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1. 发明公开

EP4166458A1 METHODS AND APPARATUS FOR PERFORMING PROPULSION OPERATIONS USING ELECTRIC PROPULSION SYSTEMS 审中-实审
公开(公告)号：EP4166458A1
公开(公告)日：2023-04-19
申请号：EP22178754.2
申请日：2013-11-28
申请人： The Boeing Company
发明人： CAPLIN, Glenn N , ASTON, Richard W , PETERKA, III JAMES J
IPC分类号： B64G1/00 , B64G1/24 , B64G1/40 , B64G1/64 , B64G1/28 , B64G1/32 , B64G1/36 , B64G1/42 , B64G1/44 , B64G1/66
摘要： Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes a frame, a power source coupled to the frame and a payload coupled to the frame, the payload to receive or transmit data. The apparatus also includes an electric propulsion system coupled to the frame. The electric propulsion system is to enable attitude control, momentum control, and orbit control of the apparatus.

2. 发明公开

EP4003842A1 SATELLITE MODULE FOR ATTITUDE DETERMINATION 审中-实审
公开(公告)号：EP4003842A1
公开(公告)日：2022-06-01
申请号：EP20751291.4
申请日：2020-07-16
申请人： D-Orbit SpA
发明人： FERRARIO, Lorenzo , BEVILACQUA, Marco , ZORZI, Luca , GRIMOLDI, Giorgio
IPC分类号： B64G1/36 , B64G1/66 , G01S3/786

3. 发明授权

EP3887258B1 DISPOSITIF ET PROCÉDÉ DE DÉTERMINATION D'ATTITUDE D'UN SATELLITE ÉQUIPÉ D'ACTIONNEURS GYROSCOPIQUES, ET SATELLITE EMBARQUANT UN TEL DISPOSITIF 有权
公开(公告)号：EP3887258B1
公开(公告)日：2022-06-01
申请号：EP20726224.7
申请日：2020-03-17
发明人： LAURENS, Philippe , LESPRIER, Jeremy
IPC分类号： B64G1/28 , B64G1/36 , G01C21/24

4. 发明授权

EP3428578B1 INERTIALSENSORSYSTEM FÜR FLUGKÖRPER 有权
公开(公告)号：EP3428578B1
公开(公告)日：2021-10-27
申请号：EP18172404.8
申请日：2018-05-15
发明人： NEWZELLA, Alfons , SCHODER, Johannes
IPC分类号： G01C21/16 , B64G1/36 , G01C23/00 , G05D1/10 , B64G1/28 , F42B15/08

5. 发明公开

EP3887258A1 DISPOSITIF ET PROCÉDÉ DE DÉTERMINATION D'ATTITUDE D'UN SATELLITE ÉQUIPÉ D'ACTIONNEURS GYROSCOPIQUES, ET SATELLITE EMBARQUANT UN TEL DISPOSITIF 有权
公开(公告)号：EP3887258A1
公开(公告)日：2021-10-06
申请号：EP20726224.7
申请日：2020-03-17
申请人： Airbus Defence and Space SAS
发明人： LAURENS, Philippe , LESPRIER, Jeremy
IPC分类号： B64G1/28 , B64G1/36 , G01C21/24

6. 发明公开

EP3634856A1 ATTITUDE STABILIZATION AND ORBITAL DISTRIBUTION FOR SMALL SATELLITES 审中-公开
公开(公告)号：EP3634856A1
公开(公告)日：2020-04-15
申请号：EP18810233.9
申请日：2018-05-31
申请人： Swarm Technologies, Inc.
发明人： SPANGELO, Sara , LONGMIER, Benjamin
IPC分类号： B64G1/24 , B64G1/00 , B64G1/10 , B64G1/22 , B64G1/28 , B64G1/36

7. 发明授权

EP2690020B1 Procédé de réduction du moment cinétique et de contrôle d' attitude d' un engin spatial 有权转让
公开(公告)号：EP2690020B1
公开(公告)日：2020-01-08
申请号：EP13175810.4
申请日：2013-07-09
申请人： Thales
发明人： Caullier, François , Delhay, Faustine , Lacambre, Jean-Marc , Brouillard, Etienne
IPC分类号： B64G1/24 , B64G1/26 , B64G1/28 , B64G1/36 , B64G1/00 , B64G1/40

