| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 241 | Power source for artificial sattelite | JP4884381 | 1981-04-01 | JPS57162917A | 1982-10-06 | KASAI KOITAROU |
| 242 | Controller for attitude of artificial satellite | JP16759980 | 1980-11-28 | JPS5790300A | 1982-06-04 | INOUE MASAO; TSUCHIYA KAZUO |
| 243 | Propellant tank of artificial satellite | JP5660579 | 1979-05-09 | JPS55148940A | 1980-11-19 | KUWANO YOSHIAKI |
| PURPOSE: To make propellant of an artificial satellite separable from the inner wall of a tank and facilitate its discharge, by introducing pressurized gas in the tank of the propellant. CONSTITUTION: A propellant tank 1 is internally equipped with a metallic porous body 7 close to the internal circumference, and blade-type metallic bodies 9 intalled at intervals of 90 degree. A compressed gas piping 4 has its opening in the clearance between the tank 1 and the metallic body 7. Pressurized gas introduced from the piping 4 flows in the tank 1 through the blade-type metallic bodies 9 to gather the propellant in the tank 1 to the internal circumference and the metallic bodies 9, thus separates the propellant from an area 6 filled with the pressurized gas. An outlet 3b of the propellent, being enclosed by other metallic bodies 8a, 8b, is disposed to the tank 1 to facilitate discharge of the propellent through said outlet 3b by the effect of the pressurized gas. COPYRIGHT: (C)1980,JPO&Japio | ||||||
| 244 | Artificial satellite system | JP4323178 | 1978-04-14 | JPS54136115A | 1979-10-23 | HISHIDA YOSHIHIKO |
| PURPOSE:To obtain a large amount of data featuring a high resolving power by giving a contol to turn the antenna of the mobile satellite by 180 deg. while the satellite goes half round the earth and thus making the antenna oppose to the antenna of the stationary satellite at all times. CONSTITUTION:A posture control is given to mobile satellites 2-4 which go round the low orbit on the earth 1 so that their camera installing directions may turn to the center of the earth. Based on this control, the direction is conrolled for the antennas. In other words, antennas 7 have turn of 180 deg. while the position shifts from satellite 2 to 4. Thus, a control is given so that the antenna has a 180 deg. turn in the opposite direction while the mobile satellite goes half round the earth 1. As a result, antennas 7 of satellites 2-4 are alaways made to oppose to antenna 6 of stationary satellite 5, thus obtaining the picture or the like featuring a high resolving power for a sufficient time of a day. | ||||||
| 245 | 비상시 주 광경로 확보를 위한 안전장치가 구비된 인공위성용 미러 구동장치 | KR1020120001189 | 2012-01-04 | KR101303091B1 | 2013-09-06 | 이경민; 오현웅 |
| 본 발명은 인공위성에서 사용되는 적외선 검출기의 교정에 필요한 광경로를 확보할 수 있도록 비상시 교정 미러를 강제적으로 수납 상태로 전환시키는 안전장치가 구비된 인공위성용 미러 구동장치에 관한 것으로서,
지상 또는 목표물로부터 입사되는 적외선의 주 광경로(101)에 배치된 교정 미러(201)와, 일측 단부가 메인 프레임(203)에 회전 가능하게 결합되며 교정 미러를 지지하는 미러 지지 프레임(202)과, 메인 프레임에 설치되어 미러 지지 프레임을 회전시켜 교정 미러가 수납 상태인 제1위치 또는 전개 상태인 제2위치로 회전되도록 하는 미러 구동 수단(204)과, 미러 지지 프레임의 위치를 회전 위치를 감지하여 제어부(120)로 전송하는 위치감지수단과, 비상시 미러 구동 수단과 별개로 교정 미러를 제1위치로 강제 회전시키는 안전장치를 포함하고, 안전장치는, 미러 지지 프레임의 타측 단부와 미러 구동 수단의 회전축을 연결하되 필요에 따라 미러 지지 프레임으로부터 분리되는 구속해제장치(207)와, 일단은 메인 프레임에 장착되고 타단은 미러 지지 프레임에 장착되어 교정 미러가 제2위치에서 제1위치로 회전하도록 복원력을 제공하는 정하중 스프링(208)으로 이루어진 것을 특징으로 한다. |
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| 246 | 비상시 주 광경로 확보를 위한 안전장치가 구비된 인공위성용 미러 구동장치 | KR1020120001189 | 2012-01-04 | KR1020130080340A | 2013-07-12 | 이경민; 오현웅 |
| PURPOSE: A mirror driving apparatus for an artificial satellite with a safety device is provided to rotate a correction mirror by using a drive unit, thereby providing the infrared ray information to a correctable infrared ray detection unit. CONSTITUTION: A mirror driving apparatus for an artificial satellite with a safety device comprises a safety device. The safety device forcibly turns a correction mirror (201) to a first position separately from a mirror driving unit (204). The safety device comprises a restriction removal unit (207) and a static load spring (208). The restriction removal unit connects the end part of the other side of a mirror supporting frame (202) with a rotary shaft of the mirror driving unit, and separates the end part of the other side of a mirror supporting frame (202) from a rotary shaft of the mirror driving unit as occasion demands. The static load spring has one end which is mounted on a main frame (203) and the other end which is mounted to the mirror supporting frame, and provides a restoring force for the correction mirror to move from a second position to a first position. | ||||||
