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Aircraft wind tunnel test model side strip wing/canard pitch angle controllable motion system

A wind tunnel test, slatted wing technology, used in aerodynamic tests, machine/structural component testing, control using feedback, etc., to achieve the effect of rudder surface action or active flow control

Active Publication Date: 2017-04-12
中国航空工业空气动力研究院
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  • 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

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  • Aircraft wind tunnel test model side strip wing/canard pitch angle controllable motion system
  • Aircraft wind tunnel test model side strip wing/canard pitch angle controllable motion system
  • Aircraft wind tunnel test model side strip wing/canard pitch angle controllable motion system

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] like figure 1 As shown, an aircraft wind tunnel test model side strip wing / canard pitch angle controllable motion system includes a fuselage head assembly 1, an aircraft model body shaft system longitudinal axis 2, a first left locking screw 3, a left connecting Shaft 4, left wing / canard 5, left wing / canard rotating shaft 6, left bearing 8, left bearing seat 9, second left locking screw 10, left reversing bevel gear pair 11, third left locking Screw 12, left motor mounting seat 13, left motor and encoder 14, left main wing 15, first right locking screw 16, right connecting shaft 17, right strip wing / canard wing 18, right strip wing / canard wing shaft 19, Right bearing 21, right bearing seat 22, right motor mount 23, right motor and encoder 24, third right locking screw 25, right reversing bevel gear pair 26, second right locking screw 27, right main wing 28, Computer 29, left motor driver 30 and right motor driver 31; Left main wing 15, right main wing 28, left bearing ...

Embodiment 2

[0026] There are three methods for the deflection control commands of the left and right side bars:

[0027] (1) The stepped deflection control command can realize the stepwise change of the pitch angle of the side strip wing / canard wing, that is, the static adjustment of the pitch angle angle, which is used for static tests;

[0028] (2) Uniform speed motion control command, which can adjust the displacement and speed of the movement, and can realize the uniform speed change of the pitch angle of the wing / canard, which can be used in the dynamic deflection test to test the dynamic effect of the deflection of the side strip, that is, to dynamically adjust the pitch In addition, the beneficial interference of the aerodynamic vortex system of the side wing / canard wing and the aerodynamic vortex system of the main wing can be obtained, thereby realizing active flow control or equivalent to the role of the rudder surface, and improving the aerodynamic characteristics of the aircraf...

Embodiment 3

[0031] There are five methods of synchronous / asynchronous control commands for the left wing / canard 5 and the right wing / canard 18:

[0032] (1) Left wing / canard 5 or right wing / canard 18 individual deflection control command, used to realize the left wing / canard 5 or right wing / canard 18 individually controllable deflection;

[0033] (2) The same-phase synchronous deflection control command of the left wing / canard 5 and the right wing / canard 18 is used to realize the same-phase synchronous controllable control of the left wing / canard 5 and the right wing / canard 18 deflection;

[0034] (3) The opposite phase of the left wing / canard 5 and the right wing / canard 18, that is, the 180° phase difference synchronous deflection control command, is used to realize the left wing / canard 5 and the right wing / canard 18 The anti-phase synchronous controllable deflection of ;

[0035] (4) Any phase difference synchronous deflection control command of the left strip / canard 5 and the right s...

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PUM

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Abstract

The invention discloses a controllable strake wing / canard wing pitching angle movement system of an airplane wind tunnel test model. The controllable strake wing / canard wing pitching angle movement system comprises a headpiece and frame component, an airplane model shafting vertical axis, left and right connecting shafts, left and right strake wings / canard wings as well as rotary shafts thereof, left and right bearings, left and right bearing seats, left and right reversing bevel gear pairs, left and right motor installation bases, left and right motors and a coder, left and right main wings, a computer and left and right motor drivers, wherein the right strake wing / canard wing is fixed with the right strake wing / canard wing rotary shaft, the right strake wing / canard wing rotary shaft is connected with the right end of the right connecting shaft, the left end of the right connecting shaft is connected with lower gears of the right reversing bevel gear pair, the same connecting mode is adopted at the left side; the left strake wing / canard wing rotary shaft axis and the right strake wing / canard wing rotary shaft axis are symmetrically arranged along longitudinal symmetrical surfaces of the airplane model shafting vertical axis. The controllable strake wing / canard wing pitching angle movement system can be used for realizing controllable yaw motion of the strake wing / canard wing pitching angle, and changing the mode of regulating the strake wing / canard wing pitching angle through a fixed angle plate in a static mode in the conventional wind tunnel test.

Description

technical field [0001] The invention relates to an aircraft wind tunnel test model side strip wing / canard wing pitch angle controllable motion system. 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 wing and the aircraft model, but these corner pieces can only achieve the angle of the existing design, and cannot be continuously adjusted or dynamically changed. [0003] In traditional aircraft design, the canard is a control surface. In the wind tunnel test simulation, some fixed angle pieces are designed to fix and connect the canard and the aircraft model. These angle pieces can only realize the angle of the existing design, and cannot be continuously adjusted or dynamical...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D3/12G01M9/02
Inventor 刘国政明强于金革多勐金沙张伟
Owner 中国航空工业空气动力研究院
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