Unmanned aerial vehicle fuselage structure

Abstract

The utility model discloses an unmanned aerial vehicle fuselage structure which comprises a skin, a longitudinal beam, a floor, a conformal antenna support, a plurality of common frames and force bearing frames, the force bearing frames are evenly distributed in the middle of the floor, and the common frames are arranged at the two ends of the force bearing frames; the longitudinal beams are arranged between the adjacent force bearing frames; the conformal antenna bracket comprises a first conformal antenna bracket and a second conformal antenna bracket; the first conformal antenna bracket and the second conformal antenna bracket are respectively arranged on the first skin and the second skin; by adopting the technical scheme, the plurality of bearing frames are uniformly distributed in the middle of the floor, and the common frames are arranged at the two ends of the bearing frames; the longitudinal beams are arranged between the adjacent force bearing frames; the first shape-preserving antenna bracket and the second shape-preserving antenna bracket are respectively arranged on the first skin and the second skin, so that the weight of the fuselage is reduced, the array equipment can be modularly designed to be convenient to replace and maintain, and the space utilization rate of the fuselage is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle facilities, and in particular to a fuselage structure of an unmanned aerial vehicle. Background Art

[0002] At present, my country's UAV industry is developing rapidly, and large-scale long-flight UAVs are widely used in relay, broadcasting, exploration and other fields. With the application of large array geophysical antennas on UAVs, due to the space limitations of the traditional configuration of the body structure, the geophysical antenna array needs to be installed externally, which affects the aerodynamic shape of the UAV and increases fuel consumption. At the same time, the extra weight of the body structure increases, reducing the fuel carrying capacity, resulting in a significant decrease in range and flight time, and reduced mission execution efficiency.

[0003] Based on this, this application is made. Utility Model Content

[0004] The technical problem to be solved by the utility model is to provide a UAV fuselage structure which reduces the weight of the fuselage, enables modular design of array equipment for easy replacement and maintenance, and improves the utilization of fuselage space.

[0005] In order to solve the above technical problems, the technical solution of the utility model is:

[0006] A drone fuselage structure comprises a skin, a longitudinal beam, a floor, a conformal antenna bracket, a plurality of common frames and a bearing frame, wherein the plurality of bearing frames are evenly arranged in the middle of the floor, and the common frames are arranged at both ends of the bearing frames; the longitudinal beam is arranged between adjacent bearing frames; the skin comprises a first skin, a second skin, a third skin, a fourth skin, a fifth skin and a sixth skin, wherein the first skin and the second skin are respectively arranged at both sides of the bearing frame, the third skin and the fourth skin are respectively arranged at both ends of the bearing frame, and the fifth skin and the sixth skin are respectively arranged at the top of the bearing frame and the bottom of the floor;

[0007] The conformal antenna bracket comprises a first conformal antenna bracket and a second conformal antenna bracket, and the first conformal antenna bracket and the second conformal antenna bracket are respectively arranged on the first skin and the second skin.

[0008] Preferably, a hinge is provided between one side of the conformal antenna bracket and the skin.

[0009] Preferably, wing joint lugs are provided on both sides of the load-bearing frame, and the wing joint lugs and the load-bearing frame are manufactured by machining.

[0010] Preferably, the first skin, the second skin, the floor and the longitudinal beam constitute a fuel tank compartment, and a sealant is provided between the first skin, the second skin, the floor and the longitudinal beam, and the sealant is HM105 sealant from Beijing Institute of Aeronautical Materials.

[0011] Preferably, the conformal antenna bracket includes a reinforcement frame, a grille and a wave-transmitting wall panel, a plurality of grids are evenly distributed in the middle of the reinforcement frame, the wave-transmitting wall panel is arranged on one side of the reinforcement frame, and the reinforcement frame, the grille and the wave-transmitting wall panel are made by co-curing and integrally molding.

[0012] Preferably, the skin, common frame, longitudinal beam and floor are made of T700 carbon fiber-epoxy resin composite material, with isotropic ultimate tensile strength ≥500Mpa and equivalent modulus ≥70Gpa.

[0013] Preferably, the load-bearing frame is machined from 7050-T7451 aluminum alloy, with a tensile strength of ≥510Mpa and a modulus of ≥70Gpa.

[0014] Preferably, the opening and closing angle of the hinge is greater than 90°.

[0015] Preferably, the reinforcement frame and the grille are made of T700 carbon fiber-epoxy resin composite material, and the wave-transmitting skin is made of ultra-high molecular weight polyethylene fiber-epoxy resin composite material, with a comprehensive dielectric constant of ≤3.0 and a tangent loss tgδ≤0.002.

