Composite board frame structure of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle composite board frame structure which relates to the technical field of unmanned aerial vehicles and comprises two side plates, a bottom transverse plate, a top plate and a top transverse plate are connected between the two side plates in a mortise and tenon joint mode, an end plate is connected to one side of each side plate in a mortise and tenon joint mode, and longitudinal plates are connected to the interiors of the bottom transverse plate and the end plates in a mortise and tenon joint mode. Each of the side plates, the bottom transverse plate, the end plates, the top plate and the top transverse plate comprises two carbon fiber plate layers and a foamed aluminum layer in the middle, composite plates of the carbon fiber plate layers and the foamed aluminum layers are cooperatively matched with tenon-and-mortise connection structures, the whole structure is in mutual tenon-and-mortise connection and supporting to form a whole machine frame, and the low density, high strength and low cost of the carbon fiber plates are fully utilized. The unmanned aerial vehicle has the advantages of high strength, high tensile strength, uniform omnidirectional strength and high rigidity of the foamed aluminum layer, so that the device is light in weight, the strength can be ensured, and the cruising ability and the load performance of the unmanned aerial vehicle are improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles (UAVs), and in particular relates to a composite plate frame structure for an UAV. Background Art

[0002] Large UAVs play a key role in transportation and rescue due to their excellent load-bearing capacity and endurance. They can break through geographical restrictions and quickly deliver heavy cargo such as medical equipment and disaster relief supplies to remote areas such as mountainous areas and islands with inconvenient transportation. The body frame structure of large UAVs mainly uses titanium alloy or aluminum alloy pipe welded skeleton as the main load-bearing frame, covered with composite materials or metal skin to form a complete aerodynamic shape.

[0003] The traditional UAV metal frame structure causes the entire machine to be too heavy, thereby reducing the UAV's endurance and load performance. To solve the above problems, we provide a UAV composite plate frame structure. Utility Model Content

[0004] The purpose of the present invention is to provide a composite plate frame structure for a UAV to solve the problem in the above-mentioned background technology that the traditional metal frame structure of a UAV causes the weight of the entire machine to be too large, thereby reducing the endurance and load performance of the UAV.

[0005] The above technical objectives of the present invention are achieved through the following technical solutions: a composite plate frame structure for a drone, comprising two side panels, a bottom transverse plate, a top plate, and a top transverse plate connected between the two side panels by mortise and tenon joints, an end plate connected by mortise and tenon joints on one side of the side panels, and a longitudinal plate connected by mortise and tenon joints inside the bottom transverse plate and the end plates;

[0006] The side panels, bottom transverse panels, end panels, top panels and top transverse panels all include two carbon fiber plate layers and a foam aluminum layer in the middle.

[0007] Preferably, the foam aluminum layer has a density of approximately 0.25 g / cm³ and a thickness of 7 mm, and the carbon fiber board layer has a density of approximately 1.7 g / cm³ and a thickness of 1 mm.

[0008] Preferably, two frame mechanisms are provided between the two side panels, and the frame mechanisms include two arc tubes, the two ends of the arc tubes are respectively connected to the bottom horizontal plate and the top horizontal plate by mortise and tenon joints, and two connecting tubes are fixedly connected between the two arc tubes, a first carbon fiber tube is fixedly sleeved inside the arc tube, both ends of the first carbon fiber tube are fixedly sleeved with the side panels, a second carbon fiber tube is fixedly sleeved on one side of the arc tube, and one end of the second carbon fiber tube is fixedly sleeved with the side panel.

[0009] Preferably, a connector is bolted to one side of the side panel, an outer side of the connector is bolted to the top horizontal panel, and a lifting ring is threadedly connected to the top of the connector.

[0010] Preferably, through holes are provided inside the side panels, bottom transverse panels, end panels, top panels and top transverse panels, and the bottom of the top transverse panel is connected to the top panel by mortise and tenon joints.

[0011] The utility model has the following beneficial effects:

[0012] The device uses a composite panel composed of carbon fiber panels and foam aluminum layers in coordination with a mortise and tenon joint structure. The overall structure is connected and supported by mortise and tenon joints to form the entire machine frame. It fully utilizes the advantages of low density and high tensile strength of carbon fiber panels, as well as the advantages of uniform omnidirectional strength and high rigidity of foam aluminum layers, making the device light while ensuring strength, thereby improving the UAV's endurance and payload performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a three-dimensional schematic diagram of the structure of the utility model;

[0014] Figure 2 This is an exploded view of the local structure of the utility model;

[0015] Figure 3 It is a three-dimensional diagram of the local structure of the utility model;

[0016] Figure 4 It is a three-dimensional diagram of the local structure of the utility model;

[0017] Figure 5 This utility model Figure 3 A partial enlarged view of point A in the middle;

[0018] Figure 6 It is a partial structural sectional view of the utility model.

[0019] Figure numerals: 1, side panel; 2, bottom horizontal panel; 3, end panel; 4, longitudinal panel; 5, top panel; 6, top horizontal panel; 7, frame mechanism; 701, arc tube; 702, connecting tube; 703, first carbon fiber tube; 704, second carbon fiber tube; 8, connecting piece; 9, lifting ring; 101, carbon fiber plate layer; 102, foam aluminum layer. DETAILED DESCRIPTION

[0020] The present invention will be described in further detail below with reference to the accompanying drawings.

[0021] Example 1:

[0022] refer to Figure 1-6A composite plate frame structure for a drone includes two side panels 1, a bottom transverse panel 2, a top panel 5, and a top transverse panel 6 are connected between the two side panels 1 by mortise and tenon joints, an end panel 3 is connected to one side of the side panel 1 by mortise and tenon joints, and a longitudinal panel 4 is connected to the bottom transverse panel 2 and the end panel 3 by mortise and tenon joints inside.

