国际空间站哥伦布舱系统级环境控制系统试验

介绍了国际空间站哥伦布舱的系统级环境控制系统试验。该试验既没有使用大型真空设备也没有使用太阳模拟器或红外灯等外热流模拟设施,而是直接在总装大厅的大气环境下实施。试验工况包括发射、正常和故障运行等模式。试验有效验证了哥伦布舱集成全局热数学模型,以及主动热控系统和环境控制与生命保障系统的接口关系。     

Medical concerns for exploration-class missions

The Space Exploration Initiative will challenge life scientists with a diverse set of crew medical risks. The varied sources of this cumulative risk are identified and briefly discussed in terms of risk assessment and preliminary plans for risk management. The roles of Space Station Freedom and other flight programs are discussed in the context of exploration medical objectives; and the significant differences between Space Station era (second generation) and exploration medical support systems (third generation) are reviewed.     

Ignition system for oxygen/hydrogen auxiliary propulsion systems

When the oxygen/hydrogen bipropellant combination was selected for use in the Space Shuttle Main Engine, it became apparent that many advantages may result if the Auxiliary Propulsion System Engines were to use the same propellants. A new ignition system, possessing a dramatically new level of reliability, durability and response, is required because the oxygen/hydrogen combination is not hypergolic and the projected missions will require a very large number of fast-response engine starts.The objective of this program was to obtain basic data for spark torch ignition methods at operating conditions typical of a Space Shuttle Orbiter Auxiliary Propulsion System. The research included ignition analysis and igniter design, fabrication and hot-fire test.Extensive testing of spark torch igniters was performed (chamber pressure, 206.8 N/cm², 300 psia, nominal) in the Igniter-Only and Igniter-Complete Thruster (thrust, 6672 N, 1500 lbF, nominal) operational modes. Reliable, repeatable ignitions were obtained with spark energies of 1–10 mJ. Hot-fire test results showed there is no effect of back pressure (1.013 × 10⁵ to 1.333 × 10^?2 N/m², 7.60 × 10² to 1 × 10^?4 mm Hg) or low temperature (O₂, 170 K, 306 R; H₂, 107 K, 193 R) on the response of the igniter or the ignition delay of the thruster over the ranges tested. Igniter durability and pulse capability were demonstrated with 150 sec of continuous operation and 1000 consecutive pulses, respectively. Durability was further demonstrated with a series of 2500 Igniter-Complete Thruster ignitions at nominal chamber pressure. No limiting variables were encountered. The hot-fire test results showed the spark torch igniter is capable of meeting fully the typical Space Shuttle Orbiter Auxiliary Propulsion System mission requirements.     

Assessment of space environmental factors by cytotoxicity bioassays

Cellular bioassays for detection of cyto- and genotoxicity are useful in the risk assessment of space environmental factors. Such bioassay systems have the potential complement the physical detector systems used in space, insofar as they yield intrinsically biologically weighted measures of cellular responses. The experiment Cellular Responses to Radiation in Space (CERASP) has been selected by NASA/ESA to be performed on the International Space Station. It will supply basic information on the cellular response to radiation applied in microgravity. One of the biological endpoints under investigation will be survival reflected by radiation-dependent reduction of constitutive expression of the enhanced variant of green fluorescent protein (EGFP), originally isolated from the bioluminescent jellyfish Aequorea victoria. In this ground based study, the usefulness of this approach in comparison to standard techniques (colony forming ability test, MTT test) is shown.     

A systems engineering environment for integrated satellite development

Space mission implementation faces a very dynamic environment with fast-paced information technology advancement and shrinking space budgets. A more focused use of decreasing public investments in space requires a cost reduction over their entire life cycle, up to the end of the useful life of a spacecraft. The anticipation of cost, schedule, risk and performance requirements from all over the product life cycle to the early stages of product development is generally recognised as a necessary condition to reduce life cycle cost. In order to cope with the intrinsic functional complexity of space products, such requirements engineering activity must be performed in a structured way within a systems engineering approach. This paper aims to describe how Cradle, a commercial systems engineering environment software package, can be used for integrated satellite development, taking into consideration functional and life cycle process requirements. Cradle has requirements management, system modelling, performance modelling, configuration management and document generation capabilities integrated in the same environment. Also, the paper provides some examples of application and highlights how Cradle can enhance the satellite development related activities performed by the Brazilian Institute for Space Research (INPE).     

