Wing and fuselage structure of fixed-wing unmanned aerial vehicle suitable for carrying flight
By employing a three-section wing structure and streamlined design, the problem of insufficient payload capacity in traditional fixed-wing UAVs has been solved, achieving a high payload ratio and low-cost rapid assembly and disassembly, thereby improving the payload capacity and flight efficiency of UAVs.
Patent Information
- Application Number
- CN202520295533.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-24
- Publication Date
- 2025-12-19
- Estimated Expiration
- 2035-02-24
AI Technical Summary
Traditional fixed-wing drones suffer from limited wing lift, insufficient storage space in the fuselage, and complex structure, resulting in insufficient payload capacity and high cost, making it difficult to meet the needs of rapid production and practical application.
It adopts a three-section wing structure, with the middle section of the wing nested and connected to the cargo bay, and the outer section of the wing connected to the middle section using mortise and tenon joints and pins. Combining carbon fiber and linden wood materials, it is designed with streamlined and trapezoidal airfoils to increase lift and reduce manufacturing costs.
It achieves high payload ratio and low cost for rapid assembly and disassembly, meets the strength requirements for heavy-load flight, and improves the payload capacity and flight efficiency of UAVs.
Smart Images
Figure CN223686859U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to fixed wing unmanned plane technical field, concretely is a kind of fixed wing unmanned plane wing and fuselage structure suitable for carrying flight. BACKGROUND
[0002] Fixed wing unmanned plane has unique advantage in many aspects such as speed, endurance, load, voyage, self structure, can select multiple flight modes, changes energy consumption mode according to different functions, cruise system low energy consumption, with the characteristics and advantages of large load, high endurance, more energy saving and economic, can work in the environment that other types of unmanned plane cannot adapt, not only can be applied to boundary patrol, military defense and other fields, in the field of agriculture, industry, plant protection has extremely important application value. For a long time, fixed wing unmanned plane is difficult to be widely applied due to its complex structure design and high cost, which limits the development and practical application of fixed wing unmanned plane. With the demand of fixed wing unmanned plane carrying material and landing with load, for example, in crop sowing, land detection, cruise investigation.
[0003] Traditional fixed wing aircraft cannot meet the demand of carrying and rapid production due to the limited wing lift, limited storage space of fuselage compartment and complex production, therefore, improvement needs to be made on traditional fixed wing aircraft to increase wing lift and storage space of compartment to adapt to existing technical demand. UTILITY MODEL CONTENT
[0004] To solve the problems in the above background art, the utility model aims at providing a fixed wing unmanned plane wing and fuselage structure suitable for carrying flight, which has the advantages of high load ratio, low cost and quick disassembly and assembly.
[0005] To achieve the above-mentioned purpose, the utility model provides the following technical scheme: a fixed wing unmanned plane wing and fuselage structure suitable for carrying flight, comprising a carrying compartment and a wing body, the wing body comprises a wing support beam, the wing body comprises a wing outer segment, a wing middle segment and a wing connecting mechanism, the surface of the carrying compartment is provided with a connecting U-shaped groove, the inside of the carrying compartment is respectively provided with a 3mm basswood board and a 3mm carbon fiber board, the wing support beam comprises a 5x5 carbon square tube, a 1.5mm carbon fiber board and a basswood board structure support, the surface of the carrying compartment is provided with a carrying compartment U-shaped groove, the wing body comprises a wing middle segment beam and a wing rib, and the carrying compartment U-shaped groove is inserted with the wing middle segment beam.
[0006] As preferred in the utility model, the wing connecting mechanism comprises a wing middle segment jack provided on the surface of the wing middle segment, the surface of the wing outer segment is provided with a wing outer segment carbon fiber plug, the surface of the wing outer segment is provided with a latch hole, and the wing outer segment carbon fiber plug is inserted with the wing middle segment jack.
[0007] As the utility model is preferred, the whole of the object carrying bin is streamline design, the object carrying bin includes inner layer and outer layer, and the inner layer is 3mm carbon fiber plate, and the outer layer is 5mm Chinese lime wood board.
[0008] As the utility model is preferred, the wing body adopts slow airfoil, the chord length of the wing body is 0.425m, the span length of the wing body is 0.769m, and the aspect ratio of the wing body is 8.588.
[0009] As the utility model is preferred, the wing body layout adopts trapezoidal wing.
[0010] Compared with the prior art, the utility model has the beneficial effects as follows:
[0011] 1, the utility model adopts the wing body and divides into three section type structures, the wing body middle section is connected with the object carrying bin nesting, has + 3 ° angle of attack, the wing body middle section and the wing body outer section adopt mortise and tenon + bolt connection, meet the structural strength, can realize quick disassembly and quick installation simultaneously, the connecting part uses the bolt limit and fixes, meets the strength requirement of big load weight flight under the premise of not damaging aerodynamic performance, and the device has the advantages of high load ratio, low cost and quick disassembly.