[0023] The side panels 1 , the bottom transverse panel 2 , the end panels 3 , the top panel 5 and the top transverse panel 6 each include two carbon fiber plate layers 101 and a foam aluminum layer 102 in between.

[0024] Specifically, the connection between the side panels 1, the bottom transverse panels 2, the end panels 3, the top panels 5, the top transverse panels 6 and the longitudinal panels 4 adopts a mortise and tenon structure, which specifically includes but is not limited to: straight tenons plus adhesives, the gap between the tenons and mortises is matched, and glue is applied to the joint surface to enhance the bonding strength, and a rigid connection is formed after curing. The number of bottom transverse panels 2 and end panels 3 is preferably four, but those skilled in the art can adjust their number according to actual needs. The number of longitudinal panels 4 is preferably ten, but those skilled in the art can adjust their number according to actual needs. The number of top transverse panels 6 is preferably two, but those skilled in the art can adjust their number according to actual needs.

[0025] refer to Figure 6 The density of the foam aluminum layer 102 is about 0.25g / cm³ and the thickness is 7mm. The density of the carbon fiber board layer 101 is about 1.7g / cm³ and the thickness is 1mm. The overall density of the composite board is about 0.5g / cm³, forming a high-strength, low-density composite board.

[0026] refer to Figure 3 and Figure 4 Two frame mechanisms 7 are provided between the two side panels 1. The frame mechanism 7 includes two arc tubes 701. The two ends of the arc tube 701 are respectively connected to the bottom transverse plate 2 and the top transverse plate 6 by mortise and tenon joints. Two connecting tubes 702 are fixedly connected between the two arc tubes 701. A first carbon fiber tube 703 is fixedly sleeved inside the arc tube 701. Both ends of the first carbon fiber tube 703 are fixedly sleeved with the side panel 1. A second carbon fiber tube 704 is fixedly sleeved on one side of the arc tube 701. One end of the second carbon fiber tube 704 is fixedly sleeved with the side panel 1, which is used to improve the strength of the UAV cabin door frame.

[0027] refer to Figure 5 One side of the side panel 1 is bolted with a connector 8, the outer side of the connector 8 is bolted to the top horizontal plate 6, and the top of the connector 8 is threadedly connected to a lifting ring 9. By setting the lifting ring 9, the device can be easily hoisted.

[0028] refer to Figure 2The side panels 1, bottom transverse panels 2, end panels 3, top panels 5 and top transverse panels 6 are all provided with through holes. The bottom of the top transverse panel 6 is connected to the top panel 5 by mortise and tenon joints. By setting through holes, triangular holes and circular holes are used in the preferred embodiment. Those skilled in the art should understand that the shape can be adjusted according to actual needs to reduce the weight of the composite panel, but its strength can meet the requirements of the whole machine.

[0029] Brief description of usage process: The overall structure of the device is connected with mortise and tenon joints to form the whole machine frame, which fully utilizes the advantages of low density and high tensile strength of the carbon fiber plate layer 101 and the advantages of uniform omnidirectional strength and high rigidity of the foam aluminum layer 102, making the device light in weight while ensuring the strength of the whole machine.

[0030] This specific embodiment is merely an explanation of the present invention and is not a limitation of the present invention. After reading this specification, those skilled in the art may make non-creative modifications to the present embodiment as needed. However, as long as they are within the scope of the claims of the present invention, they are protected by patent law.

Claims

1. A composite plate frame structure for an unmanned aerial vehicle, comprising two side panels (1), characterized in that: A bottom transverse plate (2), a top plate (5) and a top transverse plate (6) are connected between the two side plates (1) by mortise and tenon joints, an end plate (3) is connected to one side of the side plates (1) by mortise and tenon joints, and a longitudinal plate (4) is connected to the inner mortise and tenon joints of the bottom transverse plate (2) and the end plate (3); The side panels (1), bottom transverse panels (2), end panels (3), top panels (5) and top transverse panels (6) all include two carbon fiber plate layers (101) and a foamed aluminum layer (102) in between.

2. The composite plate frame structure for a drone according to claim 1, characterized in that: The foam aluminum layer (102) has a density of approximately 0.25 g / cm³ and a thickness of 7 mm, and the carbon fiber plate layer (101) has a density of approximately 1.7 g / cm³ and a thickness of 1 mm.

3. The composite plate frame structure for a drone according to claim 1, characterized in that: Two frame mechanisms (7) are provided between the two side panels (1), and the frame mechanism (7) comprises two arc-shaped tubes (701), the two ends of the arc-shaped tubes (701) are respectively connected to the bottom transverse plate (2) and the top transverse plate (6) by mortise and tenon joints, two connecting tubes (702) are fixedly connected between the two arc-shaped tubes (701), a first carbon fiber tube (703) is fixedly sleeved inside the arc-shaped tube (701), both ends of the first carbon fiber tube (703) are fixedly sleeved with the side panels (1), a second carbon fiber tube (704) is fixedly sleeved on one side of the arc-shaped tube (701), and one end of the second carbon fiber tube (704) is fixedly sleeved with the side panels (1).

4. The composite plate frame structure for a drone according to claim 1, characterized in that: A connecting piece (8) is bolted to one side of the side plate (1), the outer side of the connecting piece (8) is bolted to the top transverse plate (6), and a lifting ring (9) is threadedly connected to the top of the connecting piece (8).

5. The composite plate frame structure for a UAV according to claim 1, characterized in that: Through holes are provided inside the side panels (1), bottom transverse panels (2), end panels (3), top panels (5) and top transverse panels (6), and the bottom of the top transverse panels (6) is connected to the top panel (5) by mortise and tenon joints.

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