货运飞船一定会在返回大气过程中被烧毁么?

正一般来说,货运飞船的重要使命主要包括3个:运送货物补给到空间站,帮助空间站维持轨道(推高),运送货物垃圾离开空间站。垃圾种类很多,例如实验过程产生的无用甚至有害物质、航天员生活产生的不可回收废物等。在任何一个航天器返回大气的过程中都会产生大量热量,这足以烧毁绝大部分     

太空探索公司获准启动空间站补给飞行

美航宇局局长博尔登8月23日宣布，该局已正式批准太空探索技术公司从10月份开始进行国际空间站货运补给飞行。该公司将因此成为首家为国际空间站提供服务的私营飞船所有者和经营者。由于太空探索公司已成功履行了4亿美元的NASA“商业轨道运输服务”计划验证飞行协议，它已可以开始按2008年签订的16亿美元“商业补给服务”计划合同的要求执行12次货运补给飞行任务。     

Polar卫星在低高度时表面正高电位的统计研究

基于Polar卫星1996-2008年的表面电压数据,研究了卫星在低轨区域出现正高电位（异常事件）与太阳活动的关系及其发生位置的磁地方时（MLT）分布.研究表明:太阳辐射与异常事件发生次数呈正相关,太阳活动越活跃,异常事件出现次数越多,但不会影响航天器表面电位;异常事件发生占比呈现明显季节性变化,在太阳活动高年,冬季和夏季次数较多,春季和秋季次数较少,在太阳活动低年,每月次数均维持在较低水平,而一个月内异常事件次数没有明显规律;在分布上南北半球表现出相似性,异常事件均不会发生在地磁纬度50°-60°区域,极区和昏侧发生次数较多,而不同的是异常事件在南半球发生得更多更集中;虽然太阳活动与航天器在低高度时表面出现正高电位的次数呈正相关,但即使在太阳活动峰年,航天器异常事件发生率也不超过10%.     

载人航天器轨道运行段的救生问题

本文讨论了载人航天器轨道运行阶段的救生技术的发展、栽人航天器轨道运行段救生的方法及特点、并将各种方法的优缺点进行了比较。本文指出:用停靠在空间站上的轨道救生艇直接救生是最佳的空间站轨道救生方式。     

NASA增订4次货运补给任务

<正>为满足新一轮商业补给服务合同生效前的空间站补给需求,NASA已将太空探索公司和轨道ATK公司现有的国际空间站"商业补给服务"(CRS)合同再续延一年,即延至2017年底,并增订了4次货运补给任务,其中太空探索公司3次,轨道ATK公司1次。这4次飞行将在2017年进行,将作为从现有的CRS合同向CRS2合同的过渡。CRS2合同将涉及2018年到至少2020年的     

"面向空间站运营的低成本货物运输"方案开始征集

按计划,我国空间站将于2022年前后全面建成,之后进入常态化运营与应用阶段,货运飞船每年要进行2～3次补给. 为丰富空间站运营与应用阶段的货物运输途径,中国载人航天工程办公室近期发布了征集"面向空间站运营的低成本货物运输"方案设想的公告,拟探索发展低成本货物运输手段,形成对基本物资运输系统的必要和有益补充,构建起灵活高...     

航天器在轨流体补给系统的概念研究

1 概况 □□航天器寿命受到航天器上可消耗物质装载量的限制。航天器上可消耗流体物质包括推进剂、制冷剂、电源介质和生保气体等。航天器载荷舱内载有一些低温测量仪器（如红外天文望远镜），需要通过低温制冷系统来维持低温测量仪器的工作温度，因此制冷剂耗损直接影响测量仪器的寿命。航天器变轨和轨道保持需要消耗一定的燃料，对于长期工作航天器，其燃料将影响航天器的在轨寿命和轨道保持要求。 在空间轨道上建立长期的大型空间实验室（如国际空间站），需要消耗大量的流体物质，因而需要定期地补给燃料。例如，航天大国正积极致力于…     

新款“天鹅座”货运飞船升空

正2015年12月6日,联合发射联盟公司的"宇宙神"5-401型运载火箭在卡纳维拉尔角空军基地发射了轨道A T K公司的一艘"天鹅座"货运飞船。本次发射执行的是轨道ATK公司在美国航宇局"商业补给服务"计划下的第4次正式的国际空间站货运补给任务,任务代号"天鹅座"CRS-4。这是轨道ATK公司在2014年10月28日采用本公司"心宿二"火箭发射"天鹅座"飞船失败后首次执行空间站货运补给任务,也是太空探索公司"猎鹰"9火箭6月28日发射"龙"货运飞船失败后美国首次恢复向空间站发射商业货运飞船。     

空间扫描

和平号空间站升高轨道它于１月２７日借助与其对接的进步号货运飞船发动机的动力，把轨道升高了１０００ｍ。在通常情况下，由于地球引力和超高空大气摩擦力的作用，和平号平均每昼夜降低轨道１００ｍ，而且在目前太阳活动高峰期间和平号每昼夜降低轨道约达２５０ｍ。因此...     

