Attitude standard deviation estimation and correction method of star sensor and payload

Abstract

The invention discloses an attitude standard deviation estimation and correction method of a star sensor and a payload. The attitude standard deviation estimation and correction method comprises the following steps of 1, according to payload characteristics, determining a location formula of an incident light vector of a payload and building a payload error model with payload standard deviation, 2, according to star sensor characteristics, building a star sensor error model with star sensor standard deviation, 3, through the payload, determining measured deviation by observation data of a known target and corresponding star sensor measured data, and building a payload and star sensor standard deviation measurement equation according to the measured deviation, the payload standard deviation and the star sensor standard deviation, 4, carrying out estimation of the star sensor or payload standard deviation according to the payload and star sensor standard deviation measurement equation, and 5, correcting the star sensor or payload measured data by the estimated standard deviation. The attitude standard deviation estimation and correction method can reduce star sensor and imaging payload attitude standard deviation and improve imaging quality and an image positioning precision.

Description

technical field [0001] The invention relates to a calibration method of an attitude measurement reference of a high-precision remote sensing satellite. Background technique [0002] In order to observe the ground or other targets and obtain remote sensing images, remote sensing satellites are equipped with payloads such as cameras, and the precise registration and positioning of the obtained images is the key to ensuring the quality of image products, and its performance directly reflects the quality of a country's aerospace Capabilities and levels of remote sensing applications. [0003] Due to different observation purposes, imaging mechanisms or technical approaches, there are remote sensing payloads in which all components are fixed relative to the satellite, and remote sensing payloads that use moving parts such as pendulum mirrors for scanning and imaging. From the perspective of attitude reference calibration, the scanning imaging payload of the swinging mirror is mo...

AI Technical Summary

Problems solved by technology

From the perspective of attitude reference calibration, the scanning imaging payload of the swinging mirror is more complex, and there are errors in scanning angle measurement and deformation of the swinging mirror with temperature

At present, the star sensor is the standard configuration of the high-precision observation satellite attitude measurement system, and it is the key component to determine the orientation and position of the image. However, the star sensor has a slow-varying error due to the influence of temperature and the spatial change of the field of view.

In addition, there are thermal variations in the mounting structure between the star sensor and the payload

Three factors lead to slow-varying deviations in the attitude references of the star sensor and the payload, making it difficult for high-precision image registration and positioning

Patent CN201110291301 "A Star Sensor Low-Frequency Error Compensation Method Based on Landmark Information", uses the payload to calibrate the low-frequency error of the star sensor based on the observation information of known landmarks. This method represents the mainstream direction of star sensor calibration , since it does not involve the deformation of the payload itself and the influence of the benchmark after the movement of the pendulum mirror, if it is applied to a satellite with a pendulum mirror scanning imaging payload, the impact of the change of the payload benchmark cannot be evaluated, and the calibration accuracy cannot be guaranteed

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