我国首次自主火星探测任务中环绕器的研制与实践

火星探测是国际深空探测的重点和热点,2020年,中国、美国、阿联酋的火星探测器相继发射升空。我国的首颗自主火星探测器——"天问一号"由环绕器、着陆巡视器组成,将一步实现火星的"绕、着、巡"。其中,火星环绕器作为探测器的核心组成部分,承载着地火转移、制动捕获、离轨分离、中继通信以及环火科学探测等重要任务。本文简要回顾了我国火星环绕器的研制历程,介绍了环绕器的基本方案,分析了研制过程中的技术难点和关键技术攻关情况,指出了未来技术发展方向,提出了构建通用化环绕平台的构想,为后期的深空探测任务提供参考。     

未来的深空探测与空间环境模拟

文章介绍了国内外有代表性的深空探测计划的内容、特点和意义,包括:欧空局的Exo Mars火星车、美国"2020火星车"以及中国的2020火星探测计划;金星着陆探测进展情况;欧空局木星系统探测计划"木星冰月亮探索者(JUICE)"和美国的"木卫二飞越任务(Europa Clipper)";"蜻蜓号(Dragonfly)"土卫六探测项目;美国的"彗星天体生物学探索取样返回(CAESAR)"项目;月球探测计划等。还分析了未来深空探测对空间环境模拟的具体要求,空间环境模拟对推动深空探测发展的重要意义;提出了对我国未来开展空间环境模拟试验的建议。     

Observation of aphelion cloud belt over Martian tropics,its evolution,and associated dust distribution from MCS data

The present study uses five Martian years of observations from Mars Climate Sounder onboard Mars Reconnaissance Orbiter for investigating the Aphelion Cloud Belt (ACB) over the tropics. Analysis of zonal mean water ice column opacity suggests that the spatial extension of the ACB is mainly confined over the tropics and mid-latitudes (-20 – 40°N) during L_S ~ 45 – 135° (L_S = 0° signifies northern spring equinox). The ACB is seen primarily in the nighttime only due to the truncation of the daytime profile observations at significantly higher altitudes (at ~30 km). Zonal mean ice extinction profiles show ACB’s altitudinal range within ~10 – 40 km, and the existence of a thin cloud band in the absence of a thick ACB during aphelion season. Three phases of the ACB could be identified as the formation phase during L_S = 45 – 75° (phase 1), the peak phase during L_S = 76 – 105° (phase 2), and the decaying phase during L_S = 106 – 135° (phase 3). Observation of the cloud latitude belt shows a northward movement starting from phase 2, prominent over regions nearby Lunae Planum and Xanthe Terra. During this phase, the top level of thick clouds within the ACB decreases to ~20 km in the southern hemisphere, while it increases a little over the northern hemisphere (NH). The decreasing tendency continues in phase 3 over the entire region ?10 – 10°N, and the thick cloud base moves higher over the NH, though the vertical depth of it becomes narrower than phase 2. Temperature profiles do not show any noticeable influence on the northward evolution of the ACB. However, the study at a regional level indicates a possible association of upper tropospheric dustiness with the ACB’s evolution. The mechanism is evident in the correlation analysis mostly at an altitude range of ~18 – 35 km. The migrating semidiurnal tide (SMD) as a proxy of dust or water ice forcing, and the calculated upper tropospheric dust radiative heating, shows an apparent northward movement of their peak amplitude within the three phases of the ACB. This match between the spatiotemporal variations of the SMD and the water ice was not observed previously. However, the correlating behavior seems to be prominent in the areas nearby Lunae Planum and Xanthe Terra and the upper-tropospheric region of the atmosphere.     

