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MON3 is used as a propellant for the bipropellant thruster in the spacecraft propulsion. MON3 is Nitrogen Tetroxide (N2H4) with 3wt% solution of NO. Heat transfer characteristics with boiling of the MON3 have been measured. The critical heat transfer was identified when the superheat temperature was around 50 ℃ (degree C) under different flow parameters. Pressure vibration from 8 to 22Hz frequency was observed in the specific flow parameters during the boiling of MON3. These frequencies are in good agreement with that of combustion perturbations observed in the test injector which simulated the actual bipropellant thrusters., 資料番号: PA1410027000

We here propose a nuclear electric propulsion system that adopts a small nuclear reactor, MHD (Magneto-Hydro-Dynamics) energy conversion system, ceramic laser, and magnetic nozzles. The present status of the system design is presented along with the future plan. The system is a combination of technologies that Japan has been playing the leading role in their development., 資料番号: AA0063739011, レポート番号: JAXA-SP-07-020

通信ビジネスの競争は激しく、商用静止衛星の運用はさらなる効率化およびコスト削減が求められている。軌道運用も例外ではなく、運用の効率化およびコスト削減が必須であり、実際の衛星運用でどのような南北制御ストラテジおよび東西制御ストラテジが採用されているか紹介する。Bipropスラスタの軌道制御ストラテジは、すでに効率化・コスト削減が進められてきており、今後さらなる最適化を行うためには電気推進などの新しいアクチュエーターの衛星搭載が求められている。電気推進はさまざまなメリットがある反面、衛星運用の負荷を増加させるデメリットもあり、今後、衛星運用のシステムとして最適化が望まれる。, The number of spacecraft in geostationary orbit is increasing and the competition of the communication service are also harder than before. In this environment spacecraft operation is need more efficient and cost reduction than before. Not the exception of an orbit control, spacecraft operator has to keep considering more effective maneuver strategy. In this report, current maneuver strategy of Bipropellant thruster satellite is introduced and then a request as spacecraft operator for a new actuator of the electric propulsion is shown., 資料番号: AA0063739003, レポート番号: JAXA-SP-07-020

Orbital dynamics of consecutive, low-thrust trajectories is overviewed. Focusing on the thrust direction constraints (e.g., transversal and radial thrust direction constraints), various trajectory design strategies of low-thrust missions are summarized with concrete examples., 資料番号: AA0063739006, レポート番号: JAXA-SP-07-020

日本独自のシステムとして、長寿命・高信頼を特徴とするマイクロ波放電式イオンエンジンが開発され、「はやぶさ」小惑星探査機に応用された。これ以外にも、DCアークジェット、MPD(Magneto Plasma Dynamic)アークジェット、ホールスラスタなど、各種電気推進が研究開発されている。これらは、従来の化学推進より高い噴射速度をもち、効率的な推進剤利用によって宇宙機の長寿命化に貢献する。また、慣性(弾道)飛行していたこれまでの「人工惑星」「人工衛星」とは異なり、電気推進を搭載する宇宙機は、動力航行する能力を持ち、大型ロケットを用いずとも遠方への到達を可能にし、「宇宙船」に分類されるべき新しい技術である。今後立案される深宇宙探査においては、数100kgのペイロードを目的天体へ運ぶ、1トン級の宇宙機の実現が見込まれる。これは、地球表面と近地球を往復する旧来の宇宙輸送系に対して、近地球と深宇宙を結ぶ「深宇宙輸送システム」という新しい概念を導くであろう。, The microwave discharge ion engine mu 10 has long life and high reliability because of electrode-less plasma generation in both the ion generator and the neutralizer. Four mu 10s, each generating a thrust of 8 mN, propelled Hayabusa explorer to asteroid Itokawa. Electric propulsions including DC arcjets, MPD (Magneto Plasma Dynamic) arcjets, Hall thrusters as well as ion engines generate jets much faster than those of chemical rockets and make spacecraft fly by power in deep space so as to reach planets and objects. Diverse space technologies such as the orbit determination, orbit planning, automation, space communication, space propulsion, and so on, will establish the new concept and real system on 'Deep Space Transportation' between near Earth and deep space progressing from Space Transportation System between Earth surface and LEO (Low Earth Orbit)/GEO (Geostationary Orbit)., 資料番号: AA0063223018, レポート番号: JAXA-SP-06-015

