| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Artificial satellite structure | JP2002099021 | 2002-04-01 | JP2003291899A | 2003-10-15 | TAKANO MASAHIRO; TAKADA SHIRO; KABASHIMA SHIGENORI; HAHN STEVEN |
| PROBLEM TO BE SOLVED: To provide an artificial satellite structure having a module configuration in which a payload assembly and a bus assembly are independent from each other to avoid cost increase due to complex design, and capable of mounting enough number of electronic devices on the payload assembly while maintaining the size and the strength at the same level as a conventional structure. SOLUTION: The artificial satellite structure comprises a payload assembly 1 which is formed in the shape of a box by a payload assembly panel 3, and a bus assembly 2 which is formed at a lower end of the payload assembly 1 by a bus assembly panel 4. Four tubular type cylinders 5 are arranged in a square in the bus assembly 2, and inside each cylinder 5, fuel tanks 6 on which fuel is dividedly loaded are arranged and fixed to the cylinder by a plurality of tank support points 8 on the circumference. COPYRIGHT: (C)2004,JPO | ||||||
| 182 | Heat shield for artificial satellite | JP756997 | 1997-01-20 | JPH10203499A | 1998-08-04 | KANAMAKI YUICHI; YAMADA AKIRA |
| PROBLEM TO BE SOLVED: To enable a shield to extend/contract, extend the shield when a thruster is operated, interrupt radiation heat to a satellite main unit from the thruster, contract the shield when the thruster is not operated, and reduce a radiation quantity to the peripheral space from the satellite main unit. SOLUTION: In a plurality of sector members 4a to 4h provided with one or a plurality of circular arc-shaped slits 5 and one or a plurality of pins 6, the pin provided in one sector member adjacent to each other is slidably inserted to the slit of the other sector member, to be partly piled mutually connected, without connecting the fellow sector members in both ends, assembly is performed so as to form a circle having a center hole in an extending condition and a sector shape in a contracting condition and one sheet of the sector members is fixed to a mounting part of an artificial satellite main unit and the other sector member with an engaging part is movably engaged with a rail provided in a mounting part periphery of the artificial satellite main unit to be driven, by motor for performing extension/contraction. COPYRIGHT: (C)1998,JPO | ||||||
| 183 | Solar paddle for artificial satellite | JP31005391 | 1991-10-30 | JPH05116692A | 1993-05-14 | KUROBA TORU; ODATE YUICHI |
| PURPOSE: To achieve the effective increase of generated output with relatively small weight increase by providing a reflecting mirror additionally at the edge part of a light receiving face in a solar paddle fitted in blade shape to the body structure of an artificial satellite, and reflecting the reflected light of the sunlight on the light receiving face. CONSTITUTION: A solar paddle 1 is fitted in blade shape to the tip part of a bar like support body 3 protrusively provided at the body structure 2 of an artificial satellite. The solar paddle 1 is provided with a solar panel 5 stuck to one face side of a base material panel 4 of rectangular plate shape, and supported by the support body 3 in such a way that this one face side faces the direction of the sun. In this case, a reflecting mirror 6 of long plate shape formed along the longitudinal direction is fixed to the lower edge of the base material panel 4 in such a state that the reflecting face is inclined diagonally upward on one face side. The solar panel 5 is irradiated not only by direct light from the sun but also by the reflected light from the reflecting mirror 6. The effective increase of generated output is thereby achieved with relatively small weight increase. COPYRIGHT: (C)1993,JPO&Japio | ||||||
| 184 | Controller for artificial satellite | JP23302289 | 1989-09-11 | JPH0397013A | 1991-04-23 | KOMATSU OSAMU |
| PURPOSE: To perform the relative position control of high precision and to prevent the excitation of structural vibration by comparing the present attitude of a manipulator with the compensating thrust of an artificial satellite to perform the feedback control. CONSTITUTION: A means 6 (compensator) which estimates the compensating thrust to be given to the artificial satellite having the manipulator in accordance with the present relative position and the relative speed of the artificial satellite 1 to a working object and given object values and a means 9 (triangular wave or saw tooth wave generator) 9 which generates a triangular wave or a saw tooth wave with an oscillation frequency different from the present natural vibration frequency of the satellite 1 are provided. Further, a means 10 (comparator) which compares the compensating thrust and the triangular wave or the saw tooth wave, a pulse generating means 11 which determines the timing of turning-on/off of a pulse by the comparison result signal and determines the code of the pulse by the code of the compensating thrust, and a means 2 (thruster and controller) which controls a thrust generator by the generated pulse are provided. Thus, the stable control where structural vibration is hardly excited is performed and the control precision is improved. COPYRIGHT: (C)1991,JPO&Japio | ||||||