[0016] Preferably, a maintenance cover is provided on the third skin.

[0017] By adopting the above technical scheme, since the several load-bearing frames are evenly distributed in the middle of the floor, the common frames are arranged at both ends of the load-bearing frames; the longitudinal beams are arranged between adjacent load-bearing frames; the first conformal antenna bracket and the second conformal antenna bracket are respectively arranged on the first skin and the second skin, the fuselage structure of the UAV is reduced in weight, the array equipment can be modularly designed for easy replacement and maintenance, and the utilization rate of the fuselage space is improved. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0019] Figure 2 It is an exploded view of the utility model;

[0020] Figure 3 It is a structural schematic diagram of the utility model conformal antenna bracket;

[0021] Figure 4 It is a structural schematic diagram of the load-bearing frame of the utility model.

[0022] In the figure, 1-skin, 2-longitudinal beam, 3-floor, 4-conformal antenna bracket, 5-ordinary frame, 6-load-bearing frame, 7-hinge, 8-wing joint ear, 9-fuel tank compartment, 10-

[0023] Maintenance cover, 101-first skin, 102-second skin, 103-third skin, 104-fourth skin, 105-fifth skin, 106-sixth skin, 401-

[0024] First conformal antenna bracket, 402-second conformal antenna bracket, 403-reinforcement frame, 404-grid, 405-wave-transparent wall panel. DETAILED DESCRIPTION

[0025] The specific implementation methods of the present invention are further described below in conjunction with the accompanying drawings. It should be noted that the description of these implementation methods is used to help understand the present invention, but does not constitute a limitation of the present invention. In addition, the technical features involved in each implementation method of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0026] like Figure 1-4 As shown, a UAV fuselage structure includes a skin, a longitudinal beam, a floor, a conformal antenna bracket, a plurality of common frames and a bearing frame, wherein the plurality of bearing frames are evenly arranged in the middle of the floor, and the common frames are arranged at both ends of the bearing frames; the longitudinal beam is arranged between adjacent bearing frames; the skin includes a first skin, a second skin, a third skin, a fourth skin, a fifth skin and a sixth skin, wherein the first skin and the second skin are respectively arranged at both sides of the bearing frame, the third skin and the fourth skin are respectively arranged at both ends of the bearing frame, and the fifth skin and the sixth skin are respectively arranged at the top of the bearing frame and the bottom of the floor;

[0027] The conformal antenna bracket includes a first conformal antenna bracket and a second conformal antenna bracket, and the first conformal antenna bracket and the second conformal antenna bracket are respectively arranged on the first skin and the second skin, which reduces the weight of the fuselage, and the array equipment can be modularly designed for easy replacement and maintenance, and the fuselage space utilization is improved.

[0028] In addition, a hinge is provided between one side of the conformal antenna bracket and the skin, and the conformal antenna bracket can rotate around the hinge with a rotation angle of 100 degrees, so that the conformal antenna bracket can be fully opened for easy maintenance and replacement.

[0029] Furthermore, wing joint ears are provided on both sides of the load-bearing frame, and the wing joint ears and the load-bearing frame are machined together to improve the connection strength between the load-bearing frame and the wing joint ears.

[0030] In addition, the first skin, the second skin, the floor and the longitudinal beam constitute the fuel tank compartment, and a sealant is provided between the first skin, the second skin, the floor and the longitudinal beam. The sealant is HM105 sealant from Beijing Institute of Aeronautical Materials, which improves the sealing effect between the first skin, the second skin, the floor and the longitudinal beam.

[0031] Furthermore, the conformal antenna bracket includes a reinforcement frame, a grille and a wave-transmitting wall panel. A plurality of grids are evenly distributed in the middle of the reinforcement frame, and the wave-transmitting wall panel is arranged on one side of the reinforcement frame. The reinforcement frame, the grille and the wave-transmitting wall panel are made of co-curing and integrally molded, thereby improving the overall strength of the conformal antenna bracket, while improving production efficiency and reducing production costs.

[0032] In addition, the skin, common frame, longitudinal beam and floor are made of T700 carbon fiber-epoxy resin composite material, with isotropic ultimate tensile strength ≥500Mpa and equivalent modulus

[0033] ≥70Gpa.

[0034] Furthermore, the load-bearing frame is machined from 7050-T7451 aluminum alloy, with a tensile strength of ≥510Mpa and a modulus of ≥70Gpa.

