A high-precision pointing and tracking control method for satellites in different-plane orbits

An orbiting satellite, pointing and tracking technology, which is applied to space navigation equipment, space navigation aircraft, space navigation vehicle guidance devices, etc. Application value, guaranteed stability margin, easy engineering effect

Active Publication Date: 2022-08-02
BEIHANG UNIV
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  • Abstract
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  • Claims
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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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  • A high-precision pointing and tracking control method for satellites in different-plane orbits
  • A high-precision pointing and tracking control method for satellites in different-plane orbits
  • A high-precision pointing and tracking control method for satellites in different-plane orbits

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Embodiment Construction

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

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

[0140] Step 1: Establish the attitude dynamics and kinematic equations of the rigid body 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 in OX b Y b Z b The component array in is written as ω=[ω x ω y ω z ] T , the attitude quaternion Q=[q 0 q 1 q 2 q 3 ] T , the superscript "T" on the right represents the transpose of the matrix, q 0 Called the subscript of the quaternion, q=[q 1 q 2 q 3 ] T is called the vector part of the quaternion, then the attit...

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Abstract

The invention relates to a high-precision pointing and tracking control method for satellites in different-plane orbits. The attitude of the target and its motion law, analyze the spectrum characteristics; 3. Design the controller according to the frequency domain control theory, analyze the control accuracy and give the parameter design law. Aiming at the pointing and tracking task of different-plane orbits, the invention establishes a general desired attitude and motion law, and can avoid the singularity of the operation; considering the inertia error, the output error of the actuator and the vibration characteristics, the designed controller can meet the frequency domain index and The time domain accuracy index can be widely used in practical 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 amplitude and rapid change of target attitude and target angular velocity at the moment when the orbits of satellites in different-plane orbits meet, the inertia error, the high-frequency vibration of the actuator and the Output error, realize high-precision pointing 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, the application of spacecraft in the military and civilian fields has become more and more extensive, and the requirements for the accuracy of spacecraft pointing control have become higher and higher. In some space missions such as surveillance, capture and satellite formation, it is necessary for the spacecraft to point a...

Claims

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Application Information

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Patent Type & Authority Patents(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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