High-precision pointing tracking control method for different-plane orbit satellite

A technology for orbiting satellites and pointing tracking, which is applied to space navigation equipment, space navigation vehicles, space vehicle guidance devices, etc., and can solve problems such as the contradiction between integration and system stability margins, and poor PD control accuracy

Active Publication Date: 2020-12-22
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The technical problem to be solved by the present invention is: in the process of satellite pointing control in different plane orbits, the determination of the attitude motion law of the cooperative target, the poor PD control accuracy in the design of the traditional frequency domain controller, and the contradiction between the integral and the system stability margin, Considering the periodicity of the controller output, the uncertainty of the inertia and the disturbance characteristics of the actuator, a non-singular target attitude determination method and a pointing tracking controller design and analysis idea are provided, which can ensure the stability margin in the frequency domain and can be used for different-plane orbits High precision pointing and tracking control of satellite

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  • High-precision pointing tracking control method for different-plane orbit satellite
  • High-precision pointing tracking control method for different-plane orbit satellite
  • High-precision pointing tracking control method for different-plane orbit satellite

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Embodiment Construction

[0138] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0139] Such as figure 1 As shown, a high-precision pointing and tracking control method of a different-plane orbit satellite in the present invention, the specific implementation steps are as follows:

[0140] Step 1: Establish the attitude dynamics and kinematics equations of the rigid satellite, and simplify the transfer function of the dynamic system.

[0141] If the coordinate system OX b Y b Z b Relative reference coordinate system OX a Y a Z a The angular velocity at OX b Y b Z b The component array in is written as ω=[ω x ω y ω z ] T , attitude quaternion Q=[q 0 q 1 q 2 q 3 ] T , the superscript "T" on the right indicates the transpose of the matrix, and q 0 Called the standard part of the quaternion, q=[q 1 q 2 q 3 ] T is called the vector part of the quaternion, then the attitude kinematics equation descr...

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Abstract

The invention relates to a high-precision pointing tracking control method for a different-plane orbit satellite. The method comprises the following steps: step 1, building an attitude dynamics and kinematics equation of a rigid satellite, and giving a transfer function expression; step 2, establishing an attitude and a motion law of a cooperative target according to the orbit information, and analyzing spectral characteristics; and step 3, designing a controller according to a frequency domain control theory, analyzing control precision and giving a parameter design rule. According to the method, aiming at a pointing tracking task of a different-plane track, the universal expected attitude and the motion rule are established, and singularity of operation can be avoided; and inertia errors, actuating mechanism output errors and vibration characteristics are considered, and the designed controller can meet frequency domain indexes and time domain precision indexes and can be widely applied to actual engineering.

Description

technical field [0001] The invention relates to a high-precision pointing and tracking control method for satellites in different-plane orbits. Aiming at the problems of large and fast-changing target attitude and target angular velocity at the moment of orbital intersection of satellites in different-plane orbits, the inertia error, high-frequency vibration of the actuator and Output error, realize high-precision pointing and tracking control, and ensure the stability margin of the system. The invention belongs to the field of spacecraft attitude control. Background technique [0002] With the continuous development of aerospace technology, spacecraft are more and more widely used in military and civilian fields, and the requirements for the precision of spacecraft pointing control are getting higher and higher. In some space missions, such as surveillance, capture and satellite formation, it is necessary for the spacecraft to track the target on different orbits. Due to t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/15B64G1/24G06F119/14
CPCG06F30/20G06F30/15B64G1/244G06F2119/14B64G1/245
Inventor 吴晗金磊
Owner BEIHANG UNIV
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