Aircraft beam structure with wings

Abstract

The utility model relates to the technical field of aircrafts, in particular to a winged beam structure for aircrafts, which comprises two support beams and a connecting plate, the end parts of the two support beams close to the connecting plate are both connected with the connecting plate, four connecting blocks are integrally formed on one side of the connecting plate, and the connecting blocks are connected with the connecting plate. Flange strips are integrally formed on the edges of the two supporting beams, two connecting blocks are connected with one flange strip through rivets, the other two connecting blocks are connected with the other flange strip through rivets, and a plurality of supports are connected between the two flange strips through rivets. The support between the two supporting beams can improve the strength and load resistance of the two supporting beams, the space between the two supporting beams facilitates laying of cables, the supporting beams, the connecting plates and the connecting blocks are arranged, a stable triangular supporting system can be formed among the supporting beams, the connecting plates and the connecting blocks, and the stability of the supporting beams is improved. Therefore, the overall strength and the load resistance are improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and particularly relates to a winged beam structure for an aircraft. Background Art

[0002] An aircraft refers to a heavier-than-air aircraft that generates forward thrust or pull by a power plant with one or more engines, and generates lift by fixed wings of the fuselage and flies within the atmosphere. A winged beam (spar) is provided inside the wing of a small aircraft. The spar is mainly composed of a web and flanges (or flange strips). Most of the spars are fixedly connected to the fuselage at the root. After the wing is impacted, the root of the spar is prone to breakage. Therefore, a winged beam structure for an aircraft is proposed to improve the bearing capacity and strength. Content of the Utility Model

[0003] In view of the problems in the prior art, the utility model provides a winged beam structure for an aircraft.

[0004] The technical solution adopted by the utility model to solve its technical problems is a winged beam structure for an aircraft, including a support beam and a connecting plate. There are two support beams, and the ends of the two support beams close to the connecting plate are both connected to the connecting plate. Four connecting blocks are integrally formed on one side of the connecting plate. Wing flange strips are integrally formed on the edges of the two support beams. Two of the connecting blocks are connected to one of the wing flange strips by rivets, and the other two connecting blocks are connected to the other wing flange strip by rivets. A plurality of brackets are connected between the two wing flange strips by rivets.

[0005] By adopting the above technical solution, the brackets between the two support beams can not only improve the strength and load resistance performance of the two support beams, but also the space between the two support beams is conducive to the laying of cables. The arrangement of the connecting blocks on the connecting plate can form a stable triangular support system among the support beam, the connecting plate and the connecting blocks, thereby improving the overall strength and load resistance performance.

[0006] Specifically, a connecting seat is provided on the side of the support beam away from the connecting plate, and the connecting seat is connected to the two wing flange strips by rivets.

[0007] By adopting the above technical solution, the arrangement of the connecting seat can connect one ends of the two wing flange strips away from the connecting plate, making the two support beams and the wing flange strips more stable.

[0008] Specifically, a plurality of relief holes are provided on both of the two support beams.

[0009] By adopting the above technical solution, the arrangement of the relief holes can reduce the overall weight.

[0010] Specifically, a plurality of reinforcing ribs are integrally formed in both of the two wing flange strips.

[0011] By adopting the above technical solution, the setting of the reinforcing rib can improve the strength of the flange strip.

[0012] Specifically, a U-shaped support seat is provided between the two flange strips. One side of the support seat close to the connecting plate is connected to the connecting plate by rivets, and both of the two flange strips are connected to the support seat by rivets.

[0013] By adopting the above technical solution, the setting of the support seat can connect one ends of the two flange strips close to the connecting plate, further improving the overall strength.

[0014] Advantages of the present utility model:

[0015] (1) For the winged beam structure for an aircraft of the present utility model, the bracket between the two support beams can not only improve the strength and load-bearing performance of the two support beams, but also the space between the two support beams is conducive to the laying of cables. The setting of the connecting blocks on the connecting plate can form a stable triangular support system among the support beams, the connecting plate and the connecting blocks, thereby improving the overall strength and load-bearing performance.

[0016] (2) For the winged beam structure for an aircraft of the present utility model, the setting of the connecting seat can connect one ends of the two flange strips far from the connecting plate, making the two support beams and the flange strips more stable. The setting of the support seat can connect one ends of the two flange strips close to the connecting plate, further improving the overall strength. The setting of the reinforcing rib can improve the strength of the flange strip. Description of the drawings

[0017] The present utility model will be further described below in conjunction with the drawings and embodiments.

[0018] Figure 1 is a schematic structural diagram of the present utility model;

[0019] Figure 2 is of the present utility model Figure 1 an enlarged view of the structure at A in;

[0020] Figure 3 is of the present utility model Figure 1 an enlarged view of the structure at B in.

