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Three-view field synthesis star map simulation system and method adopting double-sided light splitting right-angle prism

A right-angle prism and simulation system technology, applied in the field of spacecraft calibration, can solve the problem that there is no way to meet the integrated function of mobile star map tracking and multi-field of view, and achieve the effect of expanding the use function and calibration accuracy, simple structure and simple operation

Active Publication Date: 2022-04-12
NANJING ZHONGKE ASTROMOMICAL INSTR
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AI Technical Summary

Problems solved by technology

However, the current star simulators are all one system that can only realize a star map simulation function at the same time, and there is no way to satisfy the multi-field of view for fixed single star positioning, mobile star map tracking, and large field of view star map reference. Integrated function

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  • Three-view field synthesis star map simulation system and method adopting double-sided light splitting right-angle prism
  • Three-view field synthesis star map simulation system and method adopting double-sided light splitting right-angle prism
  • Three-view field synthesis star map simulation system and method adopting double-sided light splitting right-angle prism

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Embodiment Construction

[0019] The specific implementation manner and working principle of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0020] This embodiment provides a three-field synthetic star map simulation system using a double-sided light-splitting rectangular prism. The simulation system has the characteristics of large field of view and high precision, and can realize a star simulator containing multiple star point information and multiple star maps.

[0021] Such as figure 1 As shown, the three-field-of-view synthetic star map simulation system using a double-sided right-angle prism includes a point light source 1, a beam splitter 2, a collimation system 3, a star sensor 4, a first light source 5, and a first star point division plate 6 , second light source 7 , second star reticle 8 , and imaging lens group 9 . Through coating technology and optical path design, it is possible to realize three-field star map simulation w...

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Abstract

The invention discloses a three-view field synthesis star map simulation system and method adopting a double-sided light splitting rectangular prism. The system comprises a point light source, a beam splitter, a collimation system, a star sensor, a first light source, a first star point reticle, a second light source, a second star point reticle and an imaging lens group. A light path of the simulation system comprises a fixed single-star map light path, a first large-field-of-view star map light path and a second large-field-of-view star map light path. According to the actual requirements of the star sensor, the three star maps can be overlapped pairwise or three star maps can be overlapped on the star sensor CCD to form the star simulator with multiple star maps, so that the use function and the calibration precision of the star simulator are expanded, the operation is simple, and the star simulator has very high universality and practicability.

Description

technical field [0001] The invention belongs to the technical field of spacecraft calibration, and in particular relates to a three-field-of-view synthetic star map simulation system and method using a right-angle prism with double-sided spectroscopic design. Background technique [0002] Attitude is an important parameter that affects the trajectory and orientation of a moving object. For spacecraft that require precise positioning, the attitude needs to be precisely controlled. The star sensor is a high-precision space attitude optical sensor, which can calculate the position deviation and attitude deviation of the aircraft in real time through the star map in the field of view. The aircraft can be corrected according to the provided data to avoid uncontrolled rollover in the orbit; due to the characteristics of fast calculation and high precision of the star sensor, it has become a very important part of the spacecraft. [0003] Due to the limitation of natural conditio...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
Inventor 李金鹏王鑫蕊杨永兴王赛亚张景源马永韩宇
Owner NANJING ZHONGKE ASTROMOMICAL INSTR
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