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An Event-Driven Satellite Attitude Control Method

A satellite attitude control and event-driven technology, applied in the field of satellite attitude control, can solve the problems of wasting available resources, increasing the load pressure of data transmission, etc., and achieve the effect of realizing efficient utilization, reducing the number of data packets, and ensuring control performance

Active Publication Date: 2020-07-24
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve unnecessary data transmission in the existing time-driven control method. Due to the limited resources of communication and information transmission, redundant data packet transmission will increase the load pressure of data transmission and waste limited available resources. problem, and propose an event-driven satellite attitude control method

Method used

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  • An Event-Driven Satellite Attitude Control Method
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  • An Event-Driven Satellite Attitude Control Method

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Experimental program
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specific Embodiment approach 1

[0023] Specific implementation mode one: a kind of event-driven satellite attitude control method based on the present implementation mode, the specific process is:

[0024] Step 1: Establish the satellite attitude dynamic behavior (satellite rotation process) as a flexible arm model, conduct theoretical analysis on the flexible arm model, and obtain the state space equation of the flexible arm model;

[0025] Step 2: Design hybrid event-driven conditions based on the state-space equation of the flexible arm model;

[0026] Step 3: Based on the mixed event-driven conditions, using the Lyapunov (Lyapunov) stability theory, obtain the conditions to ensure the passivity of the flexible arm model;

[0027] Step 4: Based on the passivity conditions obtained in Step 3, design the controller criterion of the flexible arm model.

specific Embodiment approach 2

[0028] Specific embodiment two: the difference between this embodiment and specific embodiment one is that in the step one, the satellite attitude dynamic behavior (satellite rotation process) is established as a flexible arm model, and the flexible arm model is theoretically analyzed to obtain the flexible arm The state space equation of the model; the specific process is:

[0029] The flexible deformation of the flexible arm is:

[0030]

[0031] Among them, w(x,t) is the elastic deformation of the flexible beam relative to the OXY coordinate system, n in the formula (1) represents the decomposition of the elastic deformation w(x,t) into n vibrations with different frequencies, the so-called n-order mode, n is the number of elastic deformation modes, and the value is a positive integer, is the mode shape function corresponding to the ith mode determined according to the boundary conditions of the flexible beam, q i (t) is the modal coordinate corresponding to the i-th ...

specific Embodiment approach 3

[0063] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is: J, M in the formula 8 θq , M qq 、K qq The expression of is as follows:

[0064]

[0065]

[0066]

[0067]

[0068] The formula 10 in The expression is:

[0069] in

[0070]

[0071]

[0072]

[0073] Other steps and parameters are the same as those in Embodiment 1 or Embodiment 2.

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Abstract

The invention provides a satellite attitude control method based on event driving, and relates to a satellite attitude control system model. The satellite attitude control method aims to settle problems of unnecessary data transmission, data transmission load pressure increase caused by redundant data packet transmission because of limited resources for communication and information transmission,and wastage of the limited available resource in an existing time driven control method. The satellite attitude control method comprises the steps of 1, establishing a flexible arm model based on satellite attitude dynamics behavior, performing theoretical analysis on the flexible arm model, and obtaining a state space equation of the flexible arm model; 2, designing a hybrid event driving condition based on the state space equation of the flexible arm model; 3, based on the hybrid event driving condition, through utilizing a Lyapunov stability theory, obtaining a condition for ensuring passivity of the flexible arm model; and 4, designing a controller principle of the flexible arm model based on a passive condition. The satellite attitude control method is used for the field of satelliteattitude controlling.

Description

technical field [0001] The invention relates to a satellite attitude control method. Background technique [0002] Since the mid-20th century, artificial satellites have been used more and more: exploration satellites can survey terrain; weather satellites can detect cloud patterns and observe wind direction and speed; spy satellites can gather military intelligence; experimental satellites can help scientists do many things in space. Experiments that cannot be completed on the earth, and the posture and alignment of satellites after in-orbit service are very important to complete the corresponding tasks, and also play a decisive role in their own life and use. Attitude control is a method to achieve attitude stability by using the dynamic characteristics of the satellite itself and the environmental moment. Since the ground does not have the conditions to simulate the actual operating environment of satellites, the simulation of satellite attitude control problems using ma...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
Inventor 费中阳关朝旭杨宪强史爽郭捷
Owner HARBIN INST OF TECH
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