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Camera attitude determination method and system

A camera attitude and determination method technology, which is applied in image data processing, special data processing applications, instruments, etc., can solve the problems of inaccurate determination of camera attitude, inaccurate determination of satellite body attitude, and inability to meet application scenarios, and achieves improved determination. Accuracy, Effect of Increased Measurement Capability

Pending Publication Date: 2022-01-18
CHINA ACADEMY OF SPACE TECHNOLOGY
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AI Technical Summary

Problems solved by technology

The above-mentioned direct use of star sensor installation matrix and camera installation matrix will lead to inaccurate determination of satellite body attitude and inaccurate determination of camera attitude. Required application scenarios
[0006] With the successful development of the on-orbit real-time measurement device for the installation angle of the star sensor and the camera installation angle, it makes up for the fact that the on-orbit installation matrix of the star sensor and the camera cannot be obtained directly. A camera attitude determination method based on joint processing of star sensor installation angle and camera installation angle measurement data, realizing direct determination of satellite camera attitude

Method used

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  • Camera attitude determination method and system
  • Camera attitude determination method and system

Examples

Experimental program
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Effect test

Embodiment 1

[0046] to combine figure 1 , the camera pose determination method steps are as follows:

[0047] Step 1: Obtain on-orbit real-time measurement data of the star sensor, gyroscope, star sensor installation angle, and camera installation angle. Among them, the quaternions measured by star sensor 1 and star sensor 2 are Q_STS1 and Q_STS2; the measured value of gyro angular velocity is wm; the three-axis installation angle variation of star sensor 1, star sensor 2 and camera is deltaphi_sts1, deltaphi_sts2, deltaphi_cm , both are 3D vectors.

[0048] Step 2: Star sensor, gyroscope, star sensor installation angle, camera installation angle data preprocessing. Fits a linear function and takes data at synchronized time points as the result.

[0049] Step 3: Calculate the star sensor 1 measurement coordinate system optical axis pointing to r_sts1 in the inertial space coordinate system. And the optical axis of the measurement coordinate system of the star sensor 2 under the calcula...

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Abstract

The invention discloses a camera attitude determination method based on combined processing of in-orbit real-time measurement data of a star sensor, a gyroscope, a star sensor mounting angle and a camera mounting angle. The method comprises the following steps: introducing the real-time measurement data of the star sensor mounting angle, and improving a satellite body attitude determination method; introducing real-time measurement data of a camera mounting angle, and providing a direct determination method of a satellite camera attitude. The invention provides a preprocessing and using method of star sensor installation angle measurement data and camera installation angle measurement data, and the determination precision of the satellite body attitude and the camera attitude is improved. On the basis of using the star sensor and the gyroscope, the mounting angle measuring capability of the star sensor and the camera is increased, and the high-precision attitude determination of the satellite body attitude or the satellite camera attitude is completed.

Description

technical field [0001] The invention relates to a method and a system for determining camera attitude. Background technique [0002] The attitude determination method of the satellite body is often obtained by joint filtering of the observation data of the star sensor and the gyroscope. The method for determining the attitude of the satellite camera is based on the determined result of the attitude of the satellite body, and uses the installation matrix of the camera measurement coordinate system relative to the coordinate system of the satellite body to obtain the camera attitude quaternion or attitude matrix. [0003] The result measured by the star sensor is the attitude quaternion of the star sensor measurement coordinate system relative to the inertial coordinate system. Using the star sensor to measure the installation matrix of the coordinate system relative to the satellite body coordinate system, the attitude quaternion or attitude matrix of the satellite body syst...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06T7/73G06F30/20G06F119/14
CPCG06T7/73G06F30/20G06F2119/14
Inventor 景泉陈曦郭倩蕊赵利民刘希刚李少辉高洪涛
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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