[0035] Additionally, the hinge has an opening angle greater than 90°, allowing the conformal antenna bracket to be fully opened.

[0036] Furthermore, the reinforcement frame and the grille are made of T700 carbon fiber-epoxy resin composite material, and the wave-transmitting skin is made of ultra-high molecular weight polyethylene fiber-epoxy resin composite material, with a comprehensive dielectric constant of ≤3.0 and a tangent loss tgδ≤0.002.

[0037] In addition, a maintenance cover is provided on the third skin to facilitate fuselage maintenance.

[0038] The working principle of the utility model is as follows:

[0039] The antenna array or other array-type airborne equipment is installed inside the conformal antenna bracket, and the conformal antenna bracket is used to achieve aerodynamic shape maintenance and antenna load transfer;

[0040] The skin on both sides of the fuselage is set on the inner side of the conformal antenna bracket to bear various loads to ensure that the conformal antenna bracket only bears a lower load, so that it can be manufactured with low-strength wave-transparent materials and adopt a detachable connection method. At the same time, it can realize the flip function to provide a completely open channel for the maintenance of the antenna array or other equipment; the integral fuel tank is arranged under the fuselage floor, and the front and rear through-machine space is retained above the floor to facilitate the installation and maintenance of other equipment.

[0041] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited to the described embodiments. For those skilled in the art, various changes, modifications, substitutions and variations of these embodiments are made without departing from the principles and spirit of the present invention, and still fall within the scope of protection of the present invention.

Claims

1. A UAV fuselage structure, characterized in that: It includes a skin, a longitudinal beam, a floor, a conformal antenna bracket, a plurality of common frames and a bearing frame, wherein the plurality of bearing frames are evenly arranged in the middle of the floor, and the common frames are arranged at both ends of the bearing frame; the longitudinal beam is arranged between adjacent bearing frames; the skin includes a first skin, a second skin, a third skin, a fourth skin, a fifth skin and a sixth skin, wherein the first skin and the second skin are respectively arranged at both sides of the bearing frame, the third skin and the fourth skin are respectively arranged at both ends of the bearing frame, and the fifth skin and the sixth skin are respectively arranged at the top of the bearing frame and the bottom of the floor; The conformal antenna bracket comprises a first conformal antenna bracket and a second conformal antenna bracket, and the first conformal antenna bracket and the second conformal antenna bracket are respectively arranged on the first skin and the second skin.

2. The UAV fuselage structure according to claim 1, characterized in that: A hinge is provided between one side of the conformal antenna bracket and the skin.

3. The UAV fuselage structure according to claim 1, characterized in that: Wing joint lugs are arranged on both sides of the load-bearing frame, and the wing joint lugs and the load-bearing frame are made of one piece by machining.

4. The UAV fuselage structure according to claim 1, characterized in that: The first skin, the second skin, the floor and the longitudinal beam constitute a fuel tank compartment, and a sealant is provided between the first skin, the second skin, the floor and the longitudinal beam, and the sealant is HM105 sealant of Beijing Institute of Aeronautical Materials.

5. The UAV fuselage structure according to claim 2, characterized in that: The conformal antenna bracket includes a reinforcement frame, a grille and a wave-transmitting wall plate. A plurality of grids are evenly distributed in the middle of the reinforcement frame. The wave-transmitting wall plate is arranged on one side of the reinforcement frame. The reinforcement frame, the grille and the wave-transmitting wall plate are made by co-curing and integrally molding.

6. The UAV fuselage structure according to claim 2, characterized in that: The skin, common frame, longitudinal beam and floor are made of T700 carbon fiber-epoxy resin composite material, with isotropic ultimate tensile strength ≥500Mpa and equivalent modulus ≥70Gpa.

7. The UAV fuselage structure according to claim 3, characterized in that: The load-bearing frame is machined from 7050-T7451 aluminum alloy, with a tensile strength of ≥510Mpa and a modulus of ≥70Gpa.

8. The UAV fuselage structure according to claim 2, characterized in that: The opening and closing angle of the hinge is greater than 90°.

9. The UAV fuselage structure according to claim 5, characterized in that: The reinforcement frame and the grille are made of T700 carbon fiber-epoxy resin composite material, and the wave-transmitting skin is made of ultra-high molecular weight polyethylene fiber-epoxy resin composite material, with a comprehensive dielectric constant of ≤3.0 and a tangent loss tgδ≤0.

002.

10. The UAV fuselage structure according to claim 1, characterized in that: A maintenance cover is provided on the third skin.

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