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Method of avoiding the sun for cameras of geostationary remote sensing satellites

A technology for remote sensing satellites and the sun, applied in the field of orbital kinematics, can solve the problem of not being able to ensure that the camera is not irradiated by the sun, and achieve the effect of simple design, fast response speed and high reliability

Active Publication Date: 2020-03-06
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

This method has a good effect on stray light suppression, but it cannot ensure that the camera is not illuminated by the sun

Method used

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  • Method of avoiding the sun for cameras of geostationary remote sensing satellites
  • Method of avoiding the sun for cameras of geostationary remote sensing satellites
  • Method of avoiding the sun for cameras of geostationary remote sensing satellites

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Embodiment Construction

[0020] In order to make the objects and advantages of the present invention clearer, the present invention will be described in further detail below in conjunction with the examples. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0021] like figure 1 Shown, the embodiment of the present invention provides a kind of method for avoiding the sun of still remote sensing satellite camera, comprises the steps:

[0022] S1. Calculate the line of sight vector according to the structural characteristics of the camera

[0023] The line-of-sight vector is selected according to the camera detector type; e.g. figure 2 As shown, if the camera is a small field of view detector, the center of the optical axis is selected as the line of sight vector of the camera; if the camera is a long line array detector, the line of sight passing through the two ends of the detector is selected as...

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Abstract

The invention discloses a method for automatic sun avoidance of a camera during on-orbit working of a stationary remote sensing satellite. The method comprises the steps that firstly, the sight vectorof the camera is calculated according to the structure characteristics of the camera; secondly, the positions of the Earth and the sun under a satellite body coordinate system are calculated according to the relative position relation of a satellite, the Earth and the sun and attitude information of the satellite; thirdly, the appropriate Earth contour threshold value and the sun avoidance threshold value are selected, and whether sun avoidance is needed or not is judged according to the sight vector of the camera and the position relation of the Earth and the sun; and finally, after sun avoidance is successfully judged, a sun avoidance signal is triggered, and sun avoidance is implemented. The design is simple, reliability is high, the response speed is high, and the important significance on safety protection during working of the stationary orbit remote sensing satellite camera is achieved.

Description

technical field [0001] The present invention relates to orbital kinematics, in particular, relates to a method for camera autonomous sun avoidance during the orbit of a stationary remote sensing satellite. Background technique [0002] Because the remote sensing satellite in geostationary orbit is far away from the earth, the earth cannot block the sunlight well. At some specific moment, the angle between the sunlight vector and the boresight direction of the camera is relatively small. If no measures are taken, the sunlight may enter the camera The field of view will seriously affect the normal operation of the remote sensing camera, and even cause damage to the camera detector, resulting in major on-orbit accidents. Therefore, it is necessary to take measures to protect the camera field of view from sunlight. [0003] After investigation, the current conventional method is to install a camera hood, but this method can only avoid the influence of stray light, and cannot so...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/22B64G1/10
CPCB64G1/10B64G1/22
Inventor 吕旺王田野信思博王皓
Owner SHANGHAI SATELLITE ENG INST
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