| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | 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. | ||||||
| 162 | 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. | ||||||
| 163 | 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. | ||||||
| 164 | 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. | ||||||
| 165 | 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). | ||||||
| 166 | 인공위성 시스템에서의 솔라 어레이 열진동 제거방법 | KR1019990010185 | 1999-03-25 | KR1020000061262A | 2000-10-16 | 오영택 |
| PURPOSE: A method is provided to ensure stability of an artificial satellite system by eliminating a thermal flutter phenomenon of a solar array caused when the artificial satellite passes through an eclipse. CONSTITUTION: A method comprises a first step of allowing a control unit to calculate an angle formed by an artificial satellite and the sun using a solar energy measure data, a second step of judging whether the body of the artificial satellite initially enters an eclipse area using the angle calculated in the first step, a third step of allowing the control unit to return to the first step if it is judged that the body of the satellite is not entered in the second step, and allowing the control unit to rotate the solar array by 90 degree so that an angle between the sun and the solar array surface becomes horizontal if it is judged that the body of the satellite initially entered, a fourth step of allowing the control unit to calculate an angle between the satellite and sun using a solar energy measure data, a fifth step of judging whether the body of the satellite is completely escaped from the eclipse area, and a sixth step of allowing the control unit to return to the fourth step if it is judged that the body of the satellite is not completely escaped from the eclipse area, and allowing the control unit to rotate the solar array by 90 degree so that an angle between the sun and the solar array surface becomes vertical. | ||||||
| 167 | 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 | ||||||
| 168 | 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 | ||||||
| 169 | Artificial satellite globe | JP18818491 | 1991-07-02 | JPH0511690A | 1993-01-22 | AMANO TAKESHI |
| PURPOSE:To offer the artificial satellite globe which enables the position relation between various artificial satellites revolving around the earth and the ground, specially, the longitudes of principal cities and the mutual position relation between plural artificial satellites to easily be understood and easily presents an eclipse phenomenon based upon the array of the sun, earth, and satellites and the longitude of points on the ground where radio waves from stationary satellites can be received, the longitudes of the artificial satellites, etc. CONSTITUTION:An artificial satellite model is held detachably at the peripheral edge part of a circular outward flange which surrounds the entire periphery of a terrestrial globe 1 above the equator 1a of the terrestrial globe 1 to enable the positions of respective stationary satellites about the earth to easily be understood, and various information is written on a disk to assist said understanding. Further, a polar tracking satellite model which revolves in the sky above the earth is held detachably at the outer peripheral edge part of a guide member 11 which surrounds nearly the whole periphery of the terrestrial globe 1 along a plane containing the earth's axis of the terrestrial globe 1 and is rotatable on the earth's axis to easily and clearly understand the motion, etc., of the polar tracking satellite. | ||||||
| 170 | Thruster for artificial satellite | JP28062485 | 1985-12-12 | JPS62139800A | 1987-06-23 | KIKUCHI MASAKUNI |
| 171 | Thruster for artificial satellite | JP23279284 | 1984-11-05 | JPS61110699A | 1986-05-28 | SEKI TOKIAKI |
