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公开(公告)号：US20240051686A1
公开(公告)日：2024-02-15
申请号：US18447699
申请日：2023-08-10
CPC分类号： B64G1/68 , H10N30/1061 , H10N30/302 , D06M11/83 , D10B2401/18
摘要： Described herein, is a sensing textile for a spacecraft, comprising an aerospace-grade fabric substrate having a surface and one or more sensing fibers coupled to the aerospace-grade fabric substrate, wherein at least a subset of the sensing fibers extends above the surface of the substrate. In some embodiments, the sensing fibers comprises one or more of an impact sensor, a charge sensor, a thermal sensor or radiative surface. Some embodiments, the sensing fibers are configured to form one or more patterned topologies about the surface of the aerospace-grade fabric substrate. In some embodiments, the patterned topologies comprises one or more of a pile, looped pile, waffle, spacer, seersucker, plissé, or an embroidery.
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公开(公告)号：US08564430B2
公开(公告)日：2013-10-22
申请号：US12863035
申请日：2009-01-16
申请人： Yukihito Katazawa , Akira Sakurai
发明人： Yukihito Katazawa , Akira Sakurai
IPC分类号： G08B23/00
CPC分类号： B64G1/68
摘要： The present invention has the object of simplifying apparatus configuration and avoiding a requirement for calibration. The present invention achieves the above object by forming a detection sheet element that retains in a predetermined array pitch a plurality of conductive detection lines that are lead lines formed by etching or the like on a non-conductive thin film that can be exposed in a space environment. A detection circuit connected to each detection line of the detection sheet element is provided. When an object flying in space collides with the detection sheet body, since a detection line on the detection sheet element is ruptured, constant monitoring of the conductivity of the detection line by the detection circuit enables detection of the object flying in space that has collided with the detection sheet element when a detection line is ruptured. Furthermore a means of solution is adopted in which an effective diameter of a colliding object flying in space can be detected from the number of severed detection lines.
摘要翻译： 本发明的目的是简化装置配置并避免对校准的要求。 本发明通过形成一种检测片元件来实现上述目的，该检测片元件以预定的阵列间距将多个导电检测线作为导电线，该导电检测线是通过蚀刻等形成的导电薄膜，其可以暴露在空间中的非导电薄膜上 环境。 提供了连接到检测片元件的每个检测线的检测电路。 当在空间中飞行的物体与检测片体碰撞时，由于检测片元件上的检测线破裂，所以通过检测电路对检测线的导电性进行持续的监视，能够检测到与空间相撞的物体飞行 当检测线破裂时的检测片元件。 此外，采用一种解决方案，其中可以从切断的检测线的数量检测在空间中飞行的碰撞物体的有效直径。
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公开(公告)号：US20110050258A1
公开(公告)日：2011-03-03
申请号：US12863035
申请日：2009-01-16
申请人： Yukihito Katazawa , Akira Sakurai
发明人： Yukihito Katazawa , Akira Sakurai
CPC分类号： B64G1/68
摘要： The present invention has the object of simplifying apparatus configuration and avoiding a requirement for calibration. The present invention achieves the above object by forming a detection sheet element that retains in a predetermined array pitch a plurality of conductive detection lines that are lead lines formed by etching or the like on a non-conductive thin film that can be exposed in a space environment. A detection circuit connected to each detection line of the detection sheet element is provided. When an object flying in space collides with the detection sheet body, since a detection line on the detection sheet element is ruptured, constant monitoring of the conductivity of the detection line by the detection circuit enables detection of the object flying in space that has collided with the detection sheet element when a detection line is ruptured. Furthermore a means of solution is adopted in which an effective diameter of a colliding object flying in space can be detected from the number of severed detection lines.
