Composite wing with integral fuel tank
A technology of composite materials and integrated fuel tanks, which is applied in the directions of wings, aircraft parts, transportation and packaging, etc., and can solve the problems of lightning protection and electrical lapping of composite wings, and easy oil leakage.
Pending Publication Date: 2022-04-01
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0002] Composite materials have the advantages of high specific strength and good fatigue performance, and are used more and more in aircraft. However, the connection of composite materials is generally a clearance fit. The lightning protection and electrical lap of the wing are also difficult to solve
Method used
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[0056] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.
[0057] as attached figure 1 As shown, the composite wing 100 provided by the present application with an integral fuel tank is mainly composed of a wing box section 10 , a flap 20 , an aileron 30 and a wingtip 40 .
[0058] Such as Figure 2 to Figure 11 As shown, the wing box section 10 includes a front beam 111, a rear beam 112, a short beam 14 of the landing gear, a plurality of ribs 131-138, a leading edge diaphragm 121, a trailing edge diaphragm 122, an inner flap support arm 151 and an outer Flap arm 152 , inner aileron arm 161 and outer aileron arm 162 , pitot tube 17 , electrical lap path 18 , upper wall plate 191 , and lower wall plate 192 .
[0059] The front beam 111 and the rear beam 112 extend...
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The invention provides a composite material wing with an integral fuel tank, which comprises a wing box section, a flap, an aileron and a wingtip, wherein the wing box section comprises a front beam, a rear beam, an undercarriage short beam, a plurality of wing ribs, a front edge partition plate, a rear edge partition plate, an inner flap support arm, an outer flap support arm, an inner aileron support arm, an outer aileron support arm, an airspeed tube, an electric lap joint path, an upper wall plate and a lower wall plate; the front beam and the rear beam extend in the wingspan direction, and the wing ribs are arranged between the front beam and the rear beam and are vertically arranged; the front edge partition plate and the rear edge partition plate are arranged on the front side of the front beam and the rear side of the rear beam respectively and form a pneumatic plane supporting structure of the wing together with the wing ribs. The upper wall plate and the lower wall plate are laid on a pneumatic plane supporting structure formed by the front beam, the rear beam, the wing ribs, the front edge partition plate and the rear edge partition plate to form a wing pneumatic molded surface; wherein the front beam, the rear beam, the wing ribs, the front edge partition plate, the rear edge partition plate, the upper wall plate, the lower wall plate and the wing tip are all of a composite material structure, and the integral oil tank is located between the two wing ribs in the middle.
Description
technical field [0001] The application belongs to the technical field of aircraft wing design, in particular to a composite material wing with an integral fuel tank. Background technique [0002] Composite materials have the advantages of high specific strength and good fatigue performance, and are used more and more in aircraft. However, the connection of composite materials is generally a clearance fit. The lightning protection and electrical lap of the wing are also more difficult to solve. [0003] For upper and lower monoplanes, the left and right wings are generally integrated, which can avoid the bending moment of the wing from being transmitted to the fuselage, reduce the weight of the fuselage structure, and for the integrity and direct force transmission of the wing and fuselage, The wings protrude out of the fuselage, which increases aerodynamic drag. . Contents of the invention [0004] It is an object of the present application to provide a composite airfoi...
Claims
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IPC IPC(8): B64C3/00B64C3/34
Inventor 韩宝钰吉飞王晓阳胡振杰党敏
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA