Abstract Today everyone have a lot of meetings. The meetings¡¦ efficiency is quite low and group decision-making quality is bad. In foreign, many methods have good effects on it. Open space technology is one of them. But it has some conditions and assumptions which don¡¦t fit our culture and the conditions of our companies. We have to improve Open space technology to draw its effects. We improve it according to our assumptions and principles. We also assist it with some technologies, like Talking stick, circling, and catalytic mechanism. They all have outstanding and stable results. They can help Open space technology to overcome the deficit of ideal conditions. This research¡¦s main point is to introduce and collect the creative ways of the improved Open space technology. In two hospitals, we can see the improved Open space technology which has obvious effects and promote the group decision-making quality a lot. It still can get good results under the deficit of ideal conditions. We conclude that it has 9 traits as followed: 1. It lowers the barrier of inertia. 2. Interactions 3. Positive feedback 4. Participation 5. The form of activity 6. Safety 7. Closer contact with others 8. Appreciative attitude 9. Truly contribution This research is a initial research and introduction of the improved Open space technology. We suggest other researchers can popularize the improved Open space technology and get the more generalization results.

<p>Spacecraft on interplanetary missions or advanced satellites orbiting the Earth all require propulsion systems to complete their missions. Introducing microelectromechanical systems technology to the space industry will not only reduce size and weight of the propulsion system, but can also increase the performance of the mission.</p><p>Fluid handling systems are used in chemical and electric propulsion. Some components incorporated in a fluidic handling system are presented and evaluated in this work.</p><p>Microsystems are very sensitive to contamination. Reliable, robust, and easily integrated filters were modeled, manufactured, and experimentally verified.</p><p>A fluid connector, designed to withstand large temperature variations and aggressive propellants was manufactured and characterized. Similar designs was also be used as a thermally activated minute valve.</p><p>The feasibility of a cold gas system for precise attitude control has been demonstrated. Steps towards improving the performance (from specific im-pulse 45 s) have been taken, by the integration of suspended heater elements.</p><p>For electric propulsion, two thermally regulated flow restrictors have been characterized. These devices can fine-tune the propellant flow to e.g. an ion engine.</p><p>A single-use valve using a soldered seal has also been successfully dem-onstrated within a pressure range of 5 to 100 bar.</p><p>The microsystem-based propulsion systems of tomorrow’s spacecraft need to be demonstrated in space, in order to gain necessary credibility. </p>

The PAMELA satellite experiment will soon be launched and during its 3 year mission perform measurement of charged particle fluxes in the cosmic radiation. PAMELA is specifically designed to identify antiprotons and positrons in the vast background of other charged particles. These antiparticle measurements will be performed using: a permanent magnet spectrometer, a scintillator based time of flight system, an electromagnetic imaging calorimeter, a transition radiation detector and a scintillator triggered neutron detector. There is also a scintillator based anticoincidence system to reject spurious triggers from out of acceptance events (developed and built at KTH). These detectors will allow the background in the antiproton and positron measurements to be significantly reduced, and PAMELA will thus be able to perform high precision measurements with unprecedented statistics and over a wide energy range, far surpassing any previous experiment. To determine the antiparticle identification and background rejection capability of the experiment, studies have been performed using simulations and data collected at particle beams. These studies have focused on: the proton rejection in positron measurements (using the calorimeter), contamination by locally produced pions in antiproton measurements and estimations of the expected statistics due to the energy dependence (caused by e.g. the geomagnetic field and the magnetic field in the spectrometer) of the gathering power. This work significantly extends previous studies of the PAMELA performance in antiparticle identification.

Spacecraft on interplanetary missions or advanced satellites orbiting the Earth all require propulsion systems to complete their missions. Introducing microelectromechanical systems technology to the space industry will not only reduce size and weight of the propulsion system, but can also increase the performance of the mission. Fluid handling systems are used in chemical and electric propulsion. Some components incorporated in a fluidic handling system are presented and evaluated in this work. Microsystems are very sensitive to contamination. Reliable, robust, and easily integrated filters were modeled, manufactured, and experimentally verified. A fluid connector, designed to withstand large temperature variations and aggressive propellants was manufactured and characterized. Similar designs was also be used as a thermally activated minute valve. The feasibility of a cold gas system for precise attitude control has been demonstrated. Steps towards improving the performance (from specific im-pulse 45 s) have been taken, by the integration of suspended heater elements. For electric propulsion, two thermally regulated flow restrictors have been characterized. These devices can fine-tune the propellant flow to e.g. an ion engine. A single-use valve using a soldered seal has also been successfully dem-onstrated within a pressure range of 5 to 100 bar. The microsystem-based propulsion systems of tomorrow’s spacecraft need to be demonstrated in space, in order to gain necessary credibility.

<p>The PAMELA satellite experiment will soon be launched and during its 3 year mission perform measurement of charged particle fluxes in the cosmic radiation. PAMELA is specifically designed to identify antiprotons and positrons in the vast background of other charged particles. These antiparticle measurements will be performed using: a permanent magnet spectrometer, a scintillator based time of flight system, an electromagnetic imaging calorimeter, a transition radiation detector and a scintillator triggered neutron detector. There is also a scintillator based anticoincidence system to reject spurious triggers from out of acceptance events (developed and built at KTH). These detectors will allow the background in the antiproton and positron measurements to be significantly reduced, and PAMELA will thus be able to perform high precision measurements with unprecedented statistics and over a wide energy range, far surpassing any previous experiment. To determine the antiparticle identification and background rejection capability of the experiment, studies have been performed using simulations and data collected at particle beams. These studies have focused on: the proton rejection in positron measurements (using the calorimeter), contamination by locally produced pions in antiproton measurements and estimations of the expected statistics due to the energy dependence (caused by e.g. the geomagnetic field and the magnetic field in the spectrometer) of the gathering power. This work significantly extends previous studies of the PAMELA performance in antiparticle identification.</p>

