Stochastic control of pitch motion of satellites using stabilizing flaps

The modelling, analysis and synthesis of an attitude control system for low orbit artificial satellites using stabilizing flaps are presented. The function of the system is to maintain the satellite aligned with the local vertical. The aerodynamic forces on the satellite are modelled assuming free molecular flow using the kinetic theory of gases. The control system development is considered through the application of stochastic control concepts. The satellite motion is described by the equations of motion based on Newtonian formulation. Starting from the separation principle, a sequential procedure is developed in which the state estimation and control problems are handled simultaneously. State estimate is provided by Kalman filter using the information about the position of the satellite and of the flaps. The controller acts on satellite in real time, and the stabilizing flaps are the only control elements.     

Attitude dynamics of a pendulum-shaped charged satellite

In this paper, we investigate the possibility of the use of the Lorentz force, which acts on charged satellite when it is moving through the magnetic field, as a means of satellite attitude control. We first derive the equations of attitude motion of charged satellite and then investigate the stability of the motion. Finally we propose an attitude control method using the Lorentz force. Our method requires moderate charge level for future Lorentz-augmented satellite.     

Study of a bunch of three algorithms for magnetic control of attitude and spin rate of a spin-stabilized satellite

We consider the angular motion of an axi-symmetrical satellite equipped with an active magnetic attitude control system. Dynamics of the satellite is studied on the entire control loop, consisting of a bunch of three successively used algorithms. The control cycle includes the stages of nutation damping, spinning up the satellite about its symmetry axis, and reorienting the symmetry axis into a preset direction in the inertial space. The results are confirmed by numerical simulations.     

Development of a scheduling algorithm and GUI for autonomous satellite missions

In this paper, a scheduling optimization algorithm is developed and verified for autonomous satellite mission operations. As satellite control and operational techniques continue to develop, satellite missions become more complicated and the overall quantity of tasks within the missions also increases. These changes require more specific consideration and a huge amount of computational resources, for scheduling the satellite missions. In addition, there is a certain level of repetition in satellite mission scheduling activities, and hence it is highly recommended that the operation manager carefully considers and builds some appropriate strategy for performing the operations autonomously. A good strategy to adopt is to develop scheduling optimization algorithms, because it is difficult for humans to consider the many mission parameters and constraints simultaneously. In this paper, a new genetic algorithm is applied to simulations of an actual satellite mission scheduling problem, and an appropriate GUI design is considered for an autonomous satellite mission operation. It is expected that the scheduling optimization algorithm and the GUI can improve the overall efficiency in practical satellite mission operations.     

卫星控制系统多转台多模拟器半物理仿真方法

卫星控制系统半物理仿真是在实验室中模拟卫星在轨道上运动特性的一种试验方法 ,它通常用于验证卫星控制系统方案和性能指标。卫星控制系统半物理仿真包括将硬件接入路的卫星动力学仿真和运动学仿真。仿真计算机计算卫星的动力学和运动学方程 ;转台模拟卫星在空间的运动 ;目标模拟器用来模拟作为卫星姿态敏感器的参考目标 (太阳、地球和恒星等 )的环境特性。为了将控制系统硬件接入试验路 ,必须适当地处理一系列的关键技术。卫星控制系统多转台多模拟器半物理仿真方法适用于带有多种敏感器的复杂卫星仿真。     

某型号卫星磁环境兼容性分析与控制

某型号卫星的主探测器光电倍增管对卫星的磁环境非常敏感,因此卫星的磁兼容分析和磁设计非常重要。文章结合此卫星的特点对整星的磁场和磁矩等磁兼容性进行了分析计算;对载荷的磁屏蔽方案进行了分析和试验,并根据试验结果给出了磁屏蔽的优化方案;通过分析磁兼容性对姿轨控系统的影响,提出了卫星设计的约束条件,最后给出了磁兼容性分析的结论。     

基于模型预测的轨道自主快速大机动控制

为改善太阳同步轨道(SSO)卫星轨道大机动经典控制方法的性能,提出了一种基于卫星动力学模型预测的轨道自主机动控制算法,用大推力轨控发动机开环控制加小推力器闭环修正进行控制。给出了制导策略和算法流程。理论分析和仿真结果表明,该控制算法适于卫星轨道自主快速机动控制,其轨控精度较高,收敛时间可满足快速性要求。     

