Achievements of Space Scientific Experiments Aboard SJ-8 Satellite

As scientific experiment payloads, microgravity experiments of fluid physics, life science,combustion science, physics and accelerator measurement were conducted on board the Chinese recoverable satellite SJ-8 during 18-day orbital flight. The experimental payloads and an experiment support system constituted the microgravity experiment system of the flight mission. This article has presented the briefs of the scientific achievements of these space experiments, the composition and performance of the Microgravity Experimental System (MES) and the general picture of the overall flight mission, respectively.      

Selection and biomedical training of cosmonauts.

The first cosmonauts were selected from the flying personnel. These individuals enjoying good health were more familiar with the conditions and effects of the factors similar to those which are to be found in space missions. In future, because of the complication of tasks to be solved in space missions, an inflight utilization and testing of sophisticated space technology, and conducting a broad spectrum of scientific studies, a demand arose for including cosmonaut-researchers--highly qualified representatives of various scientific specialities--in a flight crew. In this connection, a necessity was created for changing some evaluation criteria to assess the health status of the chosen candidates considering their age and physical fitness. In specific cases, during the selection process some health-improving measures related to professional significance of the candidates for a position of cosmonaut-researcher was carried out. The prime goal of cosmonauts selection is to predict their good tolerance for a particular space mission while maintaining health and adequate performance throughout the flight, completing the flight tasks and assuring successful return to the Earth. Inclusion of cosmonaut-researchers in space crews requires study of an effect of spaceflight factors on reactions of female subjects in simulated ground-based investigations. At present, the preparation of cosmonauts, can be defined as a continuous purposeful process of training, forming and maintaining operational skills, bringing up the crewmembers to acquire professionally significant psychological and physical features essential for effective work to be done in space mission. The preparation of cosmonauts consists mainly of technical, aviation and space, medical-biological and scientific trainings.     

返回式卫星数字姿态控制系统及飞行试验结果

简要介绍我国返回式卫星上用的计算机数字姿态控制系统的方案;重点阐述姿态确定和相平面控制律的设计方法;最后简述飞行试验的结果。     

空间科学实验柜被动式减振系统研究

载人航天二期我国将发展短期有人照料的空间实验室,将开展一系列空间科学实验.国际空间站和我国神舟飞船实际微重力水平测量结果表明,需采取必要的减振措施才能满足特殊科学实验要求,鉴于此对空间科学实验柜被动式减振系统进行了研究和设计.根据空间科学实验柜在载人航天器内的实际安放状态,对其进行了减振布局.将实验柜本身作为刚体,建立6自由度的减振系统动力学模型,然后在ADAMS中建立了空间科学实验柜及减振系统三维实体模型,对减振系统进行仿真,得出系统时域、频域及随机输入下的响应特性.对减振系统参数进行优化,提高了系统的减振效果.      

面向复杂飞行任务的脑力负荷多维综合评估模型

针对多显示界面多飞行任务状态下的脑力负荷评价问题,设计了飞行仪表监控、飞行数字计算及飞行雷达探测3种不同类型的飞行任务,综合采用多种不同测评方法在飞行试验平台上开展脑力负荷实验测量和综合评价模型研究。实验结果表明:随着飞行任务类型的增多,NASA任务负荷指数（NASA-TLX）的主观评价分值显著增高;飞行正确探测率逐渐下降,反应时间显著延长;事件相关电位（ERP）测量技术中的P3a的峰值（在Fz电极处）逐步降低,心电（ECG）测量技术中的SDNN指标的数值逐步降低,眼电（EOG）测量技术中的眨眼次数没有显著变化。在此基础上,基于贝叶斯判别分析方法,建立了面向复杂飞行任务的脑力负荷多维综合评估模型,并将该综合评估模型与基于单一指标、双指标、三指标、四指标的模型进行了比较,结果显示:所提多维综合评估模型对于多显示界面多飞行任务中的显示界面脑力任务设计的等级分类预测准确率最高,其平均分类预测准确率为82.22%。所提多维综合评估模型为大型复杂系统中显示界面脑力任务设计提供了有效的量化方法和科学依据,有助于歼击机和运输类飞机设计人员优化显示界面脑力任务设计,并为相关型号飞机显示系统的适航审定工作提供新的验证工具。      

Balloon support systems performance for the cosmic rays energetics and mass mission

The Ballooncraft Support Systems were developed by NASA Wallops Flight Facility for use on ULDB class balloon missions. The support systems have now flown two missions supporting the Cosmic Rays Energetics and Mass (CREAM) experiment. The first, CREAM I, flown in December 2004, was for a record breaking 41 days, 21 h, and the second flight flown in December 2005, was for 28 days, 9 h. These support systems provide CREAM with power, telecommunications, command, and data handling including flight computers, mechanical structures, thermal management, and attitude control to help ensure a successful scientific mission. This paper addresses the performance and success of these support systems over the two missions.     

