| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Maneuver device for artificial satellite | US10078109 | 2002-02-20 | US06622969B2 | 2003-09-23 | Toshiaki Yamashita |
| The present invention provides a maneuver device for an artificial satellite, which causes small attitude error during maneuver and which requires a shorter period of setting time for obtaining a target attitude. The maneuver device is provided with: a feed forward torque instruction signal generator 8 which outputs a feed forward torque instruction signal 11 based on a maneuver plan; a thruster 10 which outputs control torque based on the feed forward torque instruction signal 11; and an attitude control signal calculator 6 to which an attitude angle and an angular velocity of the artificial satellite as well as a target attitude angle and a target angular velocity are input and which outputs an attitude control signal 13. The maneuver device is further provided with a disturbance compensating signal calculator to which the feed forward torque instruction signal 11 and a detected angular velocity signal 16 are input, and which generates and outputs a disturbance compensating signal 12. The maneuver device is yet further provided with a reaction wheel 7 which generates control torque based on the attitude control signal 13 and the disturbance compensating signal 12. | ||||||
| 142 | Maneuver device for artificial satellite | US10078109 | 2002-02-20 | US20020148930A1 | 2002-10-17 | Toshiaki Yamashita |
| The present invention provides a maneuver device for an artificial satellite, which causes small attitude error during maneuver and which requires a shorter period of setting time for obtaining a target attitude. The maneuver device is provided with: a feed forward torque instruction signal generator 8 which outputs a feed forward torque instruction signal 11 based on a maneuver plan; a thruster 10 which outputs control torque based on the feed forward torque instruction signal 11; and an attitude control signal calculator 6 to which an attitude angle and an angular velocity of the artificial satellite as well as a target attitude angle and a target angular velocity are input and which outputs an attitude control signal 13. The maneuver device is further provided with a disturbance compensating signal calculator to which the feed forward torque instruction signal 11 and a detected angular velocity signal 16 are input, and which generates and outputs a disturbance compensating signal 12. The maneuver device is yet further provided with a reaction wheel 7 which generates control torque based on the attitude control signal 13 and the disturbance compensating signal 12. | ||||||
| 143 | Attitude determination system for artificial satellite | US919193 | 1997-08-28 | US6102338A | 2000-08-15 | Shoji Yoshikawa; Katsuhiko Yamada; Hiroshi Sakashita; Hiroo Yonechi |
| An attitude determination system for an artificial satellite capable of performing star identification without need for the aid of ground station includes an image processing module (17) for processing star images observed at predetermined time points by a star sensor (16) mounted on the artificial satellite (1) for arithmetically determining direction vectors of the observed stars, a rotation estimating module (18) for estimating a rotational motion of the artificial satellite (1) between an attitude of the artificial satellite at a predetermined time point and an attitude of the artificial satellite at another time point, an elongation estimating module (19) for estimating elongations between the direction vectors of plural stars the images of which are picked up at a same time point by the star sensor and estimating the elongations between the direction vectors of plural stars the images of which are picked up at different time points by the star sensor on the basis of the estimated rotational motion, a star identifying module (20) for establishing correspondences between a plurality of the stars for which relation of the elongation has been determined and stars on a star catalog for identifying the stars, and an attitude angle estimating module (21) for estimating an attitude angle of the artificial satellite on the basis of result of identification of the stars. | ||||||
| 144 | Artificial satellite communication system | US886228 | 1992-05-21 | US5871181A | 1999-02-16 | Jonathan Mass |
