Multi-point imaging rapid maneuvering control method for low-orbit optical remote sensing satellite

A technology of optical remote sensing and satellite, applied in the field of aerospace

Active Publication Date: 2021-03-09
CHANGGUANG SATELLITE TECH CO LTD
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Problems solved by technology

The above methods fail to achieve high-precision and fast maneuvering control of optical remote sensing satellites under the condition that the satellite reaction flywheel torque and angular momentum are limited

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  • Multi-point imaging rapid maneuvering control method for low-orbit optical remote sensing satellite
  • Multi-point imaging rapid maneuvering control method for low-orbit optical remote sensing satellite
  • Multi-point imaging rapid maneuvering control method for low-orbit optical remote sensing satellite

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Embodiment Construction

[0054] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0055] A low-orbit optical remote sensing satellite multi-point imaging fast maneuvering control method, the method includes the following steps:

[0056] Step 1: Carry out kinematic dynamics modeling for low-orbit optical remote sensing satellites: define F I Indicates the inertial coordinate system, F B Indicates the satellite body coordinate system; the satellite body coordinate system F B Relative to the inertial coordinate system F I The angular velocity is expressed as body coordinate system F B Relative inertial coordinate system F I The pose of is represented as a unit quaternion and satisfy the constraints where q 0 is the scalar part of the quaternion Q, q=(q 1 ,q 2 ,q 3 ) is the vector part of the quaternion Q, Represents an n-dimensional real vector space, and the kinematics and dynamics equations of the satellite a...

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Abstract

The invention discloses a multi-point imaging rapid maneuvering control method for a low-orbit optical remote sensing satellite, belongs to the technical field of aerospace, and aims to control the attitude of the satellite to an expected value in the shortest time under the condition that the reaction flywheel moment of the satellite and the angular momentum of the satellite are limited, so thatan optical load has an imaging state. The method comprises the following steps: carrying out kinematics and dynamics modeling on a low-orbit optical remote sensing satellite; carrying out satellite attitude planning; converting the attitude planning result from an orbit coordinate system to an inertial coordinate system; establishing a satellite error kinematics kinetic equation in combination with attitude planning information; dividing the attitude of the satellite into an inner loop and an outer loop, establishing a controller, and realizing multi-point imaging rapid maneuvering control ofthe low-orbit optical remote sensing satellite. The method has both attitude maneuver rapidity and high-precision attitude stability, in the attitude maneuver process, the satellite attitude can stably converge to the planned attitude, and the control method is simple in structure, easy to implement and capable of being applied to engineering practice.

Description

technical field [0001] This patent belongs to the field of aerospace technology, and specifically relates to a fast maneuvering control method for multi-point imaging of low-orbit optical remote sensing satellites. Background technique [0002] With the rapid development of the low-orbit satellite constellation industry, low-orbit optical remote sensing satellites have become the backbone of the remote sensing information industry due to their high-quality, wide-ranging imaging capabilities. The maneuverability and stability of the satellite attitude control system directly affect the imaging time and quality of the satellite, and are one of the important indicators of the optical remote sensing satellite system. In the field of satellite control engineering, the stability and rapidity of the system are contradictory, and the general control method is difficult to achieve both. Therefore, it is of great significance to study the fast maneuvering control method of multi-poin...

Claims

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Application Information

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IPC IPC(8): B64G1/28
CPCB64G1/285
Inventor 曲友阳刘萌萌李峰童鑫戴路
Owner CHANGGUANG SATELLITE TECH CO LTD
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