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Aircraft radar stealth airfoil and production method thereof

A radar stealth and aircraft technology, applied in aircraft, unmanned aircraft, wings, etc., can solve the problems of limited structural space and low bonding force

Inactive Publication Date: 2020-08-14
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical solution of the present invention is to overcome the shortcomings of low bonding force and limited structural space in the existing airfoil stealth technical solution, and provide a new wedge-shaped metal base and coated with unequal thickness absorbing Coating material obtains airfoil with rounded leading edge shape and preparation method thereof

Method used

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  • Aircraft radar stealth airfoil and production method thereof
  • Aircraft radar stealth airfoil and production method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] The shape of the leading edge section of the missile wing is as follows: figure 1 As shown, among them, the radius of the leading edge is 10mm, the wedge width is 25mm, the subsonic naca airfoil is adopted, and the relative thickness of the airfoil is 10%.

[0041] The airfoil is machined as follows:

[0042] (1) Processing metal materials

[0043] Adopt conventional construction technology to complete the processing and molding of the wing surface metal material;

[0044] (2) Processing of absorbing materials

[0045] After grinding and cleaning the surface of the metal material, apply commercially available radar wave-absorbing paint on the front edge of the metal material by spraying or brushing, and make the coating thickness reach or Exceeding the structural design thickness;

[0046] (3) post-processing

[0047] After the coating is cured, the part of the absorbing material that is higher than the designed thickness is polished and modified to ensure a smooth...

Embodiment 2

[0049] The shape of the leading edge section of the missile wing is as follows: figure 2 As shown, the radius of the leading edge is 5mm, the rear end of the wedge surface and the shape of the airfoil transition smoothly, the width of the wave-absorbing material is 30mm, and the subsonic naca airfoil is adopted, and the relative thickness of the airfoil is 10%.

[0050] The airfoil is machined as follows:

[0051] (1) Processing metal materials

[0052] Adopt conventional construction technology to complete the processing and molding of the wing surface metal material;

[0053] (2) Process absorbing material patch

[0054] According to the designed shape, the upper and lower patches consistent with the three-dimensional shape of the application part are prepared in the mold.

[0055] For the convenience of subsequent pasting, the upper and lower patches are prepared as adjacent whole pieces

[0056] (3) Pasting and molding of absorbing materials

[0057]After grinding an...

Embodiment 3

[0059] The shape of the leading edge section of the missile wing is as follows: figure 2 As shown, among them, the leading edge radius is 20mm, the rear end of the wedge surface and the wing shape transition smoothly, the wave-absorbing material paste width is 40mm, the subsonic naca airfoil is adopted, and the relative thickness of the airfoil is 12%.

[0060] The airfoil is machined as follows:

[0061] (1) Processing metal materials

[0062] Adopt conventional construction technology to complete the processing and molding of the wing surface metal material;

[0063] (2) Process absorbing material patch

[0064] According to the designed shape, the upper and lower patches consistent with the three-dimensional shape of the application part are prepared in the mold.

[0065] For the convenience of subsequent pasting, the upper and lower patches are prepared as adjacent whole pieces

[0066] (3) Pasting and molding of absorbing materials

[0067] After grinding and cleani...

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Abstract

The invention belongs to the technical field of radar stealth aircraft design, and particularly relates to a metal base material stealth airfoil component suitable for a subsonic aircraft and a production method thereof. A front edge of the airfoil is composed of a metal material and a wave-absorbing material. The metal material part is in a wedge shape. The wave-absorbing material part is dividedinto an upper part and a lower part which are distributed on two inclined planes of a wedge and are solidified with the wedge into a whole; a thickness of the primary wave-absorbing material close toa peak of the wedge and a bottom of the wedge is small; the thickness of the material near the middle position of the inclined plane of the wedge is large; and the solidified airfoil is smooth in appearance. The front edge of the metal airfoil is produced into a wedge shape, and the outer side of the wedge is coated with a crescent camouflage coating so that a remarkable electromagnetic echo suppression effect in a horizontal direction is realized.

Description

technical field [0001] The invention belongs to the technical field of radar stealth for weapon equipment, and in particular relates to a radar stealth wing surface of an aircraft and a preparation method thereof, which is suitable for a radar stealth wing surface component of a subsonic aircraft and a preparation method thereof. Background technique [0002] The wing is an important electromagnetic radiation part of a missile or military aircraft. In order to reduce the radar echo of the aircraft and better realize the radar stealth of various military aircraft, a certain thickness of radar absorbing coating is usually applied on the outer surface of the wing. material or radar absorbing patch material, this method can achieve a certain stealth effect, but the thickness of this type of material is generally about 1mm, and the conventional application method is generally to apply a wave-absorbing coating material of equal thickness on the leading edge. It is suitable for air...

Claims

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Application Information

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IPC IPC(8): B64C3/00B64C3/14B64C30/00B64F5/10B05D7/14B05D7/24
CPCB64C3/00B64C3/14B64C30/00B64F5/10B05D7/14B05D7/24B64C2003/149B64U20/10
Inventor 张松靖乔治冯国成冷淑香王瑞
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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