Unmanned transport plane body structure

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle fuselage structure which comprises an upper skin, a lower skin and a framework. The plurality of upper skins are spliced and arranged on the top surface of the framework, and the lower skins are arranged on the bottom surface of the framework; the upper skin and the lower skin are attached to the outer surface of the framework and connected on the outer side of the framework. Wherein the lower skin is of an integrated structure. According to the unmanned transport plane body structure, the force transmission route is more visual, the manufacturing period is shorter, the manufacturing cost is lower, the structural weight is better reduced, the strength performance is improved, the structural strength is safe and reliable, and the unmanned transport plane body structure is easy to maintain.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a fuselage structure for an unmanned transport aircraft. Background Technology

[0002] With the development of the low-altitude economy, unmanned aerial vehicles (UAVs) are entering the logistics and transportation field, and UAVs with medium- and long-haul routes and large payloads are gradually becoming the mainstream.

[0003] Currently, the fuselage structure of traditional aircraft is either a four-panel fuselage structure or a segmented fuselage structure. The fuselage skin has a large number of parts, and multiple skin panels need to be connected and transitioned by recessed areas. This design increases the weight of the fuselage structure and makes the force transmission path less clear and linear. Utility Model Content

[0004] This invention provides a fuselage structure for an unmanned transport aircraft, which solves the problem that the existing fuselage structures have a large number of skins and connecting transition structures, resulting in a large weight and low strength.

[0005] This utility model provides a fuselage structure for an unmanned transport aircraft, including: an upper skin, a lower skin, and a frame;

[0006] The upper skin consists of multiple pieces, which are spliced ​​together and disposed on the top surface of the frame, while the lower skin is disposed on the bottom surface of the frame.

[0007] The upper skin and the lower skin are respectively attached to the outer surface of the skeleton, and the upper skin and the lower skin are connected to the outside of the skeleton;

[0008] The lower skin is an integrated structure.

[0009] According to the present invention, the fuselage structure of an unmanned transport aircraft includes a lower skin comprising a first composite layer, a sandwich layer, and a second composite layer.

[0010] The interlayer is sandwiched between the first composite layer and the second composite layer.

[0011] According to the unmanned transport aircraft fuselage structure provided by this utility model, both the first composite layer and the second composite layer are carbon fiber composite layers.

[0012] According to the present invention, the fuselage structure of an unmanned transport aircraft is a composite solid layer.

[0013] According to the present invention, the frame and the lower skin of an unmanned transport aircraft are connected by a first adhesive layer.

[0014] According to the present invention, the fuselage structure of an unmanned transport aircraft includes a crossbeam and a partition frame.

[0015] The crossbeam is arranged along the length of the fuselage structure, the partition is arranged along the width of the fuselage structure, and the crossbeam and the partition are fixedly connected.

[0016] The lower skin covers the crossbeam and the partition frame.

[0017] According to the unmanned transport aircraft fuselage structure provided by this utility model, at the connection between the upper skin and the lower skin, one of the upper skin and the lower skin is provided with a groove, and the other is provided with a protrusion;

[0018] The protrusion is inserted into the groove.

[0019] According to the present invention, in an unmanned transport aircraft fuselage structure, the mating surfaces of the groove and the protrusion are connected by a second adhesive layer.

[0020] According to the unmanned transport aircraft fuselage structure provided by this utility model, the second adhesive layer includes an adhesive layer and rivets;

[0021] The rivet is connected to the groove and the protrusion respectively, and the adhesive layer fills the peripheral wall of the rivet.

[0022] According to the present invention, a fuselage structure for an unmanned transport aircraft is provided, wherein multiple upper skin panels are connected sequentially along the length of the fuselage structure.

[0023] The unmanned transport aircraft fuselage structure provided by this utility model, by designing the lower skin of the fuselage as a one-piece molded structure, avoids the connection transition between the lower skin segments. This not only makes the force transmission path more intuitive, but also reduces the number of molds, lowers the manufacturing cost of molds, and facilitates subsequent production and maintenance. Compared with the traditional segmented lower skin structure, this utility model has a shorter manufacturing cycle, lower manufacturing cost, better reduces structural weight, improves strength performance, and ensures structural strength, safety, reliability, and ease of maintenance. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a partial schematic diagram of the fuselage structure of the unmanned transport aircraft provided by this utility model.