The extravehicular mobility unit: A review of environment,requirements, and design changes in the US spacesuit

Requirements are rarely static, and are ever more likely to evolve as the development time of a system stretches out and its service life increases. In this paper, we discuss the evolution of requirements for the US spacesuit, the extravehicular mobility unit (EMU), as a case study to highlight the need for flexibility in system design. We explore one fundamental environmental change, using the Space Shuttle EMU aboard the International Space Station, and the resulting EMU requirement and design changes. The EMU, like other complex systems, faces considerable uncertainty during its service life. Changes in the technical, political, or economic environment cause changes in requirements, which in turn necessitate design modifications or upgrades. We make the case that flexibility is a key attribute that needs to be embedded in the design of long-lived, complex systems to enable them to efficiently meet the inevitability of changing requirements after they have been fielded.     

The extravehicular mobility unit: A review of environment, requirements, and design changes in the US spacesuit

Requirements are rarely static, and are ever more likely to evolve as the development time of a system stretches out and its service life increases. In this paper, we discuss the evolution of requirements for the US spacesuit, the extravehicular mobility unit (EMU), as a case study to highlight the need for flexibility in system design. We explore one fundamental environmental change, using the Space Shuttle EMU aboard the International Space Station, and the resulting EMU requirement and design changes. The EMU, like other complex systems, faces considerable uncertainty during its service life. Changes in the technical, political, or economic environment cause changes in requirements, which in turn necessitate design modifications or upgrades. We make the case that flexibility is a key attribute that needs to be embedded in the design of long-lived, complex systems to enable them to efficiently meet the inevitability of changing requirements after they have been fielded.     

Quality management for space systems in ISRO

In a little over four decades, the Indian Space Program has carved a niche for itself with the unique application driven program oriented towards National development. The end-to-end capability approach of the space projects in the country call for innovative practices and procedures in assuring the quality and reliability of space systems. The System Reliability (SR) efforts initiated at the start of the projects continue during the entire life cycle of the project encompassing design, development, realisation, assembly, testing and integration and during launch. Even after the launch, SR groups participate in the on-orbit evaluation of transponders in communication satellites and camera systems in remote sensing satellites. SR groups play a major role in identification, evaluation and inculcating quality practices in work centres involved in the fabrication of mechanical, electronics and propulsion systems required for Indian Space Research Organization's (ISRO's) launch vehicle and spacecraft projects. Also the reliability analysis activities like prediction, assessment and demonstration as well as de-rating analysis, Failure Mode Effects and Criticality Analysis (FMECA) and worst-case analysis are carried out by SR groups during various stages of project realisation. These activities provide the basis for project management to take appropriate techno-managerial decisions to ensure that the required reliability goals are met. Extensive test facilities catering to the needs of the space program has been set up. A system for consolidating the experience and expertise gained for issue of standards called product assurance specifications to be used in all ISRO centres has also been established.     

Adaptive environmental control for optimal results during plant microgravity experiments

The SVET Space Greenhouse (SG)--the first and the only automated plant growth facility onboard the MIR Space Station in the period 1990-2000 was developed on a Russian-Bulgarian Project in the 80s. The aim was to study plant growth under microgravity in order to include plants as a link of future Biological Life Support Systems for the long-term manned space missions. An American developed Gas Exchange Measurement System (GEMS) was added to the existing SVET SG equipment in 1995 to monitor more environmental and physiological parameters. A lot of long-duration plant flight experiments were carried out in the SVET+GEMS. They led to significant results in the Fundamental Gravitational Biology field--second-generation wheat seeds were produced in the conditions of microgravity. The new International Space Station (ISS) will provide a perfect opportunity for conducting full life cycle plant experiments in microgravity, including measurement of more vital plant parameters, during the next 15-20 years. Nowadays plant growth facilities for scientific research based on the SVET SG functional principles are developed for the ISS by different countries (Russia, USA, Italy, Japan, etc.). A new Concept for an advanced SVET-3 Space Greenhouse for the ISS, based on the Bulgarian experience and "know-how" is described. The absolute and differential plant chamber air parameters and some plant physiological parameters are measured and processed in real time. Using the transpiration and photosynthesis measurement data the Control Unit evaluates the plant status and performs adaptive environmental control in order to provide the most favorable conditions for plant growth at every stage of plant development in experiments. A conceptual block-diagram of the SVET-3 SG is presented.     

Microgravity research and user support in the Space Station era: The Microgravity User Support Centre

Future space systems, such as Columbus, the planned European contribution to the International Space Station, offer ample possibilities for microgravity research and application. These new opportunities require adequate user support on ground and novel operational concepts in order to ensure an effective utilization. Extensive experience in microgravity user support has been accumulated at DFVLR during the past Spacelab 1 and D1 missions. Based on this work, a Microgravity User Support Centre (MUSC) has been built and is active for the forthcoming EURECA-A1 and D2 missions, to form an integrated support centre for the disciplines life sciences and material sciences in the Space Station era. The objective of the user support at MUSC is to achieve:

• easy access to space experiments for scientific and commercial users,

• efficient preparation of experiments,

• optimum use of valuable microgravity experimentation time,

• cost reduction by concentration of experience.

