深空干涉测量天线G/T值指标设计

G/T是天线的一项重要技术指标,在综合考虑测地VLBI(Very Long Baseline Interferometry,甚长基线干涉测量)和航天器VLBI观测两者需求的基础上,提出了深空干涉测量天线的G/T指标设计方法.首先根据射电源的空间分布以及流量密度特性,确定了测地VLBI和航天器VLBI观测模式下射电源流量密度的要求.在此基础上建立了2种观测模式下时延误差与深空干涉测量天线G/T之间的关系模型.最后参考目前国际国内测地VLBI观测中的通用参数设置以及月球探测任务中航天器VLBI观测的参数设置,对不同观测任务、不同观测模式下的G/T要求进行仿真分析.综合测地VLBI和航天器VLBI观测仿真分析的结果,S频段G/T建议不小于32 dB/K,X频段G/T建议不小于43 dB/K.仿真分析结果可以作为后续深空干涉测量天线G/T设计的参考.     

大功率空间核电推进技术研究进展

大功率空间核电推进系统是空间核电源技术和大功率电推进技术的高度融合,具有高能量密度、超高比冲、较大推力的优势,可适用于超大型航天器轨道转移任务、远距离无人深空探测任务、载人火星等大型深空探测任务,能够极大地拓展人类深空探测的能力。本文针对大功率空间核电推进技术,对其工作原理和系统组成进行了介绍,同时开展了关键技术梳理,重点归纳了国内外在技术领域的研究历程和最新进展。     

Energy and power

Energy sources for aerospace systems include electrochemicals, mechanical rotation, solar illumination, radioisotopes, and nuclear reactors. Energy is converted to power with engines, turbines, photovoltaics, thermoelectric and thermionic devices, and electrochemical processes. Although some early spacecraft flew with battery power, for longer flights the choice has been either solar or nuclear. Manned spacecraft must have power for the total mission duration including boost into orbit, on-orbit, and subsequent re-entry. Batteries are too heavy for extended manned space missions; tradeoff study alternatives range from radioisotope heated thermionic converters to hyperbolic-fueled engines. Arrays of solar cells are the obvious choice for powering space stations and for other extended-duration missions. This article emphasizes developments for space and airplane power systems. Enabling technologies are described along with significant spin-offs and future systems     

各推力级霍尔推力器研究现状与展望

介绍了霍尔推力器原理的基础上,推导分析了霍尔推力器推力的影响因素,总结了改变其推力的主要方法。概述了微牛级、毫牛级和牛级等不同推力级适用的航天任务类型,按照3个级别对国内外霍尔推力器型号进行了分类,分别对3个推力级各系列型号的发展及趋势进行了梳理与分析。对各推力级霍尔推力器发展的关键技术进行了展望。针对其中的技术瓶颈与发展趋势进行了总结分析。全面、系统地针对各推力级霍尔推力器进行了综述。结果表明:毫牛级发展最为成熟的推力级,而随着航天任务类型逐渐丰富,微牛级和牛级霍尔推力器发展潜力愈发突出;研究结果提出了霍尔推进器应提升整体性能、扩展推力覆盖范围,强化多模式工作能力,发展空心阴极以及探究不同推进剂等建议。该研究结果对于霍尔电推进的进一步发展具有参考价值。      

人工智能在航天器制导与控制中的应用综述

航天器制导与控制技术是保障空间任务顺利实施的关键技术之一。当前,动力学模型的强非线性以及参数不确定性制约了高精度姿轨控技术的发展,而系统故障则决定航天器姿轨控的成败。以机器学习为代表的新一代人工智能技术航天器制导控制领域展现了巨大的应用潜力。首先对基于人工智能技术的轨迹制导和姿态控制中的研究发展及应用现状进行归纳,分析航天器轨迹规划、姿态控制、故障诊断以及容错控制技术的发展趋势。然后,从鲁棒轨迹规划、自适应姿态控制、快速故障诊断和自适应容错控制等4个方面总结适用于未来航天任务的航天器姿轨控关键技术。最后,针对智能姿轨控技术的应用所面临的挑战,从姿轨控架构、算法最优性、算法的训练以及技术验证等方面提出相应的发展建议。     

