| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Mass release mechanism for satellites | US3424403D | 1967-02-14 | US3424403A | 1969-01-28 | HULL WILSON E |
| 62 | Passive communications satellite or similar article | US3420469D | 1966-07-22 | US3420469A | 1969-01-07 | JOHNSON JOHN S; MCCULLOUGH EDWARD E |
| 63 | Protecting apparatus | JP2003408211 | 2003-10-22 | JP2005126027A | 2005-05-19 | NAKAGAWA TAKEO |
| <P>PROBLEM TO BE SOLVED: To solve the problem that there is a difficulty in the efficient and economical supply of raw materials for manufacturing various institutions in outer space, for example, a lack of the means for supplying raw materials of iron to manufacturing systems (groups) arranged in the gravity-free outer space in the neighborhood of the earth. <P>SOLUTION: A protecting apparatus is composed of a transportation apparatus for carrying iron meteorites, an observation apparatus for sending/receiving the information observed by an observation object mounted on board the transportation apparatus to/from an earth control object, and a control apparatus for controlling the whole transportation apparatus. <P>COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 64 | Assembling man-hour estimation system and assembling man-hour estimation method for communication satellite | JP2003188146 | 2003-06-30 | JP2005025338A | 2005-01-27 | YOSHIMURA YUJI; FUNADA MASAHIKO; KOSHO KENJI; TAKEUCHI KEIJI |
| PROBLEM TO BE SOLVED: To provide an assembling man-hour estimation system allowing easy estimation of assembling man-hours of a communication satellite. SOLUTION: This system comprises: an equipment information database 3 storing heat generation density of communication equipment loadable in the communication satellite; an installation man-hour database 2 storing work man-hours in each installation process of the communication satellite with the work man-hours associated to the heat generation density; a connection relation input part 5 for inputting connection relation of the communication equipment constituting the communication satellite; an equipment information extraction part 6 extracting the heat generation density from the equipment information database 3 on the basis of the inputted connection relation; and an installation man-hour generation part 7 extracting the work man-hours from the installation man-hour database 2 on the basis of the heat generation density, and generating installation man-hours of a plurality of installation processes from the work man-hours. COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 65 | Satellite introducing method, and device and program for proposing introduction route | JP2003078496 | 2003-03-20 | JP2004284479A | 2004-10-14 | AOKI HIROKO |
| <P>PROBLEM TO BE SOLVED: To provide a satellite introducing method for rapidly introducing a satellite introduced in a geostationary transfer orbit to an inclined synchronization orbit having an arbitrary right ascension of ascending node, and a device and a program for proposing an introduction route to propose an optimum introduction route therefor to a person engaged therein. <P>SOLUTION: The introduction route proposing device 10 presents an introduction route requiring least amount of propellant among a first introduction route via a first transfer circular orbit having the same orbit angle of inclination as that of an inclined synchronization orbit ISO, and then, via a second transfer circular orbit having the same right ascension of ascending node as the inclined synchronization orbit ISO, a second introduction route having the same orbit angle of inclination as that of the inclined synchronization orbit ISO, and having the same right ascension of ascending node as that of the inclined synchronization orbit ISO after via the first transfer circular orbit in which the ascending node and the descending node are inverted from each other, and a third introduction route via the first circular transfer circular orbit having the same orbit angle of inclination as that of the geostationary transfer orbit GTO, and via the second transfer circular orbit having the same right ascension of ascending node and the orbit angle of inclination as those of the inclined synchronization orbit ISO. <P>COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 66 | Computer program to have computer control production of command plan for control of artificial celestial body | JP2002089713 | 2002-03-27 | JP2003285799A | 2003-10-07 | NOMURA KAZUYA |