带柔性伸杆小卫星振动控制的半物理仿真实验

在空间探测任务中,为了避免卫星平台剩磁对空间待测信息的干扰影响,需采用轻质的伸杆机构支撑各类探测载荷远离卫星本体,而伸杆的弹性振动不可避免地会耦合作用到卫星本体,从而降低卫星本体的姿态控制精度和稳定度。针对此问题,提出了一种基于伸杆最优指令整形结合本体自适应扰动抑制滤波器的复合振动控制策略,即采用指令整形技术抑制柔性伸杆的弹性振动,同时设计自适应扰动抑制滤波器进一步抵消柔性伸杆残余振动对本体的干扰影响,最后在搭建的半物理仿真实验平台上对控制方法进行了实验验证。结果表明：此方法在有效抑制柔性伸杆残余振动的基础上,通过干扰抵消和抑制的控制策略可显著提高此类航天器的姿态控制精度和稳定度。     

Attractive manifold-based adaptive solar attitude control of satellites in elliptic orbits

The paper presents a novel noncertainty-equivalent adaptive (NCEA) control system for the pitch attitude control of satellites in elliptic orbits using solar radiation pressure (SRP). The satellite is equipped with two identical solar flaps to produce control moments. The adaptive law is based on the attractive manifold design using filtered signals for synthesis, which is a modification of the immersion and invariance (I&I) method. The control system has a modular controller–estimator structure and has separate tunable gains. A special feature of this NCEA law is that the trajectories of the satellite converge to a manifold in an extended state space, and the adaptive law recovers the performance of a deterministic controller. This recovery of performance cannot be obtained with certainty-equivalent adaptive (CEA) laws. Simulation results are presented which show that the NCEA law accomplishes precise attitude control of the satellite in an elliptic orbit, despite large parameter uncertainties.     

小卫星综合测试中的接口安全控制

安全控制是小卫星综合测试的重要任务之一,主要包括卫星与地面接口及卫星本身设备间接口逻辑安全控制。文章详细介绍了测试中的安全控制措施,包括供电和接地、电缆检查、功率标定、入口电平控制、关键工序制定等措施。这些安全控制措施有效可行,可靠地保证了人员、卫星和地面设备安全,确保了综合测试质量。     

Attitude stabilization of a satellite by magnetic coils

Stabilization problem for a satellite is considered. The only measurement is of the geomagnetic field in the satellite coordinates. The control is carried out by a magnetic moment of current coils (magnetorquers) mounted on the satellite body. The stabilizer constructed in this work solves the problems of magnetic and gravitational stabilization. Qualitative analysis and results of numerical simulation are presented. The results of simulation show that the proposed stabilization system is reliable, and has an appropriate accuracy and does not need powerful sources of energy, and therefore can be used for attitude control of small satellites.     

集群卫星网络信息拓扑控制技术探讨

集群卫星网络所具有的高动态拓扑、信息异构及灵活组网的特性,使其对信息层面的拓扑控制提出了新的挑战,需要在现有的卫星网络拓扑控制技术的基础上进一步研究。在深入解析集群卫星网络信息拓扑控制内涵的基础上,根据集群卫星网络特点,提出通用的集群卫星网络信息拓扑模型及星地拓扑控制策略,并对现有的卫星拓扑控制算法进行分类说明,根据拓扑的分类方法,分析不同卫星拓扑控制技术在运用于集群卫星网络中的限制条件,最后针对应用需求及技术特点,指出集群卫星网络拓扑控制技术的发展趋势及研究方向。     

GEO光学遥感卫星阳光入侵规避方法

地球静止轨道(GEO)光学遥感卫星的相机每天午夜时分存在阳光入侵问题,致使相机焦面存在潜在损伤,严重时将影响卫星的使用寿命。文章调研了国内外GEO光学遥感卫星针对此问题的解决方式,在综合考虑相机、电能、机动、热控、测控等各项影响因素之后,提出了一种应用约束规避算法的阳光入侵规避方法,首先将卫星设计的工程约束条件转换为空间几何约束条件,通过将明确约束参数后的算法引入卫星姿态控制器来调整卫星姿态指向,避免阳光入侵相机内部。典型工况的仿真分析结果表明:在规避过程中,相机光轴矢量与阳光入射矢量夹角满足约束条件,此方法有效,可满足卫星在轨应用。     

