Atsushi Sasaki
(Hachinohe Institute of Technology, Japan)

We designed an low-power electrothermal pulsed plasma thruster (ET-PPT), named HIT-A machine, with a propellant feeding mechanism using solid propellant i.e., Teflon (poly-tetra fluoro-ethylene (PTFE)), referring results of preliminary study. HIT-A is made as the use for low-power, light weight and small-sized pulsed plasma thruster. Both the ET-PPT and capacitors were mounted on a thrust stand with a 1-mm-long perpendicular pendulum which was developed for a precise measurement of an impulse bit. However, thrust performance gradually decreased with shot number because of uneven receding of a PTFE surface. In order to obtain unsteady phenomena, we investigate numerical simulation of discharge, plasma particle flow, heat transfer to the PTFE, heat conduction inside the PTFE and ablation of PTFE. It turns out that the impulse bit and mass shot decrease uniformly for the nozzle diameter, while the thrust, the specific impulse and thrust efficiency changes parabolically for the nozzle diameter, and these have a maximum. This implies that the performances for nozzle diameter bear an optimization point. A calculated result is compared with experimental data of HIT-A.

Makoto Nose
(Osaka Institute of Technology, Japan)

Experimental studies were carried out to examine the effect of hollow anode configuration on performance of 1-kW class anode-layer Hall thruster TALT-2. The thruster was operated with a divergent-type hollow anode. The results showed that some increment in thrust and thrust efficiency was realized by changing the width of hollow anode. With a wider hollow anode the thrust efficiency reached 0.58 with a mass flow rate of 4 mg/s at a discharge voltage of 400 V. This is expected because of more efficient ionization and lower wall losses in a wider anode.

Masato Tanaka
(Osaka Institute of Technology, Japan)

The Project of Osaka Institute of Technology Electric-Rocket-Engine onboard Small Space Ship (PROITERES) was started at Osaka Institute of Technology in 2007. In PROITERES, a nano-satellite with electrothermal pulsed plasma thrusters (PPTs) will be launched in 2011. The main mission is powered flight of nano-satellite by electric thruster. An unsteady numerical simulation was carried out to investigate physical phenomena in the discharge system including plasma and discharge electric circuit and to predict performance characteristics for electrothermal PPTs. The calculated Mach number intensively increased downstream from the discharge cavity exit; that is, the supersonic flow was established in the nozzle cathode. Both the calculated impulse bit and mass shot were higher than the measured ones with a discharge energy per one shot of 2.4 J/s for the satellite although with 14.6 J/s the calculated results agreed well with the measured ones. And the calculated results of 40,000 shots qualitatively agreed well with the measured ones.

Hiroki Sato
(The Graduate University for Advanced Studies, Japan)

Plasma flowfields and performances of an MPD arcjet (mass flowrate of 0.4 g/s and the discharge current of 5 kA), which uses hydrogen as apropellant, are studied by solving magnetoplasmadynamic equations. Inthe case of three-temperature model including the translation Ttr,vibration Tvib, electron Te temperatures, the calculated thrust,specific impulse and thrust efficiency are 7.49 N, 1911s and 21.3%,respectively. The calculated flow shows a temperature nonequilibriumstate (Te = 2.53 eV, Tvib = 1.32 eV, Ttr = 0.60 eV) near the inlet ofthe MPD arcjet, and it is found that coupling between the electron andthe vibrational energy is stronger than that between the electron andthe translational energy. Because the discharge current path by thethree-temperature model can explain the important feature of hydrogenMPD (current expansion to the downstream), the three-temperature modelcan reproduce the experimental results.

Naoji Yamamoto
(Kyushu University, Japan)

For the application of Hall thrusters to the small satellite, we have been developing a low power Hall thruster. As an initial test, we evaluated the thrust performance of 50 W class End type Hall thruster developed at Kyushu University. The outer diameter and length of the acceleration channel are 18 mm and 7 mm, respectively. A thrust stand was developed, since estimated thrust is 1-3 mN, which is too small to measure conventional thrust stand for Hall thrusts. The error of this thrust stand is less than 3% at 1 mN calibration. The thrust, the discharge current and the thrust efficiency at xenon mass flow rate of 0.27 mg/s and discharge voltage of 150 V were 0.76 mN, 0.24 A and 4.2%, respectively. At mass flow rate of 0.41 mg/s, the thrust increased with an increase in discharge voltage and the thrust became 1.6 mN at discharge voltage of 250 V. For the improvement of the thrust performance, the submitted paper will discuss the experimental result using a miniature two-stage Hall thruster. For the plasma production, microwave discharge is used