Preload relaxation analysis and reliable life prediction of space connection and separation device based on accelerated degradation tests

The safety and reliability of space connection and separation device has become a key issue due to the increasing service span of deep space exploration mission. The long-term preload relaxation (a key failure mode) of connection and separation devices is focused in this paper. A series of tests have been designed and implemented to investigate the preload relaxation regulation and a comprehensive method has been constructed to analyze and predict the reliable lifetime of the device. The two-stage preload relaxation law of the device is found and reasonably considered. Due to the different relaxation mechanism, the first-stage preload relaxation is assessed based on the working-condition test results, and the second-stage preload relaxation is characterized by accelerated test results. Finally, the service reliability and reliable life are evaluated. The experiment and assessment results demonstrate the reasonability and effectiveness of the proposed method which can achieve long-service reliability analysis for space connection and separation device within limited time.     

Tracking and data acquisition for space exploration

The tracking and data acquisition systems provide the key link between the remote spacecraft and the scientific experimenter on the ground. The operation of the space experiment takes place through the links of command, telemetry and tracking. The evolution from the early very simple spacecraft missions toward more complex and sophisticated missions has been paralleled by a similar evolution in the tracking and data acquisition systems. The early Minitrack interferometer tracking system still carries the major tracking workload for space missions; however greater tracking accuracy requirements for more recent missions, such as the Orbiting Geophysical Observatory and the Apollo mission, have brought about the development of unified tracking and data acquisition systems which utilize hybrid pseudo-random code/sidetone ranging techniques. The data acquisition has evolved from analog telemetry systems to the present day heavy use of PCM digital telemetry. Likewise the command systems have evolved from early simple on/off command systems into PCM digital command data systems. The trend is toward greater real time control of more complex functions on board the spacecraft. Newer spacecraft are incorporating computer-type systems in the spacecraft which require programming and memory load through the ground command link. The most attractive concept for the next generation network for tracking and data acquisition is a network consisting of synchronous-orbit Tracking and Data Relay Satellites for covering launches and low-orbit earth satellites plus a few selected ground stations for supporting spacecraft in high earth orbit and lunar orbit.     

Review of in-space assembly technologies

With the rapid development of space technology and the increasing demand for space missions, the traditional spacecraft manufacturing, deployment and launch methods have been unable to meet existing needs. In-space assembly (ISA) technologies can effectively adapt to the assembly of large space structures, improve spacecraft performance, and reduce operating costs. In this paper, the development and technologies for ISA are reviewed. ISA is classified from multiple angles, and the research status of ISA is shown clearly through the visual mapping knowledge domain. Then the development status of autonomous robot assembly in the United States, Europe, Japan, Canada and China is reviewed. Furthermore, the key technologies of ISA are analyzed from three aspects: assembly structure design, robot technologies and integrated management technologies. ISA technologies are still facing major challenges and need to be further explored to promote future development. Finally, future development trends and potential applications of ISA are given, which show that ISA will play a vital role in human space exploration in the future.     

Flexible piloted Mars missions using the TIHTUS engine

The present investigation points out the potential of continuously propelled spacecraft for piloted Mars missions and compares them to impulsive propulsion (chemical and nuclear thermal) and ballistic trajectories. Although the results are related to piloted Mars missions, the stated issues raised hold true for a broad range of space missions. It is demonstrated that the use of impulsive propulsion leads to inflexible missions and may result in long total mission durations. Meanwhile, the use of continuous electric propulsion not only guarantees short total mission durations of Mars missions with moderate masses but also results in highly flexible missions. These criteria can be met with a continuous electric propulsion system that provides a thrust level of 100 N and 3000 s of specific impulse. Great potential lies in electric hybrid thrusters. The high-power, two-stage hybrid plasma thruster TIHTUS is currently being developed at the Institute of Space Systems (IRS). Its technology including preliminary laboratory testing results are presented.     

