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EKF filtering algorithm and neural network combined autonomous phase control method

A filtering algorithm and neural network technology, applied in the field of aerospace applications, can solve problems such as satellite attitude interference

Active Publication Date: 2021-11-19
CHANGGUANG SATELLITE TECH CO LTD
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Problems solved by technology

[0007] In order to solve the problem of interference caused by neglecting satellite attitude in the orbit control process in the prior art, the present invention provides an autonomous phase control method combining EKF filter algorithm and neural network

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  • EKF filtering algorithm and neural network combined autonomous phase control method
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  • EKF filtering algorithm and neural network combined autonomous phase control method

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specific Embodiment approach 2

[0113] Specific Embodiment 2. This embodiment is an embodiment of an autonomous phase control method combining an EKF filter algorithm and a neural network described in the specific embodiment 1. Taking a satellite with a chemical propulsion system as an example, the propulsion system Containing 5 thrusters, the effectiveness of the proposed control method is verified by simulation. The maximum control torque is 0.5Nm, and the deviation value and initial trajectory of the propulsion system are shown in Table 1 and Table 2.

[0114] Table 1 Propulsion system deviation

[0115] parameter parameter value geometric mounting deviation θ a =[0.5;0;0;0;0.5]°

Geometric installation deviation azimuth θ ac =[90; 90; 90; 90; 90]°

thrust deviation θ b =[1;1;1;1;1]°

Thrust Deviation Azimuth θ bc =[90; 90; 90; 90; 90]°

centroid offset I mc =[0.01; 0.01; 0.01] mm

[0116] Table 2 Initial orbital parameters

[0117]

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Abstract

The invention discloses an autonomous phase control method combining an EKF algorithm and a neural network, relates to the technical field of aerospace application, and aims to solve the problem of interference caused by the neglect of satellite attitude in an orbit control process in the prior art. According to the control method of the invention, the satellite orbit is determined by using an extended Kalman filtering algorithm, the drift of the satellite phase is calculated through the determined orbit, when the satellite phase drifts out of a set phase threshold value, the adjustment of the attitude of the satellite is started and orbit control is performed, and an orbit control quantity and a control direction on the satellite are autonomously generated in advance. In order to ensure the attitude stability in the orbit control process, an attitude control method based on four obliquely-installed thrusters is provided, and a neural network is adopted to approach disturbance torque. Mathematical simulation results prove that the provided autonomous phase control method is effective and feasible. The method is high in reliability, and high-precision autonomous phase control can be achieved through the design algorithm and scheme.

Description

technical field [0001] The invention relates to the technical field of aerospace applications, in particular to an autonomous phase control method based on a neural network. Spacecraft orbit determination and control, used to realize and optimize satellite orbit control functions. Background technique [0002] Since the phase maintenance of remote sensing satellites is the key technology to meet the needs of ground applications, as the number of satellites increases, the phase control task will become more and more heavy, increasing the pressure on ground operators and ground stations, so autonomous phase control is the solution to this problem effective means. At present, there are few researches and applications on autonomous orbit control of remote sensing satellites. [0003] Prior art 1, Du Yaoke, Yang Shengqing, Complete, Wang Wenyan, Chen Junli. Strict return to orbit-keeping control of near-Earth satellites [J]. Acta Aeronautics Sinica, 2018, 39(12): 334-344. The...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242B64G1/244B64G1/245Y02T90/00
Inventor 王国刚戴路徐开范林东
Owner CHANGGUANG SATELLITE TECH CO LTD