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公开(公告)号：EP2232201A1
公开(公告)日：2010-09-29
申请号：EP08860434.3
申请日：2008-12-10
申请人： Moser, Mark K.
发明人： Moser, Mark K.
CPC分类号： G01S3/7862 , F24S20/70 , F24S25/12 , F24S30/45 , F24S30/48 , F24S50/20 , F24S2030/115 , Y02E10/47
摘要： A tracking device for automatically following a moving light source that is detectable in the presence of ambient light. A carrier platform including one or more radiant energy conversion devices and a sensor array is mounted to an upright support column with a universal joint. Three independently-operated, linear actuators are equally angularly spaced about the support column with an upper end connected to the carrier platform with a universal hinge and a lower end connected to a floating base with a spherical hinge. A sensor array carried by the carrier platform includes a primary sensor associated with each actuator. During operation, when a primary sensor is not receiving direct radiant energy, the actuator retracts, and when it is receiving radiant energy directly, the actuator extends. The result is that the platform will directly track the sun across the horizon.
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公开(公告)号：EP2087327A1
公开(公告)日：2009-08-12
申请号：EP07875115.3
申请日：2007-11-12
发明人： TURNER, Mark, A.
CPC分类号： F42B10/46 , F41G7/226 , F41G7/2293 , G01J1/0407 , G01J1/0422
摘要： An apparatus for detecting radiation includes an entry window configured to receive radiation from a target, the entry window having an outer surface and an inner surface, such that the outer surface is not parallel to the inner surface. The apparatus further includes a radiation transmission assembly configured to receive at least a portion of the radiation received by the entry window. The apparatus further includes a radiation sensor configured to receive at least a portion of the radiation from the radiation transmission assembly.
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公开(公告)号：EP1337806B1
公开(公告)日：2008-12-10
申请号：EP01993812.5
申请日：2001-11-08
CPC分类号： G01C21/025 , B64G1/361 , B64G7/00 , G01C25/00
摘要： The invention concerns a bench comprising: a) means supporting (1) the stellar sensor (2) to be tested; b) a video monitor (3); c) means controlling (8, 9, 10, 11) display, on the video monitor (3), of a moving sky portion; d) optical means (7) to form an image of said screen on a sensitive surface of a stellar sensor (2) mounted on the support means (1); and e) means (13) for testing the sensor (2). The invention is characterised in that the means controlling (8, 9, 10, 11) the video monitor (3) comprise means for real time simulation (11) of the movement on a predetermined orbit of a satellite equipped with said attitude control system, the system using in closed loop the signals transmitted by said tested sensor (2).
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34.发明公开Attitude acquisition method and spacecraft attitude acquisition and control system 有权姿态确定方法和Raumfahrzeugslagebestimmungs-和控制系统
公开(公告)号：EP1422138A3
公开(公告)日：2008-07-02
申请号：EP03026297.6
申请日：2003-11-15
申请人： The Boeing Company
CPC分类号： G01C21/025 , B64G1/26 , B64G1/285 , B64G1/288 , B64G1/361 , G05D1/0883
摘要： Attitude acquisition methods and systems are provided which reduce the time generally required to acquire spacecraft attitude estimates (76) and enhance the probability of realizing such estimates (76). The methods and systems receive, over a time span Δt, successive frames of star-sensor signals (70) that correspond to successive stellar fields-of-view (102A-102N), estimate spacecraft rotation Δr throughout at least a portion of the time span Δt, and, in response to the spacecraft rotation Δr, process the star-sensor signals (70) into a processed set of star-sensor signals that denote star positions across an expanded field-of-view (120) that exceeds any of the successive fields-of-view (102A-102N). The expanded field-of-view (120) facilitates identification of the stars (104,105,106,108,110,112,114) that generated the processed set of star-sensor signals to thereby acquire an initial attitude estimate (72).
