Conformal antenna installed on front edge of airfoil

Abstract

The utility model belongs to the field of aircraft structure design, and particularly relates to a conformal antenna mounted on the front edge of an airfoil, which comprises a skin, a partition plate, an end rib, a root rib, a conformal antenna and a core, a cavity is formed between the skin and the partition plate. The conformal antenna is of an equal-diameter columnar structure, the conformal antenna and the core are both arranged in the cavity, and the end rib and the root rib are fixedly connected to the two ends of the conformal antenna respectively. During assembly, the conformal antenna and the core are combined and placed into the skin, the partition plate covers the skin, and finally, the upper end rib and the root rib are mounted, so that integral fixation can be completed; during disassembly, the skin, the partition plate, the end rib, the root rib, the conformal antenna and the core are integrally disassembled from the front edge of the airfoil and then integrally replaced. The conformal antenna is simple in structure, reliable in installation, beneficial to improving aerodynamic efficiency and reducing weight, easy to replace, low in replacement cost, good in rigidity and capable of enhancing bird impact resistance of the airfoil structure when installed on the front edge of the airfoil.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural design, and specifically relates to a conformal antenna mounted on the leading edge of a wing. Background Technology

[0002] In aircraft structural design, there is a need to install conformal antennas. Shortwave antennas are relatively long and require maintenance. Installing antennas externally to the aircraft structure would negatively impact aerodynamic characteristics and hinder structural integration and weight reduction. Existing conformal antennas are often integrated with the entire wing leading edge structure, making them impossible to remove separately. This results in poor antenna replaceability; generally, antenna problems require replacing the entire wing leading edge, leading to high maintenance costs. Therefore, from the perspectives of aerodynamic efficiency, structural weight reduction, and antenna maintenance, designing easily detachable and installable wing leading edge conformal antennas is essential. Summary of the Invention

[0003] The purpose of this application is to provide a conformal antenna mounted on the leading edge of a wing to solve the problem of high maintenance costs of existing conformal antennas.

[0004] The technical solution of this application is: a conformal antenna installed on the leading edge of a wing, comprising a skin, a partition, end ribs, root ribs, a conformal antenna, and a core; the skin is a bent structure with an opening on one side, the partition is disposed at the opening of the skin, and a cavity is formed between the skin and the partition; the conformal antenna is a columnar structure of equal diameter, both the conformal antenna and the core are disposed within the cavity, the end ribs and root ribs are respectively fixedly connected to both ends of the conformal antenna, and the two ends of the cavity are closed; the end ribs and root ribs are fixedly connected to the skin and the partition; the skin, partition, end ribs, root ribs, conformal antenna, and core are fixedly integrated into a single structure, and the skin and partition are bolted to the leading edge of the wing.

[0005] Preferably, the skin cross-section is an airfoil leading edge structure.

[0006] Preferably, the partition is a groove-shaped structure, and the two sides of the partition are folded upward to form flanges, the flanges being in contact with the inner wall of the skin.

[0007] Preferably, the end rib and the root rib are the same as the cross-section of the airfoil at the location, the end rib is provided with a first antenna through hole that cooperates with the conformal antenna, and the root rib is provided with a second antenna through hole that cooperates with the conformal antenna.

[0008] Preferably, the core is made of foam material, and a third antenna through-hole is provided inside the core to cooperate with the conformal antenna.

[0009] Preferably, the conformal antenna is glued and fixed to the first antenna via, the second antenna via, and the third antenna via.

[0010] Preferably, the skin, partition, end ribs and root ribs are all made of a wave-transparent material.

[0011] The conformal antenna of this application, mounted on the leading edge of the wing, is assembled by inserting the conformal antenna into the core, then placing the conformal antenna and core assembly into the skin, covering it with a partition, and finally attaching the end ribs and root ribs to complete the integral fixation. For disassembly, the skin, partition, end ribs, root ribs, conformal antenna, and core are removed from the leading edge of the wing as a whole and then replaced as a whole. The structure is simple, the installation is reliable, it is beneficial for improving aerodynamic efficiency and reducing weight, and the conformal antenna is easy to replace at a low cost. The conformal antenna has good stiffness, and its installation on the leading edge of the wing can enhance the wing structure's resistance to bird strikes. Attached Figure Description

[0012] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0013] Figure 1 This is an isometric drawing of the overall structure of this application;

[0014] Figure 2 This is an exploded view of the overall structure of this application;

[0015] Figure 3 This is a schematic diagram of the skin structure of this application;

[0016] Figure 4 This is a schematic diagram of the partition structure of this application;

[0017] Figure 5 This is a schematic diagram of the end rib structure of this application;

[0018] Figure 6 This is a schematic diagram of the root rib structure of this application;

[0019] Figure 7 This is a schematic diagram of the core structure of this application.

[0020] 1. Skin; 2. Partition; 3. End rib; 4. Root rib; 5. Conformal antenna; 6. Core; 7. First antenna via; 8. Second antenna via; 9. Third antenna via. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] A conformal antenna mounted on the leading edge of the wing, such as Figures 1-2 As shown, the structure includes a skin 1, a partition 2, end ribs 3, root ribs 4, a conformal antenna 5, and a core 6. The skin 1 is a bent structure with an opening on one side. The partition 2 is fixedly connected to the opening of the skin 1, forming a cavity between the skin 1 and the partition 2. The conformal antenna 5 is a cylindrical structure of equal diameter. Both the conformal antenna 5 and the core 6 are located within the cavity. The end ribs 3 and 4 are fixedly connected to both ends of the conformal antenna 5, sealing the two ends of the cavity. The end ribs 3 and 4 are fixedly connected to both the skin 1 and the partition 2. After the skin 1, partition 2, end ribs 3, root ribs 4, conformal antenna 5, and core 6 are fixed together, they form an integral structure. The skin 1 and partition 2 are bolted to the leading edge of the wing.

