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Experimental device for testing icing adhesion of wings

An experimental device and adhesion technology, applied in the field of aircraft safety, can solve problems such as disagreement, lack of icing adhesion theory, inconsistent measurement of icing adhesion, etc., and achieve the effect of simple and flexible installation

Inactive Publication Date: 2019-01-15
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing icing adhesion research data show that there is no clear explanation of the icing adhesion theory, and there are differences in the measurement of icing adhesion due to inconsistency

Method used

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  • Experimental device for testing icing adhesion of wings
  • Experimental device for testing icing adhesion of wings
  • Experimental device for testing icing adhesion of wings

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Experimental program
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Effect test

Embodiment Construction

[0023] The present invention will be further described below in conjunction with the accompanying drawings.

[0024] Such as figure 1 As shown, the icing adhesion test device is installed in the ice wind tunnel through the bracket 6, and the closed circuit connection with the ice wind tunnel can be connected through the experimental section box 3. Firstly, the ice wind tunnel is opened, the icing conditions are changed, and the The angle adjustment dial 7 changes the angle of attack when the wing section 8 freezes, and freezes within the freezing time; after the freezing is completed, the handwheel 1 is manually operated, and the screw 2 is rotated to drive the test section box 3 to slide The rod 5 moves in the direction, and the force sensor 4 is used to measure the pressure between the test section box 3 and the bracket 6. When the ice on the wing surface completely falls off, the value measured by the force sensor 4 changes suddenly, and the maximum value F 0 mutation to F...

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Abstract

The invention provides an experimental device for testing the icing adhesion of wings. Components comprises: a box of an experimental section, a sliding rod, a force sensor, a bracket, a lead screw, ahand wheel, an angle-of-attack adjusting plate, a wing section, a wing fixing plate, and a wing fixing shaft. The wing section is installed in the box of the experimental section, and the box of theexperimental section is driven along the sliding rod by the hand wheel and the lead screw. The angle-of-attack adjusting plate can adjust the angle-of-attack of the wing, and the icing condition can be adjusted by connecting the fixed ice wind tunnel to the experiment box bracket. After icing of the wing section in the ice wind tunnel, the device manually loads and moves the experimental section box, and measures the change value of the experimental box to the bracket pressure through a pre-calibrated force sensor to obtain the icing adhesion on the wing surface. The experimental device for testing the icing adhesion of the wing has the characteristics of simple and flexible installation, can be used for the icing adhesion test of aircrafts and helicopter wings, and can meet the needs of measuring the icing adhesion of different structural wings under different icing conditions.

Description

technical field [0001] The invention relates to an experimental device for testing the icing adhesion force of a wing, belonging to the technical field of aircraft safety. Background technique [0002] When an aircraft flies in clouds containing supercooled water droplets, ice may form on the windward surfaces such as wings, tail leading edge, propeller, helicopter rotor blades, engine air intakes, pitot tubes, and windshield. Accumulated ice adheres to the leading edge of the wing, which will reduce the maximum lift coefficient, advance the stall angle of attack, increase the drag of the aircraft, and decrease the lift-to-drag ratio; some tests have shown that when there is 1.3cm of ice accumulating on the leading When , the lift of the aircraft decreases by 50%, and the drag increases by 50%. Therefore, research on wing anti-icing is particularly important. [0003] Due to the continuous development and improvement of the ice wind tunnel, more real and reliable experimen...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N19/04
CPCG01N19/04
Inventor 张以都陈龙吴琼
Owner BEIHANG UNIV
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