Yoshiyuki Takao
(Nishinippon Institute of Technology, Japan)

A microwave discharged ion thruster of 5cm size has been fabricated and tested in Nishinippon Institute of Technology and Kyushu University. We have already developed 10cm and 2cm size microwave discharge type ion thrusters. The development of 5cm one on the basis of the previous ones is conducted to know the plasma behavior in the discharge chamber of the thruster and to confirm the design approach to small scale microwave discharge ion thrusters.

Hiroyuki Shiraishi
(Daido University, Japan)

Laser-supported Detonation (LSD), one type of Laser-supported Plasma (LSP), is considered as one of the most important phenomena because it can generate high pressure and high temperature for laser absorption. In this study, we numerically simulate LSPs, which are categorized either LSD or Laser-supported Combustion-wave (LSC), using thermal-nonequilibrium model. For the analysis model, 2-temperature (heavy particle temperature and electron temperature) model has been applied because the electronic mode is firstly excited in laser absorption and a thermal non-equilibrium state easily arises. In the numerical analyses of LSD, especially, laser absorption model is also important. Therefore, Multiply-charged ionization model is considered for describing an accurate ionization process and for precisely evaluating LSC-LSD thresholds.

Yuki Okawa
(University of Kumamoto, Japan)

Exploding Wire-Pulsed Plasma Thruster (EW-PPT) is the satellite thruster using a wire explosion. Wire explosion is the phenomenon that wire is exploded by thermal expansion due to high-voltage pulse current from capacitor bank (charging voltage : about 280V, capacity of condenser : 680-5440μF) . The produced expansion gasses after exploding a wire contribute as propulsion of thruster. Electrical Propulsion System such as Pulsed Plasma Thruster has high specific impulse but dose not have high thrust. So, it is had by microsatellite. Microsatellite can not generate high electric power. For this reason, this paper is searched by using low voltage. Meanwhile, metallic wires have some properties. For example, Density, Melt point, Electric conductivity, specific heat capacity and so no. To consider properties of wires, this research uses 9 kinds of metallic wires. They are Au, Ag ,Cu, Al, Pb, Ti, Ni, W and Pt. Therefore, purpose of this paper is to report appropriate wire as fuel by changing capacity of condenser with about 280 voltage.

Katsunori Ishii
(Shizuoka University, Japan)

Space propulsion systems are classified broadly into two categories; chemical propulsion and electric propulsion. Features of the former are high thrust and low specific impulse and those of the latter are low thrust and high specific impulse. One of them or their combination is chosen to accord with mission requirements. However, since in current propulsion systems whole propellant is carried from the earth, the ratio of the propellant to the total weight increases with the increase in the mission term, resulting in the lower payload ratio. Then, in our group, a novel space thruster whose propellant is refueled in space has been studied. As propellant, we focus on stardust at the asteroid belt between Mars and Jupiter. Star dust is a few micron to tens micron in diameter, and composed of carbon, silicon, iron and magnesium etc. A mechanism of our thruster is as follows. Firstly dust grains are injected in a plasma. Since the electron thermal speed is much faster than the ion one, the dust grains are negatively charged. Then, charged dust grains are accelerated electro-statically by a high voltage grid.In this study, a novel propellant feeding system is developed and its performances are tested.

Yuya Oshio
(The Graduate University for Advanced Studies, Japan)

One of the next-generation interplanetary propulsion system is Magnetic sail (Magsail) capturing the solar wind energy. Magsail consists of only a coil and obtain a thrust by the interaction between the solar wind and an artificial magnetic field produced by the coil. Magsail was studied by a numerical simulation and a laboratory experiment. The scale-model experiment of Magsail in laboratory consists of the magnetoplasmadynamic arcjet simulating solar wind and the coil. In recent research, the direct measurement of the thrust of Magsail is performed by using the pendulum type thrust stand in the scale-model experiment. Although the thrust measured by the pendulum type thrust stand is in agreement with the thrust by the numerical simulation result and is high reliability, this method can measure only an impulse. It is necessary to use another thrust measurement method for revealing the thrust characteristics of Magsail in detail, which is torque and unsteady characteristics etc. In this study, we developed a new type thrust stand. Measurement of the time-resolved thrust is possible by this thrust stand.