[0021] In the figure: 1, support beam; 2, connecting block; 3, connecting plate; 4, connecting seat; 5, flange strip; 6, reinforcing rib; 7, lightening hole; 8, support seat; 9, bracket. Detailed implementation manners

[0022] In order to make the technical means, creative features, achieved purposes and effects realized by the present utility model easy to understand, the present utility model will be further described below in conjunction with the specific implementation manners.

[0023] To improve the strength and load-bearing performance, as an embodiment of the present utility model, as Figure 1 , Figure 2 shown, a winged beam structure for an aircraft according to the present utility model includes a support beam 1 and a connecting plate 3. There are two support beams 1. The ends of the two support beams 1 close to the connecting plate 3 are both connected to the connecting plate 3 by rivets. Four connecting blocks 2 are integrally formed on one side of the connecting plate 3. Flange strips 5 are integrally formed on the edges of the two support beams 1. Two of the connecting blocks 2 are connected to one of the flange strips 5 by rivets, and the other two connecting blocks 2 are connected to the other flange strip 5 by rivets. A plurality of brackets 9 are connected between the two flange strips 5 by rivets.

[0024] During use, the connecting plate 3 is fixed to the aircraft fuselage by rivets or bolts. The brackets 9 between the two support beams 1 can not only improve the strength and load-bearing performance of the two support beams 1, but also the space between the two support beams 1 is conducive to the laying of cables. The arrangement of the connecting blocks 2 on the connecting plate 3 can form a stable triangular support system among the support beam 1, the connecting plate 3 and the connecting blocks 2, thereby improving the overall strength and load-bearing performance.

[0025] To improve the stability of the end of the support beam 1 away from the connecting plate 3, exemplarily, as Figure 1 shown, a connecting seat 4 is provided on the side of the support beam 1 away from the connecting plate 3, and the connecting seat 4 is connected to the two flange strips 5 by rivets.

[0026] To reduce the overall weight, exemplarily, as Figure 1 shown, a plurality of relief holes 7 are provided on both of the two support beams 1.

[0027] To improve the strength of the flange strip 5, exemplarily, as Figure 1 shown, a plurality of reinforcing ribs 6 are integrally formed in both of the two flange strips 5.

[0028] To improve the strength of the ends of the two flange strips 5 close to the connecting plate 3, exemplarily, as Figure 3 shown, a U-shaped support seat 8 is provided between the two flange strips 5. The side of the support seat 8 close to the connecting plate 3 is connected to the connecting plate 3 by rivets, and the two flange strips 5 are both connected to the support seat 8 by rivets.

[0029] When the present utility model is in use, the connecting plate 3 is fixed to the aircraft fuselage by rivets or bolts. The brackets 9 between the two support beams 1 can not only improve the strength and load-bearing performance of the two support beams 1, but also the space between the two support beams 1 is conducive to the laying of cables;

[0030] The provision of the connecting seat 4 can connect the ends of the two flange bars 5 far from the connecting plate 3, making the two support beams 1 and the flange bars 5 more stable. The provision of the support seat 8 can connect the ends of the two flange bars 5 close to the connecting plate 3;

[0031] The provision of the connecting block 2 on the connecting plate 3 can form a stable triangular support system among the support beam 1, the connecting plate 3 and the connecting block 2, thereby improving the overall strength and load-bearing performance.

[0032] The above shows and describes the basic principles, main features and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited by the above embodiments. The above embodiments and the descriptions in the specification only illustrate the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention will have various changes and improvements, and these changes and improvements all fall within the scope of protection required by the present invention. The scope of protection required by the present invention is defined by the appended claims and their equivalents. The content not described in detail in the present invention belongs to the prior art well known to those skilled in the art.

Claims

1. A winged beam structure for an aircraft, characterized in that, It includes a support beam (1) and a connecting plate (3). There are two support beams (1). The ends of the two support beams (1) close to the connecting plate (3) are both connected to the connecting plate (3). Four connecting blocks (2) are integrally formed on one side of the connecting plate (3). Flange strips (5) are integrally formed on the edges of the two support beams (1). Among them, two connecting blocks (2) are connected to one flange strip (5) by rivets, and the other two connecting blocks (2) are connected to the other flange strip (5) by rivets. A plurality of brackets (9) are connected between the two flange strips (5) by rivets.

2. The winged beam structure for an aircraft according to claim 1, characterized in that, A connecting seat (4) is provided on the side of the support beam (1) away from the connecting plate (3). The connecting seat (4) is connected to the two flange strips (5) by rivets.

3. The winged beam structure for an aircraft according to claim 1, wherein, A plurality of lightening holes (7) are provided on both of the two support beams (1).

4. A winged beam structure for an aircraft according to claim 1, characterized in that, A plurality of reinforcing ribs (6) are integrally formed in both of the two flange strips (5).

5. A winged beam structure for an aircraft according to claim 1, characterized in that, A U-shaped support seat (8) is provided between the two flange strips (5). The side of the support seat (8) close to the connecting plate (3) is connected to the connecting plate (3) by rivets. Both of the two flange strips (5) are connected to the support seat (8) by rivets.

Images