Optimal motion cueing algorithm for accelerating phase of manned spacecraft in human centrifuge

This paper presents a novel optimal Motion Cueing Algorithm(MCA) to control the rotations of a Human Centrifuge(HC) and achieve the best simulation of a Space Craft(SC)motion. Relations of the specific forces sensed by astronauts of the SC and the HC have been derived and linearized. A Linear Quadratic Regulator(LQR) controller is implemented for the problem which tends to minimize the error between the two sensed specific forces as well as control input in a cost function. It results in control...     

中国空间地球科学发展现状及未来策略

空间地球科学是以空间对地观测为主要信息获取手段,研究地球系统的各圈层及之间的相互作用、过程与演变,对地球进行系统研究的综合性交叉学科.为纪念空间科学学会成立40周年,本文系统回顾了中国空间地球科学的发展历程,分析当前面临的机遇与挑战,进而提出中国空间地球科学未来发展的建议.     

舱外航天服热控系统仿真

针对人体穿着航天服处于过热状态下的散热问题,在分别建立人体热调节系统、金属氢化物冷源和液冷服数学模型的基础上,将3个模型进行结合,对舱外航天服热控系统在5.5h的时间轴上进行综合的仿真计算,求出人体各节段的温度分布情况,液冷服的入口及出口水温,金属氢化物冷源的出口水温等参数,分析航天员的热舒适性,对航天服热控系统的设计有一定的指导作用,并为今后进一步的研究打下了基础.     

考虑人及组织因素的航天工程项目风险分析模型

针对人及组织因素是造成航天工程项目风险的重要原因,在揭示了人及组织因素产生航天工程项目风险的机理基础上,构建了考虑人及组织因素的航天工程项目风险分析模型。模型首先评价人及组织因素对航天工程元器件建造工作质量的影响,接着测度工作质量与不同缺陷类型之间的一致性概率,并应用Poisson分布计算缺陷严重性,最后根据贝叶斯定理对元器件先验失效率进行修正,通过一个经过数据处理的航天工程项目对所构建的模型和方法进行了验证。     

浅谈民机客户服务专业技术人才队伍建设

民机客户服务人才对我国民机产业发展具有重要影响,其发展建设已纳入国家“十二五冶人才建设规划。介绍了全球顶尖民机制造商波音与空客的客户服务人力资源现状,总结了其客户服务人才队伍的培养措施,最后结合中国商飞公司实际,从招聘、培养、激励及管理等方面提出了培养公司客户服务人才队伍的建议。     

采用被动侧杆的民机设计中的人为因素考虑

与中央杆/盘或主动侧杆相比,被动侧杆的最大缺陷在于缺乏反驱装置,进而产生人-机交互信息以及主/副驾交互信息的缺失,增加了人为差错的出现概率;被动侧杆由于缺乏力反馈,会造成飞行员对触觉这一最直接信息的缺失,进而影响人-机操纵权限的分配。在民机设计中,可以考虑在被动侧杆上添加模式切换按钮,从而在保持飞行员超控权限和提供有效包线保护这两者间找到最佳平衡点。被动侧杆由于缺乏反驱装置,无法实现左、右侧杆的联动,因此更容易出现叠加操纵。在民机设计中,应当从视觉、听觉、触觉全方位对叠加操纵进行提示,同时借鉴已有的接替操纵操作程序,以提高飞行员的适应性。     

人因工程学在飞机驾驶舱空间布局设计中的应用

回顾了当前驾驶舱设计中人因工程学的研究进展,重点探讨了人因工程学研究方法在飞机驾驶舱空间布局设计中的具体应用,总结了设计中需要遵循的原则,并对驾驶舱设计进一步的研究提出了若干建议。     

Usage of pre-flight data in short rendezvous mission of Soyuz-TMA spacecrafts

The paper describes the reduction of the vehicle autonomous flight duration before docking to the ISS. The Russian Soyuz-TMA spacecraft dock to the ISS two days after launch. Due to the limited volume inside Soyuz-TMA the reduction of time until docking to the ISS is very important, since the long stay of the cosmonauts in the limited volume adds to the strain of the space flight. In the previous papers of the authors it was shown that the existing capabilities of Soyuz-TMA, the ISS and the ground control loop make it possible to transfer to the five-orbit rendezvous profile. However, the analysis of the cosmonauts' schedule on the launch day shows that its duration is at the allowable limit and that is why it is necessary to find a way to further reduce the flight duration of Soyuz-TMA before docking to less than five orbits. In a traditional rendezvous profile, the calculation of rendezvous burns begins only after determination of the actual vehicle insertion orbit. The paper describes an approach in which the first two rendezvous burns are performed as soon as the spacecraft reaches the reference orbit and the values of the burns are calculated prior to the launch based on the pre-flight data for the nominal insertion. This approach decreases the duration of the rendezvous by one orbit. The demonstration flight of a Progress vehicle using the proposed profile was implemented on August 1, 2012 and completely confirmed the correctness of the imbedded principles. The paper considers the possible improvements of the proposed approach and recovery from the contingencies.