A new polyethylene balloon film

After over twenty years there is a new film introduced in the United States for fabricating scientific balloons. The film was developed by Raven and is designated Astrofilm.The film is a result of a critical selection of both the resin and extruding parameters. The film's physical properties and results of a test flight are reported. Also reported are a proposed design modification and failure analysis.     

Scientific ballooning in India – Recent developments

Established in 1971, the National Balloon Facility operated by TIFR in Hyderabad, India, is a unique facility in the country, which provides a complete solution in scientific ballooning. It is also one of its kind in the world since it combines both, the in-house balloon production and a complete flight support for scientific ballooning. With a large team working through out the year to design, fabricate and launch scientific balloons, the Hyderabad Facility is a unique centre of expertise where the balloon design, research and development, the production and launch facilities are located under one roof. Our balloons are manufactured from 100% indigenous components. The mission specific balloon design, high reliability control and support instrumentation, in-house competence in tracking, telemetry, telecommand, data processing, system design and mechanics is its hallmark. In the past few years, we have executed a major programme of upgradation of different components of balloon production, telemetry and telecommand hardware and various support facilities. This paper focuses on our increased capability of balloon production of large sizes up to 780,000 m³ using Antrix film, development of high strength balloon load tapes with the breaking strength of 182 kg, and the recent introduction of S-band telemetry and a commandable timer cut-off unit in the flight hardware. A summary of the various flights conducted in recent years will be presented along with the plans for new facilities.     

双星系统L1点悬停探测控制器设计与仿真

双小行星系统探测具有重要的科学意义,受其复杂动力学环境影响,探测任务极具挑战。利用球谐函数法对双星系统进行引力场建模,求解双星系统平动点,并选取其内部共线平动点L_1点作为双星系统悬停探测目标位置。采用航天探测实际任务中常用的脉冲推力式发动机,设计了一种原理简单、便于工程实现的常值切换bang-bang控制器。以69230Hermes双星系统为例,将Hermes近似为双椭球系统,仿真分析航天器在Hermes双星系统L_1点悬停飞行的控制效果,验证所提控制策略有效性。     

Remote sensing from the International Space Station

The time has come to give serious thought to the use of the International Space Station (ISS) as a space platform to advance remote sensing research in several scientific disciplines. The European scientific community has been developing instrumentation for deployment on the ISS for some time now. Recently, NASA opened competitions for scientific programs to be supported as “Missions of Opportunity” to utilize the “EXPRESS Pallet” facility on the ISS. A single EXPRESS Pallet has the capability of carrying a collection of instruments similar to the payload of a conventional satellite. A major difference between ISS and satellite programs is that the research funding will be expended on scientific instrumentation and analysis and not on a spacecraft, launch vehicle, and flight operations. As the ISS becomes fully operational, EXPRESS Pallets could be deployed in short periods of time compared to preparing a satellite program. The ability to retrieve, improve, and re-fly an instrument is important to a progressive research program. This allows the experiment to be responsive to data analysis in a timely manner and also keep pace with developing technology.     

大型机场滑行道航空器交通流特性仿真

滑行道是连接跑道和停机坪的纽带,是大型机场航空器场面运行的关键资源。随着场面航空器数量的不断增加,航空器在滑行道区域涌现出特有的交通流特性。基于滑行道航空器运行规则,结合元胞传输模型（CTM）,建立宏观的滑行道航空器交通流元胞传输模型,在NetLogo系统动力学仿真平台的基础上,以中国某大型机场滑行道航空器运行为例对模型进行验证,推理滑行道交通流基本参数之间的关系和相变特征。研究表明,滑行道交通流在自由流、同步流和阻塞流3种相态中演变,其中在同步流相态中,随着密度增加,流量从0.15降至0.10架次/min,速度从20降至7.64 m/s,说明流量和速度参数对于密度的变化十分敏感。当离场率与进场率的比例从0.2降至0.15时,3种相态下的临界流量从0.15、0.10降至0.13、0.05架次/min;临界速度在自由流不变,同步流和阻塞流中依次从7.64、1.07降至0.88、0.25 m/s;临界密度在自由流由0.50降至0.46架次/km,而在同步流阻塞流中依次从0.88、6.21增加至3.77、13.17架次/km。本研究揭示滑行道交通流拥堵演变机理,为制定科学合理的滑行道管理控制策略提供理论基础。      

Long-term space flights--personal impressions.