Mars entry guidance using a semi-analytical method

Future Mars missions may require improved landed accuracy to facilitate the landing site selection and finally access a region of complex terrain with high scientific return. This paper is to develop a novel, robust, and precision entry guidance algorithm for Mars entry vehicles with low lift-to-drag ratios. In the presence of large uncertainties, the entry terminal point controller algorithm can encounter severe performance degradation due to: (1) the small perturbation assumption, and (2) theoretically ignoring deviations in the atmospheric-density model, aerodynamic-force model, etc. Based on numerical technologies and the classical variation method (VM), this work develops a semi-analytical (SA) algorithm, in which combined effects of several dynamic uncertainties now can be addressed. The terminal-downrange error is predicted by a numerical predictor such that the dependence on the reference trajectory can be reduced and then the issue caused by the small perturbation assumption can be addressed. Such a predicted terminal-downrange error is finally corrected by an analytical corrector, which is designed by the VM. It is indicative that there can be no numerical iterations in the SA algorithm. Numerical results demonstrate the effectiveness of the SA algorithm.     

国外单组元变推力发动机应用与关键技术

介绍了国外单组元变推力发动机的应用现状,阐释了单组元变推力发动机的结构和设计原理,总结了研制和改进过程中的关键技术,主要包括径向双层夹套催化床设计、径向喷注器设计、流量稳定调节技术和催化床空穴控制技术等。美国为火星软着陆研制的MR-80和MR-80B无水肼单组元变推力发动机分别应用于“海盗”号和“好奇”号着陆器下降级推进系统。MR-80发动机可实现275~2835 N变推力调节,推力变比为10∶1,比冲为205 s,呈120°均布于“海盗”号着陆器三角形基座的长边。“好奇”号下降级推进系统由2个高压氦气瓶、3个推进剂贮箱、8台单组元变推力发动机、8台单组元250 N姿控发动机、1个压力控制组件和3个推进剂控制组件组成,MR-80B发动机可产生31~3603 N的真空推力,推力变比达到100∶1,比冲范围为204~223 s。     

火星进入舱开伞弹伞载荷动力放大系数研究与试验验证

Firstly, the analytical formulas of the dynamic magnification factor with the pulse time of the response spectrum of a single degree of freedom system under the rectangular and half sine pulse are derived. Then the parachute inflation and ejection low frequency high shock load dynamic simulation model of the Mars entry vehicle is built based on abaqus explict dynamics, and the influence of the shock load shape, load time and load damping are analyzed. Finally, the experiments of the opening parachute load suspension impact dynamic load and the parachute load real parachute impact dynamic load are carried out.The results show that the structure responds decline when the shock load time is less than  1 ms , and the static equivalence load becomes steady when the load time is longer than 5 ms; the dynamics equivalence load of the parachute inflation is about 1 time than static because of the smooth time wave, but the parachute ejection’s is about 1~2 times than static due to the steep rectangle wave.      

旋翼式火星无人机技术发展综述

火星表面稀薄的大气环境为旋翼式无人机在火星低空飞行提供了必要的条件。概述了火星无人机的研究背景、飞行环境与研制难点；整理了世界范围内各研究机构研制的旋翼式火星无人机的技术特点；梳理旋翼式火星无人机研究在气动特性理论、低气压飞行控制、系统集成等方面的关键技术；总结旋翼式火星无人机的仿真研究与实验研究成果；对火星无人机未来的发展趋势进行展望。     

South polar permanent CO2 ice cap presentation in the Global Mars Multiscale Model

The atmospheric influence caused by the Martian permanent south CO₂ ice cap is examined to improve the Global Mars Multiscale Model (GM3) to see if it can significantly improve the representation of south polar meteorology. However, the seasonal carbon dioxide ice in the polar regions is presented in the surface ice simulation by the Global Mars Multiscale Model but the model does not produce a permanent south CO₂ ice cap, and the physics code must modify to capture the realistic physical such as ice process detail; probably makes a bias in terms of total CO₂ ice and meteorological processes in the model aside from ice formation. The permanent south CO₂ ice cap in the model can significantly improve the representation of south polar meteorology for example in predicted surface temperatures, surface pressures, horizontal and zonal winds over the south cap and possible initiation of dust storms at south polar region during the southern summer period.     

火星探测器降落伞系统综述

文章介绍了美国火星探测器降落伞系统组成和验证试验情况;分析了5种不同探测器降落伞系统的具体差异;归纳了探测器降落伞系统的结构和性能参数;重点介绍了"凤凰号"和"火星科学实验室"降落伞系统研制过程和性能验证试验。     

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。