An all-time miniaturized star-tracking optical system

Abstract

The invention provides a miniaturized fixed star tracking optical system capable of achieving whole-day observation. The whole-day miniaturized fixed star tracking optical system comprises an imaging unit, a band-pass fiber, a main reflector, an auxiliary reflector and a scan reflector and a through hole is formed in the center of the main reflector, wherein the imaging unit, the band-pass fiber, the main reflector, the auxiliary reflector and the scan reflector are sequentially arranged along an optical axis of an imaging optical path; incident light sequentially passes through the scan reflector, the main reflector and the auxiliary reflector, is reflected for three times, and then is emitted to the imaging unit through the central through hole of the main reflector and the band-pass filter; a part of an optical path of the incident light coincides with a part of an imaging optical path in the scanning field from 30 degrees to 50 degrees so that the requirement for miniaturization of the system can be satisfied; the main reflector and the auxiliary reflector are respectively provided with a light shield and the edge of the scan reflector perpendicularly extends so that a light shielding board can be formed. Field scanning is conducted through the scan reflector, a zone between the 30-degree airspace and the 80-degree airspace of the zenith can be observed all day, and an instant field of the system is smaller than 30'.

Description

technical field

[0001] The invention belongs to the field of optical design, and relates to an all-weather star tracking system that uses stars as a reference system for navigation and positioning. Background technique

[0002] At present, in the navigation process of aircraft and ships, inertial gyroscope is the most commonly used navigation equipment, which has high instantaneous attitude measurement accuracy, but it drifts greatly under long-term working conditions, and the error accumulates over time, requiring external information sources correct its error. The star sensor uses the position invariance of the stars in the celestial coordinate system to measure the motion parameters of the carrier, and there is no attitude accumulation error. Therefore, the star sensor becomes the best system for correcting the inertial navigation measurement error. Inertial / starlight combined navigation combines starlight navigation and inertial navigation, complementing each other's ad...

Examples

Embodiment Construction

[0039] The invention expects the scanning field of view to be 30° to 80°, and more than 3Mv stars can be observed all day long, and the total length of the system is controlled within 250mm. Due to the need to observe faint targets such as stars during the day, this is an optical system that requires high stray light indicators of the optical system.

[0040] The present invention uses the scanning mirror to scan the field of view, through the rotation of 15°-42.5°, it can observe the area between the zenith 30°-85° airspace, and ensure the total length of the optical system by overlapping the scanning optical path and the imaging optical path , so as to meet the demand for miniaturization. However, this greatly increases the burden on the optical system to suppress stray light. Therefore, it has become a design difficulty in the design of stray light suppression.

[0041] The present invention considers the use of primary and secondary mirror shading covers and scanning mir...

technical field

[0001] The invention belongs to the field of optical design, and relates to an all-weather star tracking system that uses stars as a reference system for navigation and positioning. Background technique

[0002] At present, in the navigation process of aircraft and ships, inertial gyroscope is the most commonly used navigation equipment, which has high instantaneous attitude measurement accuracy, but it drifts greatly under long-term working conditions, and the error accumulates over time, requiring external information sources correct its error. The star sensor uses the position invariance of the stars in the celestial coordinate system to measure the motion parameters of the carrier, and there is no attitude accumulation error. Therefore, the star sensor becomes the best system for correcting the inertial navigation measurement error. Inertial / starlight combined navigation combines starlight navigation and inertial navigation, complementing each other's ad...

Examples

Embodiment Construction

[0039] The invention expects the scanning field of view to be 30° to 80°, and more than 3Mv stars can be observed all day long, and the total length of the system is controlled within 250mm. Due to the need to observe faint targets such as stars during the day, this is an optical system that requires high stray light indicators of the optical system.

[0040] The present invention uses the scanning mirror to scan the field of view, through the rotation of 15°-42.5°, it can observe the area between the zenith 30°-85° airspace, and ensure the total length of the optical system by overlapping the scanning optical path and the imaging optical path , so as to meet the demand for miniaturization. However, this greatly increases the burden on the optical system to suppress stray light. Therefore, it has become a design difficulty in the design of stray light suppression.

[0041] The present invention considers the use of primary and secondary mirror shading covers and scanning mir...

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