Tatsuya Muramoto
(Okayama University of Science, Japan)

Ion engine had been developed by JAXA for a long-term space transportation, such as the Hayabusa probe, with minimum propellant. The ion engine has a lifetime that is dominated by the deformation of the carbon accelerator grid in Xe ion flow. Low-energy sputtering and redeposition of sputtered particles bring the deformation of the carbon device. We study the particle balance on the carbon surface through MD simulation. The differential sputtering yield by the low-energy Xe bombardment depends on the incident angle. Sputtered particles by low-energy ion bombardment have the memory of the ion because they go through only a few collisions. The self-sputtering in an amorphous surface is enhanced than that in diamond crystal surfaces. The mean redeposition rate in the energy up to 100eV is about 0.94 at normal incidence and 0.82 - 0.75 taking account of incident angle distributions.

Tomohiko Asai
(Nihon University, Japan)

Magnetized plasma torus generated by the RMF technique has been proposed as an effective shielding method for innovative space transportations e.g. the space elevator, from energetic particle radiations in, for example Van Allen radiation belts. The plasma current driven by the RMF is expected to deflect the energetic particles. Though a torus plasma is generated around the center of the antennae in all existing RMF experiments and then expands to the external region outside the antennae, the central region should be occupied by the main body of the space vessel for the application as a "plasma shield". Therefore, demonstrations of effective plasma formation and sustainment of plasma current with an internal object are key issues for the development research of the RMF plasma shield. In this work, plasma formation and current drive have been experimentally demonstrated in a vacuum tank by using a scale model of RMF antenna sets with a dummy space elevator vessel in the center. Improvement of the plasma formation by a magnetic circuit consists of a high-permeability material has also been investigated. Besides improvement of formation efficiency, this can reduce penetration of the magnetic field into the core region of the vessel

Yoshio Aoki
(Nihon University, Japan)

In the present study, the probe climber who is the equipment who proposes the stratosphere elevator as a platform for a long-term the atmosphere observation and the remote sensing, and composes it is examined. In this report, climbing outdoor experiment up to 300m is carried out by using a remote-controlled probe climber's prototype model as shown in the photograph, and the developed probe climber model is evaluated for climbing performance. Moreover, the response vibration of the tether by the wind force and the reaction force by the climbing mechanism, etc. are considered and examined.

Junko Matsuyama
(JAXA, Japan)

JAXA developed the Micro-Particle Capturer and Space Environment Exposure Device for material exposure experiments on the exterior of the Japanese Experiment Module (JEM/MPAC&SEED) on the ISS. The device was exposed to the space environment for 8 months and retrieved via EVA in April 2010. After retrieval, the surface of the device, captured material, and debris signatures were analyzed. The entire external surface of the aluminum alloy frame became brown except for the unexposed area covered by washers. Some colored spots and small particles were detected on surface of the frame. The colored spots of optically observed contaminants are non-metallic (white, black, brown, etc.) and metallic. The coloring tendency is similar to that of past experiments, such as SM/MPAC&SEED*. The effect of ultraviolet (UV) radiation will be confirmed by comparison to the ground irradiation test sample. Additionally, the solar absorptance coefficient and the infrared emissivity of the thermal control film on the device will be measured. The contaminants will be analyzed by X-ray photoelectron spectroscopy (XPS) and time-of-flight secondary ion mass spectroscopy (TOF-SIMS). The surface and depth composition of contaminations on the aluminum frame surface of this device after space exposure will be also analyzed. This paper will introduce the results.