| <P>PROBLEM TO BE SOLVED: To facilitate formation of a command plan to cope with an increased and complicated operation demand, in accordance with the characteristics of operation control and plan decision of an artificial celestial body. <P>SOLUTION: A command plan forming device 10 to form a command plan constituted by a command for control of the artificial celestial body comprises an operation demand receiving part 11, a command plan forming part 13, and an artificial celestial body simulator 14. The operation demand receiving part 11 receives operation demand data describing a plurality of commands corresponding to a state of the artificial celestial body. The command plant forming part 13 selects a command adapted to a command plan from a plurality of commands described at operation demand data based on information indicating the state of the artificial celestial body. The artificial celestial body simulator 14 forms information indicating the state of the artificial celestial body. <P>COPYRIGHT: (C)2004,JPO | ||||||
| 67 | Water recycling method and apparatus in a closed system space | JP13506093 | 1993-05-14 | JP3398715B2 | 2003-04-21 | 久夫 一条; 武司 小林; 興彦 平佐; 泰典 遠矢 |
| 68 | Staying type space tourism institution, its construction method and repair method | JP2001037689 | 2001-01-11 | JP2002205700A | 2002-07-23 | SAOTOME TAKESHI |
| PROBLEM TO BE SOLVED: To construct in space a space tourism institution for safely and comfortably attaining the commercialization of a spacewalk, dissolving defects in a conventional spacewalk such as the unit cost and operation cost of a space suit being high and the space in the open space being attended with the danger of collision of space debris, space radiation exposure and drifting. SOLUTION: This space tourism institution is mainly composed of a transparent sphere shell having a space debris collision resisting characteristic and a space radiation shielding characteristic and holding the interior to normal temperature and normal pressure; a transparent sphere shell external module; a connection module having a function of connecting the transparent sphere shell and the external module; and a transparent sphere shell internal truss. The space tourism institution is constructed mainly by launching of a truss developing satellite, development in space, launching of the connection module and connection to the tip of the truss, injection blow molding of the transparent sphere shell and assembly. COPYRIGHT: (C)2002,JPO | ||||||
| 69 | Data relay satellite system | JP7985490 | 1990-03-28 | JP2952946B2 | 1999-09-27 | KATO HIRONORI |
| 70 | Aquatic animal breeding device | JP27541193 | 1993-11-04 | JP2915765B2 | 1999-07-05 | NAGAOKA TOSHIHARU; OKAZAKI HIROSHI |
| 71 | How to transport the cargo to the extraterrestrial and extraterrestrial equipment | JP4761285 | 1985-03-12 | JPH0818600B2 | 1996-02-28 | エフ．マーウイツク エドワード |
| 72 | New rocket launching method | JP4031894 | 1994-02-02 | JPH07215300A | 1995-08-15 | KUNO MASAYA |
| PURPOSE: To prevent the orbit correction of the earth and to protect the environment of the earth by launching an object to launch at night, or in the direction to the west in some occasion. CONSTITUTION: The main points of this proposal are to launch at night, to launch in the direction to the west, and to turn back in the direction to the east in a space. COPYRIGHT: (C)1995,JPO | ||||||
| 73 | Turbine generator | JP11962589 | 1989-05-12 | JPH071995B2 | 1995-01-11 | 一 片岡 |
| 74 | Space robot | JP7131593 | 1993-03-30 | JPH06278700A | 1994-10-04 | FURUKAWA KOICHI |
| PURPOSE: To improve the reliability of long-time operation of a small robot by providing operating legs on the peripheral wall of a robot body so that they are projected from the wall and can be freely driven, and driving- controlling the operating legs to control the attitude of the robot body. CONSTITUTION: Plural, for example, two working arms 11 are provided on a robot body 10 to work by remote control. Further, operating legs 12 are rotatably provided on four corner parts of the robot body 10. The operating legs 12 are driven to turn by connecting their base parts to driving sources such as drive motors, etc. The drive motors, etc., are controlled through an attitude control device. That is, based on movement of the positions of the center of gravity of the working arms 11 due to the operation of the working arms 11, the drive motors, etc., are driven to control the attitude of the robot body 10. The operating leg 12 can be provide on one place or two or more places. COPYRIGHT: (C)1994,JPO | ||||||
| 75 | Production of refractories | JP14574892 | 1992-06-05 | JPH05339051A | 1993-12-21 | HORIE MICHIHIKO |
| PURPOSE: To provide the process for production of a material for constituting a building to protect moon surface facilities on the moon surface by using the materials existing on the moon surface. CONSTITUTION: Oxides contg. at least silica are used as a raw material 1 and the raw material is pulverized and sieved 2. A compacting agent 3 is added to the raw material in a vacuum and the raw material is mixed 4 in the vacuum. The mixture is pressurized in the vacuum to compact 5 the raw material to a prescribed shape. The compacted raw material is sintered 6 in the vacuum of a high temp. and high pressure and the sintered raw material is cooled 7 in the vacuum. COPYRIGHT: (C)1993,JPO&Japio | ||||||
| 76 | JPS5063000U - | JP11543373 | 1973-10-03 | JPS5063000U | 1975-06-09 | |
| 77 | A SELF OPENING HINGES | PCT/GB2007/001945 | 2007-05-24 | WO2007141478A1 | 2007-12-13 | FREEMAN, Alan, John; DANDO, Glyn, Charles |
A self opening hinge comprises a tubular member with a set of circumferentially spaced blades (13, 14, 15) extending longitudinally between opposite end portions (11, 12). It can be folded by bending the blades to bring the end portions together and when released will naturally return to the straight condition under the spring action of the blades. The blade (13) which will be located on the inside of the fold when the member is in its folded condition is configured with a convex circumferential curvature as viewed from the axis of the member when in its unfolded condition, namely reversed in curvature as compared with the other blades (14, 15). In this way the stress on the inside blade when the member is folded is reduced as compared with a conventional hinge where all the blades follow a circular tube profile and are concave as viewed from the central axis. |
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| 78 | AN AIRCRAFT LAUNCH COMPLEX FOR TRANSPORTATION, FUELING AND AIR-LAUNCHING OF A MISSILE CARRIER | PCT/RU2000/000197 | 2000-05-23 | WO01066413A1 | 2001-09-13 | |
| The invention relates to aerial cargo means used for transporting equipped large-sized missile carriers to a region which is optimal for launching thereof and also for fueling and launching said carriers from the upper atmosphere to the space. The inventive aircraft complex for transportation, fueling and air-launching of a missile complex comprises an aircraft-launcher and a missile launcher with a space vehicle fixed thereto. The aircraft-launcher is assembled by using a head section and the main wing of an "Antey" aircraft, butt-jointed with the aid of a coupling section, and a rear section and an additional wing of the "Ruslan" aircraft mounted in tandem to the main wing. Propelling motors are mounted on the wings in such a way that it is possible to place the motors of the additional wing in a staggered manner in respect to the motors of the main wing. A fuselage is embodied with a common cargo compartment in which instruments and systems necessary for fueling, arming and starting operations for a missile carrier are arranged. A wheel train is embodied in combined manner and assembled with retractable landing gears e.g. a nose rotatable wheel, and a head, intermediate and rear landing gears being mounted symmetrically to the longitudinal axis of the fuselage. | ||||||
| 79 | PROCESS AND DEVICE FOR MOVING PARTICLES, AND USE OF SAID PROCESS AND DEVICE | PCT/EP1998/000948 | 1998-02-19 | WO98039567A1 | 1998-09-11 | |
| In a process for moving a particle, the same is exposed to a gaseous atmosphere, causing the formation of an adsorbate (16) on the particle surface (14). By a concerted energy supply, in particular in the form of a particle beam (17), to a limited region (18) of the particle surface (14), the adsorbate (16) located in this region (18) is desorbed, generating individual pulses which act on the particle (10) according to the reaction principle and which lead to a total or net pulse, thus causing the particle (10) to move. | ||||||
| 80 | Computer program to have computer control production of command plan for control of artificial celestial body | JP2002094447 | 2002-03-29 | JP2003285800A | 2003-10-07 | NOMURA KAZUYA |
| <P>PROBLEM TO BE SOLVED: To support formation of a command plan where the whole is rationally balanced well, as consideration is made on the characteristics of operation control of an artificial celestial body and decision of a plan, and any particular operation demand is not overemphasized. <P>SOLUTION: A command plan forming device to form a command plan to form a command plan constituted by a command for control of the artificial celestial body is provided with an operation demand receiving means 1, a processing priority control means 2, and a command plan forming means 3. The operation demand receiving means 1 obtains a plurality of commands desired to be executed and a plurality of operation demand data describing a desired order of the commands. The processing priority control means 2 forms a plurality of operation demand files consisting of a plurality of operation demand data arranged in order. The command plan forming means 3 forms a command plan in order from operation demand data, where orders arranged in the operation demand data are first, and by reflecting a command, high in a desired rank in the operation demand data, in a command plan by giving priority to the command, a command plan is formed. <P>COPYRIGHT: (C)2004,JPO | ||||||
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