| A communication system including a constellation of a plurality of artificial satellites orbiting the Earth, each artificial satellite having communication apparatus providing communication with the Earth, characterized in that the plurality of artificial satellites are in triply-geosynchronous (TGS) orbits having a period of eight sidereal hours, or twice-triply-geosynchronous (TTGS) orbits having a period of sixteen sidereal hours, which orbits are inclined with respect to the Equator and synchronized with the Earth's rotation such as to exploit the natural spacing of approximately 120.degree. in longitude of the major land masses of Europe, North America and the Far East for communication with the artificial satellites to provide for higher elevation angles in such land masses than in other areas. | ||||||
| 145 | Artificial satellite attitude control system | US606660 | 1984-05-03 | US4617634A | 1986-10-14 | Kiichiro Izumida; Ritaroh Kasai |
| A system for controlling an attitude of an artificial satellite to decide the present attitude of the satellite on a spatial coordinate and angular velocities of rotation about body axes of the satellite, by the use of inertial sensors and star sensors, to calculate an objective attitude of the satellite on the basis of the present attitude information, the angular velocities of rotation about the body axes and orbit information received from a ground station so that the attitude of the satellite and the changing rate thereof are controlled simultaneously. | ||||||
| 146 | Magnetic bearing arrangement for an artificial satellite | US469659 | 1983-02-25 | US4483570A | 1984-11-20 | Masao Inoue |
| A magnetic bearing arrangement for rotor for controlling the attitude of an artificial satellite wherein the rotor has a rotating speed and an axis of rotation which are adjusted in accordance with a change in the attitude of the satellite. The arrangement includes a stator defined by at least three segments, and each stator segment is provided with a permanent magnet to eliminate the necessity of any electromagnet for controlling radial rotor displacement and any sensor for detecting such radial displacement. The apparatus is free from any eddy currents that may cause great resistance to rotation. | ||||||
| 147 | Thruster for artificial satellite | JP24345196 | 1996-09-13 | JPH1086900A | 1998-04-07 | UESUGI KUNINORI; YAMADA AKIRA; MISHIMA HIROYUKI; FURUKAWA KATSUMI |
| PROBLEM TO BE SOLVED: To reduce an outside surface temperature in operation without changing an operation condition, and form a thruster for an artificial satellite out of metal such as titanium low in high temperature strength by coating an outside surface with a radiative paint film. SOLUTION: A thruster 1 to be used as a thruster for an artificial satellite is composed of a combustion chamber 2, a nozzle throat part 4 in which a throat 3 to minimize the passage area is arranged and a skirt part 6 having a skirt part end surface 5. A joining plane 7 of the combustion chamber 2 is joined to an artificial satellite main body. A radiative paint film 8 is laid so that the skirt part 6 is formed as a belt having a constant width on the nozzle throat part 4 side on an outer peripheral surface. Here, metal low in high temperature strength is used in the whole thruster 1, and the radiative paint film 8 may be laid on the whole outside surface of the thruster. | ||||||
| 148 | Thruster for artificial satellite | JP9185983 | 1983-05-25 | JPS59216798A | 1984-12-06 | SEKI TOKIAKI |
| 149 | 香薰挂件（人造卫星） | CN202230225936.X | 2022-04-21 | CN307523802S | 2022-08-30 | 喻广桂 |
| 1.本外观设计产品的名称：香薰挂件（人造卫星）。 2.本外观设计产品的用途：用于车载香薰。 3.本外观设计产品的设计要点：在于形状。 4.最能表明设计要点的图片或照片：设计1立体图1。 5.指定设计1为基本设计。 | ||||||
| 150 | 태양전지판 전개모듈 및 이를 포함하는 인공위성 | KR1020120036704 | 2012-04-09 | KR1020130114388A | 2013-10-18 | 이민규; 홍주성 |
| PURPOSE: A solar panel unfolding module and an artificial satellite having the same are provided to minimize the occupation space thereof when a solar panel is folded and increase the solar absorbing area of the solar panel when the solar panel is unfolded. CONSTITUTION: A solar panel unfolding module comprises a main frame, a moving member (120), tensile elastic members (122), and connection links (135). The main frame is connected to the body of an artificial satellite, and first solar panels (130) are connected to both ends thereof. The moving member is located between both ends of the main frame and has a dividing part (124) for dividing the moving member into first and second parts. The tensile elastic members are formed on both sides of the moving member and connect moving member and both ends of the main frame to each other. The connection links connect the moving member and the first solar panels to each other. | ||||||
| 151 | 자료동화를 위한 인공위성 원격탐사 자료들 생성방법 | KR1020100079969 | 2010-08-18 | KR101319370B1 | 2013-10-16 | 양찬수; 박광순 |
| 본 발명은 기상 변동 및 해양 예측의 정확도를 높일 수 있는 자료 동화용 인공위성 원격 탐사 자료들의 생성방법에 관한 것이다.
