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Laser welding method of aircraft metal pressure measuring capillary

A laser welding and capillary technology, which is applied in laser welding equipment, welding equipment, metal processing equipment, etc., can solve the problem of inability to achieve laser welding between the metal pressure measuring capillary and the outer wall of the metal shell of the aircraft, poor welding quality, and low joint strength. Problems, to improve programming efficiency and achieve the effect of large weld depth-to-width ratio and high-temperature strength

Active Publication Date: 2018-07-06
HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the current vacuum brazing process still cannot achieve reliable laser welding between the metal pressure measuring capillary and the outer wall of the aircraft metal shell, the welding quality is poor, and the strength of the joint is low

Method used

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  • Laser welding method of aircraft metal pressure measuring capillary
  • Laser welding method of aircraft metal pressure measuring capillary
  • Laser welding method of aircraft metal pressure measuring capillary

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0066] Embodiment 1 of the present invention is the laser welding method of the metal pressure-measuring capillary of the aircraft. When the parts are processed, the outer wall of the metal shell of the aircraft is designed to measure the aerodynamic pressure. Diameter; the processed metal pressure measuring capillary is inserted into the through hole of the outer wall of the metal shell of the aircraft, and the end surface of the pressure measuring capillary is higher than the surface of the outer wall of the aircraft h=0.1 ~ 0.2mm, such as image 3 shown.

[0067] The welding method of the metal pressure measuring capillary comprises the steps:

[0068] S101: Positioning welding is required before the pressure measuring capillary is welded to the side wall of the metal shell to ensure that the assembly state of the two does not change, and laser dot positioning welding is performed around the pressure measuring tube, such as Figure 4 As shown, the four places 5-1 to 5-4 ar...

Embodiment 2

[0073] Embodiment 2 of the present invention is the laser welding method of the metal pressure-measuring capillary of the aircraft. When the parts are processed, the outer wall of the metal shell of the aircraft is designed to measure the aerodynamic pressure. diameter; the processed metal pressure measuring capillary is inserted into the through hole of the outer wall of the metal shell of the aircraft, and the end surface of the pressure measuring capillary is 0.1-0.2 mm higher than the surface of the outer wall of the aircraft, such as image 3 shown.

[0074] The welding method of the metal pressure measuring capillary comprises the steps:

[0075] S201: Positioning welding is required before the pressure measuring capillary is welded to the side wall of the metal shell to ensure that the assembly state of the two does not change, and laser dot positioning welding is performed around the pressure measuring tube, such as Figure 4 As shown, the four locations of 5-1 to 5-4...

Embodiment 3

[0084] Embodiment 3 of the present invention is the laser welding method of the metal pressure-measuring capillary of the aircraft. When the parts are processed, the outer wall of the metal shell of the aircraft is designed to measure the aerodynamic pressure. diameter; the processed metal pressure measuring capillary is inserted into the through hole of the outer wall of the metal shell of the aircraft, and the end surface of the pressure measuring capillary is 0.1-0.2 mm higher than the surface of the outer wall of the aircraft, such as image 3 shown.

[0085] The welding method of the metal pressure measuring capillary comprises the steps:

[0086] S301: Positioning welding is required before the pressure measuring capillary is welded to the side wall of the metal shell to ensure that the assembly state of the two does not change, and laser dot positioning welding is performed around the pressure measuring tube, such as Figure 4 As shown, the four positions of 5-1 to 5-4...

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Abstract

The invention provides a laser welding method for a metal pressure measuring capillary of an aircraft, wherein the metal pressure measuring capillary is inserted into a through hole on the outer wall of the metal shell of the aircraft; the welding method of the pressure measuring capillary comprises the following steps: Carry out tack welding at the joint of the pressure measuring capillary and the outer wall of the metal shell of the aircraft; perform pulse laser welding at the joint of the pressure measuring capillary and the outer wall of the metal shell of the aircraft, the wall thickness of the pressure measuring capillary is 0.2mm~0.6mm; the parameters of pulsed laser welding include: laser peak power P=250W~700W, pulse frequency f=60~120Hz, duty cycle PWM=10%~30%, welding speed v=0.5~1m / min, spot diameter d is 0.05-0.5mm, defocusing amount ΔF=-0.3mm~+0.3mm. The invention realizes the reliable connection between the pressure-measuring capillary and the outer wall of the metal shell of the aircraft, and ensures the weld penetration, high-temperature strength of the weld, air tightness, pressure-measuring functionality and the accuracy requirements of the aircraft.

Description

technical field [0001] The invention belongs to the field of laser welding of fine structures, and in particular relates to a laser welding method of a metal pressure measuring capillary of an aircraft. Background technique [0002] With the development of aerospace science and technology, the flight speed of aircraft is increasing continuously, and the flutter problem of aircraft caused by aerodynamic pressure has become a hot spot of concern. Flutter is a kind of self-excited vibration of the aircraft under the excitation of aerodynamic force. It is the result of the coupling effect of aerodynamic pressure, aircraft elastic force and inertial force. When the flight speed exceeds the critical speed of flutter, the vibration amplitude and structure The stress increases dramatically and can lead to rapid failure of the vehicle within seconds. Therefore, in order to increase the flight speed and ensure the safety and reliability of the aircraft, it is necessary to analyze and...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B23K26/21B23K26/14B23K26/082
CPCB23K26/082B23K26/14B23K26/21
Inventor 王维新万佩刘巨锋付兴柏张书香杜利丁永宏
Owner HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL
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