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

Controllable Motion System of Dihedral Angle in Aircraft Wind Tunnel Test Model

A technology of wind tunnel test and motion system, applied in aerodynamic test, machine/structural component test, measuring device, etc.

Active Publication Date: 2017-12-05
中国航空工业空气动力研究院
View PDF5 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the traditional fixed angle piece connection method can no longer meet this demand

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
  • Controllable Motion System of Dihedral Angle in Aircraft Wind Tunnel Test Model
  • Controllable Motion System of Dihedral Angle in Aircraft Wind Tunnel Test Model
  • Controllable Motion System of Dihedral Angle in Aircraft Wind Tunnel Test Model

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] Such as figure 1 As shown, an aircraft wind tunnel test model dihedral dihedral controllable motion system includes fuselage head assembly 1, aircraft model body shaft longitudinal axis 2, left motor and encoder 3, left motor mounting seat 4 , left coupling 5, left front bearing housing 6, left front bearing 7, left wing 8, left wing shaft 9, left wing shaft axis 10, left rear bearing 11, left rear bearing housing 12, left main wing 13, right Motor and encoder 14, right motor mount 15, right coupling 16, right front bearing seat 17, right front bearing 18, right wing 19, right wing shaft 20, right wing shaft axis 21, right rear bearing 22, Right rear bearing seat 23, right main wing 24, computer 25, left motor driver 26 and right motor driver 27, computer 25 is connected with left motor driver 26 and right motor driver 27 electric signals respectively, left motor driver 26 is connected with left motor and encoder 3 electrical signal connection, right motor driver 27 is...

Embodiment 2

[0023] The deflection control commands of the left wing 8 and the right wing 19 can be:

[0024] (1) The stepped deflection control command can realize the stepwise change of the dihedral angle of the side strip, that is, the static adjustment of the dihedral angle, which is used in static tests; The speed runs to the specified position.

[0025] (2) Uniform motion control command, the angular displacement and speed of the motion can be adjusted, which can realize the uniform speed change of the dihedral angle of the side strip, which can be used in the dynamic deflection test to test the dynamic effect of the side strip deflection, that is, to dynamically adjust the dihedral angle. In addition, the beneficial interference of the aerodynamic vortex system of the side wing and the aerodynamic vortex system of the main wing can be obtained, so as to realize active flow control or equivalent to the role of the rudder surface, and improve the aerodynamic characteristics of the air...

Embodiment 3

[0028] The synchronous / asynchronous control instructions of the left wing 8 and the right wing 19 can be:

[0029] 1. The left side wing 8 or the right side wing 19 deflection control command alone, which is used to realize the left side wing 8 or the right side wing 19 individually controllable deflection; the implementation method is to directly send instructions to the left side wing 8 or the right side wing 19 .

[0030] 2. The same-phase synchronous deflection control command of the left wing 8 and the right wing 19 is used to realize the same-phase synchronous controllable deflection of the left wing 8 and the right wing 19; The right wing 19 sends the same command.

[0031] 3. The opposite phase of the left wing 8 and the right wing 19, that is, the 180° phase difference synchronous deflection control command, is used to realize the anti-phase synchronous controllable deflection of the left wing 8 and the right wing 19; its embodiment is Simultaneously send instructio...

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

An aircraft wind tunnel test model side dihedral controllable motion system, including the fuselage head assembly, the longitudinal axis of the aircraft model body shaft system, the left motor and encoder, the left motor mounting seat, the left coupling, the left front Bearing seat, left front bearing, left wing, left wing shaft, left side wing shaft axis, left rear bearing, left rear bearing seat, left main wing, right motor and encoder, right motor mount, right coupling, right front Bearing housing, right front bearing, right wing, right wing shaft, right wing shaft axis, right rear bearing, right rear bearing seat, right main wing, computer, left motor driver and right motor driver, right wing and right wing The shaft is fixed, the left motor and encoder drive the left wing to deflect along the axis of the left wing shaft; the right motor and encoder drive the right wing to deflect along the axis of the right wing shaft; the system has a stable structure and can realize dihedral of the side wing Dynamic changes can also control the motion parameters of the dihedral angle of the side strip.

Description

technical field [0001] The invention relates to an anhedral angle controllable motion system of an aircraft wind tunnel test model side strip wing. Background technique [0002] In traditional aircraft design, the slat wing is a fixed component that is relatively fixed to the aircraft. In the layout selection, in order to determine the relative relationship between the slat wing and the aircraft, some fixed angle pieces are designed in the wind tunnel test simulation , used to fix and connect the side strips and the aircraft model, these corner pieces can only achieve the angle of the existing design, and cannot be continuously adjusted or dynamically changed. [0003] With the improvement of aircraft layout technology, new usage requirements are put forward for the wing: in some cases, the angle of the wing needs to change continuously to achieve static control; to rudder surface action or active flow control action. Therefore, the traditional connection method of fixed a...

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): G01M9/08
Inventor 刘国政金沙于金革多勐明强王铭威
Owner 中国航空工业空气动力研究院
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