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.


Patent
California Institute of Technology and Japan Aerospace Exploration Agency | Date: 2016-11-10

A wheel includes a circular wheel main body and at least one grouser. The at least one grouser is provided along an outer circumference of the wheel main body and has a contact surface capable of drawing a first tangent line. The first tangent line is inclined opposite to a rotational direction of the wheel main body from the center line of the wheel main body.


Patent
Japan Aerospace Exploration Agency, Hitachi Zosen Corporation and W.L. Gore & Associates | Date: 2015-03-26

Provided are a water electrolysis method and a water electrolysis device in which mixing of the generated hydrogen and oxygen is greatly reduced and which have a high electrolysis efficiency, while being simplified in structure. In the water electrolysis method and water electrolysis device, water is electrolyzed by supplying water to the cathode side of an electrolytic membrane including a solid polymer membrane provided with a catalyst layer on a surface thereof and creating a potential difference between both surfaces of the electrolytic membrane. The temperature-controlled water is supplied only to the cathode side of the electrolytic membrane, while controlling the difference in pressure between both surfaces of the electrolytic membrane to 50 kPa or less.


Provided is a varnish including 1 to 500 parts by weight of an aromatic tetracarboxylic acid diester (A) represented by General Formula (1), 1 to 450 parts by weight of 2-phenyl-4,4-diaminodiphenyl ether (B), 1 to 100 parts by weight of a 4-(2-phenylethynyl)phthalic acid monoester (C) represented by General Formula (2), and 100 parts by weight of an organic solvent having a boiling point of 150 C. or less at 1 atmosphere or a mixture of two or more of the organic solvents (D). The components (A), (B), and (C) are dissolved in the varnish. (In the formula, R_(1 )is an aromatic tetracarboxylic acid diester residue; R_(2 )and R_(3 )are the same or different and are an aliphatic organic group or an aromatic organic group.) (In the formula, R_(4 )and R_(5 )are a hydrogen atom, an aliphatic organic group, or an aromatic organic group.)


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.

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