| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 201 | Artificial satellite antenna | JP2004319761 | 2004-11-02 | JP2006130988A | 2006-05-25 | WATANABE KAZUKI; WATANABE AKITO |
| PROBLEM TO BE SOLVED: To provide a light artificial satellite antenna which does not have bad influence on a satellite orbit at the time of extension, and solve a problem of hardening after extension. SOLUTION: The artificial satellite antenna comprises a shell structure 1 of an STEM type, and inflatable structure 2 functioning as an actuator for extension of the shell structure 1. A tube 6 of the inflatable structure 2 is arranged so as to be inserted in a hollow cylindrical part of the shell structure 1. The tube 6 is expanded by the pressure of gas supplied into the tube 6, and the shell structure 1 is extended by using the expanding force of the tube 6 as driving force. The artificial satellite antenna having merits of both antennas of the STEM type and the inflatable structure, and avoiding demerits of both antennas can be provided. COPYRIGHT: (C)2006,JPO&NCIPI | ||||||
| 202 | Heat conductor for artificial satellite | JP2001054832 | 2001-02-28 | JP2002255099A | 2002-09-11 | TAKANO OSAMU |
| PROBLEM TO BE SOLVED: To provide a heat conductor for an artificial satellite easily manufacturable in a short time and light in weight without requiring working accuracy. SOLUTION: A space between structural panels 4a and 4b of the artificial satellite is connected and deformed by flexibility of a carbon fiber 11 to transmit and receive heat between the panels 4a and 4b, and a cross section of carbon fiber 11 is brought into contact with the surfaces of the panels 4a and 4b. COPYRIGHT: (C)2002,JPO | ||||||
| 203 | Artificial satellite system | JP3147398 | 1998-02-13 | JPH11227697A | 1999-08-24 | INAMIYA KENICHI |
| PROBLEM TO BE SOLVED: To provide an artificial satellite system which has uniform distribution both temporally and spatially in which the ground surface staying time of the on-ground locus of the satellite is taken into consideration. SOLUTION: When the constellation to constitute the base of an artificial satellite system is to be set, the inclining angles of a number of artificial satellites are set variously so that staying time per unit of lattitudes of the satellite on-ground locus becomes uniform, and the temporal and spatial distributions of the on-ground loci are leveled. Accordingly the distribution of the on-ground loci covering all satellites is made uniform, and one or more satellites can be seen at all times from any point on the ground surface, and a global covering system with an effective number of satellites in use can be established. COPYRIGHT: (C)1999,JPO | ||||||
| 204 | Artificial satellite system | JP23454695 | 1995-09-13 | JPH0976999A | 1997-03-25 | TAKAHASHI FUMIO |
| PROBLEM TO BE SOLVED: To reduce the weight of a satellite, simplify its constitution, and reduce the price by measuring the roll angle with high accuracy from the low altitude region. SOLUTION: When the orbit altitude data are received from a satellite side, a command data inputting part 3 transmits the orbit altitude data to a signal processor 4. The signal processor 4 calculates 1/2tanθ or 1/tanθ based on the orbit altitude data from the command data inputting part 3. The attitude angle generating and processing function of a digital signal processing part 25 calculates the angle data based on the earth pulse from a comparator of an analog signal processing part 23, the satellite center reference signal from an encoder digital part 24, and one-pulse angle increment signal, and the roll output calculated from the angle data is multiplied by 1/2tanθ or 1/tanθ based on the value from the signal processor 4, and delivered to a signal conditioner 28. | ||||||
| 205 | Structure of artificial satellite | JP1804492 | 1992-02-04 | JPH05213283A | 1993-08-24 | KAMIMURA MASAYUKI |
| PURPOSE: To improve the spin stabilizing performance of an artificial satellite and to enlarge the effective utilization of an envelope by altering the mass characteristic on an orbit of a spin stabilization type artificial satellite restricted by the arrangement of apparatus in the artificial satellite housing envelope of an launching rocket. CONSTITUTION: A spin unstabilizatin type artificial satellite having apparatus arranged wholly evenly so as to effectively utilize an envelope can be modified into a spin stabilization type artificial satellite immediately after getting on an orbit by providing an extending mechanism 3 loaded on the central structure body 2 of the artificial satellite and plural divided extending structures 1a, 1b, 1c, and extending the extending structures 1a, 1b, 1c from the central structure body 2 through the extending mechanism 3 on the orbit to enlarge the moment of inertia around a spin axis Y. COPYRIGHT: (C)1993,JPO&Japio | ||||||