| 247 | 기준물체와 인공위성간의 상대위치 산출방식에 의한위성안테나 및 그 설치방법 | KR1020037005850 | 2001-10-26 | KR1020030044054A | 2003-06-02 | 권태인 |
| PURPOSE: A satellite antenna is provided to be capable of being installed by an unskillful person and at an optimized receiving state in a short time. CONSTITUTION: A reflection plate receives and collects electric waves transmitted from an artificial satellite. A reflection plate support table is connected to a back surface of the reflection plate so as to adjust and fix an azimuth angle and an angle of elevation of the reflection plate. A feed horn unit is provided at one side of the reflection plate so as to receive electric waves reflected via a reflection surface of the reflection plate. A reference scale is switched so that an installation scale directs a relative an azimuth of a desired specific fixed satellite with respect to the reflection plate established to direct a reference object. The reference scale is rotated in left and right directions on the support table. | ||||||
| 248 | 위성방송수신기의 인공위성위치추적장치에서 안테나 구동용기계장치의 결함 보상방법 | KR1019980050712 | 1998-11-25 | KR1020000033723A | 2000-06-15 | 신익룡 |
| PURPOSE: A method for compensating a defect of an antenna driving mechanical apparatus in an artificial satellite position tracing unit of a satellite receiver is provided to adjust a position of the antenna driving apparatus to a position of the artificial satellite regardless of defects of the antenna driving apparatus. CONSTITUTION: A defect compensation method comprises the steps of: recognizing an initial position, a west end position and an east end position of a satellite reception antenna; storing positions of satellites placed between the wet end position and the east end position and moving paths of the satellites; when a channel converting signal is input, determining whether a current channel is within a satellite in a state corresponding to the satellite reception antenna; and when the current channel is not within the satellite in the afore mentioned determining step, searching a position of a corresponding satellite and moving the satellite reception antenna to the searched position. | ||||||
| 249 | Non-aqueous electrolytic battery module for artificial satellite | US09664067 | 2000-09-18 | US06246217B1 | 2001-06-12 | Hiroaki Yoshida; Takefumi Inoue; Naozumi Miyanaga; Nobutaka Imamura |
| An artificial satellite is equipped with solar batteries and a non-aqueous electrolyte battery module for artificial satellite (i.e., a lithium battery). The non-aqueous electrolyte battery module is provided with a non-aqueous electrolyte battery, a temperature sensor, a charged state measurement sensor, and a computer for receiving signals output from the sensors. The managed temperature of the non-aqueous electrolyte battery in a solstice season is set so as to become equal to or lower than the managed temperature of the battery when the satellite is in the solstice season. The computer controls a temperature controller, thereby maintain the managed temperature of the battery within a given temperature range. The charged state of the lithium battery is controlled by means of turning on or off a charging switch under the control of computer. When the satellite is in the eclipse season, the managed charged state of the non-electrolyte battery is controlled so as to be a value of 50% or more. When the satellite is in the solstice season, the managed charged state of the non-aqueous electrolyte battery is controlled so as to be a value of 75% or less. | ||||||
| 250 | Artificial satellite equipped with aerodynamic orientation rudders | US535214 | 1996-01-16 | US5716031A | 1998-02-10 | Paul Duchon |
| An artificial satellite equipped with roll, yaw and pitch rudders (4, 4', 5) to impose on it rotational forces around its three axes due to the resistance of the rarefied air which surrounds the satellite (compensation for the dynamic inertia of rotating objects onboard the satellite can also be ensured). This invention applies to low-orbit satellites. | ||||||
| 251 | Fluid pressure operated head for setting mandrel rivets | US3630067D | 1970-04-30 | US3630067A | 1971-12-28 | HENSHAW JAMES N |
| A fluid pressure operated tool, is disclosed for setting blind rivets by pulling and breaking their mandrels. In addition to including means for ejecting the spent mandrel portion, the rivet head has mechanism for ensuring that its mandrel gripping jaw close prior to exerting substantial mandrel tension, open at the end of the mandrel pulling stroke, and allow reloading of the head with retention of the next mandrel rivet to be installed.