| 185 | Fuel tank for artificial satellite | JP7722789 | 1989-03-28 | JPH02254099A | 1990-10-12 | ONO TAKESHI |
| PURPOSE: To perform accurate measurement of residual fuel by a method wherein at least two fuel tanks are coupled on the rotary shaft of an electric motor symmetrically about an axis, and by revolving the fuel tank, fuel in the fuel tank is pressed against a tank wall surface by means of a centrifugal force. CONSTITUTION: At least two fuel tanks 3 are coupled on a rotary shaft 2 of an electric motor 1 symmetrically about an axis, and a fuel feed pipe 4 connected to each fuel tank 3 is connected to a secondary propulsion system in a way to extend the interior of the rotary shaft 2. By revolving the fuel tanks 3 through drive of the motor 1, fuel in the fuel tank 3 is pressed against a wall surface, and with this state, a liquid amount is detected by means of a level detector. COPYRIGHT: (C)1990,JPO&Japio | ||||||
| 186 | Separator for artificial satellite | JP8127686 | 1986-04-09 | JPS62238200A | 1987-10-19 | TOMOYA SHIGERU |
| 187 | Spin type artificial satellite | JP7636786 | 1986-04-02 | JPS62234800A | 1987-10-15 | SAKURAI YASUYUKI |
| 188 | Shunt dissipator for artificial satellite | JP437085 | 1985-01-14 | JPS61164428A | 1986-07-25 | IGARASHI MASAAKI |
| 189 | Detector for attitude of artificial satellite | JP169785 | 1985-01-09 | JPS61160399A | 1986-07-21 | NAKAMURA YOZO |
| 190 | Separator for artificial satellite | JP17548584 | 1984-08-23 | JPS6154400A | 1986-03-18 | YOSHIMOTO KIYOSHI |
| 191 | Apogee motor for artificial satellite | JP16223784 | 1984-08-01 | JPS6141700A | 1986-02-28 | KO MITSUTERU |
| 192 | Power source for artificial satellite | JP3366084 | 1984-02-24 | JPS60180440A | 1985-09-14 | KASAI KOITAROU; IJICHI KOUICHI |
| 193 | Detector for attitude of artificial satellite | JP5677883 | 1983-03-31 | JPS58183400A | 1983-10-26 | GERUHARUTO KURUTERERU; NATORI NAOYUKI |
| 194 | Controller for attitude of artificial satellite | JP5050782 | 1982-03-29 | JPS58167300A | 1983-10-03 | NATORI NAOYUKI |
| 195 | Artificial satellite system | JP2517582 | 1982-02-17 | JPS58141999A | 1983-08-23 | IWAMURA NARIAKI; KUSUSE TOMOHIRO |
| 196 | Holder for panel of artificial satellite | JP8367380 | 1980-06-20 | JPS5711200A | 1982-01-20 | YAMAMOTO KAZUO |
| 197 | Artificial satellite system | JP149180 | 1980-01-10 | JPS5699899A | 1981-08-11 | MORIKAWA HIROSHI; WAKASUGI NOBORU; IZUMIDA KIICHIROU |
| 198 | Artificial satellite system | JP2703277 | 1977-03-14 | JPS53112607A | 1978-10-02 | HISHIDA YOSHIHIKO |
| PURPOSE:To obtain the data only near the local station as well as to realize the economization for the ground station, by fixing the antenna of the ground station in the zenith direction to receive the data from the artificial sattellite. | ||||||
| 199 | Artificial satellite system | JP2012072537 | 2012-03-27 | JP2013203164A | 2013-10-07 | IKEFUCHI HIROSHI; MASUKAWA KAZUNORI; OISHI ATSUSHI |
| PROBLEM TO BE SOLVED: To provide an artificial satellite system which achieves a redundant system by a more compact configuration.SOLUTION: Each of a plurality of artificial satellites includes a plurality of functional modules. Each functional module provided in a first artificial satellite has the same function as each function module provided in a second artificial satellite. The first artificial satellite requests the second artificial satellite to cope with a trouble when the trouble occurs in an operation of the k-th functional module. The second artificial satellite performs input information, which is received from the first artificial satellite, by the k-th functional module, and transmits it to the first artificial satellite. | ||||||
| 200 | Sandwich panel and artificial satellite | JP2009046677 | 2009-02-27 | JP2010201965A | 2010-09-16 | MATSUNAGA KEIJI |
| PROBLEM TO BE SOLVED: To actualize wiring inside a sandwich panel without lowering the strength and rigidity of the sandwich panel. SOLUTION: The honeycomb sandwich panel 10 has square pipes 13a-c arranged between two skins 11a, b at previously-designed positions, and honeycomb cores 12a-d arranged between the skins 11a, b in regions excluding the square pipes 13a-c, Before electronic equipment is installed on the skins 11a, b, a hole is machined near the electronic equipment above the square pipes 13a-c so that wire harnesses connected to the electronic equipment can be sufficiently put into and out. After the electronic equipment is installed, the wire harnesses are put into the hole of the honeycomb sandwich panel 10 and passed through the square pipes 13a-c installed inside the honeycomb sandwich panel 10, and then put out of a hole made in the end face of the honeycomb sandwich panel 10 or in another place. COPYRIGHT: (C)2010,JPO&INPIT | ||||||
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