National Space Development Agency Of Japan Research Articles

NASDA aquatic animal experiment facilities for Space Shuttle.

National Space Development Agency of Japan (NASDA) has been developed aquatic animal experiment facilities for space experiments using NASA Space Shuttle. Vestibular Function Experiment Unit (VFEU) has been firstly designed and developed for Spacelab-J mission (STS-47), and 8 days space experiment with carp has been performed. Following, the VFEU, Aquatic Animal Experiment Unit (AAEU) has been developed to accommodate small aquatic animals second International Microgravity Laboratory mission (IML-2, STS-65). Four kinds of space experiments with goldfish, medaka, newt, and newt eggs have been performed for 15 days mission duration. Then, VFEU has been improved to accommodate marine fish under low temperature condition for Neurolab (STS-90) and STS-95 missions. 17 days (STS-90) and 9 days (STS-95) experiments with oyster toadfish have been performed by using the VFEU. This report summarizes the outline of these aquatic animal experiment facilities.

112 ILASによるオゾン層科学への貢献

The Improved Limb Atmospheric Spectrometer (ILAS) was a satellite sensor developed by Global Environment Division, the Environment Agency of Japan, for monitoring the ozone layer. ILAS was onboard the ADEOS (Advanced Earth Observing Satellite) MIDORI satellite which was launched on August 17, 1996 by the National Space Development Agency of Japan (NASDA). ILAS measured about 6700 vertical profiles of O3, HNO3, NO2, N2O, CH4, and H2O in the stratosphere both in the Northern and the Southern Hemispheres from November 1996 to June 1997. It provided valuable observational data for investigating the mechanism of ozone loss in high latitude stratosphere. Substantial ozone loss was found from the ILAS O3 data, which were taken in early spring in 1997 in the northern high latitude region. Simultaneously, frequent occurrence of Polar Stratospheric Clouds (PSCs) was observed.

Robust Flight Control Law Design for Automatic Landing Flight Experiment

Automatic Landing FLight EXperiment, ALFLEX, is conducted by National Aerospace Laboratory (NAL) and National Space Development Agency of Japan (NASDA) in order to develop the automatic landing technology for future unmanned reentry space vehicle, HOPE(H- II Orbiting PlanE). Total of 13 flight experiments were conducted at Woomera Australia in 1996, and all flight experiments were perfectly completed. Because ALFLEX vehicle, which is dynamically similar sub-scaled model(37%) of HOPE, is the unmanned and autonomous vehicle which has tip-fin wings, the flight control law has to achieve high-response-performance and robustness simultaneously. In this paper, the design method, which connects the MDM/MDP(Multiple Delay Model/Multiple Design Point) and the H∞ control design method combined with Exact Model Matching to achieve the objectives, is presented. And the results of flight experiment about the performance and the robustness are also presented.

Inhibition in a microgravity environment of the recovery of Escherichia coli cells damaged by heavy ion beams during the NASDA ISS phase I program of NASA Shuttle/Mir mission no. 6.

We participated in a space experiment, part of the National Space Development Agency of Japan (NASDA) Phase I Space Radiation Environment Measurement Program, conducted during the National Aeronautics and Space Administration (NASA) Shuttle/Mir Mission No. 6 (S/MM-6) project. The aim of our study was to investigate the effects of microgravity on the DNA repair processes of living organisms in the <Realtime Radiation Monitoring Device III (RRMD III)> in orbit. Heavy ion beam radiation- or ç-irradiation-damaged biological samples of Escherichia coli and the radioresistant bacterium Deinococcus radiodurans were prepared and placed in a biospecimen box, which was loaded into the RRMD III sensor unit of the Space Shuttle. Two identical sets of samples were left in the Spacehab's Payload Processing Facility (SPPF) in Florida, USA, as a control. (flight No. STS-84) was launched from NASA John F. Kennedy Space Center (KSC) in Florida, USA, on May 15, 1997. The mission duration was 9.22 days. An astronaut activated the biological samples in the biospecimen box in the Spacehab during orbit in order to start repair of the DNA damaged by heavy ion beams or ç-irradiation and the samples were incubated for 19 h 35 min at about 22ûC, the cabin temperature. The control specimens in the SPPF were subjected to the same treatment under terrestrial gravity. After returned to earth, we investigated cell recovery by comparing the repair of the radiation-damaged DNA of E. coli and D. radiodurans in the microgravity environment in space with that on Earth. The results indicated that the DNA repair process of E. coli, but not of D. radiodurans, cells was inhibited in a microgravity environment.