摘要翻译： 本发明的目的是简化装置配置并避免对校准的要求。 本发明通过形成一种检测片元件来实现上述目的，该检测片元件以预定的阵列间距将多个导电检测线作为导电线，该导电检测线是通过蚀刻等形成的导电薄膜，其可以暴露在空间中的非导电薄膜上 环境。 提供了连接到检测片元件的每个检测线的检测电路。 当在空间中飞行的物体与检测片体碰撞时，由于检测片元件上的检测线破裂，所以通过检测电路对检测线的导电性进行持续的监视，能够检测到与空间相撞的物体飞行 当检测线破裂时的检测片元件。 此外，采用一种解决方案，其中可以从切断的检测线的数量检测在空间中飞行的碰撞物体的有效直径。
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4.发明申请CORRELATING SINGLE CONTINUOUS WAVE RADAR SPACE OBJECT OBSERVATION FOR INITIAL ORBIT DETERMINATION 失效相关单波连续波雷达空间目标观测初始轨道确定公开(公告)号：US20040008137A1
公开(公告)日：2004-01-15
申请号：US10193763
申请日：2002-07-12
申请人： ITT Industries
IPC分类号： G01S013/72
摘要： Correlating observations of objects in the sky to determine an orbit includes identifying an initially identified object, determining if the initially identified object will be identifiable again, and identifying a subsequently identified object. A determination is then made by comparing characteristics of the initially identified object with the subsequently identified object. If the object correlate to one another a path or orbit of the object can be determined using the characteristics of the initially identified object and the subsequently identified object.
摘要翻译： 天体中对象的相关观测确定轨道包括识别初始识别的对象，确定初始识别的对象是否将被再次识别，以及识别随后识别的对象。 然后通过将初始识别的对象的特征与随后识别的对象进行比较来进行确定。 如果对象彼此关联，则可以使用初始识别的对象和随后识别的对象的特征来确定对象的路径或轨道。
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公开(公告)号：US20230242280A1
公开(公告)日：2023-08-03
申请号：US17927638
申请日：2021-06-10
发明人： Dorian GEGOUT , Frédéric RENAUD
摘要： A method for adjusting the path of a satellite to limit a risk of collision with items of debris each having a date of closest pass with the satellite is disclosed including: propagating at least one orbit from the reference path of the satellite according to at least one manoeuvre to the farthest date of closest pass; determining a probability of collision for each item of debris according to the at least one orbit; determining at least one overall probability according to the set of probabilities determined; selecting the lowest overall probability from among the at least one overall probability obtained; determining a command for the satellite including the manoeuvre associated with the lowest overall probability.
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公开(公告)号：US09501698B2
公开(公告)日：2016-11-22
申请号：US14638274
申请日：2015-03-04
申请人： IHI Corporation
发明人： Hajime Banno
IPC分类号： G06K9/00 , B64G1/68 , B64G3/00 , H04N5/217 , H04N5/361 , G06T5/00 , G06T5/10 , H04N5/365 , H04N5/14
CPC分类号： G06K9/00624 , B64G1/68 , B64G3/00 , G06T5/002 , G06T5/10 , G06T2207/10016 , G06T2207/20182 , H04N5/144 , H04N5/2176 , H04N5/361 , H04N5/3651
摘要： When correction values are respectively determined for noise components of “OFFSET COMPONENT OF CCD ELEMENT”, “GRADATION COMPONENT OF BACKGROUND LIGHT” and “OFFSET COMPONENT OF OPTICAL SYSTEM”, the pixel values including as less of these noise components as possible are evaluated. The evaluated pixel values include a noise component of “THERMAL NOISE PLUS READOUT NOISE COMPONENT” which is superposed onto the pixel values. With this taken into consideration, a moving object detection method of an embodiment photographs multiple images of a moving object being an observation object with a photographic area fixed, selects the smallest pixel value in each group of corresponding pixels across the images from image signals representing the images, evaluates image signals including as less of the four noise components as possible by using the smallest pixel value as the correction value for the four noise components.
摘要翻译： 当分别对“CCD元件的偏移分量”，“背景光的灰度分量”和“光学系统的偏移分量”的噪声分量确定校正值时，评估包括尽可能少的这些噪声分量的像素值。 所评估的像素值包括叠加在像素值上的“热噪声加注读噪声分量”的噪声分量。 考虑到这一点，实施例的移动物体检测方法以摄影区域固定的观察对象的运动物体的多个图像进行拍摄，从代表图像信号的图像信号中选择每个图像中的每组相应像素中的最小像素值 图像，通过使用最小像素值作为四个噪声分量的校正值来评估包括尽可能多的四个噪声分量中的较少的图像信号。
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公开(公告)号：US20120085869A1
公开(公告)日：2012-04-12
申请号：US13196869
申请日：2011-08-02
申请人： Peter Lloyd
发明人： Peter Lloyd
摘要： Apparatus for a space platform comprises a magnetic field generator and/or an electric field generator respectively configured to generate fields for influencing the trajectory of one or more items of space debris passing within a region of the apparatus. A system comprising a plurality of such space platforms may be placed in an orbit proximal to an orbit containing space debris. An individual space platform or system thereof may be used in a method for displacing earth orbital space debris out of the orbit and either towards the Earth's atmosphere where it is likely to be destroyed by the burning on re-entry into the atmosphere, or into a safer orbit from which it may be collected or in which it may be left.