| 206 | Artificial satellite controller | JP19842389 | 1989-07-31 | JPH0362205A | 1991-03-18 | KOMATSU OSAMU |
| PURPOSE: To control the motions of both an artificial sattelite and a manipulator with high accuracy by estimating the driving torque to give the feedback control to the motion locus of the manipulator and adding the compensating and driving torques for manipulator to apply the feedback control to the joint torque of the manipulator. CONSTITUTION: A servo compensator 10 estimates the driving torque to apply the feedback control to each joint angle of a manipulator 1. The estimated driving torque value is added to the compensating torque. Then a manipulator controller 2 applied the feedback control to the joint torque. Thus the compensating torque value is estimated in real time to an artificial satellite and the manipulator 1 with reflection of the motions of the present artificial satellite and manipulator 1. As a result, the highly accurate compensating torque value is obtained. Furthermore the feedback control is also carried out to the joint torque for drive of the manipulator 1. Then the highly accurate motion control is secured for both the artificial satellite and the manipulator 1. COPYRIGHT: (C)1991,JPO&Japio | ||||||
| 207 | Controller for orbit of artificial satellite | JP19734885 | 1985-09-06 | JPS6259199A | 1987-03-14 | OCHIAI KIYOSHI |
| 208 | Controller for attitude of artificial satellite | JP15630285 | 1985-07-16 | JPS6218399A | 1987-01-27 | SATO MASAO |
| 209 | Stabilizer for attitude of artificial satellite | JP12019184 | 1984-06-11 | JPS60261800A | 1985-12-25 | TAKEZAWA SUSUMU; TAKEDA NAOMICHI |
| 210 | Controller for attitude of artificial satellite | JP21525183 | 1983-11-16 | JPS60107500A | 1985-06-12 | NATORI NAOYUKI |
| 211 | Detector for attitude of artificial satellite | JP5955383 | 1983-04-05 | JPS59184100A | 1984-10-19 | SASANUMA MASAO |
| 212 | Separator for artificial satellite | JP789083 | 1983-01-20 | JPS59134100A | 1984-08-01 | SHIRAKO GOROU; OOISHI KATSUMI |
| 213 | Artificial satellite system | JP1848681 | 1981-02-10 | JPS57134399A | 1982-08-19 | IZUMIDA KIICHIROU; NISHIMURA JIYUN; YAMAGUCHI TETSUO; NATORI NAOYUKI; TOMITA MASAYUKI; TAKAZAWA GIICHI |
| 214 | Detector for attitude of artificial satellite | JP13399280 | 1980-09-26 | JPS5758599A | 1982-04-08 | OOTANI SHINICHI |
| 215 | 인공위성을 이용한 신호의 수신방법, 서비스의 제공방법,인공위성의 제어방법 및 수신단말과 인공위성을 제어하는장치 | KR1020030073102 | 2003-10-20 | KR1020040034548A | 2004-04-28 | 이와타다다요시; 마에다도시히데; 이시다다카하루; 이노우에히데키 |
| PURPOSE: A receiving method of a signal by using an artificial satellite, a supplying method of a service, a controlling method of the artificial satellite and a device for controlling a receiving terminal and the artificial satellite are provided to service communication and broadcasting functions by using an orbital satellite located at higher elevation angle, thereby reducing a shield effect of propagation. CONSTITUTION: A communication/broadcasting system(1) supplies at least either a communication service or a broadcasting service between a communication/broadcasting center station(4) and a mobile station(6) located within a beam spot(5) radiated from orbital satellites(3) or a fixed station, via the orbital satellites(3) controlled by a satellite control station(2). A terminal device(11) comprises as follows. A position measuring antenna(12) measures a position of a mobile. A communication antenna(13) communicates with the orbital satellites(3). A position measuring device(14) measures a current position or calculates a mobile speed and a mobile direction. A communication device(15) transceives data with the satellites(3). | ||||||
| 216 | Apparatus for determining attitude of artificial satellite | US09879918 | 2001-06-14 | US06523786B2 | 2003-02-25 | Shoji Yoshikawa; Katsuhiko Yamada; Haruhiko Shimoji; Masao Inoue; Norimasa Yoshida; Katsumasa Miyatake |
| An apparatus for determining the attitude of an artificial satellite by narrowing attitude candidates to a correct one in a short time. The apparatus has star sensors, a star catalog data base, star identification sections in each of which star images output from the star sensors are collated with a star catalog with respect to each star sensor to output a group of corresponding candidates, attitude computation sections for computing a value of an attitude candidate of the artificial satellite with respect to each corresponding candidate, an attitude updating section for updating the value of the attitude candidate on the basis of the star images output from the star sensor and the star catalog, and an attitude propagation section for computing the value of the attitude candidate at the present sampling time from the value of the attitude candidate at the preceding sampling time and the artificial satellite's angular velocity. An attitude candidate unification section for comparing and combining the values of attitude candidates into one candidate is provided in a loop including the attitude updating section and the attitude propagation section. | ||||||