8. 发明授权

EP3013691B1 CHIP-SCALE STAR TRACKER 有权
公开(公告)号：EP3013691B1
公开(公告)日：2018-03-07
申请号：EP14817171.3
申请日：2014-05-16
申请人： The Charles Stark Draper Laboratory, Inc.
发明人： LAINE, Juha-Pekka , BLASCHE, Gregory, P. , CHAPARALA, Murali, V. , DAWSON, Robin , LANE, Benjamin , SMITH, Stephen, P. , WALDRON, Erik
IPC分类号： B64G1/36 , G01S3/786 , G01C21/02
CPC分类号： G01S3/7867 , G01B9/06 , G01B2290/10 , G01C21/025 , G01S3/785 , G02B6/0288 , G02B6/122 , G02B6/124 , G02B6/262 , G02B6/34 , G02B6/3548 , G02B2006/12147
摘要： A chip scale star tracker that captures plane-wave starlight propagating in free space with a wafer-thin angle-sensitive broadband filter-aperture, and directs the light into a waveguide structure for readout. Angular information about the star source is determined from characteristics of the starlight propagating in the waveguide. Certain examples include internal propagation-constant-based baffling to elimination stray light from extreme angles.

9. 发明公开

EP3150495A4 CONTROL DEVICE FOR ROCKET 有权
公开(公告)号：EP3150495A4
公开(公告)日：2018-02-14
申请号：EP15799554
申请日：2015-05-20
申请人： IHI CORP
发明人： OTSUKA TAKENORI
IPC分类号： B64G1/24 , B64G1/00 , B64G1/28 , B64G1/36 , B64G1/64
CPC分类号： B64G1/242 , B64G1/002 , B64G1/288 , B64G1/36 , B64G1/40 , B64G1/645
摘要： To drop a discarded object, such as a discarded n-th-stage rocket body or a single-staged rocket of which the engine has cut-off, to impact within a safe area while consuming as much carried fuel as possible to improve launch capability. The flight path of a two-staged rocket (1) is periodically predicted during flight, and the predicted impact point when a first-stage rocket body (11) or a fairing (15) is separated and discarded is periodically predicted from a second-stage rocket (13) at each passing scheduled point in the predicted flight path. As long as there is a passing scheduled point such that the predicted impact points of the first-stage rocket body (11) and the fairing (15) are both within the safe area, a process is periodically performed to designate the passing scheduled point furthest from the launch location of the two-staged rocket (1) as the separate-and-discard point of the first-stage rocket body (11), and when the two-staged rocket (1) reaches this separate-and-discard point, the first-stage rocket body (11) or the fairing (15) is separated and discarded.

10. 发明公开

EP2908095A1 Sun sensor for determining a position of the sun relative to an object 有权
标题翻译：奥尼姆斯特（Sonnensensor zur Bestimmung der Position der Sonne hinsichtlich）
公开(公告)号：EP2908095A1
公开(公告)日：2015-08-19
申请号：EP14000559.6
申请日：2014-02-17
申请人： Astrium GmbH
发明人： Ziegler, Tobias , Hechenblaikner, Gerald
IPC分类号： G01C17/34 , B64G1/36
CPC分类号： G01C17/34 , B64G1/363
摘要： The invention regards to a sun sensor for determining a position of the sun relative to an object, in particular for use in an attitude and orbit control system of a spacecraft, with at least one detector (1500; 1600). Each of the detectors comprises a substrate (1501; 1601, 1603), preferably at least coated with a metal exhibiting a vectorial photoelectric effect (VPE), constituting at least one detector surface (1502; 1602, 1604) and emitting electrons upon exposure to UV-light; a receiving anode (1506; 1605) for collecting the electrons emitted by the metal substrate; a current sensing means for measuring a current that is generated by the electrons which are emitted by the anode, and a processing unit (2200) for evaluating the current measured by the current sensing means, wherein the processing unit (2200) is adapted to determine a position of the sun relative to the object by determining an incidence angle of solar rays from an amount of the evaluated current.
摘要翻译：本发明涉及用至少一个检测器（1500; 1600）来确定太阳相对于物体的位置的太阳传感器，特别是用于航天器的姿态和轨道控制系统中的位置。每个检测器包括基板（1501; 1601,1603），优选地至少涂覆有呈现矢量光电效应（VPE）的金属，构成至少一个检测器表面（1502; 1602,1604），并且在暴露于 UV光; 用于收集由金属衬底发射的电子的接收阳极（1506; 1605）用于测量由阳极发射的电子产生的电流的电流感测装置，以及用于评估由电流感测装置测量的电流的处理单元（2200），其中处理单元（2200）适于确定通过从所估计的电流的量确定太阳射线的入射角来确定太阳相对于物体的位置。

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