[0026] Figure 2 This is a side view of the fuselage structure of the unmanned transport aircraft provided by this utility model.

[0027] Figure label:

[0028] 1. Upper skin; 2. Lower skin;

[0029] 3. Frame; 31. Crossbeam; 32. Partition. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0031] The following is combined Figures 1-2 The fuselage structure of the unmanned transport aircraft provided in this utility model will be described in detail through specific embodiments and application scenarios.

[0032] like Figure 1 and Figure 2 As shown, this embodiment provides an unmanned transport aircraft fuselage structure, including: an upper skin 1, a lower skin 2, and a frame 3.

[0033] The upper skin 1 is provided in multiple pieces, and the multiple upper skin 1 pieces are spliced ​​together and set on the top surface of the frame 3, while the lower skin 2 is set on the bottom surface of the frame 3.

[0034] The upper skin 1 and the lower skin 2 are respectively attached to the outer surface of the skeleton 3, and the upper skin 1 and the lower skin 2 are connected on the outside of the skeleton 3.

[0035] Among them, the lower skin 2 is an integrated structure.

[0036] Understandably, multiple upper skin panels 1 can be in the form of four-sided panels, which are spliced ​​together to form a whole upper skin panel 1. Multiple upper skin panels 1 can also be in the form of segments, which are spliced ​​together sequentially along the length of the fuselage structure to form a whole upper skin panel 1.

[0037] The lower skin 2 is manufactured using a hand lay-up and pressurization process, and is integrally formed in a mold through a lay-up method. Because the lower skin 2 is integrally molded, the number of parts in the lower skin 2 is reduced, resulting in a lighter structural weight. Furthermore, the load can be quickly transferred to the entire fuselage structure through the frame 3 and the lower skin 2, making the force transmission path simpler and more intuitive, effectively improving strength performance.

[0038] Specifically, the connection between the upper skin 1 and the lower skin 2 can be a snap-fit ​​connection, a fastener connection, or an integrated curing connection.

[0039] Meanwhile, the upper skin 1 and the skeleton 3, as well as the lower skin 2 and the skeleton 3, can be connected by snap-fit, fasteners, or integrated curing.

[0040] For unmanned transport aircraft operating on medium- to long-haul routes with heavy payloads, such as an unmanned transport aircraft with a maximum takeoff weight of 1.2 tons, the lower skin 2 is designed as a single-piece structure. During the assembly of the unmanned transport aircraft's fuselage structure, firstly, the frame 3 and the lower skin 2 are glued together using structural adhesive. Then, the upper skin 1 is attached to the frame 3 from top to bottom. This invention features a simple connection structure, is easy to maintain, and has a stable and reliable structure.

[0041] The unmanned transport aircraft fuselage structure provided by this utility model, by designing the lower skin 2 of the fuselage as an integral molding structure, avoids the connection transition between the segments of the lower skin 2. This not only makes the force transmission path more intuitive, but also reduces the number of molds, lowers the manufacturing cost of molds, and facilitates subsequent production and maintenance. Compared with the traditional segmented lower skin 2 structure, the manufacturing cycle of this utility model is shorter, the manufacturing cost is lower, the structural weight is reduced, the strength performance is improved, the structural strength is safe and reliable, and it is easy to maintain.

[0042] like Figure 1 and Figure 2 As shown, the lower skin 2 in this embodiment includes a first composite layer, an interlayer, and a second composite layer.

[0043] The interlayer is sandwiched between the first composite layer and the second composite layer.

[0044] Understandably, the first and second composite layers are typically made of composite materials, with an interlayer sandwiched between them. Under bending loads, the first and second composite layers bear planar compressive and tensile loads, while the interlayer bears shear loads. Furthermore, the interlayer exhibits high bonding strength with both the first and second composite layers, effectively reducing stress concentration. This allows the unmanned transport aircraft to not only significantly reduce weight, improve flight performance and endurance during flight, but also enhance overall rigidity and fatigue resistance, while maintaining good design flexibility and corrosion resistance.

[0045] Specifically, the interlayer can be a foam layer.

