阅读说明：本技术 一种飞机机翼的梁结构 (A kind of girder construction of aircraft wing ) 是由 田仕雄 黎振勃 刘秋娥 于 2019-08-02 设计创作，主要内容包括：一种飞机机翼的梁结构,含有由上缘条、下缘条、腹板、加强支柱组成的梁本体和位于梁本体前端的整体梁框,所述整体梁框是一个框形结构,整体梁框与梁本体连接,整体梁框的前端设有与机身连接的对接面。本申请的飞机机翼的梁结构的前端设有整体梁框,整体梁框保证了翼梁结构的完整性和传力；在整体梁框中间设计有大开口,进气道布局在整体梁框的大开口中；整体梁框采用整体成型制造,减少了零件和连接件数量,从而减轻了结构重量,提高了部件装配效率,降低了生产成本；整体梁框可以采用铝合金整体锻造成形,提高结构的疲劳性能。(A kind of girder construction of aircraft wing, containing by upper edge strip, lower edge strip, web, reinforce the beam ontology that forms of pillar and unjointed beam frame positioned at beam ontology front end, the unjointed beam frame is a frame-shaped construction, unjointed beam frame is connect with beam ontology, and the front end of unjointed beam frame is equipped with the interface connecting with fuselage.The front end of the girder construction of the aircraft wing of the application is equipped with unjointed beam frame, and unjointed beam frame ensure that the integrality and power transmission of spar structure；There is big opening in unjointed beam frame medium design, inlet distribution is in the big opening of unjointed beam frame；Unjointed beam frame uses integrally formed manufacture, reduces part and connector quantity, to alleviate construction weight, improves component assembling efficiency, reduce production cost；Unjointed beam frame can use aluminium alloy integral forging and forming, improve the fatigue behaviour of structure.)

1. a kind of girder construction of aircraft wing, which is characterized in that containing by upper edge strip, lower edge strip, web, reinforce pillar and form Beam ontology and unjointed beam frame positioned at beam ontology front end, the unjointed beam frame is a frame-shaped construction, unjointed beam frame and Liang Benti Connection, the front end of unjointed beam frame are equipped with the interface connecting with fuselage.

2. the girder construction of aircraft wing as described in claim 1, which is characterized in that the unjointed beam frame contain interior reinforcing frame, Outer reinforcing frame, is equipped with connection web and reinforcing rib between interior reinforcing frame, outer reinforcing frame, the front end of the outer reinforcing frame be with The interface of fuselage connection, interface are equipped with butt hole, and the both ends of the rear end of the outer reinforcing frame each extend over out and beam The matched connection tail of ontology web.

3. the girder construction of aircraft wing as described in claim 1, which is characterized in that the front end of the beam ontology be one with it is whole Matched half frame-shaped construction of body beam frame, the top of half frame-shaped construction are the upper edge strips of beam ontology, and the lower part of frame-shaped construction is beam sheet The lower edge strip of body, the side of half frame-shaped construction are the webs of beam ontology.

4. the girder construction of aircraft wing as claimed in claim 3, which is characterized in that half frame-shaped construction portion of beam ontology front end The section of the upper edge strip and lower edge strip that divide is L-type, can be fitted and connected with the web of unjointed beam frame.

Technical field

The present invention relates to aeroplane structure designs, are further the structure design of aircraft wing, specifically a kind of aircraft wing Girder construction.

Background technique

The air-foil of large transport airplane and bomber is thicker, mostly uses beam type wing structure.The beam type wing knot of aircraft Wingbar is main bearing member in structure, and wingbar bears wing overwhelming majority shearing and moment of flexure, the wingbar of usual aircraft are The wall type structure being made of upper edge strip, lower edge strip, web and reinforcement pillar is docked in root with fuselage fixation.Wingbar and machine Wing covering constitutes closed box structure and bears wing torque.In airplane design, outside the layout of air intake duct and the pneumatic of aircraft Shape is related, and using the aerodynamic arrangement of wing root air inlet, the root of aircraft wing is arranged in air intake duct, and air intake duct is needed across aircraft machine The wing, advantage of this layout is that the front face area of aircraft is small, aerodynamic drag is small, so as to promote the flying quality of aircraft.When When aircraft uses the aerodynamic arrangement of wing root air inlet, air intake duct passes through spar, to destroy the integrality and power transmission of spar structure. The structure of air intake duct and aircraft wing interferes, especially even more serious to the interference of the load-carrying member wingbar of wing.Such as What guarantees air intake duct in the rational deployment of wing wing root, guarantees that the structural strength of wing is a difficulty of aeroplane structure design again Topic.