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| 252 | Panel type artificial satellite, and artificial satellite system therewith | JP2010111607 | 2010-05-14 | JP2011240719A | 2011-12-01 | TAKAHASHI TADAYUKI; TAKASHIMA TAKESHI; OGAWA HIROYUKI; SAKAI SHINICHIRO; IWATA NAOKO; KURODA YOSHIKATSU; MASUKAWA KAZUNORI |
| PROBLEM TO BE SOLVED: To simultaneously achieve the high function, reduced cost, short-term development and redundancy.SOLUTION: An artificial satellite system 200 is provided by joining two or more of panel type artificial satellites 100 formed by mounting a necessary minimum apparatus on a substrate 10 as an artificial satellite, and making the respective panel type artificial satellites 100 into close contact by multi networks. Since the multi networks are constituted of a communication network for performing data communication among data processing devices mounted on the respective panel type artificial satellites, a heat pipe for transmitting heat among the apparatuses mounted on the respective panel type artificial satellites 100 and a power source line for connecting electric power controllers mounted on the respective panel type artificial satellites 100, even if a failure is caused in a part of the other panel type artificial satellite 100 functioning as an assembly having the various and flexible high functions of more than functioning independently, the function as the satellite can be maintained by the communication network being the multi network, the heat pipe and the power source line. | ||||||
| 253 | 利用人造衛星的信號收信方法、服務提供方法、人造衛星之控制方法、收信終端以及人造衛星控制裝置 | TW092127841 | 2003-10-07 | TWI227973B | 2005-02-11 | 岩田忠良; 前田利秀; 石田隆張; 井上秀樹 |
| [課題]防止品質劣化，在服務區域之任何地區中，都能夠由適合於通訊、廣播之仰角的衛星接受服務之提供。 [解決手段]通信、廣播系統1係透過由衛星管制局2所控制的人造衛星之環繞衛星3，在通信、廣播中心局4和位於波束波點5內之移動台6或固定台7之間，進行通信服務及/或廣播服務的通信、廣播系統。藉由在可保持高的衛星仰角之時間帶進行此環繞衛星的切換，以防止通訊、廣播的品質劣化。 | ||||||
| 254 | 利用人造衛星的信號收信方法、服務提供方法、人造衛星之控制方法、收信終端以及人造衛星控制裝置 | TW092127841 | 2003-10-07 | TW200412050A | 2004-07-01 | 岩田忠良; 前田利秀; 石田隆張; 井上秀樹 |
| 〔課題〕防止品質劣化，在服務區域之任何地區中，都能夠由適合於通訊、廣播之仰角的衛星接受服務之提供。〔解決手段〕通信、廣播系統1係透過由衛星管制局2所控制的人造衛星之環繞衛星3，在通信、廣播中心局4和位於波束波點5內之移動台6或固定台7之間，進行通信服務及／或廣播服務的通信、廣播系統。藉由在可保持高的衛星仰角之時間帶進行此環繞衛星的切換，以防止通訊、廣播的品質劣化。 | ||||||
| 255 | Data bus control method for artificial satellite load and system thereof | US09760584 | 2001-01-16 | US06999426B2 | 2006-02-14 | Hiroaki Miyoshi |
| A periodical processing time band during which communication is periodically conducted between a plurality of communication terminals and a data bus control apparatus and a nonperiodical processing time band during which communication is nonperiodically conducted between the plurality of terminals and the data bus control apparatus are independently provided, priority communication during each nonperiodical processing time band are determined in advance. Based on a schedule, collection of communication requests to the communication terminals for conducting communication with priority during the nonperiodical processing time band is conducted, and when communication requests from the communication terminals exist, transmission is allowed if data content to be transmitted is below or equal to an allocated allowable band, and one variable length packet is transmitted from the communication terminal during the nonperiodical processing time band, and the transmission is suppressed if it is above or equal to the allocated allowable band. | ||||||
| 256 | Optical data bus communication in an artificial satellite | US09892139 | 2001-06-26 | US20020063917A1 | 2002-05-30 | Yasuhiko Mizushima; Yukio Amano |
| An optical data bus communication system of an artificial satellite includes an optical transmitter, a reflection film provided over the entire inner surface of case, and an optical receiver that receives optical signals that are transmitted from the optical transmitter both directly and after reflection and diffusing by the reflection film and reproduces the optical signals from the received signals. | ||||||
