Sagamihara, Japan

The Japan Aerospace Exploration Agency , or JAXA, is Japan's national aerospace agency. Through the merger of three previously independent organizations, JAXA was formed on 1 October 2003. JAXA is responsible for research, technology development and the launch of satellites into orbit, and is involved in many more advanced missions, such as asteroid exploration and possible manned exploration of the Moon. Its motto is One JAXA and its corporate slogan is Explore to Realize . Wikipedia.


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A vapor jet system to continuously jet vapors while suppressing cavitation. One vapor jet system includes a liquid storage part for separately storing two or more kinds of mutually insoluble liquids; a jet orifice; and a jet control part. Jetting the vapors is from a state where pressure in the space storing the vapors in the liquid storage part is higher than the saturated vapor pressure in any of the two or more kinds of liquids. Alternatively, a vapor jet system can include a fluid storage part storing one kind of liquid and at least one kind of inactive gas having a composition different from the liquid; a similar jet orifice; and a similar jet control part. Jetting the vapors and inactive gas(es) is (are) from a state where pressure in a vapor storing space in the fluid storage part is higher than the saturated vapor pressure in the liquid.


Patent
Japan Aerospace Exploration Agency | Date: 2015-04-16

A vapor jet system includes a container for storing a sublimable solid, the container having a vapor discharge port for discharging vapor generated by sublimation of the sublimable solid; a member having an opening for jetting out the vapor to the outside of the vapor jet system; a vapor flow path between the vapor discharge port and the opening; and a filter for preventing passage of the sublimable solid and allowing the vapor to pass through, the filter being provided to the vapor flow path.


A vapor jet system enabling to continuously jet out vapors for a long time while suppressing cavitation. With a vapor jet system comprising: a liquid storage part for separately storing two or more kinds of mutually insoluble liquids; a jet orifice for jetting out vapors generated by vaporization of the two or more kinds of liquids inside of the liquid storage part; and a jet control part for controlling the jetting out of the vapors from the jet orifice, jetting out of the vapors is started from a state where the pressure in the space storing the vapors in the liquid storage part is higher than the saturated vapor pressure in any of the two or more kinds of liquids. Alternatively, with a vapor jet system comprising: a fluid storage part storing one kind of liquid and at least one kind of inactive gas having a composition different from the liquid; and a similar jet orifice and a similar jet control part, jetting out of the vapors and the at least one kind of inactive gas is started from a state where the pressure in the space storing the vapors in the fluid storage part is higher than the saturated vapor pressure in the liquid.


Patent
Japan Aerospace Exploration Agency | Date: 2017-02-22

A vapor jet system includes a container for storing a sublimable solid, the container having a vapor discharge port for discharging vapor generated by sublimation of the sublimable solid; a member having an opening for jetting out the vapor to the outside of the vapor jet system; a vapor flow path between the vapor discharge port and the opening; and a filter for preventing passage of the sublimable solid and allowing the vapor to pass through, the filter being provided to the vapor flow path.


Provided are an orbit descent method and system for space debris, capable of collision avoidance operation and re-entry control without a removal satellite of complicated construction and heavy weight, and an orbit changing method and system for an artificial satellite, based on the same principles. Provided are an orbit descent method and its associated system. The method includes the steps of: bringing an artificial satellite extendably holding an electroconductive tether near to space debris orbiting around a heavenly body; attaching one end of the electroconductive tether to the space debris by an electroconductive tether attachment mechanism; extending the electroconductive tether, with the other end thereof held by the artificial satellite, by an electroconductive tether extension mechanism, and causing the orbits of the integrated and orbiting artificial satellite, electroconductive tether and space debris to descend toward the heavenly body, by action of an electromagnetic effect of a magnetic field around the heavenly body upon the electroconductive tether; and changing the orbital motions under control by the artificial satellite. The system is configured to perform the steps. Provided are an orbit changing method and system for an artificial satellite, based on the same principles.


Grant
Agency: European Commission | Branch: H2020 | Program: CSA | Phase: COMPET-09-2014 | Award Amount: 862.06K | Year: 2015

In January 2014, the ISEF participants insisted on the importance of fostering international cooperation for additional space exploration projects. The partners of IRENA (International Re-Entry demoNstrator Action), including major space agencies involved in ISEF and ISECG, are convinced of the need for demonstrators in atmosphere entry/re-entry and of the potential for international cooperation in this area. IRENA mainly aims at: - creating a cluster of European and international stakeholders to study two types of demonstrators aimed at developing entry/re-entry technologies and suitable for other enabling technologies - jointly defining two technology demonstrator projects relevant for international cooperation - contributing to a European position for ISEF and - disseminating the results and preparing the next steps. To achieve these objectives, IRENA will rely on an international and complementary team: four major European and international space agencies (CNES, DLR and JAXA as beneficiaries and NASA as a 3rd party), the two European industry leaders in entry/re-entry and space exploration (Astrium, Thales Alenia Space) and a research institute expert in dissemination and exploitation. IRENA will build on a cooperative approach to jointly define the projects, on feasibility and cost assessment studies and on implementation assessment studies (governance, funding, international cooperation). Five workshops including one in Japan, the USA and two based on Concurrent Engineering will be used to support the work. IRENAs objectives have been chosen to explicitly meet the main work programmes requirements i.e. to be in line with ISEF recommendations, to involve international countries active in space exploration, to create a cluster around several demonstrator projects, to define these projects and discuss how to build them, to target enabling technologies and to include workshops and information events.


In this paper, we propose a new design method for Gain-Scheduled Output Feedback (GSOF) controllers for continuous-time Linear Parameter-Varying (LPV) systems via Parameter-Dependent Lyapunov Functions (PDLFs). The GSOF controllers depend solely on scheduling parameters. Although our method requires a line search to obtain suboptimal controllers, it produces practical GSOF controllers, being independent of the derivatives of scheduling parameters. Our method is proved to be no more conservative than conventional design methods via constant Lyapunov functions as well as particularly structured PDLFs. © 2011 Elsevier Ltd. All rights reserved.


The present invention addresses a problem of providing a charge device capable of charging electricity storage cells while eliminating a voltage variation among the electricity storage cells without a need for at least a circuit section playing a role in voltage equalization among the electricity storage cells to be designed to have a large current capacity, and a problem of providing a charge-discharge device constructed by additionally equipping a discharging function with the charge device. Provided are a charge device and a charge-discharge device each of which comprises a convertor, an input circuit, and a multi-stage voltage doubler rectifier circuit. An element in the convertor configured to be applied with a rectangular waveform voltage is connected to the multi-stage voltage doubler rectifier circuit via the input circuit to thereby realize a voltage equalization function, and an output section of the convertor is connected to the multi-stage voltage doubler rectifier circuit to thereby realize a charging-discharging function.


There are provided a landing decision support system, a landing decision support method, and a landing decision support program that allow a general user other than a specialist to easily and accurately read information useful for a decision of an aircraft landing. A landing decision support system 1 for providing information for supporting the decision of the aircraft landing has a screen generation unit 220 that generates various screens displayed in a display unit, and a display control unit 260 that causes the display unit to display the various screens generated by the screen generation unit 220, the screen generation unit 220 includes an echo intensity screen generation unit 240 that generates an echo intensity screen, and echo intensity information included in the echo intensity screen is generated based on echo intensity data of an observation target acquired by a weather sensor, and displays a horizontal distribution of an echo intensity using a summary statistic of the echo intensity in an area around an airport in a predetermined altitude range.


A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.

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