Pramod Purohit
(NITTTR Shamla Hills, India)

Abstract: The concept of space weather is now widely used in quantitative descriptions of the physical changes in the near-Earth space environment in response to variations in solar radiation, solar plasma ejection, and the electromagnetic status of the interplanetary medium. In the last decade, the utility of radio wave transmissions from the Global Positioning System (GPS) satellites in obtaining information about the earths ionosphere simultaneously from a global network of stations has been demonstrated. Irregularities in the ionosphere due to space weather events caused by solar flares and coronal mass ejection can scatter trans-ionospheric radio signals producing fluctuations in both amplitude and phase and GPS cycle slips disrupting satellite communications and navigation. We concern our study at equatorial and sub auroral region during low solar activity. For this purpose a dual frequency GSV 4004A GPS receiver is installed at sub auroral region MAITRI, Antarctica (geomagnetic lat. 62.80 S, geomagnetic long. 52.80 E) and equatorial region BHOPAL(geographic lat. 23.20 N, geographic long. 77.60 E), Space Science Laboratory, Department of Physics, Barkatullah University. This paper discusses some space weather effects on GPS signal propagation, Total Electron Content (TEC) variation and Ionospheric scintillation.

Yuhui Zhao
(Nanjing University, China)

In the dynamical model of restricted three body problem, the conditional stability and fixed position of collinear libration points make them wildly used in space explorations. However, due to the essential instability of these points and various perturbations in reality, orbit control is necessary. Impulsive maneuvers and low thrust for station keeping are both practicable. As a kind of continuous thrust, solar sailing is highlighted for special attention because of energy-saving. Taking the orbits around the collinear libration points of the Earth Moon system as an example, this article studies three different methods to station keeping with solar sails: the optimal control law, the state dependence Riccati equation method and the Lyapunov control method. Two models of solar sail are considered. One model is to keep the lightness parameter constant and change the yaw and pitch angle of the solar sail. The other is to keep the yaw and pitch angles constant and change the lightness parameter of the solar sail. Numerical simulations are made in ' real' dynamical model and calculation results are discussed in comparison.

Masashi Miura
(The Graduate University for Advanced Studies, Japan)

Future space transportation systems should be highly reliable, responsive, frequently operable and usable for many different types of missions flexibly. Then, there are some requirements for the control system of future space vehicles. First, it should have high robustness on model errors, disturbances and unusual state. Next, it should be useful and high-performance controller under wide-range flight environment and it should be able to be designed easy and quickly. With traditional gain-scheduled designing methods, it needs a large amount of labor and time to design controllers. The last, it should be flexible enough to deal with many different kinds of missions and unexpected situations. To satisfy these requirements, a robust and adaptive control is necessary. Then, we suggest a robust adaptive control system using particle filter. Particle filter is a new powerful technique developed in mathematical-statistics which provides quick and accurate estimation of high dimensional state vector. By configuring the robust feedback controller using estimated states and parameters with particle filter, the robust and adaptive control can be realized. This presentation shows why the robust adaptive control is necessary in the future and how to achieve the robust adaptive control system with particle filter method.

Mutsuko Morimoto
(JAXA, Japan)

To maintain Halo orbits around L2 point in the Sun-Earth system using chemical propulsion, the size of the orbits is limited to about more than 650,000 km. In this paper, small halo orbits in the vicinity of L2 point by solar sails are studied. Some small halo orbits in the vicinity of L2 point have been studied by using continuous low thrust control. Tarao assumed the thrusters as ion engines and discussed the way to realize small-halo orbit.¹ Morimoto defined an artificial equilibrium point (AEP) and generated small periodic orbit around AEP with constant control acceleration on the line connecting Sun and the Earth.² Both control low assumes low thrust propulsion system, but both cannot be adapted for small halo orbit using solar sail because the direction of acceleration is restricted. By combination of two lows studied before we succeed in generating small halo orbit s, even though each low cannot be applied to solar sails by itself. ¹ Tarao, K. etc, "A Control Configured Small Circular Halo Orbit around L2," AAS paper, 05-425, 2005. ² Morimoto, M., etc. "Periodic Orbits with Low-Thrust Propulsion in the Restricted Three-Body Problem," Journal of Guidance, Control, and Dynamics, 2006, pp. 1131-1139.