This is implemented by embedding the MUSC in an active scientific environment in both disciplines, such that users can share the experience gained by professional personnel. In this way, the Space Station system is operated along the lines established on ground for the utilization of large international research facilities, such as accelerators or astronomical observatories. In addition, concepts are developed to apply advanced telescience principles for Space Station operations.     

EVA Suit 2000: a joint European/Russian space suit design

A feasibility study in 1992 showed the benefits of a common European Russian space suit development, EVA Suit 2000, replacing the Russian space suit Orlan-DMA and the planned European Hermes EVA space suit at the turn of the century. This EVA Suit 2000 is a joint development initiated by the European Space Agency (ESA) and the Russian Space Agency (RKA). The main objectives of this development program are: first utilization aboard the Russian Space Station MIR-2; performance improvement with respect to current operational suits; development cost reduction. Russian experience gained with the present extravehicular activity (EVA) suit on the MIR Space Station and extensive application of European Technologies will be needed to achieve these ambitious goals. This paper presents the current status of the development activities, the space suit system design and concentrates in more detail on life support aspects. Specific subjects addressed will include the overall life support conceptual architecture, design features, crew comfort and operational considerations.     

System test results from the GNC experiments on the PRISMA in-orbit test bed

The PRISMA in-orbit test bed will demonstrate guidance, navigation, and control strategies for spacecraft formation flying and rendezvous. The project is funded by the Swedish National Space Board and the prime contractor is the Swedish Space Corporation. The project is further supported by the German Aerospace Center, the Technical University of Denmark, and the French Space Agency. PRISMA was launched on June 15, 2010 and after three weeks of operations, all on-board systems and units have passed an initial commissioning phase. Separation of the two PRISMA satellites from each other is expected by mid-August 2010.PRISMA consists of two spacecraft: MAIN and TARGET. The MAIN spacecraft has full orbit control capability while TARGET is attitude controlled only.The Swedish Space Corporation is responsible for three groups of guidance, navigation, and control experiments. These experiments include GPS- and vision-based formation flying during which the spacecraft will fly in passive as well as forced motion. The three experiments are: autonomous formation flying, proximity operations with final approach/recede maneuvers, and autonomous rendezvous. This paper presents system test results from two of these experiments as obtained with the flight-ready system. The system tests consist of a series of simulations performed on the flight model spacecraft with a large amount of hardware in the loop.     

A new approach to optimum sizing and in-orbit utilization of spacecraft photovoltaic power systems

This paper presents a systems approach to optimization of the size and orbital life of photovoltaic systems via minimizing the nighttime energy demand while maximizing the daytime energy consumption. The Day-Night Management of Load (DANMOE) strategy calls for sizing the system to a pre-selected day/night average load power ratio and operating the spacecraft in orbit within the day and night capacity capability, rather than the conventional single orbital average power capability. Examples for the Space Station and the telecommunication satellites show that the reduction in their specific masses can be substantial using any of the photovoltaic system technologies. The DANMOE scheme may also be used effectively to extend the life of batteries on currently orbiting satellites, and hence prolong their lifetime. The paper also discusses other benefits at the spacecraft level and the method of implementing the DANMOE approach.     

The National Space Biomedical Research Institute's education and public outreach program: Working toward a global 21st century space exploration society

Space Exploration educators worldwide are confronting challenges and embracing opportunities to prepare students for the global 21st century workforce. The National Space Biomedical Research Institute (NSBRI), established in 1997 through a NASA competition, is a 12-university consortium dedicated to space life science research and education. NSBRI's Education and Public Outreach Program (EPOP) is advancing the Institute's mission by responding to global educational challenges through activities that: provide teacher professional development; develop curricula that teach students to communicate with their peers across the globe; provide women and minority US populations with greater access to, and awareness of science careers; and promote international science education partnerships.A recent National Research Council (NRC) Space Studies Board Report, America's Future in Space: Aligning the Civil Program with National Needs, acknowledges that “a capable workforce for the 21st century is a key strategic objective for the US space program… (and that) US problems requiring best efforts to understand and resolve…are global in nature and must be addressed through mutual worldwide action”. [1] This sentiment has gained new momentum through a recent National Aeronautics and Space Administration (NASA) report, which recommends that the life of the International Space Station be extended beyond the planned 2016 termination. [2] The two principles of globalization and ISS utility have elevated NSBRI EPOP efforts to design and disseminate science, technology, engineering and mathematics (STEM) educational materials that prepare students for full participation in a globalized, high technology society; promote and provide teacher professional development; create research opportunities for women and underserved populations; and build international educational partnerships.This paper describes select EPOP projects and makes the case for using innovative, emerging information technologies to transfer space exploration knowledge to students, engage educators from across the globe in discourse about science curricula, and foster multimedia collaborations that inform citizens about the benefits of space exploration for life on Earth. Special references are made to educational activities conducted at professional meetings in Austria, Canada, France, China, Greece, Italy, Russia, Scotland and Spain.     

