| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Environment observation system | JP2000079875 | 2000-03-22 | JP2001261000A | 2001-09-26 | MAEDA HIROAKI; MINE MASAYA |
| PROBLEM TO BE SOLVED: To realize a high-reliability, high-precision environment observation simply and easily. SOLUTION: A first spacecraft 10 having a signal transmitter 12 transmitting radio waves and a second spacecraft 11 having a signal receiver 13 receiving radio waves are arranged at the prescribed interval on an earth circulating orbit. Radio waves are transmitted and received between the first and second spacecraft 10, 11 to observe the environment on the propagation path of radio waves based on the received radio waves. COPYRIGHT: (C)2001,JPO | ||||||
| 82 | Method of manufacturing a refractory | JP14574892 | 1992-06-05 | JP3132688B2 | 2001-02-05 | 迪彦 堀江 |
| 83 | Artificial gravity generating system | JP19585997 | 1997-07-22 | JPH1135000A | 1999-02-09 | TOKI AKITO |
| PROBLEM TO BE SOLVED: To provide an artificial gravity generating system capable of generating artificial gravitational force in the low-gravitational space, having high structural safety, and capable of generating different gravitational environment without changing the operation of the whole system. SOLUTION: This artificial gravity generating system 100 generates artificial gravity in the low-gravity space to obtain relatively large gravity and it is provided with the circulatory space provided along the periphery of a circle assumed on the vertical plane in the gravitational direction, the artificial ground generating artificial gravity, and circulating structures 20, 30 circulating in the circulatory space with the artificial ground tilted in the downward direction toward the center of the ciecle. The artificial ground is inclined to constitute a part of the paraboloid having the same center axis as that of the circle. | ||||||
| 84 | Chemical-permeation type cell culture vessel | JP27929896 | 1996-10-22 | JPH10117767A | 1998-05-12 | TAKAOKI MUNEO |
| PROBLEM TO BE SOLVED: To provide a cell culture vessel having a chemical-addition mechanism applicable to an automatically operated cell culture apparatus. SOLUTION: A subsidiary chamber 3 separated by a membrane 2 permeating a low molecular weight substance is formed in a main chamber 1 for cell culture. A chemical solution is introduced into the subsidiary chamber 3 from a chemical solution introducing port 5 and the chemical is permeated through the membrane 2 to the main chamber l to slowly apply the chemical to the cell. The rejection molecular weight of the membrane is freely selected according to the object of cell culture. COPYRIGHT: (C)1998,JPO | ||||||
| 85 | Method of holding of the liquid in the microgravity environment and its equipment | JP19455591 | 1991-08-03 | JP2727805B2 | 1998-03-18 | 隆文 端谷 |
| 86 | Bubble producing device for environment with minute gravitation | JP740996 | 1996-01-19 | JPH09196809A | 1997-07-31 | IMAI RYOJI |
| PROBLEM TO BE SOLVED: To produce large bubbles freely and precisely. SOLUTION: A liquid supplied from a source 24 is sent to a bubble producing nozzle 18 by operating a solenoid valve 25 so as to separate the previously stored gas from the nozzle element 21 of the nozzle 18 inserted in a tank 10 storing the liquid 9, and thereby bubbles are produced, and it is made possible to produce bubbles of any desired diameter 30 by replacing the nozzle 18. | ||||||
| 87 | Navigation method using a satellite | JP16003685 | 1985-07-19 | JPH083522B2 | 1996-01-17 | JIIKUFURIITO SHUTAAKAA |
| A system and method for nagivating using satellites for transmitting coded time signals as well as additional data for the purpose of determining position, locating operations, navigation, etc., which includes, transmitting only a time signal consisting of an identification code from a plurality of orbiting navigational satellites directly to users, and distributing any data required for determining position, locating operations and navigation as well as any data on orbiting satellites and ground stations by transmission from a small number of synchronous satellites positioned in geosynchronous orbit, to users. Data from the synchronous satellites may be transmitted to users, together with a time signal, at precisely the same frequency at which the navigational satellites emit their time signals. | ||||||
| 88 | Crew attitude converting device | JP6808093 | 1993-03-26 | JPH06278699A | 1994-10-04 | WATANABE SHIGEHIKO |
| PURPOSE: To easily and safely change the attitude of a crew member in a crew attitude converting device in a gravity-free environment by accommodating the specified number of rotating bodies, the shafts of which cross each other at a right angle, their driving motors, their control device, and an accelerometer in a chassis fitted to a crew member, and providing an input device connected to the control device. CONSTITUTION: A rotating body 1a around a vertical shaft is arranged close to a rotating body 1b around a horizontal shaft, and their driving motors 4 are respectively fixed to a chassis through supporting devices 7. Further, an annular shape rotating body 1c having a recessed type frame 9 is arranged so that the rotating bodies 1a, 1b are accommodated in the recessed type frame 9. A driving motor 4 for the rotating body 1c is arranged so as to cross the respective shafts of the rotating bodies 1a, 1b at right angles, and the motor 4 is supported on the chassis through a supporting device 8. An accelerometer 3 for sending outputs of the rotating bodies 1a to 1c, its control device 2, including an input device 5, are accommodated in the chassis. The chassis is fitted to a crew member. COPYRIGHT: (C)1994,JPO | ||||||
| 89 | Propulsion power generating device in space floating or the like | JP8771393 | 1993-03-05 | JPH06255596A | 1994-09-13 | AOKI SHIRO |
| PURPOSE: To obtain propulsion power in space only by the rotating power of weights without requiring a jet rocket and material such as compressed gas. CONSTITUTION: A driving motor 3 is fitted to the offset part of a container 1, and a gear combined rotary disc 5 with a weight 6 rigidly fixed thereto is fitted through a rotary shaft 4. A weight combined power supply 7 is provided on the opposite side of the container 1. COPYRIGHT: (C)1994,JPO&Japio | ||||||
| 90 | Charger | JP23835092 | 1992-09-07 | JPH0690534A | 1994-03-29 | HONDA YUKIHIRO |
| PURPOSE:To obtain a charger that prevents the loss of a charging function when a switch of a full charging line fails or a solar battery fails to produce an output, in a charger that charges a battery by the utilization of a solar battery power when an artificial satellite and a spacecraft, or the like, is exposed to sunshine. CONSTITUTION:Two lines, that is, a charging line and a trickle charging line are made as a charging line for a battery 9. A first solar battery 1 and a second solar battery 2 are connected to a full charging line having a first switch 10 via a first diode 5 and a second diode 6, respectively. A fourth solar battery 4 is connected to a trickle charging line having a second switch 11 via a fourth diode 8. A third switch 7, a third diode and a fourth switch that effects switching of connection between the full charging line and the trickle charging line are connected in series with a third solar battery. | ||||||
| 91 | JPH01150457U - | JP4838488 | 1988-04-11 | JPH01150457U | 1989-10-18 | |
| 92 | JPS6399686U - | JP19360886 | 1986-12-16 | JPS6399686U | 1988-06-28 | |
| 93 | JPS5587900U - | JP17302178 | 1978-12-14 | JPS5587900U | 1980-06-17 | |
| 94 | JPS5360300U - | JP14270676 | 1976-10-22 | JPS5360300U | 1978-05-23 | |
| 95 | STRUCTURE LEGERE DEPLOYABLE ET RIGIDIFIABLE APRES DEPLOIEMENT, SON PROCEDE DE REALISATION, ET SON APPLICATION A L’EQUIPEMENT D’UN VEHICULE SPATIAL | PCT/FR2006/001333 | 2006-06-13 | WO2006136675A1 | 2006-12-28 | CHEYNET DE BEAUPRE, René, Jean |
La structure comprend un cordage (1-2) constitué d'au moins une corde souple (1, 2) imprégnée d'un matériau durcissant, à durcissement contrôlable, destiné à rigidifier ladite au moins une corde après son déploiement et extension. La structure peut comprendre au moins un maillage en cordage, dont au moins une corde souple (1, 2) est imprégnée du matériau durcissant et liée à elle-même et/ou à au moins une autre corde du cordage par au moins un lien (6) . Elle est indépendante de tout moyen de déploiement, mais peut également comprendre un dispositif de déploiement (3) indépendant du cordage et mettant en extension les cordes (1, 2) de la structure et les maintenant tendues pendant le durcissement du matériau durcissant. Application notamment à des structures déployables et rigidifiables embarquées à bord d'engins spatiaux. |
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| 96 | METHOD OF MODIFYING THE AXIS OF ROTATION OF THE EARTH | PCT/US2000/009952 | 2000-04-13 | WO01079613A1 | 2001-10-25 | |
| A method of modifying the Earth-rotation vector relative to the body of the planet or in inertial space by redistribution of the Earth's mass. | ||||||
| 97 | METHOD FOR PLAYING A SPACE GAME AND DEVICES FOR REALISING THIS METHOD | PCT/RU1999/000144 | 1999-04-29 | WO00037152A1 | 2000-06-29 | |
| The present invention relates to a method for playing a game that involves placing bets on the registration of a game event performed by game members (1) capable of spatial displacement. The performance of the game event is registered using a technical system (2) and according to the spatial distribution of the mobile game members (1) relative to at least one system (3) which is used for estimating the game event and which is located in the same space. The game members (1) and the system (3) are not located on the Earth but in outer space, while the registration by the technical system (2) of the performance of the game event is carried out on the Earth. In a first embodiment of the device, the games consist of races. The game members (1) consist of spacecraft, while the system (3) is a naturally occurring object and the technical system (2) sets the process of the game not on the Earth but in outer space and ensures the representation thereof on the Earth. According to a second embodiment of this device, the game members (1) consist of spacecraft, while the system (3) consist of one of said spacecraft or of a space debris. According to another embodiment of said device, the game members (1) consists of mobile objects moving at random in the outer space, while the system (3) consists of the outer surface of a spacecraft and the technical system (2) is arranged on the outer surface of the spacecraft. | ||||||