[0023] During assembly, the conformal antenna 5 is inserted into the core 6, and then the conformal antenna 5 and core 6 are combined and placed into the skin 1. The partition 2 is then placed on top, and finally the end ribs 3 and root ribs 4 are installed to complete the integral fixation. During disassembly, the skin 1, partition 2, end ribs 3, root ribs 4, conformal antenna 5, and core 6 are removed from the leading edge of the wing as a whole, and then replaced as a whole. The structure is simple, the installation is reliable, which is beneficial to improving aerodynamic efficiency and reducing weight. It is also easy to replace the conformal antenna 5, and the replacement cost is low. The conformal antenna 5 has good rigidity and, when installed on the leading edge of the wing, can enhance the wing structure's resistance to bird strikes.

[0024] like Figure 3 Preferably, the cross-section of the skin 1 is an airfoil leading edge structure.

[0025] like Figure 4 Preferably, the partition 2 has a groove-shaped structure, and the two sides of the partition 2 are folded upward to form flanges. The flanges are attached to the inner wall of the skin 1, and then bolted to the front edge of the wing through the flanges to increase the contact area between the partition 2 and the skin 1.

[0026] like Figures 5-6 Preferably, the end rib 3 and the root rib 4 are the same as the cross-section of the airfoil at their respective positions. The end rib 3 is provided with a first antenna through hole 7 that cooperates with the conformal antenna 5, and the root rib 4 is provided with a second antenna through hole 8 that cooperates with the conformal antenna 5. The interior of the end rib 3 and the root rib 4 are provided with an inner groove, which is engaged with the core 6 to enhance the positioning of the conformal antenna 5.

[0027] like Figure 7 Preferably, the core 6 is made of foam material, and a third antenna through-hole 9 that cooperates with the conformal antenna 5 is opened in the core 6 to improve the antenna's vibration resistance.

[0028] Preferably, the conformal antenna 5 is glued and fixed to the first antenna via 7, the second antenna via 8, and the third antenna via 9.

[0029] The skin 1, partition 2, end rib 3, root rib 4 and core 6 are all made by composite material molding method. By applying adhesive to the first antenna through hole 7, the second antenna through hole 8 and the third antenna through hole 9, the conformal antenna 5 is inserted into the first antenna through hole 7, the second antenna through hole 8 and the third antenna through hole 9 to complete the fixation.

[0030] Preferably, the skin 1, partition 2, end rib 3 and root rib 4 are all made of wave-transparent material to facilitate inspection of the installation status of the conformal antenna 5.

[0031] Finally, it should be noted that the accompanying drawings of the embodiments disclosed in this invention only involve the structures involved in the embodiments disclosed in this invention. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of this invention can be combined with each other.

[0032] In conclusion, the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A conformal antenna mounted on the leading edge of a wing, characterized in that: The device includes a skin (1), a partition (2), end ribs (3), root ribs (4), a conformal antenna (5), and a core (6). The skin (1) is a bent structure with an opening on one side. The partition (2) is fixedly connected to the opening of the skin (1), and a cavity is formed between the skin (1) and the partition (2). The conformal antenna (5) is a columnar structure with equal diameter. The conformal antenna (5) and the core (6) are both located in the cavity. The end ribs (3) and the root ribs (4) are fixedly connected to the two ends of the conformal antenna (5) and close the two ends of the cavity. The end ribs (3) and the root ribs (4) are fixedly connected to the skin (1) and the partition (2). The skin (1), partition (2), end ribs (3), root ribs (4), conformal antenna (5), and core (6) are fixed to form an integral structure. The skin (1) and the partition (2) are bolted to the front edge of the wing.

2. The conformal antenna mounted on the leading edge of the wing as described in claim 1, characterized in that: The skin (1) has a cross-section that is an airfoil leading edge structure.

3. The conformal antenna mounted on the leading edge of the wing as described in claim 2, characterized in that: The partition (2) has a groove-shaped structure. The two sides of the partition (2) are folded upward to form flanges, and the flanges are in contact with the inner wall of the skin (1).

4. The conformal antenna mounted on the leading edge of the wing as described in claim 1, characterized in that: The end rib (3) and the root rib (4) are the same as the cross-section of the airfoil at the location. The end rib (3) is provided with a first antenna through hole (7) that cooperates with the conformal antenna (5), and the root rib (4) is provided with a second antenna through hole (8) that cooperates with the conformal antenna (5).

5. The conformal antenna mounted on the leading edge of the wing as described in claim 4, characterized in that: The core (6) is made of foam material, and a third antenna through-hole (9) is provided inside the core (6) to cooperate with the conformal antenna (5).

6. The conformal antenna mounted on the leading edge of the wing as described in claim 5, characterized in that: The conformal antenna (5) is fixedly attached to the first antenna via (7), the second antenna via (8), and the third antenna via (9).

7. The conformal antenna mounted on the leading edge of the wing as described in claim 1, characterized in that: The skin (1), partition (2), end ribs (3) and root ribs (4) are all made of wave-transparent material.

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