During a final 4-month stage of a 1-year space flight of cosmonauts Titov and Manarov, a physician, Valery Polyakov was included on a crew for the purpose of evaluating their health, correcting physical status to prepare for the spacecraft reentry and landing operations. The complex program of scientific investigations and experiments performed by the physician included an evaluation of adaptation reactions of the human body at different stages of space mission using clinicophysiological and biochemical methods; testing of alternative regimes of exercise and new countermeasures to prevent an unfavourable effect of long-term weightlessness.     

基于航路点布局的多目标网络结构优化方法

为了提高区域航路网络结构的科学性、减轻飞行流量增长对网络运行带来的压力,提出了基于航路点布局的多目标网络结构优化方法。首先,考虑区域航路网络的组成要素,设计了反映网络综合性能的优化目标和约束条件以形成优化模型。然后,建立基于节点移动、融合、分解的航路点布局策略,进而给出优化模型的求解步骤,并利用NSGA-Ⅲ算法完成模型求解。最后,对北京飞行情报区部分区域航路网络进行仿真分析,结果表明,使用NSGA-Ⅲ算法得出的区域航路网络具有良好的综合性能。最优网络在满足约束条件的同时,保证了运行费用和非直线系数基本不变,并使得飞行冲突系数减少了10.8%。可见,所提优化方法能有效提升区域航路网络的经济性、安全性和可行性,符合中国现行空域环境和管理体制。      

子午工程探空火箭伸杆展开机构技术研究

根据子午工程探空火箭电子和电场探测需求,设计了套筒式伸杆展开机构.通过电子伸杆和电场伸杆的结构方案设计、力学仿真分析,伸杆单项力学试验,伸杆与整箭的匹配力学试验以及伸杆飞行试验验证得出,该伸杆技术方案合理可行,伸杆总体构型、布局设计及结构方案设计满足科学探测各项技术指标的要求.      

ESA microgravity payloads for the 1990s

Analysis of flight opportunities of existing and new microgravity multi-user facilities on Eureca and Spacelab and design studies of new experimental facilities for Columbus are presently in progress.

The materials and fluid sciences research community is likely to be a major user of the permanently manned Space Station/Columbus elements such as the European Attached Pressurised Module (APM) and the Man-Tended Free Flyer (MTFF).

In metallurgy, crystal growth and bioengineering initial research will be performed in the manned laboratory, whereas later on the processing will be automated and executed on unmanned platforms.

At present ESA prepares - in close cooperation with the scientific community - the hardware development of microgravity experimental facilities/laboratories for all Columbus elements through design studies. Preliminary studies which have been carried out to date are the following : Crystallisation Laboratory, Fluid Sciences Laboratory, Containerless Processing Laboratory, Thermophysical Properties Measurement Facility, Metallurgy Laboratory.

In 1998 it is planned to deepen these studies covering laboratories for the APM and for the MTFF. Details on flight opportunities in the pre-Columbus period will also be provided.     

飞行模拟器飞行指引系统控制器的设计

在现代飞机中，飞行指引系统对飞机的起飞，着陆，预选飞行高度和航向、保持飞行状态和航线飞行等方面起着十分重要的作用，它能向驾驶员提供飞机的姿态指令信号，从而确保了飞机的安全，提出了飞行效率和减轻了驾驶员飞行中的负担。本文主要讨论民机飞行模拟器中的飞行指引系统控制器的设计。     

Telemetry,telecommand and safety sub-systems for scientific ballooning from Hyderabad

Highly sophisticated balloon-borne scientific payloads have stringent requirement on the telemetry and command system. The development and fabrication of the on-board TT&C package for telemetry, tracking, command, safety and ranging for these experiments is done in-house at the National Balloon Facility (NBF) at Hyderabad. In the last few years, we have made major improvements both in the ground station and the on-board sub-systems, thereby improving the data quality, data handling speed and the general flight control along with aviation safety. The new system has telemetry data rate up to 1 Mbps. A reduction in weight, power and cost of the reengineered on-board integrated package has also lead to the ease of operation during field tests prior to launch and at remote recovery sites. In this paper, we describe the details of the new control package, its flight performance and our plans for portable S-band telemetry and telecommand system to cater to the balloon flights from Antarctic station and long duration balloon flights.     

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220~268km的无拖曳飞行和轨道维持应用,基于卫星轨道阻尼变化和有效载荷指标要求分析,研究确定了离子电推进技术指标、推力调节方案、系统组成、推力控制方案和在轨应用策略,并对推力调节方案进行了试验验证。结果表明,与无拖曳飞行卫星任务匹配的离子电推进指标为推力调节范围1~20mN,推力分辨率优于12μN,与对地观测卫星轨道维持任务匹配的指标为推力调节范围1～25mN,推力分辨率100μN。研究提出的针对超低轨道卫星应用需求的高精度推力连续调节离子电推进技术方案,具有工程任务针对性和参考价值。