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Camera full-light-path image motion measurement system for optical remote sensing satellite

A measurement system and optical remote sensing technology, applied in the field of optical remote sensing satellites, can solve problems such as literature reports of an unseen all-optical path image shift measurement system, and achieve the effects of simplifying coordinate transformation steps, high connection rigidity, and simple composition

Inactive Publication Date: 2018-10-02
BEIJING INST OF SPACECRAFT SYST ENG
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AI Technical Summary

Problems solved by technology

[0004] At present, there are no literature reports on this kind of all-optical path image motion measurement system at home and abroad.

Method used

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  • Camera full-light-path image motion measurement system for optical remote sensing satellite

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Embodiment Construction

[0020] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0021] The vibration of the optical remote sensing satellite camera is divided into the overall camera shake and the micro-vibration of the optical components. The overall camera shake is measured by the external laser displacement meter, and the micro-vibration effect of the optical components is presented through the optical path simulation. The present invention provides an optical remote sensing satellite camera all-optical path image motion measurement system, comprising a camera body 1, a laser position sensor 2, a focal plane receiver 3, a primary mirror 4, a laser displacement meter I5, a tripod I6, data acquisition and Analysis system 7, secondary mirror 8, third mirror 9, two-way inertial vibration sensor 10, laser displacement meter II11 and tripod II12, such as figure 1 shown.

[0022] The two-way inertial vibration sensor 10 can emit a highly...

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Abstract

The invention discloses a camera full-light-path image motion measurement system for an optical remote sensing satellite. The system comprises laser displacement meters, a two-way inertia jitter sensor, a reflecting mirror, a laser position sensor and a data acquisition and analysis system, wherein the two-way inertia jitter sensor is fixed on a main mirror of a camera, the laser position sensor is fixed at a focal plane receiver, the two-way inertia jitter sensor converts vibration gesture change of the main mirror of the camera into a measurable laser signal, the laser signal is reflected bythe reflecting mirror, and a camera imaging full light path is received and simulated by the laser position sensor; two laser displacement meters are used for measuring the displacement change of themain mirror of the camera in a horizontal plane in two different directions, and the laser signals received by the laser position sensor are all transmitted to the data acquisition and analysis system for analysis and calculation, so that a camera full-light-path image motion vector is obtained. The influence of mutual coupling of vibration gestures of optical elements in light paths in the camera can be overcome, and the image motion vector under camera jittering and micro-vibration joint action is obtained accurately.

Description

technical field [0001] The invention relates to the technical field of optical remote sensing satellites, in particular to an all-optical path image motion measurement system for an optical remote sensing satellite camera. Background technique [0002] The payload cameras of optical remote sensing satellites have increasingly longer focal lengths, larger apertures, higher imaging precision, and are more sensitive to micro-vibrations and jitters. When the optical remote sensing satellite is in orbit, the disturbances generated by various moving parts on the star (such as CMG, momentum wheel, solar wing drive mechanism, etc.) work normally, resulting in a small elastic deformation of the structural parameters of the payload camera over time. , and the small reciprocating motion of the overall relatively stable posture over time, the former is called micro-vibration, and the latter is called jitter, which causes abnormal image motion. The imaging condition of the payload is cl...

Claims

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Application Information

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IPC IPC(8): G01C11/02
CPCG01C11/02
Inventor 檀傈锰王光远袁宝峰丁健罗婕殷新喆管帅
Owner BEIJING INST OF SPACECRAFT SYST ENG
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