Medical Baseline Data Collection on Bone and Muscle Change with Space Flight

It has been documented that astronauts suffer from a progressive and continuous negative calcium balance in space flight. The National Space Development Agency of Japan (NASDA) discussed the experimental protocols with the National Aeronautics and Space Agency’s (NASA’s) Johnson Space Center (JSC) and has started a medical baseline collection on bone and calcium metabolism, and muscle changes with space flight. The subjects were two astronauts, a 42-year-old female and a 32-year-old male, who experienced real space flights. Fractional excretion of calcium (FECa) increased in both subjects just after the space flight. There was a negative calcium balance with urinary calcium leak even after a short flight. We also noticed a decrease (−3.0%) of bone mineral density (BMD) of the lumbar spine (L2–4), a weight bearing bone. These bone changes may be due to a negative calcium balance. However, the BMD of the skull, a nonweight bearing bone, increased after the flight. This indicates that the effect of weightlessness on bone is different in respective bones, depending on the weight loading. Our data of the bone metabolic marker clearly indicate that bone resorption is stimulated, shown by an elevation of urinary pyridinolinks and plasma tartrate-resistant acid phosphate (TRACP) activity. Bone specific alkaline phosphatase, a bone formation marker, was elevated in both subjects, but not intact osteocalcin. Whether this pathophysiological phenomenon is due to an accelerated bone resorption or suppressed bone formation is still obscure. In addition, the physiological cross-sectional area (PCSA) of muscle in the legs greatly decreased (from −10% to −15%) after the flight, and it took over a month to be recovered in both subjects. However, the muscle volume loss in the legs seemed to be reversible. To examine bone and muscle metabolism with space flight, further investigations and international standardization of experimental protocols are necessary.

117 TRMM(熱帯降雨観測衛星)による降雨のリモートセンシング

National Space Development Agency of Japan (NASDA) successfully launched the Tropical Rainfall Measuring Mission (TRMM) observatory at 06:27 (JST) on Nov. 28, 1997. The TRMM satellite carries the first spaceborne Precipitation Radar (PR) which was developed by NASDA and Communications Research Laboratory. The PR can measure the horizontal and vertical structure of rain day and night, and over ocean and land. This capability allows scientists for the first time ever to grasp the three-dimensional structure of rain in the tropics and sub-tropics around the globe. In addition to the PR, the satellite carries four more sensors which were developed by National Astronautics and Space Administration (NASA): the TRMM microwave Imager (TMI), the Visible Infrared Scanner (VIRS), and the Cloud and the Earth's Radiant Energy System (CERES), the Lightning Imaging Sensor (LIS). Preliminary results and images from these sensors are shown.

ＬＥ‐７エンジン用液体水素ターボポンプの開発

National Space Development Agency of Japan (NASDA) started to develop H-II launch vehicle in 1983 and succeeded in the 1st flight on February in 1994. Meanwhile, several troubles were experienced in the development of LE-7 which is the 1st stage engine of H-II. The LE-7 is a staged combustion cycle engine with high pressure and high Isp like SSME. Therefore, high delivery pressure and high performance were required for LH2 turbopump, which is the main key component, and caused several troubles in the development. This paper describes the development of LH2 turbopump containing the design description, the contents of some troubles and their counterplans. In addition, some activities to solve turbopump life and endurance will be introduced.

WinASEAN for remote sensing data analysis

The image analysis system ASEAN (Advanced System for Environmental ANalysis with Remote Sensing Data) was designed and programmed by a software development group, ImaSOFr, Department of Remote Sensing Technology and GIS, Institute for Geography, National Centre for Natural Science and Technology of Vietnam under technical cooperation with the Remote Sensing Technology Centre of Japan and financial support from the National Space Development Agency of Japan. ASEAN has been in continuous development since 1989, with different versions ranging from the simplest one for MS-DOS with standard VGA 320×200×256 colours, through versions supporting SpeedStar 1.0 and SpeedStar PRO 2.0 true colour graphics cards, up to the latest version named WinASEAN, which is designed for the Windows 3.1 operating system. The most remarkable feature of WinASEAN is the use of algorithms that speed up the image analysis process, even on PC platforms. Today WinASEAN is continuously improved in cooperation with NASDA (National Space Development Agency of Japan), RESTEC (Remote Sensing Technology Center of Japan) and released as public domain software for training, research and education through the Regional Remote Sensing Seminar on Tropical Eco-system Management which is organised by NASDA and ESCAR In this paper, the authors describe the functionality of WinASEAN, some of the relevant analysis algorithms, and discuss its possibilities of computer-assisted teaching and training of remote sensing.

Toward the optimization of PC-based training

Since 1992, the National Space Development Agency of Japan (NASDA) and the Economic and Social Commission for Asia and the Pacific (ESCAP) have been co-organising the Regional Remote Sensing Seminar on Tropical Ecosystem Management (Program Chairman: Prof. Shunji Murai) every year in some country in Asia. In these seminars, the members of the ISPRS Working Group VI/2 ‘Computer Assisted Teaching’ have been performing a PC-based hands-on-training on remote sensing and GIS for beginners. The main objective of the training was to transfer not only knowledge but also the technology of remote sensing and GIS to the beginners. The software and CD-ROM data set provided at the training were well designed not only for training but also for practical data analysis. This paper presents an outline of the training and discusses the optimisation of PC-based training for remote sensing and GIS.

