An extensible on-board data handling software platform for pico satellites

Miniaturization techniques enable the realization of very small satellites with interesting capabilities in space science. The University of Würzburg contributed in the scope of the cubesat program with its own pico satellite UWE-1, which is in orbit since October 2005. Despite reliable and stable operation of the on-board data handling (OBDH) system during the UWE-1 mission, the successor UWE-2 will be equipped with a more sophisticated, modular and extensible OBDH system, which was designed to facilitate the further development of the UWE satellite platform. The OBDH system was designed for high reliability and stability, but with an easier extension capability. The modular structure of the new system thus supports potential transfer to other satellite platforms.     

卫星测控数管系统的一种优化设计方法

从排队论的观点出发,提出一种可用于工程实践的系统优化设计方法。该方法在FY-3卫星测控数管系统的设计中得到了应用,FY-3卫星测控数管系统经方案阶段及初样阶段的试验验证,证明其设计合理、简单、可靠,系统的性能指标优化,满足为整星数据流服务的需要。     

基于最小系统的小卫星在轨软件重构系统设计

提出一种基于星载终端处理设备最小系统的小卫星在轨软件重构系统设计方案。依据星上信息流实现现状,设计重构系统的系统框架,提出星载终端处理设备的最小系统组成、通用功能集和需要满足的整星安全性功能需求。系统中,应用软件程序数据按照注入帧格式通过遥控通道注入到星上,可缓存在星务存储器中再分发给终端目的设备,通过最小系统软件对应用程序进行引导和加载管理,整个过程均有差错控制设计以保证其可靠性和安全性。软件重构试验和容错试验表明,利用该系统可实现星载微计算机软件和FPGA配置数据的可靠上注、可靠存储和可靠加载。     

CBERS-1卫星红外编码器

文章介绍了CBERS_1卫星上的重要设备之一———红外编码器的技术原理和实施效果。红外编码器完成了4个谱段图像数据和北极太阳定标数据的采集过程控制、模/数转换、接收OBDH送来的工程参数、产生的相对计数时间、复杂编码以及数据在不同工作模式下进行高速传输等工作 ,它是采用计算机方案设计实现操作的。     

即插即用模块化卫星体系结构研究

即插即用模块化卫星是模块化即插即用技术与卫星平台技术相结合的新型卫星系统,是实现空间快速响应的重要途径。文章介绍了即插即用模块化卫星的概念;分析了即插即用技术在航天任务中的应用;概括了即插即用模块化卫星的体系结构,主要包括功能模块、即插即用标准接口、卫星平台总线和系统软件。在传统卫星分系统划分的基础上进行功能分解,提出了即插即用模块化卫星功能模块的划分方案。文章的研究结果可为中国发展即插即用模块化卫星技术提供理论参考。     

一种用于航天器飞控演练的数管模拟器设计

飞控模拟器用于航天器飞控任务的演练,对确保飞控任务安全可靠起着关键作用.数管模拟器是飞控模拟器最重要的组成部分之一,用于模拟航天器的遥测、遥控、信息处理和传输等功能.文章介绍了一种航天器数管模拟器设计方案,它由通用工控机、通用和专用板卡、数管仿真软件几部分组成,具有真实性高、通用性高、灵活性高的特点,已在嫦娥一号和嫦娥...     

模块化热控技术及其在低轨卫星中的应用

Differently from traditional integration satellites, the modular satellites consist of several structurally independent modules and the heat dissipation is unevenly distributed, while the interface between modules should support repeatable connection separating. Therefore, the traditional thermal control design, which supports the independent heat dissipation of an integration satellite, cannot meet the thermal control requirements of the modular satellite. In this paper the modular thermal control technology is proposed. The carbon nanotube array on metal substrate is used as the thermal interface of the modules to realize the separable cross module heat transfer. The internal surface of structural panels is coated by graphene film to enhance the internal heat transfer in the modules with limited internal space. The smart thermal control coating is used at all the heat rejection surfaces to suppress the orbital heat flux variations. By using the technology, the thermal connection of the assembly and reconstruction system is built and the synergistic heat dissipation of the whole satellite is achieved. As to validate the proposed technology, the finite element model of the circular low earth orbit satellite is established and the in orbit temperature in the extreme working conditions is simulated. The result indicates that the modular thermal control technology proposed in this paper can satisfy the thermal control demand of the modular satellite.      