[0046] like Figure 1 and Figure 2 As shown, both the first composite layer and the second composite layer in this embodiment are carbon fiber composite layers.

[0047] Understandably, carbon fiber composite layers are structural layers made by combining carbon fiber as a reinforcing material with matrix materials such as resin, metal, and ceramic.

[0048] The carbon fiber composite layer has high tensile strength, high tensile modulus of elasticity, low density, high temperature and corrosion resistance, and good electrical and thermal conductivity, as well as good fatigue resistance. The first and second composite layers of the lower skin 2 utilize carbon fiber composite layers, which can reduce weight and improve flight performance, resulting in greater flight stability.

[0049] like Figure 1 As shown, the skeleton 3 in this embodiment is a composite solid layer.

[0050] Understandably, the composite solid layer has a lower density than metal, which can significantly reduce the weight of the unmanned transport aircraft. The composite solid layer also has good strength and rigidity, significantly improving the structural strength and stability of the unmanned transport aircraft. Furthermore, the composite solid layer has good corrosion resistance, allowing for long-term use in various climates and environments, extending the service life of the unmanned transport aircraft and reducing maintenance costs.

[0051] Alternatively, the composite solid layer may be a carbon fiber composite solid layer.

[0052] like Figure 1 As shown, in this embodiment, the skeleton 3 and the lower skin 2 are connected by a first adhesive layer.

[0053] Understandably, the first bonding layer uses adhesive to bond the frame 3 and the lower skin 2. This first bonding layer improves the interfacial strength between the frame 3 and the lower skin 2, ensuring the strength and reliability of the connection. Furthermore, the first bonding layer promotes uniform stress distribution, improving the fatigue resistance of the connection. It also provides good sealing performance, preventing air and moisture ingress and improving the weather resistance of the unmanned transport aircraft. Since the frame 3 and lower skin 2 of the unmanned transport aircraft have irregular shapes, the first bonding layer can adapt well to these irregular structures, improving design flexibility.

[0054] Furthermore, rivets can be placed on the first adhesive layer to form a glued layer, further increasing the connection strength between the lower skin 2 and the skeleton 3.

[0055] like Figure 1 and Figure 2 As shown, the frame 3 in this embodiment includes a crossbeam 31 and a partition frame 32.

[0056] The crossbeam 31 is set along the length of the fuselage structure, and the partition is set along the width of the fuselage structure. The crossbeam 31 and the partition are fixedly connected.

[0057] The lower skin 2 covers the crossbeam 31 and the partition 32.

[0058] Understandably, there are multiple crossbeams 31, which extend along the length of the fuselage structure. There are also multiple partitions, which are perpendicularly connected to the crossbeams 31. The multiple crossbeams 31 and the multiple partitions form a spatial three-dimensional frame to support the weight of the entire fuselage.

[0059] The lower skin 2 covers the spatial three-dimensional frame composed of the crossbeam 31 and the partition frame, and is connected to the spatial three-dimensional frame through the first adhesive layer. Based on the characteristics of the first adhesive layer, such as high connection strength, uniform stress distribution and good sealing performance, the lower skin 2 and the spatial three-dimensional frame can achieve a high-strength and highly adaptable connection through the first adhesive layer.

[0060] like Figure 1 As shown, in this embodiment, at the connection between the upper skin 1 and the lower skin 2, one of the upper skin 1 and the lower skin 2 is provided with a groove, and the other is provided with a protrusion.

[0061] The protrusion is inserted into the groove.

[0062] Understandably, the insertion connection of the groove and the protrusion allows the connection between the upper skin 1 and the lower skin 2 to be accurately positioned and aligned. Furthermore, the fact that the protrusion is locked in the groove prevents it from moving, ensuring that the upper skin 1 and the lower skin 2 fit tightly together after connection, thus preventing misalignment between the upper skin 1 and the lower skin 2.

[0063] Optionally, in this embodiment, a groove can be provided on the upper skin 1 and a protrusion can be provided on the lower skin 2, or a protrusion can be provided on the upper skin 1 and a groove can be provided on the lower skin 2.

[0064] like Figure 1 As shown, in this embodiment, the mating surfaces of the groove and the protrusion are connected by a second adhesive layer.