| 172 | Thruster for artificial satellite | JP5177684 | 1984-03-16 | JPS60197497A | 1985-10-05 | SEKI TOKIAKI |
| 173 | 人工衛星の自律運用計画システムおよび人工衛星の運用計画装置 | PCT/JP2017/025908 | 2017-07-18 | WO2018016471A1 | 2018-01-25 | 西山 岳宏; 北村 憲司 |
衛星側に衛星側運用パラメータ記憶部２２、運用計画部２３を備え、地上側に地上側運用パラメータ設定部１１、衛星側の運用パラメータ記憶部と同じ運用パラメータを記憶する地上側運用パラメータ記憶部１２、衛星側の運用計画部と同一の機能を有する運用計画推定部１４を備え、地上側運用パラメータ設定部１１において運用計画に用いる運用パラメータを決定し、地上側運用パラメータ記憶部１２と衛星側運用パラメータ記憶部２２に随時アップロードし、地上側の運用計画推測部１４と衛星側の運用計画部２３が同一の運用パラメータに基づいてそれぞれ運用計画を作成する。 |
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| 174 | SATELLITE ARTIFICIEL ET PROCÉDÉ DE REMPLISSAGE D'UN RÉSERVOIR DE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL | EP16705226.5 | 2016-01-22 | EP3212503B1 | 2017-11-22 | WALKER, Andrew, Nicholas |
| 175 | 人造衛星之整合與測試的方法及裝置 | TW088120177 | 1999-11-18 | TW479146B | 2002-03-11 | 喬瑟夫.安德森; 雷蒙.瑞肯 |
| 一種人造衛星整合與測試的系統及方法裝置其中一人造衛星(12)被組合和執行很多測試在一單一的試驗腔室(10)內，因此避免假如多重的測試腔室被使用所需的多重的安裝和分解操作，以及避免於測試腔室之間移動人造衛星的需求。 | ||||||
| 176 | 人工衛星の軌道面制御方法 | PCT/JP2014/051228 | 2014-01-22 | WO2014115753A1 | 2014-07-31 | 小泉 宏之; 青山 順一 |
【課題】主衛星のミッションを損なうことなく、しかも人工衛星の小型化及び軽量化を図った上で高い推力レベルの推進装置を備えた人工衛星と実質的に同等な軌道制御を実現することが可能な人工衛星の軌道面制御方法を提供することを目的とする。 【解決手段】主衛星と共に打ち上げられる複数の小型の人工衛星１１，１２をそれぞれの目的軌道へ投入する人工衛星の軌道面制御方法であり、主衛星の目的軌道Ｓ１に投入された小型の人工衛星１１，１２を低い推力レベルの推進装置を用いて軌道高度を変更させ、当該軌道高度における地球重力場の扁平性に起因する軌道面の遷移を利用して複数の人工衛星１１，１２をそれぞれの目的軌道Ｓ５，Ｓ９へ投入することを特徴とするものである。 |
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| 177 | 人工衛星および推力バランス調整方法 | PCT/JP2016/069106 | 2016-06-28 | WO2018003005A1 | 2018-01-04 | 細田 誠也; 田中 悠太郎; 中川 貴史 |
リアクションホイール（１１０）は角運動量を検出する。衛星制御機器（１２０）は検出された角運動量に基づいて対象スラスタを選択する。電源装置（１３０）は対象スラスタに対する調整電力を変更する。流量調整機器（１４０）は調整電力に対応する流量の推進剤を対象スラスタに供給する。これにより、対象スラスタの推力が変化する。対象スラスタの放電電流が目標電流になっていない場合、電源装置は対象スラスタに対する調整電力をさらに変更する。 |
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| 178 | ARTIFICIAL SATELLITE WITH INTEGRATED ANTENNA | EP12845914.6 | 2012-10-31 | EP2774856A4 | 2015-06-24 | MORIGUCHI, Tatsuji |
| An artificial satellite includes at least one hatch formed in a wall of the artificial satellite coming in contact with dead space of the artificial satellite, and a hatch opening and closing mechanism which opens the hatch, and the antenna is attached to the hatch. | ||||||
| 179 | Non-aqueous electrolytic battery module for artificial satellite | EP00120027.8 | 2000-09-14 | EP1091439A3 | 2002-03-06 | Yoshida, Hiroaki, Japan Storage Battery Co.,Ltd.; Inoue, Takefumi, Japan Storage Battery Co.,Ltd.; Miyanaga, Naozumi, Japan Storage Battery Co.,Ltd.; Imamura, Nobutaka, Japan Storage Battery Co.,Ltd. |
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. |
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| 180 | VEHICULAR SUSPENSION UNIT, AUTOMOBILE UTILIZING SAME, AND STEERING CONTROL METHOD | EP13819971.6 | 2013-06-28 | EP2875974A1 | 2015-05-27 | KAGEYAMA, Yusuke |
In a vehicle suspension device having lower links of a cross link structure, a reduction of a scrub radius and an increase in a kingpin slanted angle in the turning are suppressed. The vehicle suspension device includes first lower link member and a second lower link member configured to individually couple a vehicle side support part and the axle carrier having an axle of rotatably supporting a turning wheel, a first upper link member and a second upper link member, and a component of moving a virtual lower pivot point represented by a cross point of the first lower link member and the second lower link member, in a planer view, toward an outer side and frontward in a vehicle width direction, when the turning wheel is turned from a straight travel state, and moving a virtual upper pivot point represented by a cross point of the first upper link member and the second upper link member at least toward the outer side and frontward in the vehicle width direction, when the turning wheel is turned from the straight travel state. |
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