大口径长焦距空间相机热门机构方案研究

相机热门是大口径高分辨率空间相机的关键部件。文章概要介绍了空间相机热门机构的组成、工作原理及设计要点。     

飞行环境污染对航天器的影响

论述了卫星等航天器的飞行环境污染源及其影响特性，指出，从流体力学观点，在高真空低温环境状态下，喷气羽流污染影响范围有限，对航天器的空间交会或液体空间排放，只要采取相应的措施，就能够避免其对航天器的污染或损害。     

长征系列运载火箭航天发射总次数突破两位数

长征系列火箭为中国航天运载火箭的统称。文章讨论了该系列火箭的组成和航天发射情况。     

Optimal multi-site selection for a PV-based lunar settlement based on a novel method to estimate sun illumination profiles

Recently, space organizations have considered the Moon to host lunar bases. Such bases require power and energy to function. However, the efficient and safe use of the energy resources on the Moon is a huge challenge. Space photovoltaic (PV) power systems are appealing technologies due to their maturity and high solar energy availability at some locations on the Moon. The effectiveness of these PV systems depends on their selenographic location, which might necessitate the deployment of energy storage technologies to cover the base’s energy demand. Some analysts have proposed the installation of PV modules on kilometers-tall towers near the lunar poles to harvest more solar energy and limit the need for energy storage systems (ESSs). Alternatively, this paper proposes to harvest the energy from multiple sites in the lunar South Pole region using a novel technique to compute the Sun illumination profile and the LOLA topographic databases to compute the terrain elevations. The proposed algorithm seeks the most optimal configuration of sites and tower heights to minimize the longest night period and total distance between the sites. This study assesses groups of 1 to 6 sites assuming the use of towers having heights of 10, 100, and 500 [m]. The time horizon for the analysis is one Axial Precession Cycle, which is approximately 18.6 years. According to the results, a system of two sites with a separation of 42.05 [km] and towers of 500 [m] height has a maximum darkness period of only 3 [h] while another solution proposes a system of three sites with towers of 10 [m] that removes the need of EES (solar eclipse periods by the Earth are not considered). The proposed technique is suitable for engineering applications, such as base planning and operation management.     

Strategies and determinants for successful space technology transfer

The following paper reports the results of a research work carried from 2008 on the topic of strategies and determinants of space technology Transfer (TT). In particular, the aim of this study is to present: 1. The policies and strategies the major space agencies adopt for TT, 2. The operational mechanisms and determinants involved in the transfer of space technologies to other industrial sectors. To this extent we have conducted in the last five years: six case studies of large space agencies, four TT case studies concerning the construction of scientific satellites, two case studies focused on space to earth TT programs undertaken by the Japanese aerospace agency, and two TT case studies examining Italian space companies.The comparative and comprehensive analyses of these studies indicate that the space agencies of the more industrialized countries aim primarily at consolidating and developing the industrial systems in their own countries, which include the use of technology transfer programs, and that the transfer of space technologies follows the route “Earth–Space–Earth”. With regard to the determinants of the TT process, the most important of these correlate with the type of technology in transfer, whereas organizational, economic and financial determinants have less significance.     

Heavy ion contributions to organ dose equivalent for the 1977 galactic cosmic ray spectrum

Estimates of organ dose equivalents for the skin, eye lens, blood forming organs, central nervous system, and heart of female astronauts from exposures to the 1977 solar minimum galactic cosmic radiation spectrum for various shielding geometries involving simple spheres and locations within the Space Transportation System (space shuttle) and the International Space Station (ISS) are made using the HZETRN 2010 space radiation transport code. The dose equivalent contributions are broken down by charge groups in order to better understand the sources of the exposures to these organs. For thin shields, contributions from ions heavier than alpha particles comprise at least half of the organ dose equivalent. For thick shields, such as the ISS locations, heavy ions contribute less than 30% and in some cases less than 10% of the organ dose equivalent. Secondary neutron production contributions in thick shields also tend to be as large, or larger, than the heavy ion contributions to the organ dose equivalents.     

Validation of the in-flight calibration procedures for the MICROSCOPE space mission

The MICROSCOPE space mission aims to test the Equivalence Principle with an accuracy of 10^-15${10}^{-15}$. The drag-free micro-satellite will orbit around the Earth and embark a differential electrostatic accelerometer including two cylindrical test masses submitted to the same gravitational field and made of different materials. The experience consists in testing the equality of the electrostatic acceleration applied to the masses to maintain them relatively motionless. The accuracy of the measurements exploited for the test of the Equivalence Principle is limited by our a priori knowledge of several physical parameters of the instrument. These parameters are partially estimated on-ground, but with an insufficient accuracy, and an in-orbit calibration is therefore required to correct the measurements. The calibration procedures have been defined and their analytical performances have been evaluated. In addition, a simulator software including the dynamics model of the instrument, the satellite drag-free system and the perturbing environment has been developed to numerically validate the analytical results. After an overall presentation of the MICROSCOPE mission, this paper will describe the calibration procedures and focus on the simulator. Such an in-flight calibration is mandatory for similar space missions taking advantage of a drag-free system.     

空间机器人抓取未知目标的质量特性参数辨识

根据动量守恒定理,研究了单臂自由飘浮空间机器人抓取未知目标的质量特性参数辨识问题。已有文献中基于动量守恒原理进行的参数辨识只适用于系统线动量和角动量为零的情况,当两者不为零时无法得到正确的辨识结果。为解决此问题,本文首先在惯性系而非本体系下推导得到了机械臂抓取未知目标后的系统线动量和角动量,保证了其各分量的守恒特性。然后基于此特性,通过在轨测量两个时刻机器人本体的线速度、角速度以及机械臂各关节的角速度和转角信息,建立了含有未知目标质量特性参数的动量增量方程。最后根据三组测量信息,从联立的动量增量方程组中求解得到未知目标的质量特性参数。数值仿真表明,此方法在系统线动量和角动量为零和不为零两种情况下都能实现高精度的参数辨识,同时还避免了方程求解的奇异问题。