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Interactive filtering method for satellite attitude determination

A satellite attitude and interactive technology, applied in the field of interactive filtering, can solve problems such as truncation error, complex calculation, and decreased filtering accuracy

Active Publication Date: 2016-02-03
SOUTHEAST UNIV
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Problems solved by technology

Since the gyro constant drift estimation is a nonlinear state-space model, commonly used methods include EKF, UKF, and CKF algorithms, but the EKF algorithm has theoretical limitations: the linearization of the model introduces truncation errors, resulting in a decrease in filtering accuracy. At the same time, it is necessary to calculate Jacobian matrix, computationally complex

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  • Interactive filtering method for satellite attitude determination
  • Interactive filtering method for satellite attitude determination
  • Interactive filtering method for satellite attitude determination

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[0098] Below in conjunction with accompanying drawing and embodiment example the present invention is described in further detail:

[0099]A kind of optimal-REQUEST and CKF interactive filter method that the present invention proposes is used for satellite attitude determination is to carry out simulation experiment by Matlab simulation software, compare with the estimated performance of existing filter algorithm, as QUEST method, variable factor REQUEST method and optimal-REQUEST method. The simulation hardware environment is Intel(R) Core(TM) T9600CPU2.80GHz, 4GRAM, Windows7 operating system. Such as figure 2 with Figure 4 As shown, the estimated error curves of several filtering algorithms when there is no gyro constant value drift and when gyro constant value drift is included. It can be seen from the figure that the QUEST algorithm does not use gyro update, so the estimation error is only related to the measurement of the star sensor. It is related to the error and i...

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Abstract

The invention discloses an interactive filtering method for satellite attitude determination, and aims to overcome the defect that constant gyro drifts cannot be estimated by utilizing the optimal-REQUEST algorithm and improve the algorithm applicability. The method comprises the following steps: step 1, acquiring sensor measurement data, including gyroscope data and star sensor data; step 2, building a state space model of a satellite attitude estimation system, as well as building an attitude K matrix; step 3, according to the state space model, the state estimate of the known moment k, and a gyro measurement value, estimating constant gyro drifts at the moment k+1 by utilizing the CKF algorithm and the optimal quaternion at the moment k, and then compensating the gyro measurement value; step 4, according to the compensated gyro measurement value, carrying out time update and measurement update by utilizing the optimal-REQUEST algorithm, so as to obtain the optimal K matrix at the moment k+1; the remaining steps of obtaining the optimal quaternion at the moment k+1. The interactive filtering method is beneficial to improvement of the estimation precision.

Description

Technical field: [0001] The invention relates to an interactive filtering method for satellite attitude determination, and belongs to the technical field of satellite attitude estimation by using the optimal K matrix method and nonlinear filtering technology. Background technique: [0002] Satellite attitude estimation technology is one of the key technologies of aerospace technology. The satellite attitude estimation system composed of gyroscope and star sensor has been widely used due to its advantages of high attitude measurement accuracy, good reliability and strong autonomy. The K-matrix pose estimation method is a quaternion determination method based on the Wahba problem, which has the advantage of high computational efficiency. On the basis of the QUEST algorithm, ItzhackY.Bar-Itzhack proposed the REQUEST algorithm using gyroscope measurement to update the K matrix, which further improved the estimation accuracy of the QUEST algorithm. However, the REQUEST algorithm ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
Inventor 徐晓苏徐祥王捍兵杨冬瑞田泽鑫邹海军
Owner SOUTHEAST UNIV
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