超临界二氧化碳射流火星采样技术研究

火星钻探取样是火星探测的重要任务环节,火星硬岩地层的有效钻进是目前火星探测取样面临的主要难题。文章在分析比较目前主要航天国家深空探测采样技术特点与局限的基础上,论述了火星大气丰富的二氧化碳资源转化利用的可行性,提出了超临界二氧化碳射流火星采样技术,分析了超临界二氧化碳射流火星硬岩辅助钻进的机理、优势、应用前景和关键科学问题,为火星探测装置的改进和火星采样技术的创新提供参考。     

太空资源开发技术体系研究

为解决地球可持续发展面临的战略性资源重大问题和规模化太空探索面临原位资源补给重大挑战,太空资源开发已成为当前国际航天发展的前沿热点领域。在阐明太空资源开发的概念和内涵、深入分析国内外技术发展现状与趋势的基础上,结合太阳系资源分布特点,提出了太阳系资源开发体系架构和“天工开物”倡议设想。以人类社会发展紧密相关的战略性矿产资源开发为核心,以水冰资源开发和水基推进剂制备为基础,以地球为中心,由近及远,分阶段建设月球资源开发体系、近地小天体采矿体系、火星资源开发体系、主带小行星采矿体系、类木行星探索开发体系及内行星探索开发体系,逐步构建全太阳系资源的开发能力。     

火星探测用金属/CO2燃烧技术研究进展与展望

火星原位资源利用指利用火星当地资源生产火星探测所需原料和能源,减少任务载荷,降低发射成本,是火星探测不可或缺的关键技术。金属和二氧化碳是火星重要的原位资源,部分金属可以在二氧化碳气氛中燃烧,使得金属/CO_2燃烧体系在火星上扮演地球上化石燃料/空气燃烧体系的角色成为可能。从拓展金属/CO_2燃烧技术在火星探测中应用的角度出发,梳理了火星二氧化碳收集方式、火星矿物分布和冶炼、金属/CO_2燃烧技术的主要应用方式(Mg/CO_2火箭发动机和Mg/CO_2金属燃烧器)的研究进展,并对今后的研究进行了展望。     

载人火星探测任务构架及其航天运输系统研究

正随着人类社会和深空探测技术的不断发展,火星探测变得越来越有吸引力。从1960年苏联发射世界上第一个无人火星探测器至今,人类已发射无人火星探测器47次,对火星进行了详细的考察。载人火星探测在探索地外生命、星际移民、推动科技发展、提升国家地位和促进人类社会进步等方面具有重要意义。航天运输系统技术是载人火星探测任务实施的基础技术,其技术水平对载人火星探测任务的风险、复杂度和成本具有重要影响,有必要开展载人火星探测航天运输系统技术研究。     

甲烷-乙烷混合推进剂深度过冷技术的实验研究

针对甲烷采用液氮过冷可能发生甲烷冰堵风险,提出了在甲烷中添加乙烷,制备凝固温度更低的甲烷-乙烷混合推进剂的新方案,搭建实验系统测试了甲烷-乙烷凝固温度变化规律。研究发现,随着甲烷含量提高,混合推进剂凝固温度先降低后升高。当甲烷、乙烷比例为0.71∶0.29时,混合推进剂达到最低凝固温度,约73.0 K。当采用常压饱和液氮对混合推进剂过冷时,控制甲烷含量在0.52~0.81间可避免推进剂冻结。相较于常压饱和甲烷,防冻结区的混合推进剂密度提高了24.0%~38.4%,液相存在温区增大至35.7 K~40.5 K。此外,甲烷-乙烷混合推进剂具有理论比冲高、再生冷却性能佳、结焦与积碳小等优势。所提出的甲烷-乙烷混合推进剂在火星探测等任务中具有可观的应用前景。     

俄罗斯火星载人探测技术现状

火星探测是人类探索太空的重要组成部分。俄罗斯在火星探测方面具有丰富的经验和大量技术储备。文章扼要介绍了俄罗斯火星载人探测技术的发展过程,重点阐述了俄罗斯现阶段火星探测方案和关键部件的研制现状和技术能力,对该方案的可行性进行了分析,并对火星探测技术可能的国际合作方式提出建议。     

火星探测任务对环境模拟技术的需求展望

火星探测是深空探测的重点领域,任务特点决定了火星探测器发射前必须在地面进行各种验证试验。随着火星探测任务的持续深入开展将对环境模拟技术提出新的需求。文章在回顾了人类火星探测的历程之后,展望了未来火星探测任务的可能形式,分析了各种环境的地面模拟方法、试验技术所遇到的新挑战,并给出了建议。     

