电动力缆绳离轨系统中绳索建模研究

 空间碎片对在轨运行航天器的安全构成重大威胁,使废弃卫星脱离原轨道进入大气层烧毁是减少空间碎片的有效途径。利用导电缆绳与地磁场相互作用产生的洛仑兹力使卫星特别是低地球轨道卫星的轨道高度快速衰减是一种很有应用前景的离轨方式。在研究电动力缆绳离轨的刚性杆模型基础上,建立了更符合电动力缆绳特性的柔索模型,并对刚性杆模型和柔索模型进行仿真。结果表明柔索模型能更精确地体现电动力缆绳的性质。     

空间微小碎片累积作用下材料光学性能退化预示模型适用性研究

航天器在轨服役期间会遭受到大量空间微小碎片和微流星体的撞击作用,其中的微米级粒子将在航天器表面产生大面积砂蚀现象,并使材料或器件功能衰退。文章介绍了NASA空间微小碎片累积损伤材料光学性能退化预示模型并推导了两个预示模型之间的关系。利用ORDEM2000碎片分布模型估算了K8玻璃累积损伤面积。以K8玻璃为例,对比研究了两个预示模型的适用性。结果表明,当航天器外表面损伤程度小于40%,可利用Canoon模型评价和预示材料光学性能退化规律;当航天器外表面损伤程度大于40%,需利用Mirtich模型评价和预示材料光学性能退化规律。     

ISO空间碎片相关标准的研究现状

对国际标准化组织（ISO）正在拟定的空间碎片标准进行了综述,其中包含1个DIS标准、4个CD标准、3个WD标准和5个NWIP标准。这些标准与航天器的系统设计有着直接关系,尤其关系到航天器任务后的处置,希望引起国内航天器研制单位和相关用户的关注。     

美国云和气溶胶星载激光雷达综述

气溶胶的探测,尤其是全球范围内气溶胶的探测,不仅对预测未来气候的变化有重要帮助,而且可以对遥感图像的大气校正提供重要大气参数,而星载激光雷达则是实现全球气溶胶探测的最有效的手段。美国是星载激光雷达的先行者,在气溶胶探测方面,它先后实施了LITE和CALIPSO两项计划。LITE试验的成功,验证了天基激光雷达的可行性,而CALIPSO上激光雷达CALIOP的在轨正常运行,则实现了星载激光雷达的应用。文章着重介绍和评述了美国云和气溶胶星载激光雷达的发展、收发装置以及观测结果等。     

空间堆核动力技术选择研究

目前,基于太阳能、化学能的空间电源与空间推进技术,其技术能力的发展已接近极限状态,未来亟需开发基于核能的先进空间动力技术。针对低成本空间轨道运输、高功率载荷航天器、深空探测器、行星表面探测与开发等应用场景,以空间堆核电源为重点,分析了国际发展现状和未来航天需求,分别针对大功率(100 kWe～1 MWe)和小功率(1 kWe～10 kWe)应用需求,提出了技术主导方案,围绕主导技术方案梳理了关键技术,为我国空间堆核动力技术发展规划和预先研究提供参考。     

Finite-time composite guidance law with input constraint and dynamics compensation

Guidance laws are proposed for a near space interceptor with on–off type thrust as output. The target-interceptor engagement kinematics is integrated with the first-order dynamics of thruster to design guidance laws. The bang-bang type guidance law with linear sliding mode is proposed to deal with thruster dynamics, and the sufficient condition for finite time convergence is rigorously proved based on the finite-time convergence theory. According to the sufficient condition, a sliding mode guidance law with hysteresis-band switching is introduced to reduce the switching frequency of thruster. Then two guidance laws are combined into a composite guidance law to improve the guidance performance. Simulation results show that the line-of-sight angular rate can converge to a neighborhood of the equilibrium point before the final time of the guidance process, and the composite guidance law has better performance than typical guidance laws.     

Detumbling strategy based on friction control of dual-arm space robot for capturing tumbling target

The rotational motion of a tumbling target brings great challenges to space robot on successfully capturing the tumbling target. Therefore, it is necessary to reduce the target’s rotation to a rate at which capture can be accomplished by the space robot. In this paper, a detumbling strategy based on friction control of dual-arm space robot for capturing tumbling target is proposed. This strategy can reduce the target’s rotational velocity while maintaining base attitude stability through the establishment of the rotation attenuation controller and base attitude adjustment controller. The rotation attenuation controller adopts the multi-space hybrid impedance control method to control the friction precisely. The base attitude adjustment controller applies the dual-arm extended Jacobian matrix to stabilize the base attitude. The main contributions of this paper are as follows: (1) The compliant control method is adopted to achieve a precise friction control, which can reduce the target angular velocity steadily; (2) The dual-arm extended Jacobian matrix is applied to stabilize the base attitude without affecting the target capture task; (3) The detumbling strategy of dual-arm space robot is designed considering base attitude stabilization, realizing coordinated planning of the base attitude and the arms. The strategy is verified by a dual-arm space robot with two 7-DOF (degrees of freedom) arms. Simulation results show that, target with a rotation velocity of 20 (°)/s can be effectively controlled to stop within 30 s, and the final deflection of the base attitude is less than 0.15° without affecting the target capture task, verifying the correctness and effectiveness of the strategy. Except to the tumbling target capture task, the control strategy can also be applied to other typical on-orbit operation tasks such as space debris removal and spacecraft maintenance.     

基于状态空间模型的无刷直流电机控制器设计

在无刷直流时机的位置伺服系统中，采用了基于状态空间模型的优化设计方法，综合出了次优控制器、建立了广义误差系统状态方程，并利用积分罚函数分段一经法处理伺服系统不等式约束的问题，得出了次优控制算法，经仿真证实，有杉该优化方法设计出的伺服系统的稳态跟踪误差为零；稳成输出不受阶跃干扰的影响；并具有期望的瞬态响应特性。     

应急救生系统逃逸动力装置的性能分析

载人航天中，应急救生分系统是火箭一飞船系统的重要组成部分，以联盟号应急救生系统为例介绍了其组成、工作程序并研究分析了逃逸动力装置──主逃逸发动机和控制发动机的性能参数与逃逸飞行弹道特性之间的相互关系；从逃逸弹道设计技术指标出发来选取动力装置的主要性能参数（推力大小及工作时间）。仿真计算得出了有益的结论。     

弱正则空间

本文给出了弱正则空间的定义,并研究了弱正则空间的性质,指出弱正则拓扑是一分离拓扑。