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Method for determining spatial attitude accuracy of satellite

A space attitude and precision technology, applied in directions such as navigation through velocity/acceleration measurement, can solve problems such as little understanding of the internal influence relationship

Inactive Publication Date: 2012-08-08
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

Therefore, little is known about the internal influence relationship between sensor performance and attitude determination accuracy, and it cannot provide theoretical guidance for actively selecting star sensors with appropriate performance according to different mission requirements

Method used

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  • Method for determining spatial attitude accuracy of satellite
  • Method for determining spatial attitude accuracy of satellite
  • Method for determining spatial attitude accuracy of satellite

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] Step 1: Determine the influence function of gyroscope measurement accuracy on EKF attitude determination accuracy.

[0023] 1.1 Analyze the influence function form of gyroscope measurement accuracy on EKF attitude determination accuracy.

[0024] It is realized by analyzing the influence of process noise covariance matrix Q composed of gyroscope measurement noise on estimation error covariance matrix P(k / k). According to the established EKF attitude determination system equation, the state variables at each moment and the solution formula of the estimated error covariance matrix can be obtained by using the classic EKF algorithm. Due to the focus on the impact on the satellite attitude estimation accuracy, the trace of the first three-dimensional sub-matrix of the covariance matrix P(k / k) is used as a measure of the attitude estimation accuracy, and the first three-dimensional sub-matrix of the matrix M is Find the trace of the first three-dimensional sub-matrix of th...

Embodiment 2

[0061] The sensor parameters of the satellite configuration in the experiment are selected as follows:

[0062] (1) Gyro parameters are taken as: relative drift initial value: d(0)=[0.1, 0.1, 0.1] T deg / h; related time constant: 1h; gyro constant value drift: b=[1, -1, 1] T deg / h.

[0063] (2) The sampling frequency of the star sensor is 1Hz; the installation direction of the optical axis of the star sensor is consistent with the directions of the three main axes of the system.

[0064] Step 1: Determine the influence function of gyroscope measurement accuracy on EKF attitude determination accuracy.

[0065] When the measurement accuracy of the star sensor is given, for example, the measurement accuracy of the star sensor is 10″ (3σ), and only the influence of the gyro measurement accuracy change on the EKF attitude determination accuracy is considered, the gyro measurement accuracy is 0.01° / h to 0.2° / h Experiments are carried out at different experimental points between ...

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Abstract

The invention discloses a method for determining the spatial attitude accuracy of a satellite, which comprises a step of constructing a state equation and a measurement equation of an EKF attitude determination system according to the measurement equation for establishing a star sensor and a gyro in the conventional star sensor / gyro attitude determination system. The method is characterized by further comprising the following steps: (1) determining an influence function of the gyro measurement accuracy to the EKF attitude determination accuracy; (2) determining an influence function of the star sensor measurement accuracy to the EKF attitude determination accuracy; (3) determining a response function between the star sensor and the gyro measurement accuracies and the EKF attitude determination accuracy; and (4) directly calculating the EKF attitude determination accuracy by using an index of the sensor measurement accuracy. By determining the response function between the sensor measurement accuracy and the EKF attitude determination accuracy in the attitude determination system consisting of the star sensor and the gyro, the method definitely provides an influence rule of the sensor measurement accuracy to the EKF attitude determination accuracy, and lays a foundation for achieving the active guidance of engineering application.

Description

technical field [0001] The present invention relates to a method for determining satellite attitude accuracy, specifically, in a star sensor / gyroscope attitude determination system, by using the established response function between the sensor measurement accuracy and attitude determination accuracy, the accuracy of satellite attitude can be determined Determine the method. Background technique [0002] The spatial orientation of a satellite during its in-orbit operation is the prerequisite for satellite attitude control, and it provides technical support for applications such as communication, earth observation, and high-resolution imaging, and has important military and civil application values. Satellite attitude determination should be realized from two aspects of hardware measurement and software calculation. In terms of hardware, the current joint attitude determination system composed of star sensors and gyroscopes is the main attitude determination method for modern...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/18
Inventor 矫媛媛周海银王炯琦杨俊才潘晓刚段晓君刘洋郭雪姣
Owner NAT UNIV OF DEFENSE TECH
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