图解世界载人航天发展史(十九)

<正>长期载人航天器(中)实用型空间站之和平号空间站和平号空间站是苏联于1986年2月20日开始组建,至1996年4月26日组建完毕,形成由核心舱、量子1号舱、量子2号舱、晶体号舱、光谱号舱和自然号舱6个舱段组成的大型空间站,组建过程历时10年。"和平号"长31米、宽27.5米、高19米,增压空间350立方米,运行轨道倾角51.6度,近地点高度350千米,远地点高度400千米,额定乘员3人。     

Development of life support requirements for long-term space flight.

When humans move out into the solar system to stay for long durations, the most immediate challenge will be the provision of a life-supporting environment in locations that are naturally devoid of food, air, and water. Life support systems must provide these commodities in all phases of space flight--during intravehicular activity (IVA) and during extra-vehicle activity (EVA). Systems that support human life must provide: overall reliability in the space environment, allowing maintenance and component replacement in space; reduced resupply mass of consumables and spares; for planetary surfaces, the ability to utilize local resources for increased self sufficiency; and the minimized mass power and volume requirements necessary for all space flight systems. This paper will discuss the melding of these technical requirements in such a way as to meet the human needs of space flight.     

载人空间站概念

空间站与其它航天器相比,有很多优越性。文内详细地阐述了空间站的四大特征:①先入轨后上人,既提高了安全保障,又简化了研制过程;②具有自主补给消耗品、检修和更换设备的能力;③具有长期航天的素质;④具有可变更和可扩大其功能的性质。这些特征及其优越性,充分体现了空间站在未来载人航天活动中的地位和作用。     

超低轨道卫星应用离子电推进技术方案

低地球轨道大气环境对诸如科学探测和对地观测卫星的阻尼作用十分明显,而且阻尼随太阳和地磁活动以及昼夜、季节交替变化范围宽.为了保证卫星轨道精度或飞行状态满足任务要求,需要利用推进系统对卫星受到的阻尼进行实时或间歇式补偿以实现轨道或飞行状态的保持.针对轨道高度220～268 km的无拖曳飞行和轨道维持应用,基于卫星轨道阻尼...     

Energetic particle environment in near-Earth orbit.

The hazard of exposure to high doses of ionizing radiation is one of the primary concerns of extended manned space missions and a continuous threat for the numerous spacecraft in operation today. In the near-Earth environment the main sources of radiation are solar energetic particles (SEP), galactic cosmic rays (GCR), and geomagnetically trapped particles, predominantly protons and electrons. The intensity of the SEP and GCR source depends primarily on the phase of the solar cycle. Due to the shielding effect of the Earth's magnetic field, the observed intensity of SEP and GCR particles in a near-Earth orbit will also depend on the orbital parameters altitude and inclination. The magnetospheric source strength depends also on these orbital parameters because they determine the frequency and location of radiation belt passes. In this paper an overview of the various sources of radiation in the near-Earth orbit will be given and first results obtained with the Solar, Anomalous, and Magnetospheric Particle Explorer (SAMPEX) will be discussed. SAMPEX was launched on 3 July 1992 into a near polar (inclination 82 degrees) low altitude (510 x 675 km) orbit. The SAMPEX payload contains four separate instruments of high sensitivity covering the energy range 0.5 to several hundred MeV/nucleon for ions and 0.4 to 30 MeV for electrons. This low altitude polar orbit with zenith-oriented instrumentation provides a new opportunity for a systematic study of the near-Earth energetic particle environment.     

