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An optical system for a star sensor

An optical system and star sensor technology, which is applied in the optical system for star sensors and in the field of optical engineering, can solve the problem of difficult processing of aspheric optical systems, low pass rate of aspheric lens parts, unfavorable light weight of star sensors, etc. problems, to achieve good space thermal stability, good space environment adaptability, and improve the effect of attitude measurement accuracy

Active Publication Date: 2017-07-28
BEIJING INST OF CONTROL ENG
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AI Technical Summary

Problems solved by technology

After the optical system is complicated, the general volume and weight are relatively large
After the volume and weight of the optical system become larger, the star sensor needs to be structurally reinforced to meet the requirements of the stability of the optical system, resulting in a larger volume and weight of the star sensor product, which is not conducive to the light weight of the star sensor
[0008] The aspheric optical system can reduce the volume and weight of the optical system to a certain extent, but the aspheric optical system is difficult to process and the development cycle is long; at the same time, the qualified rate of the aspheric lens parts is low, resulting in a relatively high cost of the aspheric optical system. high

Method used

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  • An optical system for a star sensor

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Embodiment Construction

[0035] The star sensor is generally composed of a hood, an optical system, a detector assembly and its circuit, a data processing circuit, a secondary power supply, software (system software, application software, and star catalog), a main structure, and a reference mirror.

[0036] The star sensor uses an optical system to converge the energy of the star target, and the converged star point energy is imaged on the star sensor detector for subsequent image processing and attitude data output. Therefore, the imaging quality, volume and weight, and space environment adaptability of the optical system are the key indicators for evaluating the optical system of the star sensor.

[0037] Such as figure 1 As shown, the optical system of the present invention is composed of six lenses, the aperture stop is located on the apex of the front surface of the first lens of the optical system, and all spherical lenses are used in the system. Including aperture stop (1), first lens (2), sec...

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Abstract

The invention relates to an optical system for a star sensor. The optical system is applied to high-precision star sensors. The optical system is of an improved peaceful structure and consists of six lenses, wherein the six lenses are all spherical lenses; an aperture diaphragm is arranged on first glass; the first glass is made of fused quartz, can be used for correcting aberration and can be used as protective glass of the optical system. The optical system has the characteristics of wide spectrum, large visual field, relative large aperture and the like; the distortion is very low in relatively large spectral range and visual fields, concentration ratios of discs of confusion of each visual field are uniformly distributed, and the imaging quality is good. The optical system can work in a temperature range from -40 DEG C to 50 DEG C, has good image quality and defocusing amount at each temperature point and can meet attitude measurement requirements of the high-precision star sensors working at severe space temperature environments.

Description

technical field [0001] The invention relates to an optical system for a star sensor, which belongs to the field of optical engineering. Background technique [0002] The invention is used for star sensors used in spacecraft. The star sensor takes the star as the measurement target, images the star on the photoelectric converter through the optical system, and sends the output signal to the data processing unit through A / D conversion. After the star point extraction and star map identification, the optical axis vector of the star sensor is determined at Pointing in the inertial coordinate system, through the installation matrix of the star sensor on the aircraft, starlight navigation system and ship, determine its three-axis attitude in the inertial coordinate system. [0003] The star sensor is generally composed of a hood, an optical system, a detector assembly and its circuit, a data processing circuit, a secondary power supply, software (system software, application soft...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/02
CPCG01C21/025
Inventor 梁士通梅志武钟红军王立刘婧钟俊张运方余成武王龙陈建峰
Owner BEIJING INST OF CONTROL ENG
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