FY-2C星研制过程中的质量管理

为满足用户对风云二号(FY-2)气象卫星的要求,在C星及后续星的研制和生产中实行全程质量管理.介绍了落实责任制,文件化质量管理体系的文件制订与宣贯,包括源头控制、不可靠因素改正、严格把关与彻底归零、验收质量控制的全程质量控制,质量复查,以及发射试验质量控制等措施.C星的成功发射和正常运行,证明了其研制过程中质量管理工作的科学性和有效性.这些经验也为05星的研制建立了良好基础.     

改进RBF网络学习算法在卫星姿态控制中的应用

提出了一种基于神经网络扰动补偿的姿态控制方法，首先，针对RBF网络的常用学习算法－－正交最小二乘（OLS）算法，提出了改进的规范正交最小二乘（ROLS）算法：然后，基于某型小卫星的姿态控制问题，设计了高精度定向阶段的神经网络补偿控制器。仿真结果表明，改进的ROLS算法是有效的，神经网络补偿控制方案是可行的。     

星载大型空间天线的一种解耦控制方法

针对星载大型空间可展开天线与卫星平台之间的动力学耦合问题提出一种三自由度驱动与测量机构用于连接天线臂与卫星平台。该机构以驱动电机来控制天线臂转动,通过角度传感器对天线臂转角的测量来实现反馈控制,同时在卫星姿态控制系统中引入前馈控制进行反作用力矩补偿,实现卫星平台与天线之间的解耦控制、抑制天线的振动、提高卫星姿态控制系统的性能。通过姿态稳定状态下卫星-天线系统解耦动力学模型的建立、控制系统的设计、姿态控制的仿真分析,表明解耦机构能大幅增加天线振动的阻尼,有效提高卫星稳定性和天线指向精度。     

柔性空间飞行器的振动抑止控制

本文提出了一种带有柔性附件的卫星的振动主动抑止方法,给出了能抑止任意阶振动谐波的条件.作为举例,分析了太阳帆板的转动控制,在使帆板平稳旋转的同时,还使卫星姿态稳定无振.     

面向空间近距离操作的机械臂与服务卫星协同控制

针对航天器在轨服务任务中涉及的空间近距离操作需求，提出一种机械臂与服务卫星协同控制方法。首先建立了机械臂和服务卫星组合体动力学模型以及服务卫星和目标卫星相对位姿耦合动力学模型。然后采用全局终端滑模控制设计了机械臂轨迹跟踪控制方法，采用PD控制设计了服务卫星相对位姿耦合控制方法，并将机械臂反作用力和力矩作为前馈补偿叠加到服务卫星控制系统中，实现了两者的协同控制。最后通过数值仿真验证了控制方法的有效性。仿真结果表明，该方法能够满足空间近距离操作任务对机械臂和服务卫星的控制精度、稳定性和误差收敛时间的要求，具有工程实用性。     

气浮台在卫星控制系统仿真中的应用

本文叙述单轴和三轴气浮台仿真设备在卫星控制系统仿真中的应用,主要包括空间太阳望远镜高精度姿控系统单轴气浮台物理仿真试验研究、大型卫星平台单框架控制力矩陀螺(CGCMG)控制系统三轴气浮台物理仿真试验研究、东方红四号卫星控制系统全物理仿真试验.     

通信卫星系统潜在故障识别与应对方法

针对新一代高集成度、高复杂度通信卫星系统应用背景，以通信卫星平台长寿命、高可靠设计需求为牵引，提出一种基于系统理论事故模型与过程（STAMP）的系统级潜在故障识别与分析方法，在总体设计早期即提出对卫星平台各分系统的可靠性设计需求。以某地球同步轨道（GEO）通信卫星为例介绍该方法，通过构建系统控制逻辑架构自上至下地分析潜在的不安全控制过程，通过检查控制与反馈回路的各环节确定故障发生场景，提出对控制过程的约束条件以消除或降低故障发生的可能，最终形成有针对性的分系统可靠性设计需求。