星球探测机器人研究现状与发展展望

在简述星球探测机器人分类及其特点的基础上,首先对人类深空探测活动发展的各型星球探测机器人进行了总结分析,然后以月球、火星及小行星探测为例,分析了中国后续深空探测任务发展对星球探测机器人的需求与挑战,提出了星球探测机器人未来发展所急需突破的主要关键技术,为后续研究工作及相关工程建设提供参考。     

火星着陆自主导航与制导控制研究进展及趋势

正火星探测为人类了解宇宙演化规律、生命起源提供了宝贵平台。火星着陆过程一般包括进入、下降、着陆3个阶段,需要探测器在7min左右穿过火星大气层、打开降落伞与反推发动机,将下降速度迅速减至0。该过程历时短、速度快、机动程序复杂,常被称为"恐怖7min",是火星探测任务最为惊险的一环。采用先进的自主导航与制导控制技术是实现火星表面安全精确着陆的关键。本文结合对往火星探测任务,对着陆过程中导航与制导控制系统面临的主要技术难题进行分析,并分别对火星着陆进入点与着陆点的选取,自主导航、制导与控制技术的研究现状进行总结回顾。最后,面向未来火星探测任务需求,对自主着陆技术的发展趋势进行展望。     

“天问”一号任务火星环绕器总体设计

正深空探测是当今世界航天活动的重要领域,通过深空探测能够帮助人类研究太阳系及宇宙的起源、演变和现状,进一步认识地球环境的形成和演变过程。深空探测是一个国家综合国力和创新能力的体现,60多年来,各航天大国从未停止过深空探测的脚步。由于火星在自转周期、地形地貌等方面与地球存在诸多相似之处,火星探测一直是国际深空探测领域的热点。人类开展火星探测始于20世纪60年代,已实现了飞越、环绕、着陆、巡视、飞行等多种形式的探测,在火星大气、地形地貌与地质构造、表面物质、内部结构等方面取得众多研究成果。     

一种共轴双旋翼式火星飞行器设计及其试验验证

针对火星飞行器探测需求,提出了一种共轴双旋翼式火星飞行器,基于计算流体力学方法优选了桨叶翼型、平面形状和扭转角等结构参数,基于叶素动量理论建立了旋翼气动力学模型,利用数值模拟方法选择了旋翼转速、旋翼间距和桨叶安装角等飞行参数,设计了原理样机"火星飞鸟-I"的结构与控制系统。构建了火星大气环境模拟器和重力补偿与运动约束装置,开展了模拟火星环境下旋翼式飞行器地面飞行试验,验证了共轴双旋翼式火星飞行器的推进性能,展望了旋翼式火星飞行器技术的发展方向。研究成果对我国开展的火星探测工程具有重要借鉴价值。     

Mars Direct: Humans to the red planet by 1999

“Mars Direct”, is an approach to the space Exploration Initiative that allows for the rapid initiation of manned Mars exploration, possibly as early as 1999. The approach does not require any on-orbit assembly or refueling or any support from the Space Station or other orbital infrastructure. Furthermore, the Mars Direct plan is not merely a “flags and footprints” one-shot expedition, but puts into place immediately an economical method of Earth-Mars transportation, real surface exploratory mobility, and significant base capabilities that can evolve into a mostly self-sufficient Mars settlement. This paper presents both the initial and evolutionary phases of the Mars Direct plan. In the initial phase, only chemical propulsion is used, sendig 4 persons on conjunction class Mars exploratory missions. Two heavy lift booster launches are required to support each mission. The first launch delivers an unfueled Earth Return Vehicle (ERV) to the martian surface, where it fills itself with methane/oxygen bipropellant manufactured primarily out of indigenous resources. After propellant production is completed, a second launch delivers the crew to the prepared site, where they conduct regional exploration for 1.5 years and then return directly to Earth in the ERV. In the second phase of Mars Direct, nuclear thermal propulsion is used to cut crew transit times in half, increase cargo delivery capacity, and to create the potential for true global mobility through the use of CO₂ propelled ballistic hopping vehicles (“NIMFs”). In this paper we present both phases of the Mars Direct plan, including mission architecture, vehicle designs, and exploratory strategy leading to the establishment of a 48 person permanent Mars base. Some speculative thoughts on the possibility of actually colonizing Mars are also presented.     

Comparative assessment of human–Mars-mission technologies and architectures

We compare a variety of mission scenarios to assess the strengths and weaknesses of options for Mars exploration. The mission design space is modeled along two dimensions: trajectory architectures and propulsion system technologies. We examine direct, semi-direct, stop-over, semi-cycler, and cycler architectures, and we include electric propulsion, nuclear thermal rockets, methane and oxygen production on Mars, Mars water excavation, aerocapture, and reusable propulsion systems in our technology assessment. The mission sensitivity to crew size, vehicle masses, and crew travel time is also examined. Many different combinations of technologies and architectures are applied to the same Mars mission to determine which combinations provide the greatest potential reduction in the injected mass to LEO. We approximate the technology readiness level of a mission to rank development risk, but omit development cost and time calculations in our assessment. It is found that Earth–Mars semi-cyclers and cyclers require the least injected mass to LEO of any architecture and that the discovery of accessible water on Mars has the most dramatic effect on the evolution of Mars exploration.     