| 98 | JOINING ELEMENT FOR A JOINT WHICH IS GLUED BETWEEN TWO OR MORE BARS | PCT/DE1998/001495 | 1998-06-02 | WO98055771A1 | 1998-12-10 | |
| The invention relates to a joining element (10) produced with a sandwich-type construction, for a joint which is glued on a framework knot of a two- or three-dimensional framework used especially in the areas of air and space travel. The aim of the invention is to obtain a rigid joining element (10). To this end, the shell (12) of said joining element is configured as a U-shape, said shell being made especially from carbon fibre-reinforced plastic. A yoke wall which forms a support surface (16) extends from bar to bar in the intermediate space between two bars, said bars being arranged at an angle to each other. Two side walls (18) which form a single piece with the yoke wall and are at a distance from each other extend tangentially into cylindrical sections (20), said cylindrical sections forming a single piece with the side walls. The cylindrical sections clamp the bars between them with a prestress, acting similarly to a spring clip. Apart from being extremely rigid, the inventive joining element (10) is also characterised in that the shell (12) transmits forces to the bars predominantly in the form of shearing stresses which are advantageous for the adhesive bond, and fixes the bars to each other whilst the adhesive agent is setting. | ||||||
| 99 | STRUCTURE LEGERE DEPLOYABLE ET RIGIDIFIABLE APRES DEPLOIEMENT, SON PROCEDE DE REALISATION, ET SON APPLICATION A L'EQUIPEMENT D'UN VEHICULE SPATIAL | EP06764782.6 | 2006-06-13 | EP1893489A1 | 2008-03-05 | CHEYNET DE BEAUPRE, René, Jean |
| The invention concerns a structure comprising a rigging (1-2) consisting of at least one flexible rope (1, 2) impregnated with a hardening substance, with controllable hardening, designed to rigidify at least one rope after it has been deployed and extended. The structure may comprise at least one rigging mesh, whereof at least one flexible rope (1, 2) is impregnated with the hardening substance and bound to itself and/or to another rope of the rigging by at least one bond (6). Said structure is independent of any means of deployment, but may also comprise a deploying device (3) independent of the rigging and extending the ropes (1, 2) of the structure and maintaining them taut while the hardening material is cured. The invention is in particular applicable to deployable structures capable of being rigidified on board space crafts. | ||||||
| 100 | METHOD FOR PLAYING A SPACE GAME AND DEVICES FOR REALISING THIS METHOD | EP99921316 | 1999-04-29 | EP1057503A4 | 2002-10-30 | SAFRONOV SERGEI MIKHAILOVICH; ZAITSEV EVGENY ALEXANDROVICH; MELNIKOV ALEXEI JURIEVICH; KONSTANTINOV JURY FEDOROVICH; REZNIKOV ALEXANDR EVGENIEVICH; STAROSTIN STANISLAV VASILIEVIC |
| The present invention relates to a method for playing a game that involves placing bets on the registration of a game event performed by game members (1) capable of spatial displacement. The performance of the game event is registered using a technical system (2) and according to the spatial distribution of the mobile game members (1) relative to at least one system (3) which is used for estimating the game event and which is located in the same space. The game members (1) and the system (3) are not located on the Earth but in outer space, while the registration by the technical system (2) of the performance of the game event is carried out on the Earth. In a first embodiment of the device, the games consist of races. The game members (1) consist of spacecraft, while the system (3) is a naturally occurring object and the technical system (2) sets the process of the game not on the Earth but in outer space and ensures the representation thereof on the Earth. According to a second embodiment of this device, the game members (1) consist of spacecraft, while the system (3) consist of one of said spacecraft or of a space debris. According to another embodiment of said device, the game members (1) consists of mobile objects moving at random in the outer space, while the system (3) consists of the outer surface of a spacecraft and the technical system (2) is arranged on the outer surface of the spacecraft. | ||||||
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