一种星载电子设备的通用化自动测试系统的设计

为了解决传统卫星载荷测试系统通用性、兼容性差,测试覆盖性不足以及自动化程度低的问题,设计了一种基于开放式硬件和软件设计的通用化自动测试系统.该系统构建了通用的硬件平台以适应不同的数据接口,同时提供了模块化、开放式、可配置的软件平台,可满足不同卫星型号载荷的测试需求.并行测试的结果表明,该系统在保证产品质量的前提下,能大...     

一种模块化微小型卫星对接机构建模仿真

面向微小卫星在轨服务的连接分离技术的需求,针对一种模块化微小型卫星对接机构,分析其机构原理,推导了机构的运动方程,并利用MATLAB验证机构的运动学模型的正确性,结合仿真定量分析机构可能出现的干涉问题,给出了不干涉条件。为研制用于模块化微小型卫星的对接机构提供一种运动学建模和仿真分析的 思路 。     

A novel autonomous low-cost on-board data handling architecture for a pin-point planetary lander

There has been increased interest in the exploration of the Moon in recent years. Pin-point precision landing is highly desirable for future lunar missions. This paper is concerned with the design of the on-board data handling (OBDH) subsystem for the pin-point lunar lander of the Magnolia-1 project, funded by NASA. Four proposed on-board data handling architectures are outlined and compared in terms of power consumption, performance and reliability. Implementation results are presented, which are obtained from prototyping of the flight computer for the optimal OBDH architecture option on a Xilinx Virtex-5 Field Programmable Gate Array.     

从测控系统到数据系统

阐明了航天器数管系统与测控系统的关系 ,以及它们发展到数据系统的趋势。同时提出了数据系统的基本技术要素和实现数据系统的若干关键技术。     

Sumbandilasat—An operational technology demonstrator

Technology advances in sensor, digital technology and a standardised modular satellite bus are enabling a new generation of 80 kg micro-satellites with a better than 6.5 m GSD multi-spectral performance, to be specified, built and deployed with a dedicated launch within 12 months. The result of the standardised modular bus is lower cost, higher reliability and fast deployment. Operational remote sensing with a micro-satellite is thus within reach of individual organisations for dedicated missions. Sumbandilasat (pioneer in the Venda language) is a second generation satellite technology building on the expertise obtained in the Sunsat small satellite programme. The components used to build Sumbandilasat are the result of a technology development program of more than 3 years. Sumbandilasat is an operational technology demonstrator with more than 90% newly developed or improved subsystems and a compact refractive imager as a precursor to the MSMISat satellite with the same multi-spectral band set. The scalable, standardised modular satellite bus architecture enables satellites with a mass of 80–450 kg to be adapted to the specific mission requirements with minimum new engineering effort.     

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.     

地球同步轨道卫星多阶段任务可靠性建模

在分析地球同步轨道卫星首次变轨任务剖面的基础上,以模块化的思路进行卫星多阶段任务系统(phased-mission systems,PMS)建模,采用基于二元决策图(binary decision diagram,BDD)的静态多阶段任务可靠性分析方法和基于马尔可夫模型的动态多阶段任务分析方法来计算地球同步轨道卫星转移轨道段首次变轨的可靠性。经与传统非任务剖面可靠性分析方法的计算结果比对可知,基于任务剖面的可靠性建模分析方法可得到较为真实和精细的结果,有助于卫星的轻量化设计和研制效益提高。     

模块化卫星的多螺杆连接分析

相对于单螺栓连接或平均受力的多螺栓连接,模块化卫星的多根螺杆连接涉及被连接件的非均匀连接刚度,各螺杆处的不同连接刚度的耦合作用与影响还有待深入分析。本文基于单螺栓的载荷分析方法,通过计算被连接件的连接刚度矩阵参数,并融入到螺杆载荷分析中,从而得到计算螺杆直径与预紧力的公式。最后,给出一个模块化卫星多螺杆连接分析的算例,计算结果显示,使用M3钛螺杆、每个螺杆施加最小1Nm拧紧力矩,可以满足此模块化卫星的使用要求。     

Structure and thermal control of panel extension satellite (PETSAT)