Mars scientific investigations as a precursor for human exploration.

In the past two years, NASA has begun to develop and implement plans for investigations on robotic Mars missions which are focused toward returning data critical for planning human missions to Mars. The Mars Surveyor Program 2001 Orbiter and Lander missions will mark the first time that experiments dedicated to preparation for human exploration will be carried out. Investigations on these missions and future missions range from characterization of the physical and chemical environment of Mars, to predicting the response of biology to the Mars environment. Planning for such missions must take into account existing data from previous Mars missions which were not necessarily focused on human exploration preparation. At the same time, plans for near term missions by the international community must be considered to avoid duplication of effort. This paper reviews data requirements for human exploration and applicability of existing data. It will also describe current plans for investigations and place them within the context of related international activities.     

核热火箭发动机系统循环方案分析与设计

核热火箭发动机是未来实现载人火星探测的首选动力方案,其具备高比冲、大推力和长工作寿命等优点。我国在此方面研究较少,亟需开展核热推进技术理论及方法的研究。核热火箭发动机系统循环分析与设计是关键问题之一,对推进系统总体设计有重要意义。分析了3种可用于核热火箭发动机系统循环的方案特点,基于闭式膨胀循环设计了比冲为910 s ...     

火星进入气体辐射加热研究进展

针对飞行器进入火星大气时气体辐射加热对防热设计带来不确定性，在简述火星探测和气体辐射研究的发展历程的基础上，对火星进入气体辐射加热研究的进展进行综述。首先，针对火星大气环境描述了气体辐射加热的概念和问题由来。其次，重点综述了近年来火星进入气体辐射加热基础模型的数值和试验研究进展，其中包括：热化学非平衡气体动力学、气体辐射特性和辐射传输的计算模型与方法等数值研究；地面测试设备、试验技术和模拟火星大气环境的气体辐射测量与验证等试验研究。再次，综述了流动辐射耦合和后体气体辐射加热等火星进入器设计方面开展的研究。最后，对未来火星进入气体辐射加热研究进行了展望，提出了研究建议。     

“火星科学实验室”EDL方案及其新技术分析

"火星科学实验室"进入、下降与着陆(EDL)技术代表了目前已步入应用阶段的火星探测的最新技术。在分析该方案基础上,对其所应用的升力式进入及进入制导控制技术、基于马赫数的开伞控制技术、"矢量点乘"控制的防热罩分离技术、基于"空中吊车"的动力下降与着陆缓冲技术和"空中吊车"飞离控制技术等进行了分析,可为火星探测研究提供一定的借鉴和参考。     

核热推进载人火星探测方案设计

针对载人火星探测任务，结合我国现有技术基础，提出我国载人火星探测方案，重点研究载人火星探测任务推进系统的设计。首先，综合考虑载人深空探测任务的约束，采用Pork-Chop图设计了适用于不同任务场景的转移轨迹；然后，参考我国空间站技术，基于核热推进系统设计了我国载人火星探测任务的飞船；最后，对核热推进系统的发动机台数和推力进行了优化，得到了适用于不同任务场景的最优推进系统组合方案。本文所研究内容为我国未来载人火星探测任务提供了有益参考。     

Meditations on the new space vision: the Moon as a stepping stone to Mars

The Vision for Space Exploration invokes activities on the Moon in preparation for exploration of Mars and also directs International Space Station (ISS) research toward the same goal. Lunar missions will emphasize development of capability and concomitant reduction of risk for future exploration of Mars. Earlier papers identified three critical issues related to the so-called NASA Mars Design Reference Mission (MDRM) to be addressed in the lunar context: (a) safety, health, and performance of the human crew; (b) various modalities of mission operations ranging surface activities to logistics, planning, and navigation; and (c) reliability and maintainability of systems in the planetary environment. In simple terms, lunar expeditions build a résumé that demonstrates the ability to design, construct, and operate an enterprise such as the MDRM with an expectation of mission success. We can evolve from Apollo-like missions to ones that resemble the complexity and duration of the MDRM. Investment in lunar resource utilization technologies falls naturally into the Vision. NASA must construct an exit strategy from the Moon in the third decade. With a mandate for continuing exploration, it cannot assume responsibility for long-term operation of lunar assets. Therefore, NASA must enter into a partnership with some other entity--governmental, international, or commercial--that can responsibly carry on lunar development past the exploration phase.