航天器总装工艺组册规划与实施

近几年来我国航天器的研制任务迅速增长,传统的单型号研制模式正逐渐地被小批量与研制相结合的混线制造模式所取代。总装工艺组册规划作为一种与航天器小批量总装相适应的生产组织方式,在总装中取得了良好的应用效果。文章总结了总装工艺组册规划及实施的若干经验,同时提出了继续深入应用的思路。     

载人飞船返回舱再入着陆力学环境防护技术改进

文章对弹道-升力式载人飞船返回舱再入着陆力学环境及其乘员和舱载仪器设备的防护措施进行了理论分析和试验研究。适当的返回舱座椅安装角度有利于乘员承受再入过载。座椅缓冲系统是吸收着陆冲击能量、保护乘员最重要的环节,发挥返回舱结构缓冲吸能作用也是改善着陆冲击环境的有效措施。合理设计返回舱设备布局和安装形式可保护舱载设备免受着陆冲击损坏。防护措施的改进可有效保护乘员免受伤害,保证舱载仪器设备正常工作。     

一种航天器加筋锥壳结构轴压稳定性研究

研究了开口型截面桁条加强蒙皮锥壳结构的局部稳定性计算方法;并用平板/加筋圆筒极限轴压的有效宽度法计算其极限载荷,得出加筋锥壳结构局部稳定性和整体稳定性的分析方法。     

MIRO: Microwave Instrument for Rosetta Orbiter

The European Space Agency Rosetta Spacecraft, launched on March 2, 2004 toward Comet 67P/Churyumov-Gerasimenko, carries a relatively small and lightweight millimeter-submillimeter spectrometer instrument, the first of its kind launched into deep space. The instrument will be used to study the evolution of outgassing water and other molecules from the target comet as a function of heliocentric distance. During flybys of the asteroids (2867) Steins and (21) Lutetia in 2008 and 2010 respectively, the instrument will measure thermal emission and search for water vapor in the vicinity of these asteroids. The instrument, named MIRO (Microwave Instrument for the Rosetta Orbiter), consists of a 30-cm diameter, offset parabolic reflector telescope followed by two heterodyne receivers. Center-band operating frequencies of the receivers are near 190 GHz (1.6 mm) and 562 GHz (0.5 mm). Broadband continuum channels are implemented in both frequency bands for the measurement of near surface temperatures and temperature gradients in Comet 67P/Churyumov-Gerasimenko and the asteroids (2867) Steins and (21) Lutetia. A 4096 channel CTS (Chirp Transform Spectrometer) spectrometer having 180 MHz total bandwidth and 44 kHz resolution is, in addition to the continuum channel, connected to the submillimeter receiver. The submillimeter radiometer/spectrometer is fixed tuned to measure four volatile species – CO, CH₃OH, NH₃ and three, oxygen-related isotopologues of water, H₂ ¹⁶O, H₂ ¹⁷O and H₂ ¹⁸O. The basic quantities measured with the MIRO instrument are surface temperature, gas production rates and relative abundances, and velocity and excitation temperature of each species, along with their spatial and temporal variability. This paper provides a short discussion of the scientific objectives of the investigation, and a detailed discussion of the MIRO instrument system.     

空间站姿态/动量联合非线性控制

从Lyapunov稳定性理论出发,设计了一个非线性控制器,实现了空间站姿态和控制力矩陀螺角动量的联合控制。在此基础上,为抑制周期性环境干扰力矩对姿态控制性能的影响,引入了周期性扰动抑制滤波器,对非线性姿态/动量控制器进行了改进。改进的控制器不但可以抑制空间站姿态的周期性波动,而且可在满足特定飞行任务的前提下,建立空间站指向和控制力矩陀螺动量管理间的折中。控制器参数物理意义明确,易于调整。对空间站姿态控制/动量管理系统的仿真结果表明,该控制器是可行的。     

航天领域蒸汽压缩热泵技术研究进展

蒸汽压缩热泵是未来大型航天器热控系统和制冷设备的新方案。介绍了国际上的研究情况,阐明了此技术的优越性和可行性。分析了航天用蒸汽压缩热泵的关键技术,包括微重力相变换热器及其研究方法、无润滑高转速压缩机等。在此基础上给出了中国开展航天领域蒸汽压缩热泵的研究方案。     

航天器推进系统发动机动态特性研究

以一维流体瞬变理论为基础,采用特征线有限差分格式,编制航天器推进系统液体推进剂火箭发动机动态过程的通用仿真软件,并对某多台发动机系统的动态特性进行研究。结果表明,该模型较好地描述了系统瞬变特性和水击现象,所开发的软件可方便进行其它推进系统的分析,为发动机系统设计和优化提供指导。      

Design and Stability of Operating Mechanism for a Spacecraft Hatch

This article introduces the working principles of a spacecraft hatch including its operating process and moving trajectory. On this basis, an operating mechanism is designed to execute automatic open and close action of the hatch and measure the operating torques. Analysis on the mechanism's configuration and topological structure of each phase of movement proves that it is a typical variable freedom mechanism. The mechanism manipulates the hatch in accordance with the moving trajectory requirements through configuration transformation. Kinematic analysis and simulation of some typical configurations show that the velocity differences among mechanism components themselves and the components and their abutting components could exert influences on its working stability during configuration transformation. To solve the problem, stability conditions of configuration transformation are proposed. Appropriate control models are established for the output velocity curves of the driving servo motor and solved based on the stability conditions and rules of movement. Results from another simulation demonstrate that the proposed control models ensure smooth configuration transform and stable operation.     

微型航天器与空间非合作目标交会制导方法

星载设备能力有限的微型航天器在与空间非合作目标交会任务开始前,存放在空间轨道平台内,为了使其完成此项任务,需要设计制导方法。本文首先根据希尔（C-W）方程,设计了初制导律,然后在视线坐标系内建立了微型航天器与非合作目标间的相对运动方程,并设计了空间交会自寻的末制导律。交会任务开始时,为节省微型航天器的燃料,轨道平台根据初制导律以一定速度及释放角度释放微型航天器,微型航天器进入交会轨道,在初制导的作用下,经过若干个过渡轨道周期后接近空间非合作目标,并为末制导提供良好的交班条件,当末制导导引设备捕获并跟踪目标后可通过自寻的末制导最终完成与空间非合作目标交会任务。     

重复使用航天器发展趋势及若干思考

重复使用航天器具有快速、低成本的特性,是自由进出空间的重要技术途径之一。自从２0世纪50年代重复使用航天器的概念被提出以来,历经７０多年,重复使用航天器的研制取得了很大的进步,积累了丰富的经验和教训。基于国内外发展情况,梳理了重复使用航天器的技术路线,深入分析了其发展趋势,从设计、制造、试验、运行维护4个方面探讨了重复使用航天器的特点和难点,并提出了未来重复使用航天器发展的若干思考与建议。