Genya Ishigami
(JAXA, Japan)

This paper describes a field experiment with an exploration rover prototype at a lunar/Martian analogue terrain. The 4-wheeled rover prototype has independently steerable units on each wheel and left and right wheel pairs are connected with a rocker suspension mechanism which allows the rover to negotiate with rough terrain. The self-sustainable system of the prototype performs end-to-end operations including a system booting, an autonomous navigation, and a sampling with a manipulator. The electrical power for the rover is supplied by an onboard power management subsystem using solar array panels with rechargeable batteries. Telemetry, tracking, and command are handled via a wireless LAN communication system (reachable up to 1.0 km over 2.4 GHz band). A digital camera pair and a laser range finder (LRF) are mounted for obstacle observations and terrain feature scanning. In the mobility test on rough terrain, the data obtained such as electrical power profiles and vibration characteristics of the rover can evaluate the mobility performance. The navigation test has been also demonstrated with two different types of techniques: camera-based and LRF-based navigations. Both techniques have been confirmed such that the sensors can classify traversable/untraversable areas and then guide the rover to a safer way to be traveled.

Yohsuke Nambu
(Osaka Prefecture University, Japan)

This paper proposed a new damping method for liberation of a gravity gradient stabilized satellite using tuned vibration absorbers (TVAs). Gravity gradient stabilization (GSS) is an economic way of attitude stabilization to keep a direction of a satellite toward to the earth. This way is especially useful for small satellite systems that have received great attention for recent several years, because they desire economical design and development. Orbcomm satellites and Kanta-kun are popular examples. GSS is economic, but the satellite using only GSS behaves like pendulum, namely vibrates around the center of mass. This phenomenon is called as liberation. Liberation subjects high resolution observation and communication to a grand station. Therefore, liberation damping is big issue for GSS. In this paper, TVAs that are usually used for vibration suppression are used for liberation damping. The TVA consists of mass, spring, and dashpot system. It works well, when the natural frequency and the damping coefficient are put on optimal values. This paper obtained the optimal natural frequency and damping coefficient against the liberation explicitly. And numerical simulation showed that the liberation of the GSS satellite with TVAs decay quickly.

Koji Fujita
(Tohoku University, Japan)

Mars is the next milestone in our exploration of the solar system. The presence of an atmosphere on Mars signifies that an aircraft could travel in its atmosphere using the aerodynamic forces of flight. The aircraft allows for a platform that can cover an area that is currently lacking. A reconnaissance aircraft offers the possibility to obtain high resolution data on a regional scale of several hundreds to thousands of kilometers, which cannot be achieved with rovers or satellites. The conceptual design of a Mars airplane was developed by Tohoku University in goal of studying the feasibility of a Mars airplane. This paper discusses the steps undertaken at Tohoku University to develop a preliminary conceptual design of a 3.5kg fixed-wing, propeller-driven aircraft for Mars exploration, following a predetermined set of requirements and constraints tailored for a small scale scientific mission to Mars. The design process includes the optimization of the initial sizing and geometry of the aircraft for cruising performance, trade-off studies of the propulsion system, and a total mass build-up. Furthermore, some different aircraft configurations were proposed, following the selected baseline sizing.

Makoto Matsui
(Shizuoka University, Japan)

Development of thermal protection systems (TPS) requires the simulation of entry and re-entry conditions at ground test facilities. Arc-heaters are widely used to generate such high enthalpy flows because of their long operational time, simple structure and ease of maintenance. However, surface catalytic effects and active and passive oxidation of TPS materials have been recognized as important issues; erosion of their electrodes poses an important obstacle because polluted flows make it difficult to evaluate chemical reaction rates in front of TPS surfaces. Then, inductively coupled plasma (ICP) generators have garnered much attention. Such generators have no electrode. They can use even reactive gases such as carbon dioxide and oxygen because of their electrode-less heating. However, in ICP, plasma instability limits its operation pressure less than atmosphere. Thereby, high enthalpy flows with high plenum pressure are difficult to produce. Although Mars entry conditions might be simulated using these generators, it would be still difficult to produce Venus entry conditions. In this study, a laser driven plasma wind tunnel has been developed to produce high enthalpy CO2 flows under atmospheric pressure. Then, plume diagnostics has been conducted by emission and laser spectroscopies.

Yosuke Fukushima
(ISAS/JAXA, Japan)

In this paper a new search algorithm is proposed that is used to find better candidates of modification in the iterative repair process of onboard planning, scheduling and re-planning software functions embedded on autonomous space systems. Onboard planning and scheduling function is one of key technologies to realize autonomous space systems and there have been many researches with results of not just simulations but experiments using even real space systems. In the most of them, the iterative repair approach is taken with some heuristic search algorithms as a standard process. The reason can be thought because of a realistic point of view of implementation on the real-time systems. To try to take one step forward toward the optimal search solution, the authors propose an algorithm using a common search method in the quality control field and some simulation results of the algorithm comparing with those obtained relying only on the standard heuristic search. In addition, this paper introduces a software framework especially designed for onboard implementation and some testbed experiment results, where stress is placed on the use of a script engine that enables the system to have a capability of dynamical function update with the system working continuously.

