Combined wing spar structural member of airplane

Abstract

The utility model relates to the technical field of aircraft wing structures, in particular to an aircraft combined spar structural member which comprises a reinforcing rib plate, a reinforcing mechanism is installed on the plate wall of the reinforcing rib plate, and the reinforcing mechanism is formed by combining an H-shaped spar, an L-shaped plate A, a reinforcing plate, an L-shaped plate B and a reinforcing hole. A plurality of sets of L-shaped plates A connected with the reinforcing rib plates are installed on the beam wall of one side of the H-shaped spar through bolts, a plurality of sets of L-shaped plates B connected with the reinforcing rib plates are installed on the beam wall of the other side of the H-shaped spar through bolts, and reinforcing plates are welded to the plate walls of the L-shaped plates A and the plate walls of the L-shaped plates B correspondingly. The multiple sets of reinforcing rib plates are connected with the H-shaped spar through the reinforcing mechanisms, the reinforcing rib plates are connected through the multiple sets of row battens in a welded mode, and therefore the connecting strength of the reinforcing rib plates is improved, and the weight of the wing is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft wing structures, in particular to an aircraft combined wing spar structural component. Background Art

[0002] The aircraft wing spar structure is the main load-bearing component used to transfer concentrated loads. Suspension supports are installed on the wing spar to connect the rudder and control system. The wing spar structure is usually made of composite materials to reduce the structural weight, and the suspension supports are usually made of metal structures and assembled on the wing spar. In the case of densely arranged suspension supports, the composite wing spar is usually designed with a larger thickness to withstand larger concentrated loads, resulting in excessive structural weight. If the entire wing spar structure is made of metal materials, it will also cause the problem of excessive structural weight. For this reason, we propose an aircraft combined wing spar structure to increase the strength of the aircraft wing and reduce the weight of the aircraft wing body. Utility Model Content

[0003] In view of the problems in the prior art, the utility model provides an aircraft composite wing spar structural component.

[0004] The technical solution adopted by the present invention to solve its technical problems is a combined wing beam structure of an aircraft, including a reinforcing rib, a reinforcing mechanism installed at the plate wall of the reinforcing rib, and the reinforcing mechanism is composed of an H-shaped wing beam, an L-shaped plate A, a reinforcing plate, an L-shaped plate B and a reinforcing hole combination. A plurality of L-shaped plates A connected to the reinforcing rib are installed at the beam wall of one side of the H-shaped wing beam by bolts, and a plurality of L-shaped plates B connected to the reinforcing rib are installed at the beam wall of the other side of the H-shaped wing beam by bolts. Reinforcing plates are welded at the plate walls of the L-shaped plate A and the plate walls of the L-shaped plate B, and reinforcement holes are opened at the plate walls of the L-shaped plate A and the plate walls of the L-shaped plate B. The plate walls of the L-shaped plate A and the plate walls of the L-shaped plate B are connected to the reinforcing rib by bolts, and the bolts pass through the reinforcement holes.

[0005] By adopting the above technical solution, when the connection strength between the reinforcing rib and the H-shaped wing beam is increased, a reinforcement mechanism is installed at the plate wall of the reinforcing rib, and the reinforcement mechanism is composed of an H-shaped wing beam, an L-shaped plate A, a reinforcement plate, an L-shaped plate B and a reinforcement hole. Several groups of L-shaped plates B connected to the reinforcing ribs are installed at the beam wall on the other side of the H-shaped wing beam by bolts, and several groups of L-shaped plates A connected to the reinforcing ribs are installed at the beam wall on one side of the H-shaped wing beam by bolts. After the L-shaped plates A and L-shaped plates B are connected to the reinforcing ribs by bolts passing through the reinforcement holes, the reinforcing plates are welded at the plate walls of the L-shaped plates A and the plate walls of the L-shaped plates B, thereby increasing the lateral connection strength between the reinforcing rib and the H-shaped wing beam, and several groups of reinforcing ribs are connected to the H-shaped wing beam by the reinforcement mechanism, and the reinforcing ribs are welded by several groups of strips, thereby increasing the connection strength of the reinforcing ribs and reducing the weight of the wing.

[0006] Specifically, it also includes a connecting mechanism, and the connecting mechanism is installed on the plate wall of the reinforcing rib.