Successful Large-Scale Use of CMOS Devices on Spacecraft Traveling Through Intense Radiation Belts

This paper describes the environmental models of the radiation belts and computational techniques which have been developed for predicting the radiation hazards for spacecraft These data and techniques are then applied to the Atmosphere Explorer 51 spacecraft to explain its successful survival for more than 18 months in a severe environment In particular, the results of the analysis are used to explain the performance of sonm 2400 CMOS devices, and consequently, they demonstrate the reliability of this device technology gy in spacecraft systems.     

Observations of low energy magnetospheric plasma outside the plasmasphere

After some introductory discussions about morphological concepts and limitations of various measurement techniques, existing low energy plasma data, orginating primarily from the GEOS, Dynamics Explorer, and Prognoz spacecraft, is described and discussed. The plasmasphere measurements are not included (but for some observations of plasmasphere refilling). It is finally concluded that we are very far from a complete picture of the low-energy plasma component in the magnetosphere and that this problem has to be given high priority in planning payloads of future space plasma physics missions.     

Application of stress wave theory for pyroshock isolation at spacecraft-rocket interface

A large number of pyroshock devices are employed in spacecraft and rockets to realize stage separation and appendage deployment. Release of pyroshock devices induces high-level transient shock responses which tend to cause fatal damages in electronic equipment made of crystals and brittle materials. This paper aims to provide methods to isolate pyroshock and guarantee the safety of such equipment against high-frequency shocks. Firstly, stress wave transmission mechanism in stepped rods is investigated, upon which optimal area rate for shock isolation is achieved. Then, two spacecraft-rocket interface structures for pyroshock isolation, namely isolation hole and interim segment, are proposed. Both numerical simulations and experiments are carried out to validate the two shock isolation strategies. It is revealed that the interim segment structure shows better pyroshock isolation performance at the cost of increasing the weight of launching system whereas isolation hole is an optimal choice to reduce pyroshock response without causing weight increase.     

灯丝放电磁场约束型原子氧效应地面模拟试验设备

介绍了用于原子氧剥蚀效应研究的灯丝放电磁场约束型地面模拟设备 ( IFM)的构成及工作原理,简单阐述了装置的运行测量结果,分析了等离子体参数随试验条件的变化趋势。并用 IFM设备对 Kapton空间用材料进行了地面模拟试验,试验结果与国外空间飞行暴露试验结果相似     

CCSDS空间包在MOIMS领域中的应用

为了适应未来航天任务的发展,构建以服务为导向的、开放的、可重用的航天器任务操作系统,分析了CCSDS(Consultative Committee for Space Data Systems,空间数据系统咨询委员会)中MOIMS (Mission Operations and Information Management System,任务操作及信息管理系统)领域的任务操作服务框架的原理、层次结构及优点,对任务操作相关的通用服务、功能服务、COM(Common Object Model,通用对象模型)及MAL(Message Abstraction Layer,消息抽象层)对服务的抽象化描述方法进行了研究.MAL向任务操作相关的服务提供了通用的服务模型框架,所有服务均可用MAL消息格式进行规范化的描述,在此基础上建立了MAL消息格式与CCSDS空间包的映射关系,从而以CCSDS空间包为信息栽体实现了航天器与地面系统间的任务操作通信,可以作为以服务为导向的任务操作系统实际工程应用的参考.     

基于分层传递系统模型的航天器故障诊断方法

 针对传统的传递系统模型在航天器自主诊断系统中只能表示单一粒度诊断知识,知识表示的完备性差,导致诊断结果的分辨率不高,且诊断系统执行效率低的问题,提出了分层传递系统模型和诊断方法。为了保证不同粒度诊断知识的完备性表示,将系统模型按不同粒度和结构关系进行分层。通过自顶向下的递归搜索,先监测系统异常,再匹配故障类型,逐层缩小搜索空间,最终找出故障候选集和故障的层次关系。同时为了减小计算规模,在诊断过程中引入了分离策略,降低实时诊断计算量。应用该方法建立了某卫星测控分系统模型并进行故障仿真,结果表明该方法可以增加模型知识表示的完备性,并能有效提高诊断效率和结果的分辨率。     