Volodymyr Savchuk
(SDO Yuzhnoye, Ukraine)

Principles of construction and structure of control systems are considered by ground equipment by preparation of launches of space carriers. At ground equipment modernization under the international program Land launch SDO Yuzhnoye are realized projects on replacement of physically worn out and obsolete systems with application of modern principles of working out. For dangerous objects to a people life it is recommended to use controllers with operational systems of real time. Working out, debugging and execution of programs of control by controllers implements by means of the specialized software. The successful course of develop and modernization of control systems technological processes indicates correctness of the principles of construction, schematic, constructive and program solutions.

Philippe Nomerange
(Techspace Aero, Belgium)

Techspace Aero, as a European supplier of flow control equipment for liquid propellant rocket engines, has been a partner for the development, production and exploitation of the Vulcain and Vulcain 2 rocket engines and is taking part in the ongoing development of the Vinci cryogenic upper stage engine. The paper presents Techspace Aero range of products including the main fuel and oxidizer chamber valves and the drain valves of the Vulcain engine, and the chamber and drain valves of the Vinci engine. Techspace Aero is also the designer of the engine electrovalves controlling the pneumatic circuit that is used to actuate the engine main valves. Finally Techspace Aero also offers a solenoid operated flow control valve for 1N hydrazine thrusters for satellite attitude and orbit control system that has been developed and qualified under an ESA contract. Based on several years of successful experience and expertise, Techspace Aero has the capability to assume responsibility for the whole development process of new liquid engine flow regulation equipment, from initial technology formulation and validation through preliminary and detailed design, to development and qualification testing and industrialisation and series production.

Hideo Ohashi
(Tokyo University of Marine Science and Technology, Japan)

We propose a dust particle detector LDM (Lunar Dust Monitor) to be onboard the next Japanese lunar mission SELENE-2. The LDM is an impact ionization detector with dimensions 25 cm x 25 cm x 30 cm, and it has a sensor part (LDM-S) and an electronics part (LDM-E). The LDM-S has a target of 400 cm², to which a high voltage of +500 V is applied. The LDM-S has three meshed grids parallel to the target. When an incident particle impacts on the target, plasma gas is generated. The electrons are collected by the target and the ions are accelerated toward the inner grids as a result of the electric field. Some of the ions drift through the inner grid and reach the outer grid. The waveforms from two grids and the target are stored and sent back to ground. We can deduce the mass and velocity information of the incident dust particle from the recorded waveforms. The orbiter of SELENE-2 is planned to be in operation for one year or more, and the LDM will observe circumlunar dust over the whole operation period. We report scientific importance of dust measurement around the Moon, and current status of LDM.

Seiichi Tazawa
(National Astronomical Observatory of Japan, Japan)

The Laser Altimeter (LALT) is an instrument on board the Japanese lunar explorer KAGUYA (SELENE) which was launched on September 14, 2007 (JST).The LALT measures the distance from orbiting spacecraft to the surface of the moon. The distance is determined by measuring the complete round trip time of a laser pulse from the instrument to the lunar surface. Besides, the LALT is equipped with an intensity monitor of the returned pulses. The intensity of the returned pulses contains information concerning surface slope, roughness and reflectance of the footprints, which will contribute to the study of the lunar surface maturity and age. The LALT measured more than 10 million range data from the altitude of 100 km during the nominal observation from December 30, 2007 to October 31, 2008. During the extended mission phase, the satellite altitude was decreased to 50 km. The LALT continued observation until the controlled impact of KAGUYA onto the moon on June 10, 2009 and obtained more than 20 million range data. In this presentation, we will show the behavior of return pulse intensity acquired with range data, , especially focusing on low altitude data during the extended mission.