[0007] By adopting the above technical solution, the wing is conveniently connected to the aircraft body through the connecting mechanism.

[0008] Specifically, the connecting mechanism is composed of an L-shaped block A, a connecting plate, an L-shaped block B, an inclined block, a concave block and a connecting hole. A group of symmetrical L-shaped blocks A are installed on the plate wall of the connecting plate by bolts, and a group of symmetrical L-shaped blocks B are installed on the block wall of the concave block by bolts. The block walls of a group of L-shaped blocks A and the block walls of a group of L-shaped blocks B are connected to the reinforcing ribs by bolts. The block walls of a group of L-shaped blocks A and the block walls of a group of L-shaped blocks B are welded with inclined blocks, and connecting holes are provided on the plate wall of the connecting plate and the block walls of the concave blocks.

[0009] By adopting the above technical solution, when connecting with the external aircraft body, since a connecting mechanism is installed on the plate wall of the reinforcing rib, the connecting mechanism is composed of an L-shaped block A, a connecting plate, an L-shaped block B, an inclined block, a concave block and a connecting hole. After a group of L-shaped blocks A are connected to the connecting plate by bolts, and a group of L-shaped blocks B are connected to the concave block, inclined blocks are welded on the block wall of the L-shaped block A and the block wall of the L-shaped block B. The strength of the L-shaped block A and the L-shaped block B is increased by the inclined blocks, so that after the L-shaped block A and the L-shaped block B are connected to the reinforcing rib by bolts, since connecting holes are opened on the plate wall of the connecting plate and the block wall of the concave block, the connecting plate and the concave block are connected to the external aircraft body through the connecting holes, thereby realizing the connection of the aircraft wing.

[0010] Specifically, there are several groups of reinforcing ribs, and the reinforcing ribs are welded and connected by several groups of the row strips, and the several groups of reinforcing ribs are connected to the H-shaped wing beams by a reinforcement mechanism.

[0011] By adopting the above technical solution, the row strips and the reinforcement mechanism can increase the connection strength with the reinforcing ribs.

[0012] Specifically, the plate walls of the row strips, the plate walls of the reinforcing ribs, and the beam walls of the H-shaped spar are all connected to the skin through rivets.

[0013] By adopting the above technical solution, the strips, reinforcing ribs and H-shaped wing beams can be wrapped and sealed by the skin.

[0014] Specifically, a plurality of groups of vertical plates are welded to the plate walls of the reinforcing ribs, and through holes for connecting to the outside are opened on the plate walls of the plurality of groups of vertical plates.

[0015] By adopting the above technical solution, external bolts can be conveniently passed through the through holes, so that the vertical plate is connected to the external aircraft body.

[0016] Beneficial effects of the utility model:

[0017] The invention relates to a composite wing spar structure for an aircraft. When the connection strength between the reinforcing rib and the H-shaped spar is increased, a reinforcing mechanism is installed at the plate wall of the reinforcing rib. The reinforcing mechanism is composed of an H-shaped spar, an L-shaped plate A, a reinforcing plate, an L-shaped plate B and a reinforcing hole. Several groups of L-shaped plates B connected to the reinforcing rib are installed at the beam wall of the other side of the H-shaped spar by bolts, and several groups of L-shaped plates A connected to the reinforcing rib are installed at the beam wall of one side of the H-shaped spar by bolts. After the L-shaped plates A and L-shaped plates B are connected to the reinforcing rib by bolts passing through the reinforcement holes, the reinforcing plates are welded at the plate walls of the L-shaped plates A and the plate walls of the L-shaped plates B, thereby increasing the lateral connection strength between the reinforcing rib and the H-shaped spar. Several groups of reinforcing ribs are connected to the H-shaped spar by the reinforcing mechanism, and the reinforcing ribs are welded by several groups of strips, thereby increasing the connection strength of the reinforcing ribs and reducing the weight of the wing.