Verification plan of ocean color and temperature scanner atmospheric correction and phytoplankton pigment by moored optical buoy system

A moored optical buoy system has been developed by the National Space Development Agency of Japan (NASDA) for verification of ocean‐observing remote sensing sensors of the Advanced Earth Observing Satellite (ADEOS). An underwater spectral radiometer was specifically designed for this optical system. The two upward radiance and downward irradiance correctors were connected with fiber optical system and were placed at the depth of 1.5 m and 6.5 m. The collector parts of the radiometer were extended from the center of the buoy system in order to avoid self shading with 3 m and 1.2 m arms at the depth of 1.5 m and 6.5 m, respectively. Spectral incident irradiance was measured at top of the buoy system. Phytoplankton pigment concentrations were monitored by Aquatracka‐III fluorometer placed at the bottom of the surface float. Atmospheric temperature, pressure, humidity, wind speed and direction, water temperature at a depth of 1.2 m and 6.5 m, and wave height and direction were also monitored. In this paper, we present results from test deployment during January 16 to March 15, 1995, in the Suruga Bay, off Shizuoka, Japan, and compare the water‐leaving radiance obtained by buoy with one observed by ship. The chlorophyll a concentrations calculated from water‐leaving radiance were also compared with chlorophyll fluorescence measured by fluorometer. It was proved that the self shading and wind affected the radiance and irradiance in the sea. It becomes clear that the quality check of the buoy data is very important for verification of the satellite data. We present also the verification plan of atmospheric correction and phytoplankton pigment for ADEOS/ocean color and temperature scanner (OCTS) using the sea truth data obtained from this buoy system and ships.

Attitude Control of an Artificial Satellite Using H∞ and Two-Degree-of-Freedom Control -On-Orbit Experiments Using ETS-VI-

In this paper, results of attitude control experiments using Engineering Test Satellite VI (ETS-VI) on orbit are introduced. ETS-VI is a three-axis-stabilized satellite launched by the National Space Development Agency of Japan (NASDA) in August 1994. Identification and attitude control experiments on orbit were one of the ETS-VI mission programs and were carried out from January to March in 1995. The attitude controllers were designed using H∞ control method and two-degree-of-freedom control method. Experimental results show the effectiveness of these controllers for artificial satellite control.

From centralized to distributed: The evolution of Space Station command and control

This paper documents the evolution in the command and control (1) concept for the core systems of the Space Station. No previous National Aeronautics and Space Administration (NASA) program has had the level of international involvement, or the agreements for International Partners to participate in the command and control processes, seen in the Station Program. In the early days of station planning, all command and control was centralized in the Space Station Control Center (SSCC) in Houston, much as command and control for the shuttle is carried out in the Mission Control Center (MCC). Each International Partner agreed to provide personnel to the SSCC to be part of the SSCC team. The Space Station Program has gone through a drastic evolution in its systems command and control concept. This evolution was driven by the addition of the Russians as a new Space Station partner as well as budgetary and political pressures within the original partnership agencies. This evolution has been incremental with technical assessments at each step to ensure that the overall safety of the flight crew and vehicle were not compromised. The resulting command and control concept for the station systems maintains overall command and integration functions at the SSCC but allows control of the various station segments to be performed in five different control centers around the world. This concept allows the European Space Agency (ESA), the National Space Development Agency of Japan (NASDA), the Russian Space Agency (RSA) and the Canadian Space Agency (CSA) to participate in the daily operations of the Space Station systems they build, without the need to provide large numbers of personnel to the SSCC. Payload command and control for the experiments operated on the Space Station will not be addressed in this paper.

H-II LAUNCH VEHICLE

The development program of the H-II rocket has been initiated in 1985. The H-II rocket is a new expendable launch vehicle to meet a demand of space activities in the 1990's. With the successful development if the N rocket family,, Japan has established the technology for launching satellite into Geostationary Earth Orbit (GEO). The National Space Development Agency of Japan(NASDA) has made a major effort to obtain a heavier launch vehicle, capable of meeting the increasing needs of GEO mission. Following the II 1 rocket capable of carrying a 550 kilogram satellite into GEO and ready for a first launch in August 1986, a new launch vehicle called the H-II rocket is being planned to carry a 2 ton satellite into GEO and to be most cost effective per payload ton into GEO. This launch vehicle is of 100 percent domestic design and Japan will be able to have an independent and competitive capability in the field of space transportation systems. First launch of the H-II rocket was performed successfully in February 1994. After that, second and third H-II rocket were launched in august 1994 and march 1995.

