Space growth studies of Ce-doped Bi12SiO20 single crystal

Ce-doped Bi12SiO20 (BSO) single crystal was grown on board of the Chinese Spacecraft-Shenzhou No. 3. A cylindrical crystal, 10 mm in diameter and 40 mm in length, was obtained. The morphology of crystals is significantly different for ground- and space-grown portions. The space- and ground-grown crystals have been characterized by Cc concentration distribution, X-ray rocking curve absorption spectrum and micro-Raman spectrum. The results show that the quality of Ce-doped BSO crystal grown in space is more homogeneous and more perfect than that of ground grown one. (C) 2004 Published by Elsevier B.V.

Growth of CeO2 : Bi12SiO20 crystals in multi-position furnace(II) - Space growth experiment

Ce-doped Bi12SiO20 single crystal with size of phi10mm x 40mm was successfully grown in space on board of the spacecraft Shenzhou No.3. The surface morphology of space-grown crystal is different from that of ground-grown crystal The space- and ground-grown crystals were measured by X-ray rocking curves, absorption spectra and micro-Raman spectra. The results show that the quality of Ce-deped crystal grown in space is better than that of the ground-grown one. The effect of doping on optical properties of BSO grown in space is evident in comparison with the ground-grown crystal.

Comparison of space- and ground-grown Ce: Bi12SiO20 single crystals

Ce doped Bi12SiO20 single crystals were grown either on board of the Chinese Spacecraft-Shenzhou No.3 (SZ-3) or on the ground at the same conditions with the exception of microgravity. The surface morphology of crystals clearly showed significant differences between the space- and ground-grown portions. The space- and ground-grown crystals have been measured by X-ray rocking curve, Cc concentration distribution in growth direction, dislocation density, absorption spectrums. These results show that the compositional homogeneity and structural perfection of Ce doped crystal grown in space are obviously improved.

Satellite Constellation Design for Complex Coverage

Most traditional satellite constellation design methods are associated with a simple zonal or global, continuous or discontinuous coverage connected with a visibility of points on the Earth's surface. A new geometric approach for more complex coverage of a geographic region is proposed. Full and partial coverage of regions is considered. It implies that, at any time, the region is completely or partially within the instantaneous access area of a satellite of the constellation. The key idea of the method is a two-dimensional space application for maps of the satellite constellation and coverage requirements. The space dimensions are right ascension of ascending node and argument of latitude. Visibility requirements of each region can be presented as a polygon and satellite constellation as a uniform moving grid. At any time, at least one grid vertex must belong to the polygon. The optimal configuration of the satellite constellation corresponds to the maximum sparse grid. The method is suitable for continuous and discontinuous coverage. In the last case, a vertex belonging to the polygon should be examined with a revisit time. Examples of continuous coverage for a space communication network and of the United States are considered. Examples of discontinuous coverage are also presented.

一种空间飞行器编队重组的轨道优化方法

现有的空间飞行器编队重组的轨道规划方法在求解能量最优策略时,都预先给定了变轨花费的时间,但没有说明给定的时间是怎么选择的。将空间飞行器主从编队重组的轨道规划视为一个多目标优化问题,提出了一种小生境进化算法。该方法通过使用特定的染色体表示方法和进化算子,能有效的搜索到飞行器编队重组轨道规划问题的时间-能量前沿,并引入等值分享法保证优秀个体具有较大的选中概率和前沿的多样性。该方法能同时提供多种变轨方案,编队飞行的任务制定者从而可以根据实际应用情况选择最合适的方案。仿真结果表明了该方法的正确性。

一种基于进化计算的空间飞行器编队重构轨道规划方法

基于进化算法提出了一种两层结构的空间飞行器编队重构的轨道规划算法,高层算法通过优化构型映射来优化编队的总燃耗,实现全局规划并确保飞行器之间保持一定的安全距离以避免相互碰撞;低层规划算法采用Chebyshev多项式逼近控制变量空间,为每颗飞行器规划满足约束条件的最优轨道。该方法充分利用了编队的分布式结构,由各飞行器并行实现各自的轨道规划,能有效解决大型编队的轨道规划问题。仿真结果表明了该方法的有效性。