[0018] The utility model discloses an aircraft combined wing beam structure component, when connected to an external aircraft body, a connecting mechanism is installed at the plate wall of the reinforcing rib plate, and the connecting mechanism is composed of an L-shaped block A, a connecting plate, an L-shaped block B, an inclined block, a concave block and a connecting hole. After a group of L-shaped blocks A are connected to the connecting plate by bolts, and a group of L-shaped blocks B are connected to the concave block, inclined blocks are welded at the block wall of the L-shaped block A and the block wall of the L-shaped block B. The inclined blocks increase the strength of the L-shaped blocks A and L-shaped blocks B, so that after the L-shaped blocks A and L-shaped blocks B are connected to the reinforcing rib plate by bolts, since connecting holes are opened at the plate wall of the connecting plate and the block wall of the concave block, the connecting plate and the concave block are connected to the external aircraft body through the connecting holes, thereby realizing the connection of the aircraft wing. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0020] Figure 1 It is the main figure of the utility model;

[0021] Figure 2 This is a schematic diagram of the reinforcing rib structure of the utility model;

[0022] Figure 3 This is a schematic diagram of the reinforcement mechanism structure of the present utility model;

[0023] Figure 4 This is a schematic diagram of the connecting mechanism structure of the present utility model;

[0024] In the figure: 1. Reinforcing rib; 2. Skin; 3. Connecting mechanism; 301. L-shaped block A; 302. Connecting plate; 303. L-shaped block B; 304. Inclined block; 305. Concave block; 306. Connecting hole; 4. Vertical plate; 5. Through hole; 6. Strip plate; 7. Reinforcement mechanism; 701. H-shaped spar; 702. L-shaped plate A; 703. Reinforcement plate; 704. L-shaped plate B; 705. Reinforcement hole. DETAILED DESCRIPTION

[0025] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below in conjunction with specific implementation methods.

[0026] As an embodiment of the present invention, Figure 1 、 Figure 2 、 Figure 3 and Figure 4 As shown, an aircraft composite wing spar structure according to the present invention includes a reinforcing rib 1, a reinforcing mechanism 7 is installed at the plate wall of the reinforcing rib 1, and the reinforcing mechanism 7 is composed of an H-shaped spar 701, an L-shaped plate A702, a reinforcing plate 703, an L-shaped plate B704 and a reinforcing hole 705. A plurality of groups of L-shaped plates A702 connected to the reinforcing rib 1 are installed at one side of the spar 701 by bolts. Several groups of L-shaped plates B704 connected to the reinforcing ribs 1 are installed at one side beam wall by bolts, and reinforcing plates 703 are welded at the plate walls of the L-shaped plates A702 and the plate walls of the L-shaped plates B704. Reinforcement holes 705 are opened at the plate walls of the L-shaped plates A702 and the plate walls of the L-shaped plates B704. The plate walls of the L-shaped plates A702 and the plate walls of the L-shaped plates B704 are connected to the reinforcing ribs 1 by bolts, and the bolts pass through the reinforcement holes 705.

[0027] When in use, when the connection strength between the reinforcing rib 1 and the H-shaped spar 701 is increased, since a reinforcing mechanism is installed at the plate wall of the reinforcing rib 1, the reinforcing mechanism is composed of an H-shaped spar 701, an L-shaped plate A702, a reinforcing plate 703, an L-shaped plate B704 and a reinforcing hole 705, a plurality of groups of L-shaped plates B704 connected to the reinforcing rib 1 are installed at the beam wall of the other side of the H-shaped spar 701 by bolts, and a plurality of groups of L-shaped plates A702 connected to the reinforcing rib 1 are installed at the beam wall of one side of the H-shaped spar 701 by bolts. After the type plate A702 and the L-type plate B704 are connected to the reinforcing rib 1 by bolts passing through the reinforcement holes 705, the reinforcing plates 703 are welded at the plate walls of the L-type plate A702 and the plate walls of the L-type plate B704, thereby increasing the lateral connection strength between the reinforcing rib 1 and the H-shaped wing beam 701. Several groups of reinforcing ribs 1 and the H-shaped wing beam 701 are connected by the reinforcement mechanism 7, and the reinforcing ribs 1 are welded together by several groups of strips 6, thereby increasing the connection strength of the reinforcing rib 1 and reducing the weight of the wing.

[0028] like Figure 1 As shown, a connecting mechanism 3 is also included, and the connecting mechanism 3 is installed on the plate wall of the reinforcing rib 1.

[0029] When in use, the wing is conveniently connected to the aircraft body through the connecting mechanism 3.