본 발명에 의한 자료동화를 위한 인공위성 원격 탐사 자료들의 생성방법은 인공위성 원격탐사 자료들을 획득하는 단계; 인공위성 원격탐사 자료들의 신뢰도를 평가하는 단계; 신뢰도에 따라 인공위성 원격탐사 자료들의 가중치를 부여하는 단계;를 포함한다. |
||||||
| 152 | 자료동화를 위한 인공위성 원격탐사 자료들 생성방법 | KR1020100079969 | 2010-08-18 | KR1020120017337A | 2012-02-28 | 양찬수; 박광순 |
| PURPOSE: An artificial satellite exploration data generating method for data synchronization is provided to apply reliability satellite data pixels for the data synchronization and to implement the data synchronization according to weighted values. CONSTITUTION: An artificial satellite exploration data generating method for data synchronization includes the following: satellite exploration data is obtained(S1); the reliability of the satellite exploration data is evaluated(S2); and according to the reliability, weighted values of the satellite exploration data are applied(S3). The satellite exploration data is satellite data pixels representing marine surface temperature. The more a marine surface interface value is clear, the more the reliability of the date increases. | ||||||
| 153 | 위성영상을 이용한 네비게이션용 지도 업데이트 방법 | KR1020050093147 | 2005-10-04 | KR1020070037956A | 2007-04-09 | 곽만기 |
| 본 발명은 국가기본도로부터 추출된 DEM(Digital Elevation Model) 데이터를 이용하여 고해상도 영상위성으로부터 촬영된 영상데이터를 정사보정하여 위치정보를 일치시키고 기존 네비게이션 지도과 오버랩시켜 선형의 비교 편집을 수행하는 위성영상을 이용한 네비게이션용 지도 업데이트 방법에 관한 것으로서, 기존의 네비게이션용 지도를 업데이트하는 방법에 있어서, 인공위성에서 촬영된 영상데이터와 국가기본도로부터 추출된 DEM 데이터를 추출하여 기복변위의 오차를 정사보정하는 제1단계, 상기 기존의 네비게이션용 지도를 입력하여 상기한 영상데이터와 오버랩하는 제2단계, 상기 영상데이터가 기존의 네비게이션 지도 데이터의 위치정보가 동일한 위치정보를 가질 수 있도록 영상 데이터를 기하보정하고, 상기 영상 데이터의 추가적인 벡터선형� �� 비교 및 편집하여 상기 기존의 네비게이션 지도의 벡터선형을 추가 또는 삭제하는 제3단계를 포함하여 이루어지는 것을 특징으로 한다. 위성영상, 네비게이션, 지도, 업데이트 | ||||||
| 154 | 인공위성 태양전지판의 저온환경 전개시험 장치대 | KR1020000079452 | 2000-12-21 | KR1020020050329A | 2002-06-27 | 김정수; 김성훈; 이승우; 이주진; 김진철 |
| PURPOSE: An apparatus is provided to allow a user to observe, on the earth, the explosion of solar cell panel mounted to an artificial satellite, in the cosmos, through the apparatus with simplified structure and reduced cost, while improving reliability for test. CONSTITUTION: An apparatus comprises a solar cell panel(3); an explosion structure connected to the solar cell panel; a bungee cable arranged to a guide beam(12) for implementing gravity-free state on the earth, and which explodes the solar cell panel; an adiabatic box for providing a low temperature environment by supplying a low temperature nitrogen gas(20) through a nitrogen liquid tank(17), an evaporator(18) and a nitrogen gas supply pump(19); and a power controller(22) and a power supply(21) connected to a heater so as to operate an extra small friction bearing. | ||||||
| 155 | 인공위성에서의 복합재료 잔류응력 제거장치 및 방법 | KR1019990010188 | 1999-03-25 | KR1020000061265A | 2000-10-16 | 변국연; 서영부 |
| PURPOSE: An apparatus and a method are provided to achieve an improved reliability for composite material and a lightweight air-borne equipment. CONSTITUTION: An apparatus comprises a heating chamber(100) for heating specimen of composite material, a temperature control unit(200) for measuring the temperature of the heating chamber and generating the corresponding temperature measured data, a heating unit(300) for receiving the temperature measured data and heating the heating chamber to reach a desired temperature by being based on the received temperature measured data, an air fan(400) installed at a portion of the heating chamber and which circulated an air within the heating chamber, a motor(500) for driving the air fan, and a loading frame(600) for fixing both ends of the specimen of the composite material protruded toward an exterior of the heating chamber, and pushing or pulling in horizontal to thereby add loading to the specimen. | ||||||
| 156 | Artificial satellite for earth survey | JP3043792 | 1992-02-18 | JPH05223590A | 1993-08-31 | KUMAGAI SUSUMU |
| PURPOSE: To enable a relative position from a survey target to be calculated easily even with a low-capacity computer by providing a position measurement layer which determines a self-position in an earth fixing coordinate system. CONSTITUTION: A position measurement instrument 2 of an artificial satellite 1 for earth survey has the function of outputting a self-position in an earth fixing coordinate system. An operator 3 recognizes the position of the satellite 1 from a self-position outputted from the instrument and judges a survey range of the earth's surface from attitude information outputted from an attitude sensor 7. The operator 3 stores a survey target in the inner memory: it controls a driver 8 and turns a survey sensor 4 to the target to survey it, thereby making a survey data recorder 5 record survey data and the coordinate of this point. Recorded data is transmitted to a ground station by a survey data transmitter 6 when the satellite 1 passes above the ground station. In such a way, the artificial satellite 1 itself can survey by positional judgment without complicated coordinate conversion. COPYRIGHT: (C)1993,JPO&Japio | ||||||
| 157 | Artificial satellite for earth observation | JP14378687 | 1987-06-09 | JPH01101299A | 1989-04-19 | KASAI KOITARO; MATSUBARA KAORU; HARADA KOZO |
