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Autonomous synthetic aperture radar (SAR) satellite orbit determination method based on extended kalman filter

A technology for extending Kalman and autonomous orbit determination, applied in the field of autonomous orbit determination of SAR satellites, which can solve problems such as poor autonomy and real-time performance

Inactive Publication Date: 2012-01-04
HEILONGJIANG PATENT TECH DEV
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Problems solved by technology

[0004] The purpose of the present invention is to provide a method for autonomous orbit determination of SAR satellites based on extended Kalman filtering. The existing satellite autonomous orbit determination technology mainly adopts GPS. Since GPS is a semi-autonomous orbit determination method, there are poor autonomy and real-time performance. The problem

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  • Autonomous synthetic aperture radar (SAR) satellite orbit determination method based on extended kalman filter
  • Autonomous synthetic aperture radar (SAR) satellite orbit determination method based on extended kalman filter
  • Autonomous synthetic aperture radar (SAR) satellite orbit determination method based on extended kalman filter

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specific Embodiment approach 1

[0065] Specific implementation mode one: combine figure 1 Description; The SAR satellite autonomous orbit determination method based on extended Kalman filter of the present embodiment, described method comprises the following steps:

[0066] Step 1: Establish the satellite motion equation based on orbital dynamics, and then obtain the state equation;

[0067] Build contains J 2 The orbital dynamics equation of the satellite, under the J2000 inertial coordinate system, the orbital dynamics equation of the satellite is:

[0068] X · = F [ X ( t ) , t ] - - - ( 1 )

[0069] Written as an equation of state, that is:

[0070] dx dt = ...

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Abstract

The invention discloses an autonomous synthetic aperture radar (SAR) satellite orbit determination method based on an extended kalman filter and belongs to the technical field of autonomous satellite orbit determination. Due to the adoption of a global positioning system (GPS) which adopts a half-autonomous orbit determination mode, the conventional autonomous satellite orbit determination technology has the problems of low autonomy and low instantaneity. By the orbit determination method, the problems can be solved. The method comprises the following steps of: 1, establishing a satellite motion equation based on orbit dynamics so as to obtain a state equation; 2, establishing an observation equation by taking a distance between an SAR and a ground identification point and a Doppler shiftfrom the SAR to the ground identification point as observation values; 3, establishing a recurrence equation of the extended kalman filter; and 4, thus obtaining state information of a satellite to obtain a position and a speed vector of the satellite. By the method, the orbit determination precision of the satellite is improved; the method has the characteristics of autonomy and instantaneity; and high-precision real-time autonomous orbit determination for low-orbit satellites can be realized.

Description

technical field [0001] The invention relates to a method for autonomous orbit determination of SAR satellites, belonging to the technical field of autonomous satellite orbit determination. Background technique [0002] The satellite's autonomous orbit determination refers to the use of the satellite's own measurement components to determine the satellite's position and velocity in the inertial space without the support of the ground system, and realize autonomous orbit determination. For satellites, autonomous orbit determination is beneficial to reduce the dependence of satellites on the ground, especially in a state of war, when the ground system is damaged, it can still maintain normal operation, which is especially important for military satellites; in addition, Autonomous orbit determination can also reduce the burden on the ground system and reduce ground support costs. [0003] The existing satellite autonomous orbit determination technology mainly uses GPS, but GPS ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
Inventor 张迎春汪瑞良李晓磊
Owner HEILONGJIANG PATENT TECH DEV
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