[0030] like Figure 1 and Figure 4 As shown, the connecting mechanism 3 is composed of an L-shaped block A301, a connecting plate 302, an L-shaped block B303, an inclined block 304, a concave block 305 and a connecting hole 306. A group of symmetrical L-shaped blocks A301 are installed on the plate wall of the connecting plate 302 by bolts, and a group of symmetrical L-shaped blocks B303 are installed on the block wall of the concave block 305 by bolts. The block walls of a group of L-shaped blocks A301 and the block walls of a group of L-shaped blocks B303 are both connected to the reinforcing rib 1 by bolts. The block walls of a group of L-shaped blocks A301 and the block walls of a group of L-shaped blocks B303 are both welded with inclined blocks 304. The plate wall of the connecting plate 302 and the block walls of the concave block 305 are both provided with connecting holes 306.

[0031] When in use, when connecting with the external aircraft body, since the wall of the reinforcing rib 1 is equipped with a connecting mechanism 3, the connecting mechanism 3 is composed of an L-shaped block A301, a connecting plate 302, an L-shaped block B303, an inclined block 304, a concave block 305 and a connecting hole 306. After a set of L-shaped blocks A301 and the connecting plate 302 are connected by bolts, and a set of L-shaped blocks B303 and the concave block 305 are connected, the wall of the L-shaped block A301 and the L-shaped block B303 are connected. 3 are welded with inclined blocks 304 on the block walls, and the inclined blocks 304 increase the strength of the L-shaped blocks A301 and L-shaped blocks B303, so that after the L-shaped blocks A301 and L-shaped blocks B303 are connected to the reinforcing rib 1 by bolts, since the plate wall of the connecting plate 302 and the block wall of the concave block 305 are both provided with connecting holes 306, the connecting plate 302 and the concave block 305 are connected to the external aircraft body through the connecting holes 306, thereby connecting the aircraft wings.

[0032] like Figure 2 As shown, there are several groups of reinforcing ribs 1, and the reinforcing ribs 1 are welded together by several groups of the row strips 6, and the several groups of reinforcing ribs 1 are connected to the H-shaped wing beam 701 by a reinforcement mechanism 7.

[0033] When in use, the strips 6 and the reinforcing mechanism 7 can increase the connection strength with the reinforcing ribs 1 .

[0034] like Figure 1 As shown, the plate wall of the row strip 6, the plate wall of the reinforcing rib 1 and the beam wall of the H-shaped spar 701 are all connected to the skin 2 through rivets.

[0035] When in use, the strips 6 , the reinforcing ribs 1 and the H-shaped spar 701 can be wrapped and sealed by the skin 2 .

[0036] like Figure 1 As shown, a plurality of groups of vertical plates 4 are welded to the plate wall of the reinforcing rib 1 , and through holes 5 for connecting to the outside are opened on the plate wall of the plurality of groups of vertical plates 4 .

[0037] When in use, external bolts are conveniently passed through the through holes 5 to connect the vertical plate 4 to the external aircraft body.

[0038] When the utility model is in use, when the connection strength between the reinforcing rib 1 and the H-shaped spar 701 is increased, since a reinforcing mechanism is installed at the plate wall of the reinforcing rib 1, the reinforcing mechanism is composed of an H-shaped spar 701, an L-shaped plate A702, a reinforcing plate 703, an L-shaped plate B704 and a reinforcing hole 705, a plurality of groups of L-shaped plates B704 connected to the reinforcing rib 1 are installed at the other side beam wall of the H-shaped spar 701 by bolts, and a plurality of groups of L-shaped plates B704 connected to the reinforcing rib 1 are installed at the one side beam wall of the H-shaped spar 701 by bolts. The L-shaped plate A702 of the strong rib 1 is connected to the L-shaped plate A702 and the L-shaped plate B704 by bolts passing through the reinforcement holes 705. Since the plate walls of the L-shaped plate A702 and the plate walls of the L-shaped plate B704 are welded with reinforcement plates 703, the lateral connection strength between the strengthening rib 1 and the H-shaped wing beam 701 is increased. Several groups of strengthening ribs 1 and H-shaped wing beams 701 are connected by reinforcement mechanisms 7, and the strengthening ribs 1 are welded by several groups of strips 6, thereby achieving The connection strength of the reinforcing rib 1 is increased to reduce the weight of the wing. When connecting with the external aircraft body, a connecting mechanism 3 is installed on the wall of the reinforcing rib 1. The connecting mechanism 3 is composed of an L-shaped block A301, a connecting plate 302, an L-shaped block B303, an inclined block 304, a concave block 305 and a connecting hole 306. After a group of L-shaped blocks A301 and the connecting plate 302 are connected by bolts, and a group of L-shaped blocks B303 and the concave block 305 are connected, the L-shaped block A301 is connected to the connecting plate 302. Inclined blocks 304 are welded to the block walls and the block walls of the L-shaped block B303. The inclined blocks 304 increase the strength of the L-shaped blocks A301 and B303, so that after the L-shaped blocks A301 and B303 are connected to the reinforcing ribs 1 by bolts, since connecting holes 306 are provided on the plate walls of the connecting plate 302 and the block walls of the concave blocks 305, the connecting plate 302 and the concave blocks 305 are connected to the external aircraft body through the connecting holes 306, thereby connecting the aircraft wings.