带燃料均衡的空间多飞行器编队重构的轨道规划方法

航天任务需求的多样化对空间多飞行器编队重构的轨道规划问题不仅提出了燃料或时间最优的要求,还提出了燃料和时间最优以及燃料均衡的要求。将带燃料均衡的多飞行器编队重构的轨道规划建模为一个多目标优化问题,通过将进化计算与问题领域的知识相结合,提出了一种基于小生境进化算法的最优轨道规划方法。该方法能从变轨时间、燃料消耗和燃料消耗方差三方面分别评价一个变轨方案的最优性,并且一次规划能够提供多个Pareto最优变轨方案。仿真结果证明了该方法的正确性和有效性,还揭示了编队重构轨道规划问题的三个优化目标之间的关系,对于制定任务计划具有重要的参考价值.

High-accuracy same-beam VLBI observations using Shanghai and Urumqi telescopes

The same-beam VLBI observations of Rstar and Vstar, which were two small satellites of Japanese lunar mission, SELENE, were successfully performed by using Shanghai and Urumqi 25-m telescopes. When the separation angle between Rstar and Vstar was less than 0.1 deg, the differential phase delay of the X-band signals between Rstar and Vstar on Shanghai-Urumqi baseline was obtained with a very small error of 0.15 mm rms, which was reduced by 1-2 order compared with the former VLBI results. When the separation angle was less than 0.56 deg, the differential phase delay of the S-band signals was also obtained with a very small error of several mm rms. The orbit determination for Rstar and Vstar was performed, and the accuracy was improved to a level of several meters by using VLBI and Doppler data. The high-accuracy same-beam differential VLBI technique is very useful in orbit determination for a spacecraft, and will be used in orbit determination for Mars missions of China Yinghuo-1 and Russia Phobos-grunt.

Chemical etching of a GaSb crystal incorporated with Mn grown by the Bridgman method under microgravity conditions

A GaSb crystal incorporated with Mn has been grown by the Bridgman method on the Polizon facility onboard the FOTON-M3 spacecraft. Structural defects and growth striations have been successfully revealed by the chemical etching method. By calculating various parameters of the convection, the striation patterns can be explained, and the critical value of the Taylor number, which characterizes the convective condition of the rotating magnetic field induced azimuthal flow, was shown. The stresses generated during crystal growth can be reflected by the observations of etch pit distribution and other structural defects. Suggestions for improving the space experiment to improve the quality of the crystal are given.

空间飞行器编队重构建模与规划方法研究

编队重构是实现空间飞行器编队飞行的一项关键技术，也是自动导航和控制的重要研究领域，无论在理论研究还是实际应用上都具有重大意义。本论文针对空间飞行器编队重构问题展开了深入的研究：（1）编队重构建模；（2）空间飞行器多轨道规划；（3）空间飞行器时间-燃耗的轨道规划；（4）编队重构的协同规划；（5）考虑燃料均衡的编队重构规划。围绕编队重构建模问题，本论文在分析其特点的基础上，完善了传统的单目标优化模型，加入了现有研究通常忽略的发动机推力的精度约束，提高了模型精度以降低控制反馈误差。另外，还根据航天任务的特点，从多目标优化的角度建模了问题，优化的性能指标包括变轨时间、编队的总燃料消耗和飞行器间的燃料均衡。在多轨道规划的研究中，作者基于进化计算和参数优化方法，提出了一种空间飞行器多轨道规划算法。通过将可行轨道按其空间分布分类，并采用一种多轨道保持技术，使新提出的算法能够获得多条在空间中分布较为离散的最优/近优轨道，并可以方便地根据环境和任务要求设定希望获得的轨道之间的差异。该算法充分利用了编队飞行相对动力学方程的解耦性，简化了问题，提高了计算速度，并使最终轨道的选择更加灵活多样。作者还针对空间飞行器的变轨时间与燃料消耗的关系问题展开了研究，基于小生境进化算法，提出了一种时间-燃耗的轨道规划方法。该方法采用一种变长实值染色体编码方式和特定的种群初始化方法，能使生成的轨道满足各种约束条件，并引入等值分享法保证优秀个体具有较大的选中概率和前沿的多样性。实验表明，该算法能有效地搜索到飞行器变轨的时间-燃耗前沿，一次规划生成多个Pareto最优解，为任务制定者选择最合适的变轨方案提供可靠的依据。在编队的协同规划方面，通过分解空间飞行器编队重构问题，并与协同进化的思想相结合，提出了一种两层结构的飞行器编队重构规划算法。高层算法通过优化构型映射来优化编队的总燃料消耗，实现全局规划并确保飞行器之间保持一定的安全距离以避免相互碰撞；低层规划算法采用多轨道规划方法为各飞行器规划满足约束条件的轨道。该算法不仅实现了多颗飞行器的轨道子种群间的协同进化，还实现了高、低层规划结果的协同进化。由于利用编队的分布式结构实现了并行计算，该算法能解决大型编队重构的协同规划问题。虽然给出的最优解是唯一的，但在规划过程中为各飞行器都生成了多条散布在空间中的轨道，提供了可替换解以保证编队重构任务的顺利执行。最后本论文从多目标优化的角度建模了带燃料均衡的多飞行器编队重构规划问题，初步研究了变轨时间、燃料消耗和飞行器间的燃料均衡三个重要指标之间的关系。通过将进化计算与问题领域的知识相结合，提出了一种最优轨道规划方法，能从上述三个指标的角度分别评价一个变轨方案的最优性，并且计算量较小，一次规划能提供多个最优解决方案，能用于实际规划之前进行简单的估算，十分适合方案设计阶段应用。