摘要翻译： 用于空间平台的装置包括磁场发生器和/或电场发生器，其分别被配置为产生用于影响在装置的区域内通过的一个或多个空间碎片物品的轨迹的场。 包括多个这样的空间平台的系统可以放置在靠近包含空间碎片的轨道的轨道中。 一种单独的空间平台或其系统可以用于将地球轨道空间碎片从轨道中移出并且朝向地球大气层的方法中，其中它可能被重新进入大气中的燃烧而被破坏，或者变成 更安全的轨道，可以从中收集或在其中留下。
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公开(公告)号：US4991799A
公开(公告)日：1991-02-12
申请号：US480985
申请日：1990-02-16
申请人： Andrew J. Petro
发明人： Andrew J. Petro
摘要： An orbital debris sweeper is provided for removing particles from orbit which otherwise may impact and damage an orbiting spacecraft. The debris sweeper includes a central sweeper core which carries a debris monitoring unit, and a plurality of large area impact panels rotatable about a central sweeper rotational axis. In response to information from the debris monitoring unit, a computer determines whether individual monitored particles preferably impact one of the rotating panels or pass between the rotating panels. A control unit extends or retracts one or more booms which interconnect the sweeper core and the panels to change the moment of inertia of the sweeper and thereby the rotational velocity of the rotating panels. According to the method of the present invention, the change in panel rotational velocity increases the frequency of particles which desirably impact one of the panels and are thereby removed from orbit, while large particles which may damage the impact panels pass between the trailing edge of one panel and the leading edge of the rotationally succeeding panel.
摘要翻译： 提供了一个轨道碎片清扫机，用于从轨道上除去颗粒，否则可能会撞击并损坏轨道上的航天器。 碎片清扫机包括一个带有碎片监控单元的中央扫地机芯，以及围绕一个中央扫地机旋转轴线旋转的多个大面积的冲击板。 响应于来自碎片监测单元的信息，计算机确定个别监测的颗粒是否优选地影响旋转面板中的一个或在旋转面板之间通过。 控制单元延伸或缩回一个或多个悬臂，其将扫把机芯和面板相互连接，以改变清扫机的转动惯量，从而改变旋转面板的旋转速度。 根据本发明的方法，面板旋转速度的变化增加了期望地撞击面板之一并因此从轨道上移除的颗粒的频率，而可能损坏冲击板的大颗粒在一个的后缘之间通过 面板和旋转后面板的前缘。
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9.发明授权Meteoroid sensing apparatus having a coincidence network connected to a pair of capacitors 失效具有连接到一对电容器的符合网络的流星体感测装置
公开(公告)号：US3324388A
公开(公告)日：1967-06-06
申请号：US24953763
申请日：1963-01-04
申请人： DAVISON ELMER H
发明人： DAVISON ELMER H
IPC分类号： B64G1/68
CPC分类号： B64G1/68
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公开(公告)号：US11873121B2
公开(公告)日：2024-01-16
申请号：US17927638
申请日：2021-06-10
发明人： Dorian Gegout , Frédéric Renaud
摘要： A method for adjusting the path of a satellite to limit a risk of collision with items of debris each having a date of closest pass with the satellite is disclosed including: propagating at least one orbit from the reference path of the satellite according to at least one manoeuvre to the farthest date of closest pass; determining a probability of collision for each item of debris according to the at least one orbit; determining at least one overall probability according to the set of probabilities determined; selecting the lowest overall probability from among the at least one overall probability obtained; determining a command for the satellite including the manoeuvre associated with the lowest overall probability.
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