Space tether technology is reviewed for its status including a sounding rocket experiment deploying one-kilometer electro-dynamic tether, a small satellite experiment of tethered orbit-elevation without fuel, tethered space solar power satellite equipped with 10 km tether, and a sample-return mission from an asteroid employing a harpoon-penetrating tape-tethered corer. Future of space tether technology is also foreseen as 'free-lunch' Jovian tour, electro-dynamic re-boost, electro-dynamic tether de-orbit of satellite., 資料番号: AA0063349028

KODAMA (DRTS) was launched in 2002, and have been operated successfully on the Geostationary Orbit. Since 2004, one of the 1N thrusters that is used for East-West station keeping and momentum wheel unloading, had indicated lower thrust than that of the others. The thrust degradation is larger than the nominal pace, therefore, we started investigating the cause of the thrust degradation with FTA. We concluded that it is most probable that the thruster nozzle throat is blocked with a catalyst granule, and small catalyst particles which are produced in the catalyst bed are gathered on it, and they narrow the throat and make the thrust small. We conducted the experimental investigation of catalyst granule blockage and particle gathering with a simulated nozzle throat gas flow. We confirmed that the phenomena can occur on the orbit., 資料番号: AA0049500066, レポート番号: JAXA-SP-06-006

Rocket Based Combined-Cycle (RBCC) engines are currently being explored as advanced propulsion for space transportation. JAXA has been conducting RBCC engine research by using various experimental facilities. In order to clarify the experimental results and contribute to the improvement of designing, the analysis of the RBCC engine in an ejector-jet mode was carried out using the CFD (Computerized Fluid Dynamics) code developed in-house for unstructured grids. CFD replicated the basic flow structures in regard with barrel shocks and pseudo-shock waves. Two cases of Mach numbers (i.e., M = 1, 1.1) entering to the combustor were simulated and remarkable differences were found on the subsonic areas in the flowfields. The effect of Mach number was found to be one of the important parameters for better match to the experimental data. Vorticity and mixing were also investigated. In addition to the transverse vorticity, the streamwise vorticity were generated in the air flow, and they stirred and affected the nitrogen/air mixing., 資料番号: AA0049500027, レポート番号: JAXA-SP-06-006

Water-Energy-Cycle Space Propulsion System was defined as a space system supporting long-term and large-scale space activity. On the test stand which can change a posture, the principle model was assembled, the posture was changed in +/- 1 G, and the performance of a principle model was compared. As a result of experimenting in +/- 1 G, when it operated normally in any case and it did separation of gas and a liquid on the level of each subsystem, under terrestrial gravity environment, it came out enough and a certain thing was understood. The feel referred to as operating satisfactory also under the micro-gravity environment of space was acquired as a result of consideration. The Proton Exchange Membrane (PEM) electrolyzer and the fuel cell which were used for the experiment made the regenerative fuel cell as an experiment, and used the single cell for this research in normal temperature. The phenomenon of ignition delay has been improved by the device of injection structure, and adjustment of injection timing in the catalyst ignition experiment of hydrogen/oxygen thruster. Moreover, it turns out that water adheres to the catalyst layer surface after a combustion end., 資料番号: AA0049500064, レポート番号: JAXA-SP-06-006

This paper describes the status of the next-generation xenon-ion-engine research at IAT (The Institute of Aerospace Technology). A set of ion extraction grids, which had been pressed improperly in FY2004, was pressed again to obtain the designed shapes after reviewing the pressing process. Another set of ion extraction grids, whose peripheral regions were masked, was manufactured after this. Both results were unsatisfactory and it was finally found that important knowledge had been lost in the pressing process. However, each grid set was tested as a part of an ion thruster. A main cathode continuous operation to confirm the life of an impregnated cathode has begun and is continuing without any symptom of degradation in the cathode. Four neutralizers including two graphite-orifice-plate types were evaluated individually as a part of an ion thruster. One of the graphite-orifice-plate types showed satisfactory characteristics., 資料番号: AA0049500063, レポート番号: JAXA-SP-06-006