A regenerable carbon dioxide removal and oxygen recovery system for the Japanese Experiment Module

The Japanese Space Station Program is now under Phase B study by the National Space Development Agency of Japan in participation with the U.S. Space Station Program. A Japanese Space Station participation will be a dedicated pressurized module to be attached to the U.S. Space Station, and is called Japanese Experiment Module (JEM). Astronaut scientists will conduct various experimental operations there. Thus an environment control and life support system is required. Regenerable carbon dioxide removal and collection technique as well as oxygen recovery technique has been studied and investigated for several years. A regenerable carbon dioxide removal subsystem using steam desorbed solid amine and an oxygen recovery subsystem using Sabatier methane cracking have a good possibility for the application to the Japanese Experiment Module. Basic performance characteristics of the carbon dioxide removal and oxygen recovery subsystem are presented according to the results of a fundamental performance test program. The trace contaminant removal process is also investigated and discussed. The solvent recovery plant for the regeneration of various industrial solvents, such as hydrocarbons, alcohols and so on, utilizes the multi-bed solvent adsorption and steam desorption process, which is very similar to the carbon dioxide removal subsystem. Therefore, to develop essential components including adsorption tank (bed), condenser. process controller and energy saving system, the technology obtained from the experience to construct solvent recovery plant can be easily and effectively applicable to the carbon dioxide removal subsystem. The energy saving efficiency is evaluated for blower power reduction, steam reduction and waste heat utilization technique. According to the above background, the entire environment control and life support system for the Japanese Experiment Module including the carbon dioxide removal and oxygen recovery subsystem is evaluated and proposed.     

Attached payloads on SPACEHAB, growing from the Space Shuttle to the Space Station

Although NASA's Space Shuttle is largely dedicated in the near term to Space Station assembly, 10–16 day flight opportunities still abound for spacecraft technology demonstration payloads, and experiments for the established earth and space science communities. This paper will present the latest developments of SPACEHAB flight systems in order to accommodate the flight needs of these communities on the Space Shuttle today and the Space Station tomorrow. In particular, some examples of payloads from these disciplines will be introduced together with the accommodation and experiment objectives.     

Space product development: bringing the benefits of space down to Earth

In fulfilling the National Aeronautics and Space Administration's (NASA) responsibility to encourage the fullest commercial use of space the Space Product Development (SPD) Program, within the Microgravity Research Program Office (MRPO) located at the Marshall Space Flight Center (MSFC) in Huntsville, Alabama, is managing an organization of Commercial Space Centers (CSC's) that have successfully employed methods for encouraging private industries to exploit the benefits of space-based research. Unique research opportunities of the space environment are being made available to private industry in an effort to develop new, competitive products; create jobs; and enhance the country's quality of life. Over 200 commercial research activities have been conducted in space by the CSC's and their industrial partners during the last several years. The success of this research is evidenced by the increasing amount of industrial participation in commercial microgravity research and the potential products nearing marketability.     

DTFT-1: Analysis of the first USV flight test

The first dropped transonic flight test (DTFT) of the USV Program, performed with Castor, the first of the two spacecrafts developed within the USV Program, was performed on Saturday 24th February 2007, from Tortolì Airport in Sardinia.At 8:30 a.m. the 340 000 m³ stratospheric balloon lifted off from the East coast of Sardinia, bringing the flying test bed (FTB) up to 20.2 km before release within the isolated sea polygon controlled by Italian air force test range in Salto di Quirra (PISQ). The mission ended at 10:30 a.m. with the splash-down of the space vehicle.The flight itself was very good, with a nose-up manoeuvre under transonic conditions, reaching a maximum Mach as high as 1.08. The mission target was completely achieved as some 2 million measures were taken related to flight data, housekeeping, as well as 500 aerodynamic and structural experimental sensors. Unfortunately, the vehicle has been damaged more than expected during splash-down.Many national and international institutions and industries contributed to the mission carrying out, under the supervision and technical guide of CIRA: Italian Space Agency, Italian Air Force, Italian Navy, Italian Civil Aviation Authority, Italian Company for Air Navigation Services, Port Authorities, European Space Agency, Techno System Dev., Vitrociset, Carlo Gavazzi Space, Space Software Italia, Alcatel Alenia Space Italy, ISL-Altran Group.The paper reports the actual status of post-flight data analysis.