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Method for absolutely radiometric calibration of low orbit earth observation satellite with moon as reference

An absolute radiometric calibration and earth observation technology, applied in the field of remote sensing satellite calibration, which can solve the problems of affecting calibration accuracy, complicated operation and high cost

Active Publication Date: 2015-03-25
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

1) The calibration of the on-board calibration device mainly includes the calibration of the calibration light and the calibration of the solar diffuser. Attenuation will occur, affecting the calibration accuracy
2) Ground calibration Site calibration mainly uses ground laying targets, which is currently the most commonly used absolute radiometric calibration method, but this method requires simultaneous measurement of atmospheric parameters, which is seriously affected by weather, low efficiency, high cost, and complicated operation

Method used

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  • Method for absolutely radiometric calibration of low orbit earth observation satellite with moon as reference
  • Method for absolutely radiometric calibration of low orbit earth observation satellite with moon as reference
  • Method for absolutely radiometric calibration of low orbit earth observation satellite with moon as reference

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Embodiment

[0168] In this embodiment, given satellite orbit height H=645km, earth radius R e =6378km, lunar radius R m =1737km, take R as the distance between the center of the earth and the moon em =384400km, camera focal length f=2.6m, Kepler constant μ=3.986×10 5 km 3 / s 2 1. The size of each pixel in the satellite linear array CCD camera is p=10 μm.

[0169] 1. Determine the satellite camera exposure time t for each imaging m

[0170] According to formula (2), the exposure time t for imaging the earth is obtained e for:

[0171] t e = p f × μ ( R e + H ) 3 × ...

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Abstract

The invention provides a method for absolutely radiometric calibration of a low orbit earth observation satellite with moon as reference. The method comprises the following steps that the time during which the low orbit earth observation satellite can observe the moon is primarily determined through a satellite tool kit; the starting time of moon imaging, the ending time of moon imaging, the camera exposure time, the satellite attitude angle during imaging, the pitching angular velocity and the like are determined; according to the parameters, moon imaging is conducted, so that an image of moon is obtained; the image of the moon is analyzed through a ROLO absolutely radiometric calibration model, and absolutely radiometric calibration coefficients are obtained. By the adoption of the method, an onboard calibration device and an operating mechanism are not needed, a special ground reference source is not needed, the long-term stability of moon and the attitude maneuver capacity of the satellite are fully utilized, and the image of moon is obtained and used as a reference source.

Description

technical field [0001] The invention relates to a radiation calibration method, in particular to a lunar absolute radiation calibration method by a low-orbit earth observation satellite, and belongs to the technical field of remote sensing satellite calibration. Background technique [0002] The radiation performance of optical remote sensing satellites in orbit will be greatly degraded, and the application of quantitative remote sensing puts forward strict requirements on the accuracy and stability of absolute radiation calibration. At present, the calibration based on the on-board calibration device and the ground calibration field is a commonly used on-orbit absolute radiometric calibration method. 1) The calibration of the on-board calibration device mainly includes the calibration of the calibration light, the calibration of the solar diffuser, etc. However, due to the influence of the radiation environment of outer space and the optical, electronic and mechanical struc...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00G01C25/00G06T7/00
Inventor 满益云李海超
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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