Panel ExTension SATellite (PETSAT) [S. Nakasuka, Y. Nakamura, Panel extension satellite (PETSAT)—a novel satellite concept consisting of modular, functional and plug-in panels, in: 24th International Symposium on Space Technology and Science, invited talk, 2004-o-2, 2004 [1]] is a satellite which is made of several “functional panels”. Each panel has a special dedicated function and various combinations of different kinds of functional panels enable PETSAT to deal with various mission requirement. Development of PETSAT requires four interface requirements. These are mechanical interface, thermal interface, electrical interface and information interface. In this paper, mechanical interface and thermal interface of PETSAT are especially focused on and introduced. In the development of PETSAT issues about mechanical interface corresponds to panel structure and deployment mechanism. The structure of PETSAT is designed so as to have light weigh, enough space for devices and high stiffness. And deployment system has simple mechanism to avoid vacuum metalizing and improve reliability. On the other hand, approaches for thermal interface [K. Higashi, S. Nakasuka, Y. Sugawara, H. Sahara, K. Koyama, C. Kobayashi, T. Okada, Thermal control of panel extension satellite (PETSAT), in: 25th International Symposium on Space Technology and Science, 2006-j-02, 2006 [2]] are homogenization of temperature within panel and between panels. Homogenization of temperature within panels can be realized by heat lane plate, and that between panels is realized by magnetic fluid loop with magnetic heat pump. These approaches for mechanical and thermal interface are demonstrated in SOHLA-2 [Y. Sugawara, S. Nakasuka, T. Eishima, H. Sahara, Y. Nakamura, K. Koyama, C. Kobayashi, T. Okada, Elemental technologies for realization of panel extension satellite (PETSAT), in: 25th International Symposium on Space Technology and Science, 2006-J-01, 2006 [3]] that is satellite of technology demonstration for PETSAT.     

皮卫星星箭分离机构运动系统设计

为实现“皮星一号A”卫星无干涉分离,达到分离初始姿态要求,对皮卫星星箭分离机构运动系统进行了分析设计。首先,根据皮卫星与凸轮限位机构间的受力情况和能量守恒定理确定了凸轮轮廓尺寸和分离弹簧结构参数,在此基础上建立了星箭分离过程动力学模型,通过对动力学模型的数值计算确定满足无干涉分离条件的舱门扭簧弹性系数。星箭分离过程的仿真计算和试验校验了“皮星一号A”星箭分离机构可实现无干涉分离,皮卫星初始速度、角速率均满足所提出的各项初始分离姿态要求。     

分布式InSAR系统技术综述

概述分布式卫星干涉合成孔径雷达（InSAR）系统的定义、组成、工作体制、应用领域及特点。综述了4个典型的分布式卫星InSAR系统发展现状,分析了总体技术、编队控制、三同步和基线测量四项系统关键技术。讨论了分布式卫星InSAR系统的高分辨率与宽观测带、实时与准实时和多功能发展方向。针对可实现高分辨率与宽观测带的多通道技术,分析了相位中心个数与重频的关系,并以一发三收模式为例,设计分辨率1m、观测带宽度30km波位参数,并分析总结其技术难点。针对有望实现实时与准实时监视的中、高轨InSAR系统,分析了处理器带宽、合成孔径时间、天线尺寸、峰值功率和基线等参数与轨道高度的相互关系。以轨道高度30000km为例,设计分辨率5m、覆盖范围600km波位参数,分析并总结了系统的关键技术。     

模块化多旋转关节空间太阳能电站方案设计

文章基于多旋转关节空间太阳能电站(MR-SPS)方案,以降低远距离高压电力传输技术难度为核心,提出一种更新的模块化多旋转关节空间太阳能电站概念。该方案在分布式太阳电池分阵和多导电旋转关节基础上,对于微波发射天线阵也进行了模块化设计和分布式布局,实现了太阳电池分阵和微波发射天线分阵的一一对应,形成多个独立的太阳能发电与能量传输模块,通过模块的扩展实现整个空间太阳能电站。该方案大幅简化了空间电力传输与管理的复杂性和在轨组装的难度。同时各个模块完全独立,组装后即可单独工作,也提高了系统的可靠性。     

Development,integrated investigation,laboratory and in-flight testing of Chibis-M microsatellite ADCS

Design, analytical investigation, laboratory and in-flight testing of the attitude determination and control system (ADCS) of a microsatellites are considered. The system consists of three pairs of reaction wheels, three magnetorquers, a set of Sun sensors, a three-axis magnetometer and a control unit. The ADCS is designed for a small 10–50 kg LEO satellite. System development is accomplished in several steps: satellite dynamics preliminary study using asymptotical and numerical techniques, hardware and software design, laboratory testing of each actuator and sensor and the whole ADCS. Laboratory verification is carried out on the specially designed test-bench.In-flight ADCS exploitation results onboard the Russian microsatellite “Chibis-M” are presented. The satellite was developed, designed and manufactured by the Institute of Space Research of RAS. “Chibis-M” was launched by the “Progress-13M” cargo vehicle on January 25, 2012 after undocking from the International Space Station (ISS). This paper assess both the satellite and the ADCS mock-up dynamics. Analytical, numerical and laboratory study results are in good correspondence with in-flight data.