The Electron Cyclotron Resonance (ECR) microwave discharge Ion Engine System (IES) onboard Hayabusa has been operated in deep space. IES consists of four pair of ion thrusters and neutralizers on a rectangle shaped gimbals plate. Each engine has an exhaust nozzle of 10 cm in diameter and three grids made of Carbon-Carbon composite material. Weight of 66.2 kg Xenon propellant was loaded in a titanium alloy tank of 51 liter in volume before the launch of Hayabusa in April 2003. ECR microwave discharge generates Xenon plasma, and electric static field of 1,500 volts accelerates Xenon ions to over 30 km/sec exhaust velocity. Each engine generates thrust of 8 mN, specific impulse of 3,200 seconds, and consumes 350 watts of electric power. During the three-year flight operation, IES generated a delta-V of 1,400 m/s while consuming 22 kg Xenon propellant. The total operation time of IES is 25,900 hours. IES successfully propelled Hayabusa to the asteroid Itokawa on September 2005. During the three-month period, in-site activities such as scientific observation of Itokawa and collection of asteroid sample materials were carried out. Now Hayabusa is cruising on the Itokawa orbit waiting for the time of departure. IES is ready to propel Hayabusa back home to the Earth. IES will be operated again in early next year and Hayabusa will arrive to the Earth in middle of 2010., 資料番号: AA0049500002, レポート番号: JAXA-SP-06-006

The Japan Aerospace Exploration Agency (JAXA) is now developing a 20N-class thruster valve for spacecraft propulsion systems. We intend to develop this valve with the high reliability, and a robust and durable design. The suspended armature type was chosen for the base design of the new 20N valve based on the results of a trade-off study. Experiments and analysis were performed for the critical parts and manufacturing process. The results enabled us to manufacture a prototype model with single type 20N thruster valves. Good results were obtained in functional tests. We will now proceed to the next phase and complete the detailed design for series redundancy and prepare for the qualification test., 資料番号: AA0049500062, レポート番号: JAXA-SP-06-006

In recent days, the propulsion subsystem of spacecraft is required to achieve higher reliability and performance simultaneously. The performance of thrusters has a great impact to the weight budget of the propulsion subsystem, because high performance thruster can reduce the quantity of propellant by high-temperature combustion. If the Thruster improves performance, the spacecraft can save the weight. Ceramics is one of the most promising materials for the spacecraft on-board thrusters because of their superior performance on heat resistance. However they are brittle, and thus they have not been used in the real flight missions so far. It might be fractured due to mechanical vibration at launch, thermal shock at firing, or by collision of space debris. This paper summarizes the status of development, in which a prototype 500 N bipropellant thruster made of Si-based monolithic ceramic has been developed., 資料番号: AA0049500061, レポート番号: JAXA-SP-06-006

In the past, space propulsion systems were usually composed by accumulating the optimum design results for each component device. Therefore, 'system reliability level' was measured by long-time development tests. Recently, the new design method is required to predict 'system reliability level' at the conceptual design phase, to grasp and to optimize the distribution of 'risks and margins' because attainable 'system reliability level' strongly depends on its basic concept. This paper describes some sample approaches to measure 'system reliability level', focusing on analytical modeling of failure mechanism for rocket engine dynamic simulator. Some design parameters are picked up to understand where and how their dispersion makes an effect in the whole systems and to control the total system robustness., 資料番号: AA0049500017, レポート番号: JAXA-SP-06-006

Our 'Space Propulsion and Power System Using Water-Energy-Cycle' stores hydrogen and oxygen electrolyzed from water by solar cells during sunshine period, and as the reverse cycle, these gases provided into fuel cells generate electrical power and water during sunshade period. The stored hydrogen and oxygen are also usable as rocket propellants, and furthermore, the water and oxygen are available for the life support system at emergencies of manned space activities. Our study is to design a propulsion & power system originated from safe and non-toxic water that is one of the simplest compound on Earth, and to perform ground-based experimental testing toward a sub-scale model. The performance verification in the Space Station is necessary for the end but based upon the fundamental researches so far, we estimate the flight performances from testing such as optimization of single-cell performance, configuration of electrolysis and fuel-cell (reversible single cell or two separate cells), rocket engine combustion in vacuum, overall systems checkout, and weightlessness simulation (on the tri-axially relatable test-stand)., 資料番号: AA0049121014

The system firing test for HTV (H-2 Transfer Vehicle) was performed on June thru August, 2004. The result shows that the system provides approximately 50 percent thrust during short impulse RCS firings using four forward thrusters with GHe saturated propellant., 資料番号: AA0049056019, レポート番号: JAXA-SP-05-010

