目的使空间飞行器地面传热实验的结果能够有效地应用到空间 微重力 条件下.

Based on the analysis that thermal radiation is the major heat transfer mode of MTPS during spacecraft entry, the mechanism of coatings is presented and it is discussed that the coating should adopt TiO_2/ SiO_2 stack mode.

在分析热辐射是金属热防护系统在再入过程中主要的传热方式的基础上，介绍了纳米复合材料涂层的工作机理并确定了纳米复合材料涂层采用TiO2/SiO2的叠层方式。