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35.发明授权KOMBINIERTES ERD-STERNSENSORSYSTEM UND VERFAHREN ZUR BAHN- UND LAGEBESTIMMUNG VON RAUMFLUGKÖRPERN 有权地球联合星敏感器的系统和方法铁路，姿态空间飞行体
公开(公告)号：EP1119741B1
公开(公告)日：2005-08-03
申请号：EP99957853.7
申请日：1999-10-05
申请人： EADS Astrium GmbH
CPC分类号： G01C21/025 , B64G1/361 , B64G1/365 , G01S3/7867 , G05D1/0883
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36.发明授权Procédé de prevention des effets des protons d'origine solaire permettant une reconfiguration d'un senseur d'étoile et système de contrôle d'attitude mettant en oeuvre le procédé 有权用于预防太阳能质子的动作的过程中，其允许星传感器和姿态控制系统的重新配置与使用该方法的
公开(公告)号：EP1362785B1
公开(公告)日：2005-06-29
申请号：EP03290867.5
申请日：2003-04-08
申请人： ALCATEL
发明人： Renault, Hervé
CPC分类号： B64G1/361 , B64G1/546 , G01S3/7867
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37.发明公开REENTRY VEHICLE INTERCEPTOR WITH IR AND VARIABLE FOV LASER RADAR 审中-公开NEUEINTRITTSFAHRZEUGINTERZEPTOR带红外和可变FOV激光雷达
公开(公告)号：EP1472505A2
公开(公告)日：2004-11-03
申请号：EP03706036.5
申请日：2003-02-03
CPC分类号： F41G7/008 , F41G7/2213 , F41G7/2246 , F41G7/2253 , F41G7/2293 , G01S7/003 , G01S7/4811 , G01S7/4812 , G01S7/4813 , G01S17/023 , G01S17/66 , G01S17/89
摘要： A dual mode seeker for intercepting a reentry vehicle or other target is disclosed. In one embodiment, the seeker is configured with an onboard 3D ladar system (120) coordinated with an onboard IR detection system (125), where both systems utilize a common aperture (105). The IR and ladar systems cooperate with a ground based reentry vehicle detection/tracking system (1005) for defining a primary target area coordinate and focusing the IR FOV thereon. The IR system obtains IR image data in the IR FOV. The ladar system initially transmits with a smaller laser FOV to illuminate possible targets, rapidly interrogating the IR FOV (Fig. 4c). The ladar system obtains data on each possible target to perform primary discrimination assessments. Data fusion is employed to resolve the possible targets as between decoys/clutter and a reentry vehicle. The laser FOV is expandable to the IR FOV (Fig. 4c). Robust and reliable discrimination is obtained at high altitudes.
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公开(公告)号：EP1337806A1
公开(公告)日：2003-08-27
申请号：EP01993812.5
申请日：2001-11-08
CPC分类号： G01C21/025 , B64G1/361 , B64G7/00 , G01C25/00
摘要： The invention concerns a bench comprising: a) means supporting (1) the stellar sensor (2) to be tested; b) a video monitor (3); c) means controlling (8, 9, 10, 11) display, on the video monitor (3), of a moving sky portion; d) optical means (7) to form an image of said screen on a sensitive surface of a stellar sensor (2) mounted on the support means (1); and e) means (13) for testing the sensor (2). The invention is characterised in that the means controlling (8, 9, 10, 11) the video monitor (3) comprise means for real time simulation (11) of the movement on a predetermined orbit of a satellite equipped with said attitude control system, the system using in closed loop the signals transmitted by said tested sensor (2).
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39.发明授权Method and apparatus for controlling spacecraft attitude with rotational star trackers 有权用于控制航天器的可转动的恒星探测器姿态的方法和装置
公开(公告)号：EP1033300B1
公开(公告)日：2003-08-13
申请号：EP00104122.7
申请日：2000-02-29
CPC分类号： B64G1/361 , B64G2001/245 , G01C21/025 , G01S3/7867 , G01S5/163
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40.发明公开Method and apparatus for controlling spacecraft attitude with rotational star trackers 有权用于控制航天器的可转动的恒星探测器姿态的方法和装置
公开(公告)号：EP1033300A3
公开(公告)日：2001-07-18
申请号：EP00104122.7
申请日：2000-02-29
CPC分类号： B64G1/361 , B64G2001/245 , G01C21/025 , G01S3/7867 , G01S5/163
摘要： High precision spacecraft (108) attitude determination is produced by specially positioning (100) the spacecraft's star trackers (112) and then filtering (102) out measurement errors produced from star tracker electronics (216). In addition to the conventional azimuth and elevation controls used for star tracker pointing, the star tracker detector array (400) is rotationally positioned about its boresight (900) so that its pixels (401) are traversed by the imaged star path (404) at an angle within 20° of diagonal. This forces both vertical and horizontal spatial error components (700, 702) in the detector plane to a high frequency range at which they can easily be filtered out (102) in common
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