RAMS (Residual Acceleration Measurement System) is sub-payload of M-V Rocket NO.6. This purpose is measurement of residual acceleration of B2 & B3 motor of M-V. This time, we get a long time data of the acceleration by means of RAMS & spacecraft's acceleration. This data is useful for analysis of Spacecraft separation, tracking of M-V. This paper describes the results of measurement of RAMS., 資料番号: AA0049056022, レポート番号: JAXA-SP-05-010

This paper describes the status of the next-generation xenon-ion-engine research at ISTA (The Institute of Space Technology and Aeronautics). A set of ion extraction grids which would be ready for producing 200-mN thrust with a shorter aging period than ever was manufactured. A problem that the heater of a graphite-orifice hollow cathode failed in repeated heating was figured out. Discharge can start in five minutes from the onset of heating the main cathode. The only subject left in the main cathode life is confirming the life of the impregnated cathode. Research and Development of graphite-orifice-hollow-cathode neutralizer started. The output filter of the laboratory-model discharge supply was modified to reduce ripples in discharge current. An ion target was modified to reduce the deposition rate at the ion thruster., 資料番号: AA0049054026, レポート番号: JAXA-SP-05-008

The Institute of Space and Astronautical Science (ISAS) of Japan Aerospace Exploration Agency (JAXA) is studying a new magnetic sail propulsion system, called MagSail since 2002. A MagSail travels interplanetary space by capturing the energy of the solar wind. A MagSail realizes analogous interactions between the solar wind and an artificial magnetic field produced around a spacecraft, to obtain a force in the direction of the solar wind. In order to demonstrate the momentum transfer process of the magnetic sail, we have started a preliminary experiment. In the experimental studies, some strong interactions between the high-density (10(exp 19)/cu m) and high velocity (17 km/s) plasma flow and an artificial magnetic field of about 1 T was observed. Now, we are designing and manufacturing an experimental simulator of the magnetic sail propulsion system. Especially, development of a solar wind simulator will be a key issue for the MagSail experiments. We selected an MPD arcjet device to be the solar wind simulator. And a new twelve L-C ladder Pulse Forming Network (PFN) is also now in manufacturing and testing. In this report, a development status of the MPD solar wind simulator for the MagSail experiment is described and some experimental results are reported., 資料番号: AA0049054024, レポート番号: JAXA-SP-05-008

資料番号: AA0063347018

A series of numerical simulations of electromagnetic interaction between the solar wind and the moderately-sized magnetic sails is conducted to clarify the characteristics of reaction forces on the magnetic sail when its characteristic scale is reduced below the continuum limit at which the MHD approximations of the plasma flow fail. The hybrid particle-in-cell (PIC) method is used to take into account the non-continuum effects of the electromagnetic interactions between the flow and the magnetic field. The magnetic dipole intensity was changed so that the characteristic size of the magnetic sail changes from several hundred meters to few thousand kilometers. The results show that the drag coefficient of the magnetic sail even increases as the ratio of the ion Larmor radius to the characteristic scale of the magnetic field becomes greater than unity. This suggests that the moderately-sized magnetic sails, which are more realistic than conventional gigantic magnetic sails of several thousand kilometers from an engineering standpoint, can be one of the candidates of propulsion system for deep space missions., 資料番号: AA0048089004

Spacecraft's valves are important and key components for the mission success. But it is an undeniable fact that there are lots of failures in valves. So these valves are required to be reliable and robust at all times. This paper describes the outline of the present study for reliability improvement of spacecraft's valves and the development status of 20N-class thruster valve and Latching valve., 資料番号: AA0048057037, レポート番号: JAXA-RM-04-010

資料番号: AA0047899045

資料番号: AA0047899142

資料番号: AA0047899046

A water cycle space propulsion system has been studied for a space flight test onboard the space station Japanese Experimental Module KIBOU. The water cycle space propulsion system is characterized as a clean, safe and non-toxic system being friendly to the personnel, because the power source is based upon the solar energy in space and the water is the working fluid on the ground. In the future, the water cycle can be merged into a life support system in space as well as the propulsion and power system. This test bed on the KIBOU will provide a 250 W water electrolysis capability and the corresponding power for fuel cell as its reverse cycle. During the sunshine, the water electrolysis process is activated for 45 min of half a revolution around the earth, and the rest of the revolution during the sunshade is dedicated for a propulsion experiment using GH2/GO2 and a fuel cell experiment. The expected installation is on a pallet-type bus structure interface with a deployable exclusive solar array for this experiment and other common interfaces to the exposed facility of KIBOU. Presently, some basic experiments were finished on the ground for a single reversible cell at a room temperature environment. The fuel cell mode provides 0.1 A/sq cm current density at output voltage of 0.6 V while the water electrolysis mode provides 0.5 g/h throughput at 0.3 W/sq cm. All the water cycle system is placed on a 2-axis rotatable circular plate which can change the gravitational direction to the system so as to apply +/- 1 G. On the other hand, the ignition capability of GH2/GO2 has been greatly improved using a catalytic combustion method at the upstream of the main combustion chamber where the secondary GH2 is injected. So-called an ignition delay has been completely eliminated from the present ignition experiments. The water cycle space propulsion system will be composed of a 2 N GH2/GO2 thruster and two cells. One is used for fuel cell and the other is for electrolysis. The water filling/drain, if adopted a single cell configuration, is very much troublesome process. The pressurization of both 16 litter H2 and 8 litter O2 gaseous tanks should be limited less than 7 MPa because of the safety requirement for pressure vessels. The water tank is 4 litter. To prevent inadvertent mechanical disturbances to the ISS, the generated two thrusts are aligned to the opposite direction. The thrusting period is about 6 seconds per one revolution around the earth., 資料番号: AA0047275016

A water-energy-cycle space propulsion system is a multi-functional system, which provides electric energy storage, propulsion and thermal energy supply. The advantage to apply a water cycle system to the universe plant factory is as the next. 1) Water for the cultivation can supply it from the water-energy-cycle system. 2) Oxygen gas is available for the cultivation. 3) Hydrogen gas is available for the reduction response. 4) The heat which occurs in the fuel cells, and heat due to the combustion are available for heating. It was considered to apply this system in the plant factory as a part of the research of the water-energy-cycle system. Surveyed were commercial plant factories and their amount of electric power consumption. Then, calculated was the size of the ground experiment system. Because resources can be shared, the space plant factory is suitable for the water-energy-cycle system. Various subjects must be solved to make a plant factory and a water-energy-cycle system work in the micro gravity environment. The space plant factory using water-energy-cycle system has many advantages and is feasible. It is wanted to begin the ground experiment from now on., 資料番号: AA0047275017

資料番号: AA0045913018

資料番号: AA0033392036

資料番号: AA0033392079

航空宇宙技術研究所 24-26 Jun. 1998 東京 日本, National Aerospace Laboratory 24-26 Jun. 1998 Tokyo Japan, NALにおいて数値流体力学(CFD)を中心とする数値シミュレーション技術の新しい動向についての特別企画を実行し、多くの分野についての数値シミュレーションの現状と将来を展望した。それぞれの分野での討論会、パネルディスカッションおよびワークショップにおいて、超音速輸送機(SST)、ヘリコプタ回転翼、高エンタルピー流れ、宇宙推進、航空推進、および乱流の遷移構造とその予知、の6分野のテーマについての65の研究を記述した。, A special meeting on new trends of the numerical simulation technologies centered around Computational Fluid Dynamics (CFD) was organized and held at NAL, in which the current status and the future perspective of the technologies over a wide range of research areas were presented. In the discussions, panel discussions and workshops for each area, 65 papers of 6 fields are described, namely, Supersonic Transport (SST), helicopter rotors, high enthalpy flows, spacecraft propulsion, aircraft propulsion, and the transition structure of turbulence and its prediction., 資料番号: AA0001958000, レポート番号: NAL SP-41

宇宙利用シンポジウム 日本学術会議.宇宙航空研究開発機構 20080117-20080118 東京 日本, Space Utilization Symposium Science Council of Japan. Japan Aerospace Exploration Agency, 20080117-20080118, Tokyo, Japan, 資料番号: AA0063706000

低推力・連続加速を用いた宇宙ミッションに関する研究会 宇宙航空研究開発機構 20071102 東京 日本, Meeting on the Study of Space Missions Propelled by Low-Thrust and Sustained Acceleration Japan Aerospace Exploration Agency 20071102 Tokyo Japan, 資料番号: AA0063739000, レポート番号: JAXA-SP-07-020

将来宇宙輸送ワークショップ 宇宙航空研究開発機構 20070310 宮城 日本, Workshop on Future Space Transportation Japan Aerospace Exploration Agency 20070310 Miyagi Japan, 資料番号: AA0063586000, レポート番号: JAXA-SP-07-004