| 217 | Apparatus for determining attitude of artificaial satellite | US09879918 | 2001-06-14 | US20020117585A1 | 2002-08-29 | Shoji Yoshikawa; Katsuhiko Yamada; Haruhiko Shimoji; Masao Inoue; Norimasa Yoshida; Katsumasa Miyatake |
| An apparatus for determining the attitude of an artificial satellite arranged to narrow attitude candidates down to a correct one in a short time. The apparatus has star sensors, star catalog data bases, star identification sections in each of which star images output from the star sensors are collated with a star catalog with respect to each star sensor to output a group of corresponding candidates, attitude computation sections for computing a value of an attitude candidate of the artificial satellite with respect to each corresponding candidate, an attitude updating section for updating the value of the attitude candidate on the basis of the star images output from the star sensor and the star catalog, and an attitude propagation section for computing the value of the attitude candidate at the present sampling time from the value of the attitude candidate at the preceding sampling time and the artificial satellite body angular velocity. An attitude candidate unification section for comparing the values of a plurality of attitude candidates to combine the same into one is provided in a loop formed by the attitude updating section and the attitude propagation section. | ||||||
| 218 | Artificial satellite navigation system and method | US268129 | 1999-03-15 | US06166684A | 2000-12-26 | Shoji Yoshikawa; Katsuhiko Yamada; Hiroshi Koyama; Jun Tsukui |
| An artificial satellite navigation system and method. The artificial satellite navigation system includes a global positioning system (GPS) receiver, local satellite, and remote satellite absolute navigation units estimating the position and velocity of a local satellite or a remote satellite and bias and drift of a clock in the receiver. A difference calculation unit calculates differences in position and velocity from the local satellite and remote satellite absolute navigation units. A relative navigation unit estimates the relative position and velocity of the local satellite with respect to the remote satellite. The relative navigation unit navigates the local satellite relative to the remote satellite. | ||||||
| 219 | Positioning system utilizing artificial satellites and positioning method | US51625 | 1993-04-22 | US5363110A | 1994-11-08 | Kenichi Inamiya |
| A positioning system and method utilizing a plurality of artificial satellites, in which times of positioning time signals transmitted from at least four artificial satellites to a positioning available area are always made coincident with a standard time of a ground control station to maintain accuracy of the time. In the ground control station, phases of a receive PN code obtained from the time signal included in the positioning signal of the artificial satellite and a pseudo receive PN code obtained by delaying the standard time of the ground control station by a radio wave propagation time, measured in real time, corresponding to a range between the ground control station and the artificial satellite are compared, and from the detected time error, a time correction command signal is obtained and is transmitted to the artificial satellite to correct the time of the positioning time signal of the artificial satellite. As a result, the time of the positioning time signal can always be coincident with the standard time of the ground control station to maintain accuracy. As an original oscillator of the positioning time signals of the artificial satellites, a crystal oscillator can be used in place of an atomic clock. | ||||||
| 220 | Method and apparatus for changing orbit of artificial satellite | US477876 | 1990-04-09 | US5163641A | 1992-11-17 | Tetsuo Yasaka |
| A method and apparatus for changing the orbit of an artificial satellite. The apparatus is caused to approach a target satellite and to be coupled thereto in space so as to constitute a dumbbell-like coupled system. The apparatus has a propulsion unit. The unit generates a thrust, whereby the velocity of the center of gravity of the apparatus increases, and the apparatus rotates around the center of gravity. As a result, the coupling system is placed in transition orbit.In the transition orbit, the coupled system is released at a timing when the direction of elongation of the coupled system becomes perpendicular to the orbital velocity vector. Subsequently, the target satellite is placed in a final target orbit, and the separated orbit changing apparatus is placed in an orbit different from the target orbit. | ||||||
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