Different space weather effects in anomalies of the high and low orbital satellites

Preliminary results of the EU INTAS Project 00810, which aims to improve the methods of safeguarding satellites in the Earth’s magnetosphere from the negative effects of the space environment, are presented. Anomaly data from the “Kosmos” series satellites in the period 1971–1999 are combined in one database, together with similar information on other spacecraft. This database contains, beyond the anomaly information, various characteristics of the space weather: geomagnetic activity indices (Ap, AE and Dst), fluxes and fluences of electrons and protons at different energies, high energy cosmic ray variations and other solar, interplanetary and solar wind data. A comparative analysis of the distribution of each of these parameters relative to satellite anomalies was carried out for the total number of anomalies (about 6000 events), and separately for high (5000 events) and low (about 800 events) altitude orbit satellites. No relation was found between low and high altitude satellite anomalies. Daily numbers of satellite anomalies, averaged by a superposed epoch method around sudden storm commencements and proton event onsets for high (>1500 km) and low (<1500 km) altitude orbits revealed a big difference in a behavior. Satellites were divided on several groups according to the orbital characteristics (altitude and inclination). The relation of satellite anomalies to the environmental parameters was found to be different for various orbits that should be taken into account under developing of the anomaly frequency models.     

利用频谱分析确定空间目标太阳翼定向模式

分析对比了空间目标与可控飞行器轨道确定的不同,论述了太阳翼定向模式的不同对轨道运动特性的影响。通过地面站的测距与测角数据,推算出测量数据的地心距频谱。假定一种太阳翼定向模式,利用测量数据进行轨道确定,利用定轨数据计算地心距频谱并与测量数据的频谱比对,由此可确定太阳翼定向模式。利用数值仿真对近地太阳同步轨道和地球静止轨道两种情况进行了验证,仿真结果表明该思路和方法是有效的。     

New concepts for the avoidance or utilisation of methane in life support systems

Due to high resupply costs, especially for long-duration stays in space habitats beyond low earth orbit, future manned space missions will require life support systems (LSS) with a high degree of regenerativity. Possible ways to overcome the waste of resources and to save on resupply mass are therefore of major interest for the development of next generation environmental control and life support systems.     

Summary of radiation dosimetry results on U.S. and Soviet manned spacecraft.

Measurements of the radiation environment aboard U.S. and Soviet manned spacecraft are reviewed and summarized. Data obtained mostly from passive and some active radiation detectors now exist for the case of low Earth-orbit missions. Major uncertainties still exist for space exposure in high altitude, high inclination, geostationary orbits, in connection with solar effects and that of shielding. Data from active detectors flown in Spacelabs 1 and 2 suggest that a variety of phenomena must be understood before the effects of long-term exposure at the space-station type of orbit and shielding can be properly assessed.     

基于相控阵雷达波束篱笆的空间碎片数量与分布估计方法

随着载人航天与空间站等航天活动的增多,不能有效防护、也无法定期跟踪和编目的小尺寸(尤其是1～10 cm)碎片的危害越来越受到关注,这些碎片信息的获取依赖于统计采样技术.针对简化的相控阵雷达波束篱笆空间碎片探测模式,提出了一种采用统计技术估计空间碎片总数量以及高度和倾角分布的方法.将碎片穿越波束篱笆的过程用Poisson分布来建模,根据观测时段内穿越波束篱笆目标的平均到达率及测量的轨道高度和倾角数据来估计给定轨道高度范围或倾角范围内碎片的数量,进而得到碎片的总数量以及碎片数量随轨道高度或倾角的分布.在获取雷达散射截面信息时,该方法还可用于估计碎片数量随尺寸的分布.通过仿真实验验证了该方法的有效性.     

Feasibility study of LEO,GEO and Molniya orbit based satellite solar power station for some identified sites in India

The analysis of satellite solar power station (SSPS) is carried out for some specified locations (Delhi, Mumbai, Kolkata and Bengaluru) in India and consequently the performance of the system is evaluated for geostationary earth orbit (GEO) based SSPS, low earth orbit (LEO) based SSPS and Molniya (quasi geostationary) orbit based SSPS for sites located at different latitudes. The analysis of power; received energy over a year and weight of the rectenna array for the same beam intensity showed varied results for Molniya orbit based SSPS, LEO based SSPS and GEO based SSPS. The power delivered by the LEO SSPS was highest which indicated that this SSPS may be efficient for the short term power requirement. However, it is observed from the results of the energy received over a year that the GEO based system is suitable for base load power plant as it is capable of delivering constant energy through out a year. Further, the weight of the rectenna and hence the space required for ground station for same power output is smallest for Molniya orbit based system for a range of rectenna array radius considered. It is thus envisaged that the Molniya orbit based system would be a better choice for commercial use of SSPS. These findings may help for judicious selection of satellite orbit and ground station location for placing the satellite for SSPS for various applications.