[0039] 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 to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and improvements are intended to fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft composite wing spar structural component, characterized in that: The invention comprises a reinforcing rib (1), a vertical plate (4) and a row plate (6), wherein a reinforcing mechanism (7) is installed at the plate wall of the reinforcing rib (1), and the reinforcing mechanism (7) is composed of an H-shaped wing beam (701), an L-shaped plate A (702), a reinforcing plate (703), an L-shaped plate B (704) and a reinforcing hole (705), and a plurality of groups of L-shaped plates A (702) connected to the reinforcing rib (1) are installed at the beam wall of one side of the H-shaped wing beam (701) by bolts, and a beam wall of the other side of the H-shaped wing beam (701) is provided with a plurality of L-shaped plates A (702) connected to the reinforcing rib (1). Several groups of L-shaped plates B (704) connected to the reinforcing ribs (1) are installed by bolts, and reinforcing plates (703) are welded to the plate walls of the L-shaped plate A (702) and the plate walls of the L-shaped plate B (704), and reinforcing holes (705) are opened on the plate walls of the L-shaped plate A (702) and the plate walls of the L-shaped plate B (704), and the plate walls of the L-shaped plate A (702) and the plate walls of the L-shaped plate B (704) are connected to the reinforcing ribs (1) by bolts, and the bolts pass through the reinforcing holes (705).

2. The aircraft composite wing spar structure according to claim 1, characterized in that: It also includes a connecting mechanism (3), and the connecting mechanism (3) is installed on the plate wall of the reinforcing rib plate (1).

3. The aircraft composite wing spar structure according to claim 2, characterized in that: The connecting mechanism (3) is composed of an L-shaped block A (301), a connecting plate (302), an L-shaped block B (303), an inclined block (304), a concave block (305) and a connecting hole (306). A group of symmetrical L-shaped blocks A (301) are installed on the plate wall of the connecting plate (302) by bolts. A group of symmetrical L-shaped blocks B (303) are installed on the block wall of the concave block (305) by bolts. The block walls of a group of L-shaped blocks A (301) and the block walls of a group of L-shaped blocks B (303) are both connected to the reinforcing rib (1) by bolts. The block walls of a group of L-shaped blocks A (301) and the block walls of a group of L-shaped blocks B (303) are both welded with an inclined block (304). The plate wall of the connecting plate (302) and the block walls of the concave block (305) are both provided with a connecting hole (306).

4. The aircraft composite wing spar structure according to claim 1, characterized in that: There are several groups of reinforcing ribs (1), and the reinforcing ribs (1) are welded together by several groups of row plates (6), and the several groups of reinforcing ribs (1) are connected to the H-shaped wing beam (701) by a reinforcing mechanism (7).

5. The aircraft composite wing spar structure according to claim 4, characterized in that: The plate wall of the row plate (6), the plate wall of the reinforcing rib plate (1), and the beam wall of the H-shaped wing beam (701) are all connected to the skin (2) through rivets.

6. The aircraft composite wing spar structure according to claim 1, characterized in that: Several groups of vertical plates (4) are welded to the plate wall of the reinforcing rib plate (1), and through holes (5) connected to the outside are opened on the plate wall of the several groups of vertical plates (4).

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