Ielyzaveta Gorbenko
(Dnipropetrovsk National University, Ukraine)

Professor I.K. Kosko was born 18 June 1918. He was a scientist of Ukraine. He was managed works on the topic "Devices on the space stations". Result of work on this topic was to create standards of the space aquarium and incubator. The space aquarium it was the closed ecological system. The vital functions of the system consisted in the leadingout of fingerlings of finfishess, their growing and reproduction in the conditions of weightlessness. Works were conducted on the requirement specification of Moscow Institute of Space Researches. An aquarium participated in biological experiments, which was conducted at flight of biosputnika number 9 series "Space". An incubator behaves to the devices which are used for incubation of biological objects, for example bird eggs and it can be used for biological researches in the conditions of space flight. The purpose of creation of such incubator was become by creation of device. An incubator contains holders, which was provided rapid output and setting of eggs. Creation of space incubator rotined that possibly leadingouts of quail in the conditions of weightlessness from eggs which to the hit in space exposed to influence of the considerable oscillation loadings on the area of leadingout of rocket.

Satoshi Matsuo
(Tottori University, Japan)

We have developed a rehabilitation device which has a treadmill in a lower body positive pressure (LBPP) chamber to unload the lower extremities. The device possibly prevents development of edema in the legs because the positive pressure may reduce fluid filtration by decreasing transmural pressure gradient in the capillaries. We hypothesized that LBPP and walking exert additive effects in preventing gravity-induced edema in the legs. To test this hypothesis, we examined changes in circumferences of the thigh, calf and ankle under three conditions (WALK, 10-minutes walking without LBPP; LBPP, standing still for 10-minutes with 15 mmHg LBPP; WALK+LBPP, 10-minutes walking with 15 mmHg LBPP). The circumferences increased gradually during 40-minutes standing in each group ( Δcircumference of thigh: 0.62±0.06 cm, calf: 0.52±0.04 cm, ankle:0.22±0.02 cm). In the WALK+LBPP group, the circumference decreased significantly in all of the three parts (thigh: -0.6±0.07 cm, calf: -0.3±0.06 cm, ankle: -0.24±0.04 cm). The reduction in the circumference was greater in WALK+LBPP group than in WALK or LBPP group. These results suggest that LBPP and walking can have an additive effect on edema protection in the legs.

Shin Yamada
(JAXA, Japan)

To walk upright on the Moon or Mars, optimized walking techniques under altered gravitational conditions need to be verified. Therefore, we have been studying changes in kinematics of walking at different gravitational loads using body weight suspension systems.
Our simulation consisted of three gravitational conditions: Earth, 1 g; Mars, 1/3 g; and the Moon, 1/6 g. Surface EMG was recorded from leg muscles while subjects walked on a treadmill. Cadence, duration of stance phase, and step length were calculated from walking velocity and steps. Subsequent studies revealed that muscle activities and duration of the double support phase decreased according to the reduction of simulated gravities. These changes seemed to be caused not only by direct effects of unloading but also by kinematic adaptations to them. It can be said that a human walks slowly with a shortened stride length and elongated stance phase to adjust to low gravitational conditions.
One of the major limitations of the previous study was that the suspension system was fixed to an immovable frame, which might have had some effects on walking stability. We have started further studies using a newer movable body weight suspension system to achieve more realistic simulations.

Tomoaki Matsuo
(JAXA, Japan)

In a microgravity environment, volume load to the left ventricle is reduced and cardiac function deteriorates. As a result, maximal oxygen consumption (VO₂max), which is used to evaluate cardiovascular function and is directly related to a human's physical working capacity, decreases during spaceflight. Reduced cardiac function can lead to serious health problems such as cardiac atrophy, diastolic dysfunction, and orthostatic hypotension. Accordingly, exercise such as using a bicycle ergometer, shoud be a useful countermeasure during spaceflight. On the other hand, many astronauts also experience weight loss during spaceflight because an energy imbalance can occurr, i.e., an astronaut's total energy expenditure may exceed his/her total energy intake. Some researchers indicate that too much exercise may promote the energy deficit and have a negative impact on long-term space flight. High-intensity interval aerobic training (HIAT), which is an activity that occurs over a short period of time but has a strong impact on the heart, is a potential countermeasure for the problem. Previous studies describe several HIAT protocols designed specifically for athletes. We, Japan Aerospace Exploration Agency (JAXA), have been devising an original HIAT protocol better suited to astronauts experiencing long-term spaceflight. In this presentation, we reveal some preliminary results.