Current space debris related activities in Japan

This paper describes the current and planned efforts in the space debris field in Japan, placing emphasis on the activities of the Japan Society for Aeronautical and Space Sciences (JSASS) and National Space Development Agency of Japan (NASDA). It covers activities for space debris environment measurement, mitigation and protection and shielding. Some representative activities of individual researchers are also briefly introduced.

The properties of acoustic emission for CFRP rocket motor nozzle holders1

This paper reports the possibility of the acoustic emission (AE) application from the results of the testing performed at NASDA (National Space Development Agency of Japan) on H-I rocket motor nozz...

ＭＯＳ‐１／ＶＴＩＲデータによる海面温度画像データセットの作成

As the earth science activities for International Space Year (ISY) in Japan, a project for Sea Surface Temperature (SST) data sets has been carried out under the sponsorship by National Space Development Agency of Japan (NASDA) . Authors developed a algorithm for generation of SST data sets using MOS-1/VTIR data. 18 regional SST data sets around Japan Islands from 1989 to 1992 based on this algorithm were created by superimposing of multi-date VTIR data during about one week. The procedure of data processing consists of seven stages, radiometric correction, averaging of row data, cloud elimination, atmospheric correction using split-window equation, image registration, Masking of land area, color coding of SST value and data output. The SST distribution in data set was evaluated by comparing with actual observed sources. The results showed the validity for the investigation of SST distribution and the monitoring of ocean currents. Especially, the possibility for monitoring of the change of the Kuroshio Current was recognized.

Telescience testbed examination aboard Japanese Experiment Module (JEM): Life and material science experiments

A telescience ground testbed experiment was conducted by the National Space Development Agency of Japan (NASDA) at the Tsukuba Space Center in March 1991. The objectives of the ground testbed experiment were to extract scientists' requirements for a communication method, to evaluate the influence of transmission delay and capacity on experiment operations, and to evaluate performance and functions of the system for the testbed experiment. The microscopic operations experiment, the image furnace experiment and the onboard training experiment were selected as typical ground testbed experiments. In these experiments, motion video transmission at 320 kbps was acceptable for observing the experiments and communicating between the principal investigator and the payload specialist. In the microscopic operations experiment, motion video transmission at 1.5 Mops or more was required for detailed observation. A 4-second transmission delay (roundtrip) was allowable for mutual communication.

Status of H-II rocket first stage propulsion system

The National Space Development Agency of Japan (NASDA) is now developing the H-II rocket, which will have the capability of placing a 2.2-ton satellite into geostationary Earth orbit (GEO). Its first-stage propulsion system mainly consists of a staged combustion cycle LE-7 engine and a tank system that will contain 85 tons of usable propellant, LOX and LH2. Prior to the start of developmental tests, a review of the propulsion system design was performed with significant tradeoff study efforts, and the basic system was chosen. Since the LOX feedline is one of the important development items, some basic tests were performed. The tank outlet design was selected according to the results of the scale model tank flow test. Mechanical and thermodynamic characteristics including geysering phenomena were investigated by performing the LOX feedline cryogenic flow test in which an actual feedline and LOX were used. Future development plans are presented.

Numerical simulation of hypersonic viscous flow for the design of H-II orbiting plane (HOPE)

An unmanned winged vehicle for space transportation called H-II Orbiting Plane (HOPE) is being studied by the National Space Development Agency of Japan (NASDA). In the present paper, hypersonic computational fluid dynamics (CFD) analyses have been performed for HOPE 62A, 62B, 62C and HOPE 63 models proposed by NASDA. Through these analyses, more than 50 numerical test cases have been calculated and aero- and aerothermodynamic characteristics are investigated in detail. In the present study, numerical simulations have been done by using a flux split upwind Navier-Stokes code. The results showed excellent agreements with experiments for aerodynamic stability and heat transfer distributions and the validity of the present code is demonstrated.

Earth observing system of NASDA

Since the successful launch of Marine Observation Satellite-1 (MOS-1) in 1987, the National Space Development Agency of Japan (NASDA) has been operating, developing, and planning Earth observation satellite programs. Looking to the 1990s, our primary concern is “Global Change”. NASDA is now developing Geo-Stationary Meteorological Satellite-5 (GMS-5), the Japanese Earth Resources Satellite-1 (ERS-1) and the Advanced Earth Observing Satellite (ADEOS). These will be followed by the Japanese Polar Orbiting Platform (JPOP). In addition, NASDA is now conducting the Tropical Rainfall Measuring Mission (TRMM) in cooperation with NASA. This paper introduces the mission objectives of NASDA's programs and discusses how to conduct space-based observations for global change research activities.