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135 条记录 (耗时 0.013 秒)

    System and method for sensing attitude of a spacecraft with equalized star tracker errors along three orthogonal axes
    101.
    发明公开
    System and method for sensing attitude of a spacecraft with equalized star tracker errors along three orthogonal axes 失效
    装置和用于确定与在三个正交轴均衡星传感器误差的航天器的位置的方法。

    公开(公告)号：EP0573284A1

    公开(公告)日：1993-12-08

    申请号：EP93304284.8

    申请日：1993-06-02

    申请人： Hughes Aircraft Company

    发明人： Abreu, Rene

    IPC分类号： B64G1/36 ,  G01C21/02 ,  G01S3/786

    CPC分类号： G01S3/7867 ,  B64G1/26 ,  B64G1/361 ,  G01C21/025

    摘要： A star tracker 10 of an attitude control system 8 on board a spacecraft 9 is positioned so that the tracker's line-of-sight vector 12 intersects the origin of the reference axis but is askew from any reference axis of the spacecraft. The attitude control system transforms the data from a star tracker reference coordinate system to a spacecraft reference coordinate system so as to allow control of the attitude of the spacecraft without modification of existing equipment.

    摘要翻译： 上板象航天器9定位的姿态控制系统8的星象跟踪仪10跟踪器的线的视线矢量12相交的参考轴的原点，但是从歪斜飞船的任何基准轴。 姿态控制系统转换坐标从一个星跟踪基准数据系统航天器参考坐标系，以便使航天器的姿态的控制，而不现有设备的修改。

    Lightweight missile guidance system
    102.
    发明公开
    Lightweight missile guidance system 失效
    轻型导弹系统

    公开(公告)号：EP0436215A3

    公开(公告)日：1992-10-28

    申请号：EP90125482.1

    申请日：1990-12-24

    申请人： Hughes Aircraft Company

    发明人： Beam, Norman E. ,  Vance, Leonard D.

    IPC分类号： F41G7/22 ,  G05D1/12 ,  G01C21/02

    CPC分类号： G01C21/025 ,  F41G7/2253 ,  F41G7/2293 ,  G05D1/12

    摘要： A lightweight missile terminal guidance system 14 is disclosed which includes a seeker 16 for providing a first signal indicative of a first angle ε between a line-of-sight 15 from the missile 10 to a target 12 and a longitudinal axis 9 extending through the missile 10. The seeker 16 also provides a second signal indicative of a second angle δ between the longitudinal axis 9 extending through the missile 10 and a line-of-sight 11 between the missile 10 and a celestial body 13. A processor 18 is included for computing the line-of-sight angle σ between the line-of-sight 15 from the missile 10 to the target 12 and the line-of-sight 11 from the missile 10 to the celestial body 13 from the first and second angles ε and δ. A terminal guidance subsystem 24 computes acceleration commands from the line-of-sight σ angle which are used by a propulsion system 26 to change the velocity vector of the missile 10 in response thereto.

    STERNBILDSIMULATOR, SYSTEM UND VERFAHREN ZUM EINMESSEN EINES STERNSENSORS
    103.
    发明公开
    STERNBILDSIMULATOR, SYSTEM UND VERFAHREN ZUM EINMESSEN EINES STERNSENSORS 审中-公开

    公开(公告)号：EP4443107A1

    公开(公告)日：2024-10-09

    申请号：EP23217748.5

    申请日：2023-12-18

    申请人： Jena Optronik GmbH

    发明人： Dr.-Ing. Schmidt, Uwe ,  Möller, Erik ,  Hädrich, Bernd ,  Hahn, Steffen ,  Boy, Michael ,  Dr. Colditz, Sebastian

    IPC分类号： G01C21/02 ,  B64G1/36

    CPC分类号： G01C21/025 ,  B64G1/361

    摘要： Die vorliegende Erfindung bezieht sich auf einen kalibrierten Sternbildsimulator (1 10), ein System (100) und ein Verfahren (V) zum Einmessen und/oder Test eines auf einem Raumflugkörper (130) montierten Sternsensors (120). Der kalibrierte Sternbildsimulator (110) umfasst eine optische Vorrichtung (111) konfiguriert zum Projizieren einer definierten Sternformation (IRF) eines Sternkataloges vorzugsweise auf einen Raumflugkörper (130) montierten Sternsensor (120). Ferner umfasst der kalibrierte Sternbildsimulator (110) eine Abgleicheinheit (113) mit einer Positions- und/oder Lagereferenz (ARF) des kalibrierten Sternbildsimulators (110) konfiguriert zum Erfassen einer Position- und/oder Lage des kalibrierten Sternbildsimulators (110) im Raum, wobei die definierte Sternformation (IRF) und die Positions- und/oder Lagereferenz (ARF) in einer ersten fest kalibrierten Rotation (QOSPS) zueinander liegen. Der kalibrierte Sternbildsimulator (110) verbessert das Einmessen des Sternsensor (120) als eigenständiges Kalibriernormal. Der Sternbildsimulator (110) wird zu einem Kalibriernormal.

    PERSONAL NAVIGATION DEVICE OPERABLE IN GNSS-DENIED ENVIRONMENT
    106.
    发明公开
    PERSONAL NAVIGATION DEVICE OPERABLE IN GNSS-DENIED ENVIRONMENT 审中-公开

    公开(公告)号：EP4027173A1

    公开(公告)日：2022-07-13

    申请号：EP21201704.0

    申请日：2021-10-08

    申请人： The Boeing Company

    发明人： LI, Rongsheng

    IPC分类号： G01S19/48 ,  G01C21/02 ,  G01C21/16

    摘要： A personal navigation device comprising a body, a star tracker, an inclinometer, a clock, a GNSS receiver, and first and second position calculation modules. The first position calculation module is configured to calculate latitude and longitude of the body based on respective outputs from the star tracker, inclinometer, and clock. The second position calculation module is configured to calculate latitude and longitude of the body based on satellite signals received by the GNSS receiver. In one example, the star tracker includes a short-wave infrared camera and the inclinometer includes three accelerometers having non-coplanar axes. The personal navigation device may further include a display device, a display engine, and a user interface configured to enable selection of a particular method of calculating latitude and longitude depending on whether GNSS is available or not.