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135 条记录 (耗时 0.013 秒)

    Method and apparatus for controlling spacecraft attitude with rotational star trackers
    71.
    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：EP1033300A2

    公开(公告)日：2000-09-06

    申请号：EP00104122.7

    申请日：2000-02-29

    申请人： Hughes Electronics Corporation

    发明人： Wu, Yeong-Wei A. ,  Hein, Douglas H. ,  Didinsky, Garry ,  Augenstein, David L.

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

    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

    摘要翻译： 高精度航天器（108）姿态确定是通过特殊的定位（100）中的航天器的星跟踪（112），然后过滤来自星象跟踪仪电子设备（216）中产生（102）输出的测量误差产生的。 除了用于星象跟踪仪指示的常规方位角和仰角的控制，恒星跟踪器的检测器阵列（400）是转动地定位关于其瞄准线（900）象其像素（401）由在所述成像星路径（404）横越 在内的对角20°的角度。 这迫使在检测器平面垂直和水平空间的误差成分（700，702），以在共同在它们能够容易地过滤掉高频范围（102）

    Lightweight missile guidance system
    73.
    发明公开
    Lightweight missile guidance system 失效
    Leichtbau-Flugkörper-Lenksystem。

    公开(公告)号：EP0436215A2

    公开(公告)日：1991-07-10

    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.

    摘要翻译： 公开了一种轻型导弹终端引导系统14，其包括用于提供指示从导弹10到目标12的视线15和延伸穿过导弹的纵轴9之间的第一角度ε的第一信号的探测器16 引导器16还提供指示延伸穿过导弹10的纵向轴线9和导弹10与天体13之间的视线11之间的第二角度δ的第二信号。包括处理器18，用于 从导弹10到目标12的视线15之间的视线角度sig和从第一和第二角度ε和E的导弹10到天体13的视线11 三角洲 终端引导子系统24从推进系统26使用的视距角度计算加速度指令，以响应于此来改变导弹10的速度矢量。

    CELESTIAL NAVIGATION OBJECT AVAILABILITY USING LIGHT SOURCE ENABLED SATELLITES
    74.
    发明公开
    CELESTIAL NAVIGATION OBJECT AVAILABILITY USING LIGHT SOURCE ENABLED SATELLITES 审中-公开

    公开(公告)号：EP4462077A1

    公开(公告)日：2024-11-13

    申请号：EP24162574.8

    申请日：2024-03-11

    申请人： Honeywell International Inc.

    发明人： STEPHENS, Trevor Keith ,  SCHIPPER, Brian ,  MERRITT, Ross

    IPC分类号： G01C21/02 ,  G01S5/16

    摘要： A method and system for celestial navigation are provided. The method comprises requesting access to a light source on a low earth orbit (LEO) satellite; and sending an uplink message to the LEO satellite to power on the light source, in response to the access request. The method further comprises determining whether the LEO satellite is in view of a camera; capturing a light image, from the light source, on a focal plane location of the camera when the LEO satellite is in view of the camera; and comparing the focal plane location to a predicted location of the LEO satellite. The method updates position information of a user based on an observation error from comparing the focal plane location to the predicted location.

    DIRECT SUN IMAGING STAR TRACKER
    77.
    发明公开
    DIRECT SUN IMAGING STAR TRACKER 审中-公开

    公开(公告)号：EP4109043A1

    公开(公告)日：2022-12-28

    申请号：EP21188846.6

    申请日：2021-07-30

    申请人： The Boeing Company

    发明人： CHRIEN, Thomas George ,  SALZMAN, Thomas Daniel

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

    摘要： Described are systems and methods for direct sun imaging by a star tracker. Disclosed in a certain example is a direct sun imaging star tracker that includes an imaging sensor and a baffle. The baffle includes a star port, a sun port, and a beam splitter. The star port is configured to image first viewing environment while the sun port is configured to image a second viewing environment that includes the sun. The beam splitter is configured to combine electromagnetic radiation from the star port and the sun port into a combined image. In various examples, the systems and techniques described herein allow a star tracker to simultaneously view both the sun and the stars.