卫星编队相对轨道的分布式估计方法

研究了卫星编队的相对轨道自主确定问题,选择“无线电+激光”的测量方案,为减轻多星编队星间通信量和星上计算量的负担,将状态估计器设计为分布式构型,并利用分布式Schm idt-Kalman滤波算法对编队的相对轨道状态进行估计。仿真结果验证了该导航方案和算法的有效性。     

椭圆轨道编队飞行相对动力学初始化条件

Hill方程在椭圆轨道编队设计中具有一定的局限性,为解决这一问题,将基于Hill方程的圆轨道编队设计方法推广应用于椭圆轨道编队设计中．将T-H方程表示为参考轨道真近点角的显函数形式,推导椭圆轨道编队相对运动的状态转移矩阵．利用椭圆轨道编队相对运动动力学方程有周期解的要求,讨论椭圆轨道编队周期性运动的一般性初始化条件．最后通过数学仿真表明理论推导的正确性．推导的初始化条件可用于椭圆轨道编队队形初始设计或相对运动误差估计．     

三线阵CCD立体测绘卫星像移姿态跟踪补偿研究

介绍了三线阵CCD传感器的成像原理,分析了由于地球自转角速度的存在而产生三线阵CCD传感器像移的机理.在规划姿态跟踪策略的基础上,建立了有效成像面积和姿态机动方式的数学关系,求解关系式最大值以得到像移补偿的姿态跟踪机动策略.最后给出了姿态跟踪过程中的目标姿态和目标姿态角速度变化规律.     

锻锤的振动分析及砧下直接减振研究

本文采用双自由度阻尼振动理论计算锻锤砧座和基础的振动参数,在分析影响锻锤振动响应的重要因素基础上,提出锻锤砧下弹性垫层刚度优化方法和对锻锤基础进行直接减振方向。     

小卫星的安全性及靠性设计

详细论述了小卫星火工品点火控制电路的工作原理,元器件的选择,为防止火工品误炸所采取的各种安全措施及为避免供电接口可能发生的硬件、软件故障所采取的容错、冗余等技术措施。论述了的 小卫星安全性设计及总体电路的可靠性设计经过“北京空间飞行器总体设计部”A、B、C、D4个阶段测试。电测结果表明设计合理,工作正常,太阳电池帆板顺利解锁,达到设计要求。     

航天器交会对接位姿视觉测量迭代算法

针对航天器交会对接过程中利用单目视觉进行相对位姿参数确定问题,利利用由目标航天器上4个非共面设置的特征光标点和追踪航天器上单个CCD相机组成的交会对接航天器单目视觉测量系统,推导了交会对接航天器间相对位姿参数测量的迭代算法,将相对位姿参数求解问题转化为非线性优化问题,在目标航天器像平面空间内推导优化目标函数,利用Levenberg-Marquardt算法求解该非线性优化问题,并选择一解析算法以快速求解迭代初值,仿真结果表明算法的有效性和可靠性,能够满足交会对接航天器测量精度要求。     

Establishment of antenna membrane states FEM on analogue method

On the basis of choosing the basic element as the bar and choosing the basic mesh as the triangle as well as supposing the conditions of the element, the membrane states of an antenna reflector were researched by the analogue method, because the membrane effect was not omitted during the ending deployment process of the radial rib antenna. The expressions of the bar element＇ s section area and density were obtained, while the ex- pression of the stress state during the ending deployment process of antenna was attained. During the establish- ment process of the analogue method, the analysis method of the net shell structure was employed. Moreover, during the backward deduction of membrane stress, the continuation method was adopted. Because the expres- sion of the membrane stress state can realize the analysis on the antenna membrane state, this research has great significance of theoretical direction to the normal operation of the space deployable antenna.     

三线阵立体测绘卫星的测绘精度分析

为满足立体测绘卫星的设计要求,通过构建三线阵CCD影像的摄影测量估算模型,对三线阵CCD影像的立体测绘精度进行分析,研究了影响立体测绘精度的主要误差源.进而,依据立体测绘的精度要求,对卫星设计中所涉及的有关主要误差源,如GPS定位系统、姿态测量与控制系统、时统以及相机有效载荷系统,提出了相关的技术要求和保证测绘精度所应采取的技术措施.     

Relative navigation for satellite formation flight using a continuous-discrete converted measurement Kalman filter

The present paper develops an approach of relative orbit determination for satellite formation flight.Inter-satellite measurements by the onboard devices of the satellite were chosen to perform this relative navigation,and the equations of relative motion expressed in the Earth Centered Inertial frame were used to eliminate the assumption of the circular reference orbit.The relative orbit estimation was achieved through a continuous-discrete converted measurement Kalman filter design,in which the measurements were transformed to the inertial frame to avoid the linearization error of the observation equation.In addition,the situation of the coarse measurement period（only microwave radar measurements are available）existing was analyzed.The numerical simulation results verify the validity of the navigation approach,and it has been proved that this approach can be applied to the formation with an elliptical reference orbit.     

集群航天器网络发展现状及关键技术

为研究新兴集群航天器网络的发展现状及其亟需解决的关键技术难题,对目前该领域的文献进行了分析与总结.集群航天器是一种通过无线链路进行信息交互的,多航天器间协同工作的新型航天器构架,服务于未来日益复杂多样的空间探索任务.首先,结合卫星集群的定义,明晰了集群航天器网络的概念.然后,分析目前分布式协同工作的空间探索任务,阐述了集群航天器的发展历程,并从图论和轨道动力学角度描述了集群航天器网络的特征.最后,总结了集群航天器网络发展过程中亟需解决的关键技术难题,包括网络拓扑控制技术、路由技术、空间互联协议技术、协议跨层资源调配技术等,并结合其他领域研究热点提出了相应的发展建议.研究表明,集群航天器网络的技术研究尚处于初始阶段,仍有许多技术难题亟需解决,同时,成熟的互联网、移动传感器网络等可作为关键技术难题突破的参考.