[0065] Understandably, to further increase the connection strength between the groove and the protrusion, the mating surfaces of the groove and the protrusion are connected by a second adhesive layer. The second adhesive layer improves the interface strength between the upper skin 1 and the lower skin 2, ensuring the robustness and reliability of the connection. Furthermore, the second adhesive layer enables uniform stress distribution, improving the fatigue resistance of the connection. It also provides good sealing performance, preventing air and moisture ingress and improving the weather resistance of the unmanned transport aircraft. Since the upper skin 1 and lower skin 2 of the unmanned transport aircraft have irregular shapes, the second adhesive layer can better adapt to these irregular structures, improving design flexibility.

[0066] like Figure 1 As shown, the second adhesive layer in this embodiment includes an adhesive layer and a rivet.

[0067] The rivets are connected to the grooves and protrusions respectively, and the adhesive layer fills the periphery of the rivets.

[0068] Understandably, a rivet joins a protrusion and a recess. An adhesive layer is provided on the rivet's perimeter; this adhesive fills the gaps between the rivet and the protrusion / recess, creating a unified structure and making the connection between the protrusion and recess more secure. The adhesive layer and the rivet's structure are simple to operate and have good mechanical properties.

[0069] The adhesive layer and rivet structure of this embodiment can increase the connection area of ​​the protrusions and grooves, enhance rigidity, improve the overall connection strength, and improve the stability of the unmanned transport aircraft during flight.

[0070] Alternatively, when connecting the protrusion and the groove, the rivet can be installed either before the adhesive layer cures and then cured, or the rivet can be installed after the adhesive layer has cured.

[0071] like Figure 1 As shown, in this embodiment, multiple upper skin panels 1 are connected sequentially along the length of the fuselage structure.

[0072] It is understood that the multiple upper skin panels 1 in this embodiment adopt a segmented structure, which is divided into multiple panels from beginning to end, and the multiple panels are connected sequentially along the length of the fuselage structure.

[0073] Specifically, in this embodiment, the upper skin 1 has three parts, namely the head, middle and tail. The head, middle and tail are connected in sequence.

[0074] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A fuselage structure for an unmanned transport aircraft, characterized in that, include: Upper skin, lower skin, and skeleton; The upper skin consists of multiple pieces, which are spliced ​​together and disposed on the top surface of the frame, while the lower skin is disposed on the bottom surface of the frame. The upper skin and the lower skin are respectively attached to the outer surface of the skeleton, and the upper skin and the lower skin are connected to the outside of the skeleton; The lower skin is an integrated structure. The lower skin includes a first composite layer, an interlayer, and a second composite layer; The interlayer is sandwiched between the first composite layer and the second composite layer.

2. The unmanned transport aircraft fuselage structure according to claim 1, characterized in that, Both the first composite layer and the second composite layer are carbon fiber composite layers.

3. The unmanned transport aircraft fuselage structure according to claim 1, characterized in that, The skeleton is a composite solid layer.

4. The unmanned transport aircraft fuselage structure according to claim 1, characterized in that, The skeleton and the lower skin are connected by a first adhesive layer.

5. The unmanned transport aircraft fuselage structure according to claim 4, characterized in that, The frame includes crossbeams and partitions; The crossbeam is arranged along the length of the fuselage structure, the partition is arranged along the width of the fuselage structure, and the crossbeam and the partition are fixedly connected. The lower skin covers the crossbeam and the partition frame.

6. The unmanned transport aircraft fuselage structure according to claim 1, characterized in that, At the connection between the upper skin and the lower skin, one of the upper skin and the lower skin is provided with a groove, and the other is provided with a protrusion; The protrusion is inserted into the groove.

7. The unmanned transport aircraft fuselage structure according to claim 6, characterized in that, The mating surfaces of the groove and the protrusion are connected by a second adhesive layer.

8. The unmanned transport aircraft fuselage structure according to claim 7, characterized in that, The second adhesive layer includes an adhesive layer and rivets; The rivet is connected to the groove and the protrusion respectively, and the adhesive layer fills the peripheral wall of the rivet.

9. The unmanned transport aircraft fuselage structure according to claim 1, characterized in that, Multiple upper skin panels are connected sequentially along the length of the fuselage structure.

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