月球软着陆器动力学建模研究

建立准确、实用的月球着陆探测器动力学模型,是制导、导航和控制系统方案设计中的首要工作,文中月球软着陆探测器的推进剂贮箱采用横向对称分散布局的形式,并分析了布局方式对液体推进剂晃动的影响;将贮箱内液体考虑一阶弹簧质量模型,应用虚功率原理建立包含液体推进剂晃动的月球软着陆探测器从动力下降段至最终着陆段的动力学模型,并对动力学下降段进行了数值仿真,仿真结果可为月球软着陆探测器控制系统设计提供理论参考。     

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.     

美国新型载人火星探测技术方案

文章概括介绍了＂发现号＂宇宙飞船的布局结构。然后详细介绍了飞船用于火星探测的两种着陆舱的具体设计方案以及载人火星探测的任务剖面。最后分析了＂发现号＂宇宙飞船火星探测方案的关键可行技术和诸多设计优点。     

“凤凰号”火星探测器着陆过程

文章主要介绍了＂凤凰号＂火星着陆器的着陆过程、着陆点选择方法原则、巡航阶段工作任务,对进入（Entry）、下降（Descent）和着陆（Landing）即EDL阶段的蒙特卡罗分析结果和飞行器重建数值结果进行了总结比较。并对＂凤凰号＂相关的经验和教训进行了比较总结,这对中国未来的火星探测以及其他深空探测具有一定的借鉴作用。     

Human response to high-background radiation environments on Earth and in space

The main long-term objective of the space exploration program is the colonization of the planets of the Solar System. The high cosmic radiation equivalent dose rate represents an inescapable problem for the safe establishment of permanent human settlements on these planets. The unshielded equivalent dose rate on Mars ranges between 100 and 200 mSv/year, depending on the Solar cycle and altitude, and can reach values as high as 360 mSv/year on the Moon. The average annual effective dose on Earth is about 3 mSv, nearly 85% of which comes from natural background radiation, reduced to less than 1 mSv if man-made sources and the internal exposure to Rn daughters are excluded. However, some areas on Earth display anomalously high levels of background radiation, as is the case with thorium-rich monazite bearing sand deposits where values 200–400 times higher than the world average can be found. About 2% of the world’s population live above 3 km and receive a disproportionate 10% of the annual effective collective dose due to cosmic radiation, with a net contribution to effective dose by the neutron component which is 3–4 fold that at sea level. Thus far, epidemiological studies have failed to show any adverse health effects in the populations living in these terrestrial high-background radiation areas (HBRA), which provide an unique opportunity to study the health implications of an environment that, as closely as possibly achievable on Earth, resembles the chronic exposure of future space colonists to higher-than-normal levels of ionizing radiation. Chromosomal aberrations in the peripheral blood lymphocytes from the HBRA residents have been measured in several studies because chromosomal damage represents an early biomarker of cancer risk. Similar cytogenetic studies have been recently performed in a cohort of astronauts involved in single or repeated space flights over many years. The cytogenetic findings in populations exposed to high dose-rate background radiation on Earth or in space will be discussed.     

火星探测器使命轨道捕获策略研究

分析了火星探测器使命轨道捕获策略研究需求,给出了三种可用的典型捕获策略,建立了速度纵向平面内的飞行动力学方程,对三种典型策略进行了飞行动力学仿真,给出了各策略完成捕获所需速度增量、任务耗时及过。通过对仿真结果的分析比较,得出研究结论为：直接制动捕获任务耗时及过载较小,但速度增量需求较大;多次穿越后捕获任务耗时较长,但速度增量需求和过载较小;一次穿越后捕获速度增量需求较小且任务耗时较短,但过载较大。     

"火星探测漫游者"降落伞的研制

概述了“火星探测漫游者”探测器的降落伞系统,并介绍了降落伞系统的组成和性能,以及降落伞的研制过程的主要工作,尤其是设计人员解决和处理的一些细节问题。     

火星探测用降落伞研制试验简介

文章主要介绍了美国火星探测用降落伞研制过程以及在研制过程中的一些主要试验,并同时指出了试验中的一些特点。     

俄罗斯“火星—96”探测器

该文主要叙述俄罗斯“火星—96”探测器的飞行过程,着陆器在火星上的着陆过程以及穿透器的工作情况。     

火星探测着陆系统开伞控制方法研究

文章通过对火星探测进入轨道的分析,提出了一种以动压为控制目标的开伞控制方法,并借鉴过载-时间控制法的相关思想,结合火星探测进入轨道的特点,研究了该开伞控制法的原理和实现方法。根据火星探路者的实际进入条件,采用该方法的分析结果与实际飞行中的开伞情况基本吻合。