| PURPOSE: To increase the observation frequency for a target by use of a small number of artificial satellites by calculating a target position as seen from each artificial satellite by use of a computing device in each artificial satellite on the basis of information about orbits and attitudes, and controlling the direction of the viewing field of an observation sensor. CONSTITUTION: When a target position whose image is to be acquired by an observation sensor 2 from the ground is input to a computing device 8 via a command device 7, the relationship between the target position and the position of an artificial satellite is calculated as a function of time on the basis of orbit information about the artificial satellite 1, transmitted from an orbit information device 6. Then, since the attitude of the artificial satellite is always determined by an attitude control device 5, the direction of the target position for image acquisition by the observation sensor 2 can be calculated by the computing device 8 at an angle based on a coordinate system affixed to the artificial satellite 1. When a drive 4 is controlled so that the direction of the viewing field of the observations sensor 2 attains the angle of the target position of the artificial satellite coordinate system, the image of the target position at a certain time of the command from the ground can be acquired and transmitted to the ground by an image data transmission device 3. COPYRIGHT: (C)1989,JPO | ||||||
| 158 | 대체용 히트 파이프를 구비한 다중 히트 파이프 장치 및 이를 이용한 인공 위성용 다중 히트 파이프 장치 | KR1020080110962 | 2008-11-10 | KR1020100052087A | 2010-05-19 | 김정훈; 전형열; 김성훈 |
| PURPOSE: A multi heat pipe apparatus comprising an alternative heat pipe for maintaining a cooling effect, and a multi heat pipe apparatus for a satellite using the same are provided to maintain the performance of the satellite by maintaining a cooling effect using an alternative heat pipe even if a heat pipe is not operable. CONSTITUTION: A multi heat pipe apparatus comprising an alternative heat pipe comprises a main heat pipe(M), an alternative heat pipe (A), and a side heat pipe(S). The main heat pipe contacts with a heat source. The alternative heat pipe contacts with the heat source and the main heat pipe. The side heat pipe contacts with one side of the alternative heat pipe and the main heat pipe. When the main heat pipe is not operable, heat transfer fluid is circulated by the alternative heat pipe to cool the heat source. | ||||||
| 159 | 고 신뢰도 인공위성을 위한 인공위성 분리 신호 발생 회로 | KR1020010084613 | 2001-12-26 | KR1020030054452A | 2003-07-02 | 이상곤; 장진백; 장성수; 권기호; 심은섭 |
| PURPOSE: An artificial satellite separation signal output circuit for a high reliability artificial satellite is provided to improve the reliability in launching the artificial satellite or separating, and to minimize the failure rate by operating a backup computer stably against wrong operation of a main processor with detecting the stable separation signal. CONSTITUTION: An artificial satellite separation signal generating and detecting circuit is composed of a separation signal command circuit(10) applying a separation command signal to a separation signal generating circuit(30) in separating; the separation signal generating circuit detecting the separation signal from the separation signal command circuit and generating a pulse signal for driving a separation timer(40); the separation timer generating a time-out signal in not stopping the separation timer by a main processor(50); and a power switching relay(60) of the artificial satellite processor converting power from the main processor to an artificial satellite backup processor(51) in generating the time-out signal. The reliability is improved by operating the backup computer stably against wrong operation of the main processor. | ||||||
| 160 | 인공위성의 Ｖ휠 편각 결정방법 | KR1019990010189 | 1999-03-25 | KR1020000061266A | 2000-10-16 | 김유택 |
| PURPOSE: A method is provided to reduce administration cost for an overall satellite system while reducing time period for wheel shape design and utilizing the capacity of a momentum wheel in maximum. CONSTITUTION: A method comprises a first step of inputting status data for the relevant artificial satellite to a workstation at which V-wheel deflection angle determination algorithm is loaded, a second step of inputting maximum torque range value to the workstation, a third step of determining a weighting factor using the status data for the satellite, a fourth step of calculating a reference deflection angle value using the weighting factor, a fifth step of designing a posture control system using the reference deflection angle value, a sixth step of performing a simulation for the posture control system, a seventh step of extracting control torque values(CT(P),CT(Y)) for each axis through the simulation, an eighth step of judging whether the control torque value(CT(P)) of a pitch axis is higher than or same as the maximum torque value(T(P)), a ninth step of judging whether the control torque value(CT(Y)) of an yow axis is higher than or same as the maximum torque value(T(Y)) if CT(P) is not higher than or same as T(P), and a tenth step of determining the reference deflection angle value used for the current posture control system as a final value and displaying the final value, if CT(Y) is not higher than or same as T(Y). | ||||||
QQ群二维码
意见反馈
意见反馈