Extraterrestrial Organic Matter and the Detection of Life

A fundamental goal of a number of forthcoming space missions is the detection and characterization of organic matter on planetary surfaces. Successful interpretation of data generated by in situ experiments will require discrimination between abiogenic and biogenic organic compounds. Carbon-rich meteorites provide scientists with examples of authentic extraterrestrial organic matter generated in the absence of life. Outcomes of meteorite studies include clues to protocols that will enable the unequivocal identification of organic matter derived from life. In this chapter we summarize the diagnostic abiogenic features of key compound classes involved in life detection and discuss their implications for analytical instruments destined to fly on future spacecraft missions.     

天地一体化飞行器测控通信网络体系构建

空间信息综合应用是未来航天的发展趋势,引进网络化技术,打造天地一体化测控通信网是实现信息综合应用的必由之路.一体化测控通信网作为空间信息传输、分发的公共基础设施,将各类飞行器、地/海/空/天基测控站（接收站）及指控中心、测控中心、用户等都作为网中的标准节点,以实现测控通信任务统一指挥控制、飞行器态势综合显示、测控通信资源综合利用和可持续发展.从新时期航天科技的发展特点得出,空间网络化是必然发展趋势.总结了国内外航天网络化发展的研究成果,提出测控通信网络化的定义、未来体系结构以及实施步骤,设计了空间网络化飞行验证试验的基本方案,剖析了空间网络化体系构建的关键技术.     

我国空间站运行的测控通信工作模式初探

在分析我国载人空间站在轨运行的任务特点和对测控通信提出的新要求的基础上,对测控通信工作模式进行了探讨。针对任务中心,采用分布式模式进行任务的组织和实施,建立常态化工作体系;针对测控通信资源的使用,对资源进行简化、优化,发挥天、地基各自优势,并实现天地基资源统一调度;针对在轨故障诊断和应急处置,提出了“天地联合,以地为主”的载人航天故障诊断模式和实现途径;针对空间站遥操作需求,提出了一套工作模式和实施流程;针对测控通信长期执行任务的可靠性,提出了任务中心容灾备份工作模式和通信路由的备份模式。以期为后续任务工作模式设计提供参考。     

载人火星探测进展及其EDL过程GNC关键技术

随着火星探测技术的不断发展和探测任务的不断推进，载人火星探测在未来将会成为火星探测的重要手段。首先，回顾了无人火星探测任务的发展历程，对比分析了部分无人火星探测器进入、下降与着陆（EDL）过程的参数。然后，结合无人火星探测、载人月球探测和载人航天再入过程，梳理了载人火星探测的特点及需求，系统地总结了前苏联/俄罗斯和美国的载人火星探测研究进展以及技术储备。接着，归纳了载人火星探测的体系构成、集结方式和主要的技术挑战。最后，概括了载人火星EDL过程面临的难题，重点阐述了EDL的导航、制导与控制（GNC）关键技术。     

Kelvin–Helmholtz Instability: Lessons Learned and Ways Forward

The Kelvin–Helmholtz instability (KHI) is a ubiquitous phenomenon across the Universe, observed from 500 m deep in the oceans on Earth to the Orion molecular cloud. Over the past two decades, several space missions have enabled a leap forward in our understanding of this phenomenon at the Earth’s magnetopause. Key results obtained by these missions are first presented, with a special emphasis on Cluster and THEMIS. In particular, as an ideal instability, the KHI was not expected to produce mass transport. Simulations, later confirmed by spacecraft observations, indicate that plasma transport in Kelvin–Helmholtz (KH) vortices can arise during non-linear stage of its development via secondary process. In addition to plasma transport, spacecraft observations have revealed that KHI can also lead to significant ion heating due to enhanced ion-scale wave activity driven by the KHI. Finally, we describe what are the upcoming observational opportunities in 2018–2020, thanks to a unique constellation of multi-spacecraft missions including: MMS, Cluster, THEMIS, Van Allen Probes and Swarm.