This thesis describes and evaluates the design of nanospacecraft based on advanced multifunctional microsystems building blocks. These systems bring substantial improvements of the performance of nanosatellites and enable new space exploration, e.g. interplanetary science missions using minute space probes. Microsystems, or microelectromechanical systems, allows for extreme miniaturization using heritage from IC industry. Reducing mass and volume of spacecraft gives large savings in terms of launch costs. Definition and categorization of system and module level features in multifunctional microsystems are used to derive a spacecraft optimization algorithm which is compatible with commonly used concurrent engineering methods. The miniaturization of modules enables modular spacecraft architectures comprising powerful multifunctional microsystems, which are applicable to satellites between 10 and 1000’s of kg. This kind of complete spacecraft architecture has been developed for the NanoSpace-1 technology demonstrator satellite. The spacecraft bus uses multifunctional design to enable distributed intelligence and autonomy, graceful degradation, functional surfaces, and distributed power systems. The increase in performance of the new spacecraft architecture as compared with conventional nanosatellites is orders of magnitudes in terms of power storage, scientific payload mass ratio, pointing stabilization, and long time space operation. This high-performance system-of-microsystems architecture has been successfully employed on two space robotic concepts: a miniaturized submersible vehicle for Jupiter’s Moon Europa and a miniaturized spherical robot. The submersible is enabled by miniaturization of electronics into 3-dimensional, vertically integrated multi-chip-modules together with new interconnection methods. These technologies enabled the submersible vehicle tube-shaped design within 20 cm length and 5 cm diameter. The spherical rover was developed for long range and networked science investigations of interplanetary bodies. The rover weighs 3.5 kg and is shown to endure direct reentry on Mars, which increases the ratio between the landed mobile payload mass and the initial mass in Mars orbit by a factor of 18.

Die Verknüpfung von geodätischen Raumtechniken wie GNSS, DORIS, SLR oder VLBI zur Ableitung eines geodätischen Referenzrahmens wie dem ITRF gelingt erst durch sogenannte Kolokationsstationen. Die geometrischen Beziehungen zwischen den betriebenen Raumtechniken sind dabei aus präzisen lokalen Vermessungen abzuleiten. Es wird ein Konzept zur automatisierten Bestimmung des IVS-Referenzpunktes am TWIN Radioteleskop Wettzell vorgestellt. Erste Untersuchungsergebnisse werden präsentiert.

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This thesis is about how space technology is experienced in the social domain and how its purpose is recast from different viewpoints. The author is an artist and the approach taken foregrounds qualities of experience and viewpoint in which artists have a particular investment. This approach opens up the ways that affect, agency and authorship cross social domains that are directly and indirectly associated with the production of space technologies. A key focus is a group project led by the author that was initiated in response to the launch in October 2008 of the Chandrayaan-1 spacecraft by the Indian Space Research Organisation (ISRO). The project took place in Bengaluru, India where the spacecraft was built. Taking the ambivalence that surrounds the uses and purposes of space technologies as a starting point, a description of the spacecraft is developed from a number of viewpoints, including the mission scientists, public media and the participants of the artist-led project. The interventionist strategies of the project shed light on the ways that technologies can be accessed through their imaginaries and this has significance for large-scale technologies, such as spacecraft, for which physical access is delimited and much of the infrastructure is invisible or hidden from public view. The thesis proposes ways of reinstating missed qualities of viewpoint and experience within the affective spaces of space technology through the imperative to articulate first-person engagements with the world that is bound into artistic interpretation. What is further proposed is that by picturing the interrelations and flows of space technology in social domains through the lenses of experience and viewpoint, a 'technographic picture' is created that then becomes available as a tool with which to re-imagine spacefaring. This is a crucial addition to discussions about the interplay between science, technology and society that recognises the intimate spaces at the core of such large-scale concepts. It offers a new transdisciplinary modality that incorporates an artistic approach with which to make sense of the structurally ambivalent pursuits of spacefaring.

Science and technology have a tendency to clump together in places where they spawn other forms of societal activities. Sometimes these places become famous through processes known as place-making, or the social construction of place. Because the scientific and technological activities affect the places, and the places conversely affect the science and technology, it is relevant to study how and why these connections emerge. This dissertation examines the particular case of the northern Swedish town of Kiruna, which has become known for being a `space town' because of its scientific, technological, and other activities that relate to the near space around the earth. The overall objective is to analyse the processes underlying the making of Kiruna as a space town in the period 1943--2000. Five parts make up the study. First is an examination of how the development of space physics research in Kiruna led to the setting up of a scientific observatory. The second part studies how the Swedish participation in the European Space Research Organisationmade Kiruna the place for a rocket base. Next follows an analysis of how local business efforts contributed to forming a new satellite technology business and the Space House office building. The fourth part concerns how the visions to establish a space `university' eventually led to the emergence of the Space Campus. Last is an epilogue that briefly analyses the space tourism efforts in Kiruna. A central finding is that the space town has emerged as the result of entwined processes where, on the one hand, ideas about the near space around the earth have led to new activities and physical structures, and, on the other hand, these new activities and built structures conversely have inspired to new ideas. Of importance is also the geographical place where these developments have occurred. Here, a reoccurring argument to placing the activities and structures in Kiruna was the town's geographically favourable location for specific scientific and technological activities. Another finding is that the development has gradually led to the emergence of a kind of identity or notion of Kiruna as a particular place for space activities. Although this form of place-making has occurred largely through spontaneous processes, it was also the result of intentional efforts. Together, these different place-making processes have formed the `space town' of Kiruna.