Star sensor optical imaging system for deep space exploration spacecraft attitude-determination

Abstract

The invention discloses a star sensor optical imaging system for deep space exploration spacecraft attitude-determination, and belongs to the technical field of optical system. In order to overcome the problems existing in prior art, an incident light is reflected by a front surface of a first reflector, and is injected to a rear surface of a second reflector; then injected to a first positive meniscus lens after being reflected by the second reflector; the incident light passes through the first positive meniscus lens, a first negative meniscus lens, a second negative meniscus lens and a second positive meniscus lens in order, and then is received by a detector finally; a center distance between the front surface of the first reflector and the rear surface of the second reflector is d1; the center distance between the rear surface of the second reflector and the front surface of the first positive meniscus lens is d2; a center distance between the rear surface of the first positive meniscus lens and the front surface of the first negative meniscus lens is d3; a center distance between the rear surface of the first negative meniscus lens and the front surface of the second negative meniscus lens is d4; a center distance between the rear surface of the second negative meniscus lens and the front surface of the second positive meniscus lens is d5; and a center distance between the rear surface of the second positive meniscus lens and the detector is d6.

Description

technical field [0001] The invention relates to a star sensor optical imaging system for attitude determination of a deep space exploration aircraft, which can be applied to the attitude determination of an outer space deep space exploration aircraft and belongs to the technical field of optical systems. Background technique [0002] There are various imaging types of star sensors according to the range of wavelengths used and the types of detectors. The structure of the star sensor that has been reported so far mostly adopts the transmissive type of the fully transmissive lens, the focal length of the system is generally 20mm-60mm, and the effective entrance pupil diameter is generally 10mm-50mm. This will lead to disadvantages such as low incident light energy received by the image detector per unit time, prolonged dynamic motion imaging integration time, slow image refresh rate, and slow speed of satellite attitude determination when observing targets such as faint small ...

AI Technical Summary

Problems solved by technology

This will lead to disadvantages such as low incident light energy received by the image detector per unit time, prolonged dynamic motion imaging integration time, slow image refresh rate, and slow speed of satellite attitude determination when observing targets such as faint small stars in deep space, which cannot be applied. In the field of attitude determination of spacecraft and satellites for deep space exploration in the future

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