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携带食物和研究设备等的进步-7号无人货运飞船因Kurs-NA交会系统故障的因素,其首次与国际太空站的交会失败。Kurs-NA交会系统是Kurs对接装置的升级型号。多年来Kurs装置一直用于俄罗斯联盟号载人飞船和进步号货运飞船。Kurs-NA系统将原5个天线合并为1个,升级了电子设备,目的是提高安全性,降低功率。与旧Kurs对接系统相比, 相似文献
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中国首次空间交会对接任务已进入发射实施阶段,在先后发射天宫一号目标飞行器和神舟八号飞船后,中国还将发射神舟九号、神舟十号飞船,继续实施空间交会对接飞行任务,并将在2020年建造长期载人空间站。本刊特编撰"空间交会与对接"专题,以飨读者。 相似文献
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1967年4月“联盟”1号飞船成功发射后,苏联就开始筹备载人飞船交会对接任务,这是苏联载人航天核心项目——N1-L3载人登月计划的需求。虽然N1-L3项目占用了大部分资源,但为了保障两艘“联盟”载人飞船对接成功,苏联还是进行了一系列对接试验。 相似文献
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9月15日NASA宣布,它已同俄罗斯联邦航天局商定,把联盟号火箭下次向国际空间站发射联盟号载人飞船的时间定在11月14日。NASA称,这项决定是在俄方查明联盟号火箭8月24日发射进步号货运飞船失败的原因后做出的,将使国际空间站连续10年有人值守的纪录不会中断。双方曾考虑一旦俄火箭不能及时复飞将撤离空间站上人员,使空间站处于无人值守状态。 相似文献
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《中国航天》2006,(3):46-46
俄罗斯能源火箭航天公司总裁谢瓦斯季亚诺夫去年12月23日说.到2009年其飞船制造量要增加一倍。他说.目前该公司每年制造2艘联盟号载人飞船和4艘进步号货船.以保证向国际空间站运送宇航员和货物。公司最近决定.在2009、2010和2011年间每年制造4艘联盟号和8艘进步号飞船。之所以增加飞船产量.是因为美国航宇局已同意订购俄飞船。按计划.美将减少航天飞机发射次数.并使其在2010年完全退役.因而今后美将不得不借助俄飞船向空间站运送人员和货物。另据报道,今后俄将利用联盟号飞船大力发展前往国际空间站的太空旅游。俄联邦航天局发布的消息说,目前美、日、俄等国的多名富翁已表示打算花2000万美元做太空旅游。美国航宇局最近已同俄航天局达成协议.将为今春其宇航员威廉斯乘联盟号前往空间站和站上指令长麦克阿瑟乘船返回地面向俄方支付4380万美元的费用.其中也包括使用联盟号作为救生飞船及将在9月份接替威廉斯的一名美宇航员在俄训练的费用。 相似文献
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前苏联联盟号飞船,自1966年11月首次飞行试验到1990年底,已进行了89次发射。如从研究运输工具角度出发,将由联盟号衍生的进步号飞船也计入在内,则已有135次的发射记录。在飞船的发展过程中曾出现过联盟、联盟T、联盟TM和进步号等几种型号。从外形上看,飞船有时带太阳电池帆板,有时不带;有时装对接装置,有时不装。其推进系统有时带主发动机,有时不带。那么联盟号究竟出现过多少种状态?这些状态与所执行的任务有何关系?在其发展过程中又起何作用? 相似文献
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中国首次交会对接任务的技术成就和展望 总被引:2,自引:1,他引:1
首次交会对接任务的成功实施,使中国突破和基本掌握了航天器交会对接及其组合体的控制与管理技术,标志着中国载人航天工程二期任务取得重大突破,为空间实验室及后期空间站的建设奠定了坚实基础。文章对国内外交会对接技术进行了对比,对所取得的技术成就进行了综述,指出任务成功具有提升国家威望、产生广泛社会效益、带动基础学科发展、推动航... 相似文献
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根据有人参与的交会对接任务,其飞行器间通信、遥测模式多变和手控参与多的数据管理特点,文章从两飞行器间的总线通信与并网管理、遥测管理、手控支持等方面,提出了在自主交会对接过程中和组合体状态下的数据管理解决途径,经过成功执行我国首次交会对接飞行任务,验证其合理可行,可靠性和安全性高,可满足交会对接数据管理需求。 相似文献
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The development of protective suits for space use started with the Vostok-suit SK-1, first used by Yu. Gagarin on April 12, 1961, and then used on all subsequent Vostok-flights. The technical background for the design of these suits was the work on full pressure protective suits for military pilots and stratospheric flights in the 1930's through 50's. The Soviet-Russian space programme contains a large number of 'firsts', and one of the most well known is the first EVA by Leonov in 1965. This event is also the starting point for a long series of space suit development for Extravehicular Activities over the last 35 years. The next step to come was the transfer in void space of crew members between the two spacecraft Soyuz 4 and 5 in 1969. As has later become known this was an essential element in the planned Soviet lunar exploration programme, which in itself required a new space suit. After the termination of the lunar programme in 1972, the space suit development concentrated on suits applicable to zero-gravity work around the manned space stations Salyut 6, Salyut 7 and MIR. These suits have become known as the ORLAN-family of suits, and an advanced version of this suit (ORLAN-M) will be used on the International Space Station together with the American EMU. This paper covers the space suit development in the Soviet Union in the 1960's and the experience used from the pre-space era. 相似文献
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Reduction of flight duration after insertion till docking to the ISS is considered. In the beginning of the human flight era both the USSR and the USA used short mission profiles due to limited life support resources. A rendezvous during these missions was usually achieved in 1–5 revolutions. The short-term rendezvous were made possible by the coordinated launch profiles of both rendezvousing spacecraft, which provided specific relative position of the spacecraft or phase angle conditions. After the beginning of regular flights to the orbital stations these requirements became difficult to fulfill. That is why it was decided to transfer to 1- or 2-day rendezvous profile. The long stay of a crew in a limited habitation volume of the Soyuz-TMA spacecraft before docking to the ISS is one of the most strained parts of the flight and naturally cosmonauts wish to dock to the ISS as soon as possible. As a result of previous studies the short four-burn rendezvous mission profile with docking in a few orbits was developed. It is shown that the current capabilities of the Soyuz-FG launch vehicle and the Soyuz-TMA spacecraft are sufficient to provide for that. The first test of the short rendezvous mission during Progress cargo vehicle flight to the ISS is planned for 2012. Possible contingencies pertinent to this profile are described. In particular, in the majority of the emergency cases there is a possibility of an urgent transfer to the present 2-day rendezvous profile. Thus, the short mission will be very flexible and will not influence the ISS mission plan. Fuel consumption for the nominal and emergency cases is defined by statistical simulation of the rendezvous mission. The qualitative analysis of the short-term and current 2-day rendezvous missions is performed. 相似文献
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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. 相似文献