Solar suppression angle-free star sensor
A sensor and solar technology, applied in the field of solar immune star sensors, can solve the problems of inability to complete space missions, can not work normally, limit the application range of star sensors, etc. reduced effect
Active Publication Date: 2018-04-06
BEIJING INST OF CONTROL ENG
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Problems solved by technology
[0005] (1) The sun suppression angle is a value larger than the half field angle, so the star sensor cannot work normally within a large cone angle range near the sun near the optical axis of the star sensor, which limits the performance of the star sensor range of applications, some special space missions cannot be completed
[0006] (2) the light-absorbing material of star sensitive sensor optical system lens barrel structure and picture frame inner surface of prior art is matte black paint, and its light absorption coefficient is about 97%, relatively low, can not satisfy the requirement of solar immune star sensor optical system Scattered light absorption requirements
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[0036] like image 3 As shown, a solar immune sensor includes a support structure 1, a primary image optical system 2, a polarizer 3, a primary spatial light modulator 4, a primary image aperture 5, a secondary spatial light modulator 6, and a secondary Optical system 7, Leo aperture 8, three-stage spatial light modulator 9, photodetector 10, connecting cable 11 between photodetector 10 and information processor 12, information processor 12, complete machine mounting flange 13, Outer shading cover 21; primary image optical system 2 comprises first correction lens 14, primary reflector 15, second correction lens group 16; the central area of the second transmission surface of first correction lens 14 is coated with reflective film to form secondary reflection mirror surface 20 , the incident light of the star target and the sun passes through the first correcting lens 14, is reflected by the main reflector 15, is reflected on the secondary reflector 20, and after being reflec...
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The invention provides a solar suppression angle-free star sensor. The star sensor comprises a primary image optical system. A fixed star and solar target light enters the primary image optical systemfrom an outer light shield, generates a linearly polarized light via a polarizer; the linearly polarized light reaches a primary image diaphragm through a primary spatial light modulator to form a primary image, reaches a Leo diaphragm after continuously reaching a secondary optical system through a secondary spatial light modulator, and reaches a photoelectric detector from the Leo diaphragm through a tertiary spatial light modulator to form a secondary image on the photoelectric detector; an information processor is used for collecting and saving digital images output by the photoelectric detector; and a feedback control system is formed by the information processor, the photoelectric detector, the primary spatial light modulator, a secondary spatial light modulator and the tertiary spatial light modulator. The solar suppression angle-free star sensor can overcome the influence of structural scattered straylight entering between a semi-angular field and a solar suppression angle ofthe star sensor, and can solve the problem of image surface straylight suppression that sunlight directly enters the field angle of the star sensor.
Description
technical field [0001] The invention relates to a star sensor, in particular to a solar immune star sensor. Background technique [0002] At present, star sensors are often used for attitude measurement of spacecraft. The main principle of this sensor is: using the law that the position of stars is basically immobile relative to inertial space, the star map is obtained by photoelectric imaging of stars in a sky area, and then the star sensor The image is processed and identified to obtain the direction of the optical axis of the measurement sensor in the inertial space, and the three-axis attitude of the spacecraft can be obtained by converting the star sensor installation coordinate system on the spacecraft and the spacecraft attitude coordinate system. [0003] In the prior art, the star sensor hardware includes a light shield, an optical system (lens), an electronic system, electrical appliances, and a structural interface. The electronic system includes a photodetector ...
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Login to View More IPC IPC(8): G01C21/02
CPCG01C21/025
Inventor 郝云彩
Owner BEIJING INST OF CONTROL ENG