Dynamic star simulator projection optical system with athermalization function

Abstract

The invention discloses a dynamic star simulator projection optical system with an athermalization function. The system comprises a diaphragm, a lens cone and a star point display device, wherein thediaphragm is matched with an entrance pupil of a star sensor; the star point display device is installed at the tail end of the lens cone; and a first lens, a second lens, a third lens, a fourth lensand a fifth lens are sequentially and coaxially arranged in the lens cone from the front end to the tail end; the first lens is a biconvex lens, the second lens is a biconvex lens, the third lens is abiconcave lens, the fourth lens is a meniscus lens of which the convex surface faces the diaphragm and the fifth lens is a meniscus lens of which the concave surface faces the diaphragm. The inter-satellite angular distance error precision of a simulated star point is high and is superior to 2'', and under actual use, the image quality of the optical system can be kept stable at different temperatures, so that the ground test and calibration requirements of a high-precision star sensor at different temperatures are met.

Description

technical field [0001] The invention belongs to the technical field of spacecraft calibration, in particular to a dynamic star simulator projection optical system with adiabatic difference. Background technique [0002] In recent years, the aerospace industry has developed rapidly, and the use of space vehicles has become more and more extensive. With the development of space technology and the improvement of aircraft attitude positioning requirements, the star sensor, as a high-precision space attitude measurement device for capturing and measuring its flight attitude information in a space vehicle, has higher and higher technical specifications. The star simulator, as a device for accurately simulating the position of stars in the sky on the ground of the star sensor, has also received more and more attention. In order to adapt to the extreme environment and further ensure the test performance of the star simulator, the star simulator is required in- The environment of 40...

AI Technical Summary

Problems solved by technology

[0003] The main disadvantage of the existing optical system of the dynamic star simulator is that the accuracy of the inter-satellite angular distance error is not high enough. Imaging quality is easily affected by changes in ambient temperature, which usually exceeds the focal depth of the optical system. The operating temperature range of the star sensor is required to be -40°C to 60°C. The existing dynamic star simulator optical system cannot operate within the operating temperature range. Internal guarantee accuracy requirements, high temperature range control requirements, unable to meet the ground testing and calibration requirements of high-precision star sensors at different temperatures

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