Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Aircraft structure static strength PID parameter debugging method

A technology of parameter debugging and aircraft structure, applied in the direction of electric controllers, controllers with specific characteristics, etc., can solve problems such as test piece structure and test equipment safety hazards, load oscillations, etc.

Active Publication Date: 2016-04-27
CHINA AIRPLANT STRENGTH RES INST
View PDF4 Cites 2 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In the prior art, the PID control parameters of the aircraft structure test are mainly obtained by building the test platform through manual trial and error during the test process, so the load may oscillate during the debugging process, causing harm to the structure of the test piece and the safety of the test equipment. lead to potential risks

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Aircraft structure static strength PID parameter debugging method
  • Aircraft structure static strength PID parameter debugging method
  • Aircraft structure static strength PID parameter debugging method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

No PUM Login to View More

Abstract

The present invention discloses an aircraft structure static strength PID parameter debugging method. The method comprises the steps of (1) obtaining the parameters of a spray nozzle baffle plate servo valve in a channel to be debugged and an asymmetric actuating cylinder, (2) establishing the mathematical models of a controller, the spray nozzle baffle plate servo valve and the asymmetric actuating cylinder in the channel to be debugged, (3) carrying out conversion to generate a controller transfer function, a spray nozzle baffle plate servo valve transfer function and an asymmetric actuating cylinder transfer function, (4) coupling the controller transfer function, the spray nozzle baffle plate servo valve transfer function and the asymmetric actuating cylinder transfer function, (5) determining the PID parameter range in the channel to be debugged, (6) judging whether the PID parameter in a Bode diagram is in accordance with a system stability threshold, and if so, ending the debugging. According to the aircraft structure static strength PID parameter debugging method, the installation of a test device is not needed, a test preparation time is saved, and the test cost and risk are reduced.

Description

technical field [0001] The invention relates to the technical field of aircraft structure static strength test, in particular to a PID parameter debugging method for aircraft structure static strength. Background technique [0002] The aircraft structural strength test generally adopts PID control, and the PID control law is proportional, integral, differential (damping) control, that is, according to the deviation of the system, the control adjustment amount is calculated by using the proportional, integral, and differential algorithm to realize the control of the system . [0003] In the prior art, the PID control parameters of the aircraft structure test are mainly obtained by building the test platform through manual trial and error during the test process, so the load may oscillate during the debugging process, causing harm to the structure of the test piece and the safety of the test equipment. lead to potential risks. [0004] Therefore, it is desirable to have a te...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): G05B11/42
CPCG05B11/42
Inventor 赵洪伟路璐米征吝继锋张永兴毛爽
Owner CHINA AIRPLANT STRENGTH RES INST
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com