Design method of light introducer for solar sensor with high precision and large field of view with different apertures

Abstract

The invention discloses a method for designing a sun sensor light introducer with high precision, large view field and different apertures. The method comprises the following steps: S1, setting the distances from a view field angle of the sun sensor and the light introducer to an image sensor; S2, calculating the minimum distance of an incident hole; S3, confirming incident aperture sizes of different incident angle light introducers; S4, confirming the diameter of the minimum incident angle small hole diffraction spot and the distance of edges of incident hole groups; S5, setting a safe gap value of the incident hole groups, and calculating the central distance of the incident hole groups; S6, calculating a measurable sub-view field range of the incident hole groups, and the requested number of the incident hole groups; S7, judging whether the distance of the incident holes meets the requirements of the step 2 or not, if the distance of the incident holes meets the requirements of the step 2, implementing the step 8, otherwise implementing the step 3; S8, obtaining the aperture sizes of different incident hole groups according to the sizes of incident holes and the measurable sub-view field range of the incident hole groups; and S9, solely encoding the small hole distance, and thus completing the design of the light introducer. By adopting the method, the view field angle range, the resolution ratio and the sun incident angle extraction precision of the sun sensor can be simultaneously improved.

Description

technical field [0001] The invention relates to the technical field of solar sensor attitude measurement, in particular to a design method for a light introducer of a solar sensor with high precision, large field of view and different apertures. Background technique [0002] The sun sensor is an important part of the attitude and orbit control system of the spacecraft. The orientation of the spacecraft to the sun is realized by measuring the angle between the sun's rays and the coordinate system of the sun sensor. The sun sensor is mainly divided into analog and digital. The analog sun sensor has a simple structure, but its accuracy is low and it is easily affected by stray light, so it is not suitable for high-precision attitude determination and control systems. Compared with the analog sun sensor, the digital sun sensor has higher measurement accuracy, and its optical system can eliminate the influence of stray light. In 2002, JPL Laboratory of the United States proposed ...

AI Technical Summary

Problems solved by technology

However, for the porous light introducer designed based on the principle of pinhole imaging, due to the diffraction effect of the pinholes, the diffraction imaging between adjacent pinholes will interfere, especially in the case of a large field of view, which will affect the accuracy of image centroid extraction

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