Star sensor installation error matrix and navigation system star-earth combined calibration and correction method

A technology for installing error matrix and star sensor, which is applied in the field of star sensor installation error matrix and satellite-ground joint calibration and correction of navigation system, and can solve the problem of incapable of star sensor installation matrix and navigation system deviation calibration and correction, inability to star sensitivity Problems such as the calibration of the error of the installation matrix of the device

Active Publication Date: 2015-07-22
HARBIN INST OF TECH
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Problems solved by technology

[0005] The purpose of the present invention is to solve the problem that the existing star sensor calibration method cannot complete the calibration of the error of the installation matrix of the star sensor, and cannot regularly calibrate and correct the installation matrix of the star sensor and the deviation of the navigation system, and proposes A method of star sensor installation error matrix and navigation system star-ground joint calibration and correction

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  • Star sensor installation error matrix and navigation system star-earth combined calibration and correction method
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specific Embodiment approach 1

[0040] Specific implementation mode one: combine figure 1 To illustrate this embodiment, a method for joint calibration and correction of star sensor installation error matrix and navigation system star-earth is specifically carried out according to the following steps:

[0041] A method for joint calibration and correction of star sensor installation error matrix and navigation system star-ground is carried out according to the following steps:

[0042] Step 1: Establish M ground measurement receiving stations on the fixed space coordinates under the satellite sub-satellite point trajectory, and the satellite transmits laser information to the M established ground measurement receiving stations. The laser information includes satellite attitude information θ t,m and orbital parameter information X t,m Data, M is a positive integer;

[0043] The establishment of the ground survey receiving station, according to figure 1 It can be seen that the ground measurement receiving...

specific Embodiment approach 2

[0064] Specific embodiment two: the difference between this embodiment and specific embodiment one is that: the ground measurement receiving station in the step two uses the optical measurement equipment whose precision is higher than the precision of the star sensor to measure the satellite attitude information θ in the step one t,m and orbital parameter information X t,m Carry out measurements to obtain the satellite attitude information θ measured by the ground measurement receiving station t,m and the orbit parameter information X measured by the ground survey receiving station t,m , and establish the satellite attitude information measurement model and the orbit parameter information measurement model; the specific process is:

[0065] (1) Establishment of satellite attitude information measurement model

[0066] combine figure 2 , image 3 and Figure 4 , the two oblique lines are the planes where the two photosensors are located, and the normal vectors of the two ...

specific Embodiment approach 3

[0095] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is: in the described step 3, utilize the multi-vector attitude determination method in combination with the satellite attitude information measurement model obtained in the step 2, calculate and determine by the ground measurement receiving station The estimated value of the satellite attitude information of Using the satellite orbit dynamics model, combined with the filtering method to calculate the estimated value of the orbit parameter information determined by the ground measurement receiving station Estimates of satellite attitude information to be determined by ground survey receiving stations and orbit parameter information estimates determined by ground survey receiving stations storage; the specific process is:

[0096] (1) The multi-vector attitude determination method combines the satellite attitude information θ measured in step 2 t,m The data to deter...

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Abstract

The invention relates to a star sensor installation error matrix and navigation system star-earth combined calibration and correction method, and aims at solving the problem that a conventional star sensor calibration method cannot preferably complete the calibration of an installation error matrix of a star sensor and cannot calibrate and correct the star sensor installation error matrix and navigation system deviation at regular intervals. The method is realized according to the following steps: (1) acquiring information theta<t,m> and X<t,m>; (2) establishing an attitude information and orbital parameter information measurement model; (3) determining values shown in the specification; (4) calculating values shown in the specification; (5) solving an arithmetic mean value; (6) establishing a practical attitude installation matrix and orbital parameter information correction model of the star sensor; (7) determining the direction of delta theta; (8) correcting the (6); (9) determining the attitude and the orbital parameter information; and (10) rerunning every N attitudes. The star sensor installation error matrix and navigation system star-earth combined calibration and correction method is applied to the field of satellite attitude determination technology and satellite navigation technology.

Description

technical field [0001] The invention relates to a method for joint calibration and correction of a star sensor installation error matrix and a navigation system. Background technique [0002] In recent years, starlight astronomical navigation systems represented by star sensors have been widely used in aviation, aerospace and other fields due to their good concealment, high precision, and no attitude accumulation error. The star sensor is a high-precision astronomical sensor, and its measurement accuracy can reach arcsecond level. [0003] When the star sensor is applied on the satellite, due to the influence of space environment and other factors, there are some errors in the measurement value, among which the most influential one is the error of the installation matrix, which can reach angle classification or even angle level. The error of the installation matrix is ​​mainly due to the influence of factors such as satellite vibration and space environment during the launc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 李敏耿云海张迎春陈雪芹李化义谢成清盛靖
Owner HARBIN INST OF TECH
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