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。     

行星际空间环境对探测器可靠性影响分析

空间环境是影响航天器可靠性的重要因素。与地球轨道航天器相比,行星际探测任务可能会遭受更加恶劣的空间环境,例如极端温度环境,辐射环境,腐蚀性大气环境、宇宙尘等,再加上行星际任务寿命长,采用先进的器件和材料,空间环境对行星际探测器的可靠性构成严重的威胁,直接关系到探测目标能否实现。因此考虑空间环境对行星际探测器的影响,开展相关的预先研究无论是对于制定行星际空间探测计划,还是搭载仪器的设计都具有非常重要的意义。文章分析了极端温度、辐射环境和行星表面综合环境对探测器的影响,并对开展相关研究提出了建议。     

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。     

液体镜头技术应用于空间探测的初步探讨

文章介绍了一种方兴未艾的镜头技术——液体镜头技术，分析了几种典型液体镜头的工作原理和控制方法，并初步探讨了其在空间探测领域应用的可能性。     

我国空间探测发展的原则

论述了我国空间探测发展的基本原则。     

大学新生入学适应教育探析

本研究以410名大学新生为被试,采用问卷法调查了入学第一个学期学生的精神健康水平,考察了他们的入学适应状况,调查结果表明:一部分学生在新环境的适应上存在较多问题.本文在调查研究的基础上,对提高大学生入学适应水平的教育途径和方法做出了尝试性的探讨.     

Developing the global exploration roadmap: An example using the humans to the lunar surface theme

The development of the Global Exploration Roadmap (GER) by 12 space agencies participating in the International Space Exploration Coordination Group broadly outlines a pathway to send humans beyond low Earth orbit for the first time since Apollo. Three themes have emerged: Exploration of a Near-Earth Asteroid, Extended Duration Crew Missions, and Humans to the Lunar Surface. The lack of detail within each of these themes could mean that realizing the goals of the GER would be significantly delayed. The purpose of this paper is to demonstrate that many of the details needed to fully define and evaluate these themes in terms of scientific rationale, economic viability, and technical feasibility already exist and need to be mapped to the GER. Here, we use the Humans to the Lunar Surface theme as an example to illustrate how this process could work. By mapping documents from a variety of international stakeholders, this process can be used to cement buy-in from the current partners and attract new ones to this effort.     

On the measurements of the moon’s infrared temperature and its relation to the phase angle

Radiometric measurements of the thermal radiation originating from the moon’s surface were obtained using an infrared detector operating at wavelengths between 8 and 14 μm. The measurements cover a full moon cycle. The variation of the moon’s temperature with the lunar phase angle was established. The lunar temperatures were 391 ± 2.0 K for the full moon, 240 ± 3.5 K for the first quarter, and 236 ± 3 K for the last quarter. For the rest of the phase angles, the lunar temperature varied between 170 and 380 K. Our results are comparable with those obtained previously at these phase angles. For the new moon phase, the obtained temperature was between 120 and 133 K. With the exception of the new moon phase, our measurements at all the phase angles were consistent with those obtained using Earth-based data and those obtained by the Diviner experiment and the Clementine spacecraft. At the new phase, our measurements were comparable with those obtained from the ground but were significantly higher than those obtained by the Diviner and Clementine data. We attribute this inconsistency to either the calibration curve of our detector, which does not perform well at very low temperatures, or to infrared emission from the atmosphere. A simple linear model to predict the lunar temperature as a function of the phase angle was proposed. The experimental errors that affect the measured temperatures are discussed.     

Automated design architectures for co-orbiting spacecraft swarms for planetary moon mapping

This work describes the design and optimization of spacecraft swarm missions to meet spatial and temporal visual mapping requirements of missions to planetary moons, using resonant co-orbits. The algorithms described here are a part of Integrated Design Engineering and Automation of Swarms (IDEAS), a spacecraft swarm mission design software that automates the design trajectories, swarm, and spacecraft behaviors in the mission. In the current work, we focus on the swarm design and optimization features of IDEAS, while showing the interaction between the different design modules. In the design segment, we consider the coverage requirements of two general planetary moon mapping missions: global surface mapping and region of interest observation. The configuration of the swarm co-orbits for the two missions is described, where the participating spacecraft have resonant encounters with the moon on their orbital apoapsis. We relate the swarm design to trajectory design through the orbit insertion maneuver performed on the interplanetary trajectory using aero-braking. We then present algorithms to model visual coverage, and collision avoidance in the swarm. To demonstrate the interaction between different design modules, we relate the trajectory and swarm to spacecraft design through fuel mass, and mission cost estimations using preliminary models. In the optimization segment, we formulate the trajectory and swarm design optimizations for the two missions as Mixed Integer Nonlinear Programming (MINLP) problems. In the current work, we use Genetic Algorithm as the primary optimization solver. However, we also use the Particle Swarm Optimizer to compare the optimizer performance. Finally, the algorithms described here are demonstrated through numerical case studies, where the two visual mapping missions are designed to explore the Martian moon Deimos.