Summary of the invention

The purpose of the present invention is to provide a kind of inlet distribution the aircraft wing of wing wing root girder construction.One kind flies The girder construction of machine wing, which is characterized in that containing the beam ontology being made of upper edge strip, lower edge strip, web, reinforcement pillar and be located at The unjointed beam frame of beam ontology front end, the unjointed beam frame are a frame-shaped constructions, and unjointed beam frame is connect with beam ontology, unjointed beam frame Front end be equipped with the interface that connect with fuselage.

The unjointed beam frame contains interior reinforcing frame, outer reinforcing frame, and connection web is equipped between interior reinforcing frame, outer reinforcing frame And reinforcing rib, the front end of the outer reinforcing frame are the interfaces connecting with fuselage, interface is equipped with butt hole, and described is outer The both ends of the rear end of reinforcing frame each extend over out and the matched connection tail of beam ontology web.

The front end of the beam ontology is one and matched half frame-shaped construction of unjointed beam frame, and the top of half frame-shaped construction is beam The upper edge strip of ontology, the lower part of frame-shaped construction are the lower edge strips of beam ontology, and the side of half frame-shaped construction is the web of beam ontology.

The upper edge strip of half frame-shaped construction part of beam ontology front end and the section of lower edge strip are L-types, can be with unjointed beam frame Web be fitted and connected.

The beneficial effects of the present invention are: 1) front end of the girder construction of the aircraft wing of the application be equipped with unjointed beam frame, whole Body beam frame ensure that the integrality and power transmission of spar structure；2) there is big opening in unjointed beam frame medium design, inlet distribution exists In the big opening of unjointed beam frame；3) unjointed beam frame uses integrally formed manufacture, reduces part and connector quantity, to mitigate Construction weight, improves component assembling efficiency, reduces production cost；4) unjointed beam frame can use aluminium alloy solid forging Forming, improves the fatigue behaviour of structure.

Attached drawing is described in further detail the application with reference to embodiments.

Detailed description of the invention

Fig. 1 is aircraft wing beam assembling structure schematic diagram.

Fig. 2 is aircraft wing girder construction schematic diagram.

Fig. 3 is beam body construction schematic diagram.

Fig. 4 is unjointed beam mount structure schematic diagram.

Fig. 5 is the connection schematic diagram of beam ontology Yu unjointed beam frame.

Number explanation in figure: 1 beam ontology, 2 unjointed beam frames, edge strip on 3,4 lower edge strips, 5 webs, 6 reinforce pillars, in 7 plus Strong frame, 8 outer reinforcing frames, 9 connection webs, 10 reinforcing ribs, 11 interfaces, 12 butt holes, 13 connect tails, 14 fuselages, 15 air intake ducts, 16 wing wallboards

Specific embodiment

Referring to attached drawing, a kind of girder construction of aircraft wing is bolted at interface 11 with fuselage 14, with wing Siding 16 is bolted, and air intake duct 15 passes through unjointed beam frame 2.

Unjointed beam frame 2 of the girder construction of the aircraft wing of the application by beam ontology 1 and positioned at 1 front end of beam ontology forms.Beam Ontology 1 is by upper edge strip 3, lower edge strip 4, web 5, reinforcement pillar 6 by riveting.1 front end of beam ontology is one and half frame shape knots The section of structure, the upper edge strip 3 of half frame-shaped construction part and lower edge strip 4 is L-type, passes through rivet with the connection web 9 of unjointed beam frame 2 Connection；The web of the beam ontology 1 of half frame-shaped construction side and the connection web 9 of unjointed beam frame 2 pass through rivet interlacement.

In implementation, unjointed beam frame can be integrated machine addition shape, be also possible to aluminium alloy integral forging and forming, in embodiment Unjointed beam frame use aluminium alloy integral forging and forming, unjointed beam frame contains interior reinforcing frame 7, outer reinforcing frame 8, interior reinforcing frame 7, Connection web 9 is equipped between outer reinforcing frame 8 and reinforcing rib 10, the front end of the outer reinforcing frame 8 are the docking connecting with fuselage Face 11, interface are equipped with butt hole 12, and the both ends of 8 rear end of outer reinforcing frame each extend over out to be matched with beam ontology web Connection tail 12.