資料番号: AA0049500000, レポート番号: JAXA-SP-06-006

宇宙エネルギーシンポジウム 宇宙航空研究開発機構 20050307 神奈川 日本, Space Energy Symposium Japan Aerospace Exploration Agency 20050307 Kanagawa Japan, 資料番号: AA0049120000

Accelerating research and development work on advanced space engines, such as scramjet engines and reusable rocket engines, requires cooperation in experiments and calculations. In addition to the existing large scale experimental facilities at the Kakuda Space Propulsion Laboratory, such as the Ramjet Engine Test Facility (RJTF) and High Enthalpy Shock Tunnel (HIEST), a new super computing system was introduced in March of 1997. The system is a numerical simulator for space propulsion engines, dubbed the Numerical Space Engine (NSE). The NSE system employs the new concept of a virtual engine test bed allowing researchers to simulate easily a virtual space engine exactly like in an engine test bed. This is made possible by new computational technology such as real-time visualization, steering, and multimedia technologies. The NSE system was replaced in March 2002 with an NEC SX6/64CPU. This paper provides an overview of the replaced Numerical Space Engine., 資料番号: AA0047426000, レポート番号: JAXA-RM-03-031

Accelerating research and development work on advanced space engines, such as scramjet engines and reusable rocket engines, requires co-operation for experiments and calculations. In addition to the existing large scale experimental facilities at the Kakuda Research Center, such as Ramjet engine Test Facility (RJTF) and High Enthalpy Shock Tunnel (HIEST), a new super computing system was introduced in March of 1997. The system is a numerical simulator for space propulsion engines, dubbed the Numerical Space Engine (NSE). The NSE system employs the new concept of a virtual engine test bed allowing researchers to simulate easily a virtual space engine just like in an engine test bed. This is made possible by new computational technology, such as real-time visualization, steering, and multimedia technologies. The main server of the NSE is a vector parallel supercomputer, the NEC SX4/25CPU. The NSE will be used to investigate various phenomena inside the engines. Research and development work at the experimental facilities is expected to be greatly assisted by the NSE. This paper provides an overview of the Numerical Space Engine., 資料番号: AA0046105000, レポート番号: NAL TM-768

並列ベクトル計算機の自動並列化機能はユーザのプログラムコーディングの負担を軽減するのに有効である。共有メモリ方式の並列ベクトル計算機では主にDOループを対象に自動並列化が行われている。しかし、分散メモリ方式の並列ベクトル計算機では実現されていない。本報告は、その自動並列化機能を用いて2本の宇宙推進系プログラムの並列処理を行い、それらの実行結果の比較・検討を行ったものである。結果として、以下のことが定量的に得られた。 (1)相対的に並列化率が大きく、並列効率のよいプログラムは、性能向上率が大きい。 (2)使用したPE台数に対する予測値と実測値との差に最も影響を与えたものはメモリ競合時間であった。また、メモリ競合時間の割合は並列化率の高いプログラムの方が低いプログラムより高い。, An automatic parallelization function is effective for the reduction of parallel program coding problems. In a shared-memory vector-parallel computer, Fortran program DO loops are automatically parallelized, generally, but this does not occur in a distributed-memory vector-parallel computer. This report describes the comparison and the investigation of the parallel processing time of two programs on space propulsion system by an automatic parallelization function of the SX-3R system. As a result, the following is quantitatively obtained. (1) The performance efficiency of a program parallelized relatively highly and efficiently is large. (2) The memory conflict time is the longest in the difference between an estimated time and a measured time. And ratio of the conflict time per the difference time of a highly parallelized program is higher than for a low one., 資料番号: AA0032789000, レポート番号: NAL TR-1430

Two projects are introduced in this paper to verify the performance of space tether technology. A sounding rocket will be launched in the summer of 2009 to deploy a bare electro-dynamic tape tether having a length of 300 m. The other project to verify the space tether technology is a small satellite to deploy a bare 25 km electro-dynamic tape tether, and the launch is expected in 2013 with employing a new solid motor rocket. These verifications of tether technology will lead to a large numbers of applications of space tether technology and some future projects are also introduced., 資料番号: AA0063706026

We are conducting the research and development of 50 kg to 100 kg class micro satellite propulsion system. Xenon cold gas jet system was selected by the conceptual study, and some key components have been studied and developed. In FY2005, the propulsion system experimental model was developed., 資料番号: AA0049500067, レポート番号: JAXA-SP-06-006