Masahiro Terada
(JAXA, Japan)

Hair root cells actively divide in a hair follicle, and they sensitively reflect physical conditions. By analyzing the human hair root, we can know stress levels on the human body and metabolic conditions caused by microgravity environment and cosmic radiation. Thus JAXA Space Biomedical Research Office (J-SBRO) has started a human research by analyzing astronauts' hair which is nicknamed "HAIR". However, in this experiment, there is a limitation of sampling only five strands of hair from astronauts. Therefore, we must develop the method to analyze no less than five hair roots. To achieve this purpose, we performed the microarray analyses using the extracted RNA from one or five hair roots.
We compared RNA data from a single hair root with those from five pieces of hair root. The extracted RNA from a single hair root is not enough amount for microarray analyses, but the amplified RNA was sufficient to obtain the gene expression data.
These results suggested that we could perform the genetic analyses even on one or five hair roots. These hair samples will give us useful physiological information to examine the effect of space flight.

Hsin-Jang Shieh
(National Dong Hwa University, Taiwan)

A multi-input power system shown in figure is developed for increasing the working time of wheeled mobile robots. In figure, the operation is as follows. 1) Solar cell with full power and lithium battery with full charge. Almost all the solar cell output power supplies to the robot and the battery output power is turned into a supplementary supplier. 2) Solar cell with full power and battery with low charge. The solar cell output power supplies to both the robot and battery. In this condition, the battery is operated in charging mode. After charging completed, the power system is operated with 1). 3) Solar cell with low power and battery with full charge. Almost all the battery output power supplies to the robot. In this situation, the robot automatically moves to a place with better illumination so that the solar cell output power is large enough to supply. 4) Robot sleeping and solar cell with enough output power. Check the state of charge of the battery. If the battery charge is low, the power charging flow from the solar cell is turned on whereas the robot is still in sleeping mode.

Akihiko Yamagishi
(Tokyo University of Pharmacy and Life Science, Japan)

TANPOPO, dandelion, is the name of a grass whose seeds with floss are spread by the wind. We propose the analyses of interplanetary migration of microbes, organic compounds and meteoroids on ISS-JEM. Ultra low-density aerogel will be used to capture micrometeoroid and debris. Particles captured by aerogel will be used for several analyses after the initial inspection of the gel and tracks. Careful analysis of the tracks in the aerogel will provide the size and velocity dependence of debris flux. The particles will be analyzed for mineralogical, organic and microbiological characteristics. To test the survival of microbes in space environment, microbial cells will be exposed. Organic compounds are also exposed to evaluate the possible denaturation under the conditions. Aerogels are ready for production in Japan. Aerogels and trays are space proven. All the analytical techniques are ready..

Shingo Yoneda
(University of Tokyo, Japan)

Atomic oxygen flows are required to simulate space environments at low earth orbit (LEO). Since spacecrafts have velocities of ~7.8 km at LEO, atomic oxygen dissociated by ultraviolet ray from the sun collide with them with a translational energy of ~4.5 eV, resulting in the severe degradation of their surface materials. Currently, a laser detonation technique is a unique method to produce high speed atomic oxygen flows. However, the operation time of this type of simulators is restricted less than the order of millisecond. In this study, 2kW continuous wave CO2 laser was used to produce stationary high speed atomic oxygen flows. The pure oxygen plasma with the plenum pressure up to 0.5 MPa was produced and expanded through the convergent-divergent nozzle. Then, laser absorption spectroscopy was applied to measure the flow velocity using a OI 777nm line.

Akira Doi
(Kyushu University, Japan)

This paper briefly introduces the IDEA project (The project for In-situ Debris Environment Awareness) initiated at Kyushu university. The IDEA project aims to establish in-situ monitoring network for the micro debris environment. The following missions will be assigned to piggyback satellites planned to be launched after 2013: the first mission is to evaluate the confidence of existing models that describe the current debris environment, and the second one is to monitor the micro debris environment of the primary satellite and satellites in the same orbital altitude. The IDEA project focuses development resources on the mission achievement; the principle we follow is to make the most of using confirmed or existing technology and equipment, and to improve those if necessary. Based on that philosophy, this paper specifies what are required for the mission operation and specification of IDEA satellites, and its relations. This paper also discusses desirable parameters of the specified elements.