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Space camera in-orbit absolute calibration method based on fixed star

A space camera, star technology, applied in image data processing, measuring devices, instruments, etc., can solve the problems of long calibration interval, increase human and material resources, etc., to save calibration time, reduce calibration cost, and take into account programmable sexual effect

Active Publication Date: 2015-06-24
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

Traditional calibration methods are gradually unable to meet the needs of high-precision quantitative remote sensing applications. For example, on-board calibration will be affected by the uncertainty of the on-orbit environment and instrument attenuation; while field calibration methods will be affected by the number of visits. Due to the limitation of weather and weather conditions, as the device ages, on-orbit calibration needs to be carried out periodically, manpower and material resources must be increased, and the calibration interval is longer

Method used

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  • Space camera in-orbit absolute calibration method based on fixed star
  • Space camera in-orbit absolute calibration method based on fixed star
  • Space camera in-orbit absolute calibration method based on fixed star

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Embodiment Construction

[0041] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0042] Assuming that the radiance received by the space camera from the target scene in its instantaneous field of view is SRF, in the ideal case where all imaging links are linear systems, the schematic diagram of the energy transfer process of the system is as follows figure 2 as shown, figure 2 It is a schematic diagram of the transfer function of the space camera system of the present invention.

[0043] SRF=A 0 ·Ω det ·τ ota (λ)·R det (λ)·R elec (λ)·R A / D (λ)·E NL (λ)·τ noise (λ)·τ NL (λ)·Δλ (1-1)

[0044]

[0045] in:

[0046] A 0 - the effective area of ​​the entrance pupil diameter of the space camera;

[0047] Ω det - the solid angle of the entrance pupil diameter of the space camera;

[0048] τ ota (λ)—the total transmittance of the optical system of the space camera including various optical elements;

[0049] R d...

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Abstract

The invention relates to a space camera in-orbit absolute calibration method based on a fixed star. According to the method, the dynamic adjusting capability of a satellite platform attitude machine is adequately utilized, a corresponding relation between a fixed-star source with stable target radiation characteristic and a gray value output by a space camera is established, and the space camera in-orbit absolute radiation calibration is realized according to the advantages of the fixed star imaging and the optimized absolute calibration algorithm. An imaging mode adjusted by satellite attitude is adopted, the requirement for a calibration environment is low, an additional calibration device is not needed, and the in-orbit absolute calibration does not depend on the special calibration field, so that the calibration cost is remarkably reduced, and the calibration time is saved.

Description

technical field [0001] The invention relates to an on-orbit absolute calibration method for a space camera based on stars, in particular to a method for on-orbit absolute calibration of a space camera using a star with stable target radiation characteristics as a light source, and belongs to the technical field of on-orbit radiation calibration. Background technique [0002] Absolute radiation calibration is to establish the quantitative relationship between the digital signal recorded by the remote sensor and the corresponding radiation energy. The joint report of the National Institute of Standards and Technology NIST (National Institute of Standards and Technology) gives the definition of radiometric calibration as follows: Calibration is to determine the performance of the instrument in the space domain, time domain, and spectral domain during a series of measurements. Radiation performance, whose output is a numerical value related to the actual radiant energy measureme...

Claims

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/00G06T7/80
Inventor 叶钊王超窦强韩杏子董小静尹欢
Owner AEROSPACE DONGFANGHONG SATELLITE
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