基于复合喷气压电驱动器的柔性机械臂振动控制

空间机器人和大型柔性空间结构在航天器调姿、变轨、外部扰动的情况下将引起振动问题,其低频大幅值振动将持续很长时间,这将影响航天器系统的稳定性和控制精度。为了快速抑制低频大幅值振动及残余振动,提出采用复合可控反作用力幅值的喷气式驱动和压电陶瓷驱动方案进行振动控制。进行基于复合控制的柔性臂系统动力学建模并给出控制算法。设计并建立柔性机械臂试验平台,构建气动驱动控制回路及压电驱动控制回路。进行基于压电陶瓷驱动器、喷气式驱动器及复合喷气和压电驱动器的柔性臂大幅值低频模态振动控制的几种方法试验比较研究。试验结果表明,采用的控制方案和方法既可以快速地抑制柔性机械臂统的低频大幅值振动,又明显地同时抑制高频和低频小幅值残余振动。

基于Stewart平台六维力传感器的分区静态标定方法

基于Stewart平台的六维力传感器具有结构紧凑、刚度大、量程宽等特点,它在工业机器人、空间站对接等领域具有广泛的应用前景。好的标定方法是正确使用传感器的基础。由于基于Stewart平台的六维力传感器是一个复杂的非线性系统,所以采用常规的线性标定方法必将带来较大的标定误差从而影响其使用性能。标定的实质是,由测量值空间到理论值空间的映射函数的确定过程。由函数逼近理论可知,当只在已知点集上给出函数值时,可用多项式或分段多项式等较简单函数逼近待定函数。基于上述思想,本文将整个测量空间划分为若干连续的子测量空间,再对每个子空间进行线性标定,从而提高了整个测量系统的标定精度。实验分析结果表明了该标定方法有效。

空间对接缓冲试验台对接环重力平衡技术

在空间对接机构地面缓冲实验平台上,为了模拟空间失重状态,研制了一种高精度、高响应速度的主动对接环重力平衡装置。介绍了对接环重力平衡装置的机构原理。对对接过程随动装置的随动性对系统的干扰进行了详细分析。进行了重力平衡器相关实验,从实验数据和理论分析可以得出:所设计的重力平衡装置完全满足对摩擦阻力和惯性阻力设计指标的要求,重力平衡达到1.1%的精度。

Shaping Inputs to Reduce Vibration in Flexible Space Structures

Future NASA plans to launch large space strucutres solicit the need for effective vibration control schemes which can solve the unique problems associated with unwanted residual vibration in flexible spacecraft. In this work, a unique method of input command shaping called impulse shaping is examined. A theoretical background is presented along with some insight into the methdos of calculating multiple mode sequences. The Middeck Active Control Experiment (MACE) is then described as the testbed for hardware experiments. These results are shown and some of the difficulties of dealing with nonlinearities are discussed. The paper is concluded with some conclusions about calculating and implementing impulse shaping in complex nonlinear systems.