| 257 | Data bus control method for artificial satellite load and system thereof | US09760584 | 2001-01-16 | US20010014084A1 | 2001-08-16 | Hiroaki Miyoshi |
| A periodical processing time band during which communication is periodically conducted between a plurality of communication terminals and a data bus control apparatus and a non-periodical processing time band during which communication is non-periodically conducted between the above-described plurality of communication terminals and the above-described data bus control apparatus are independently provided, and communication terminals for conducting communication with priority during each non-periodical processing time band are determined in advance. Based on a schedule, collection of communication requests (polling) to the communication terminals for conducting communication with priority during the above-described non-periodical processing time band is conducted, and in case that the communication requests from the communication terminals exist, transmission is allowed if a data content to be transmitted, which is averaged by a time period during which transmission of a plurality of packets is conducted, is below or equal to an allocated allowable band, and one variable length packet is transmitted from the communication terminal during the non-periodical processing time band, and the transmission is suppressed if it is above or equal to the allocated allowable band. | ||||||
| 258 | Apparatus for measuring the attitude of an artificial satellite on the ground | US3612699D | 1970-05-28 | US3612699A | 1971-10-12 | ASANO KUNIJI; SHIGEHARA MASAMICHI |
| An upright stand has a sphere rotatably mounted on the top thereof. An artificial satellite is in turn mounted on the sphere such that its center of gravity coincides with the center of sphere. The center of the sphere also coincides with the origin of three axes of coordinates of the artificial satellite, the three axes being orthogonal to each other. A pair of optical-measuring devices are provided to measure the vertical deviations of two points on a circumference of a great circle, the center of which coincides with the center of the sphere, from a horizontal reference plane which includes the center of the sphere thereon. The aforesaid two points on the circumference of the great circle are on two orthogonal diameters of the great circle. A device is provided to calculate the attitude of the artificial satellite from the two electrical outputs of the pair of opticalmeasuring devices and an electrical reference input signal which represents the coordinates of the center of the great circle.
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| 259 | Communication system having a multiple-access,man-made satellite | US3470477D | 1967-08-04 | US3470477A | 1969-09-30 | BATTAIL GERARD PIERRE; BROSSARD PIERRE CLAUDE |
| 260 | Solar cell panel for loading on artificial satellite and artificial satellite | JP2007058657 | 2007-03-08 | JP2008221876A | 2008-09-25 | MASAI TAKUMA |
| PROBLEM TO BE SOLVED: To provide a solar cell panel loaded on an artificial satellite to reduce the mass of a large-sized antenna to be deployed. SOLUTION: This artificial satellite is provided with a plurality of solar cell panels 1 constituted by arranging solar cells 10 on a surface and forming an electrical conductive face on a rear surface and hinges 2 for connecting the solar cell panels to one another so as to be deployed. The hinges 2 hold the solar cell panels by forming a difference in angle between the panels so that the electrical conductive face of each solar cell panel 1 forms an antenna reflecting mirror face approximately while the solar cell panel 1 is deployed. COPYRIGHT: (C)2008,JPO&INPIT | ||||||
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