[0012] 2, the utility model discloses the setting of wing middle section socket, wing outer section carbon fiber plug and bolt hole, and then realizes the stable connection of wing middle section and wing outer section. BRIEF DESCRIPTION OF DRAWINGS
[0013] Figure 1 It is the structure schematic diagram of the utility model;
[0014] Figure 2 It is the structure schematic diagram of the object carrying bin of the utility model;
[0015] Figure 3 It is the structure schematic diagram of the wing middle section of the utility model;
[0016] Figure 4 It is the structure schematic diagram of 5x5 carbon square tube of the utility model;
[0017] Figure 5 It is the connecting structure schematic diagram of wing middle section and wing outer section of the utility model;
[0018] Figure 6 It is the connecting structure schematic diagram of wing middle section and object carrying bin of the utility model.
[0019] In the figure: 1, the object carrying bin; 1-1, basswood board; 1-2, connecting U-shaped groove; 1-3, 3mm carbon fiber plate; 2, wing body; 2-1, wing outer section; 2-2, wing middle section; 2-3, wing connecting mechanism; 2-4, 5*5 carbon square tube; 2-5, 1.5mm carbon fiber plate; 2-6, basswood board structure support; 3, wing support beam; 3-1, wing middle section jack; 3-2, wing outer section carbon fiber plug; 3-3, bolt hole; 3-4, object carrying bin U-shaped groove; 3-5, wing middle section beam; 3-6, wing rib. DETAILED DESCRIPTION
[0020] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.
[0021] As shown in Figures 1 to 6 , a fixed-wing unmanned aerial vehicle wing and fuselage structure suitable for carrying flight, comprising an object carrying bin 1 and a wing body 2, the wing body 2 includes a wing support beam 3, the wing body 2 includes a wing outer section 2-1, a wing middle section 2-2 and a wing connecting mechanism 2-3, the surface of the object carrying bin 1 is provided with a connecting U-shaped groove 1-2, the inside of the object carrying bin 1 is respectively provided with a 3mm basswood board 1-1 and a 3mm carbon fiber plate 1-3, the wing support beam 3 includes a 5*5 carbon square tube 2-4, a 1.5mm carbon fiber plate 2-5 and a basswood board structure support 2-6, the surface of the object carrying bin 1 is provided with an object carrying bin U-shaped groove 3-4, the wing body 2 includes a wing middle section beam 3-5 and a wing rib 3-6, and the object carrying bin U-shaped groove 3-4 is inserted with the wing middle section beam 3-5.
[0022] Referring to Figure 5 , the wing connecting mechanism 2-3 includes a wing middle section jack 3-1 arranged on the surface of the wing middle section 2-2, the surface of the wing outer section 2-1 is provided with a wing outer section carbon fiber plug 3-2, the surface of the wing outer section 2-1 is provided with a bolt hole 3-3, and the wing outer section carbon fiber plug 3-2 is inserted with the wing middle section jack 3-1.
[0023] As a technical optimization scheme of the utility model, the wing middle section jack 3-1, the wing outer section carbon fiber plug 3-2 and the bolt hole 3-3 are arranged, so that the stable connection of the wing middle section 2-2 and the wing outer section 2-1 is realized.
[0024] Referring to Figure 2The whole of the object-carrying bin 1 is streamlined, the object-carrying bin 1 comprises an inner layer and an outer layer, and the inner layer is a 3mm carbon fiber plate 1-3, and the outer layer is a 5mm basswood plate 1-1.
[0025] As a technical optimization scheme of the utility model, the whole of the object-carrying bin 1 is streamlined, the object-carrying bin 1 is 760mm long, 270mm wide and 150mm high, the side of the object-carrying bin 1 is made of 2mm basswood combined with 1mm aviation plywood, the front of the object-carrying bin 1 and the connecting part of the battery bin and the power assembly are made of 3mm carbon fiber plate 1-3, the rear of the object-carrying bin 1 and the connecting part of the tail section are made of 3mm carbon fiber plate 1-3, the object-carrying bin 1 comprises an inner layer and an outer layer, and the inner layer is a 3mm carbon fiber plate 1-3, and the outer layer is a 5mm basswood plate 1-1, the cutting positions of the two pieces of wood are respectively arranged at different positions, and the two pieces of wood are staggered and superposed to enhance the torsional resistance, meanwhile, the hollow cross-shaped cross structure is adopted to reduce the weight, the position of the clamping groove of the object-carrying bin 1 is moved forward to the head direction, so that the center of gravity of the whole machine is close to the center of the front three-point landing gear to the maximum, and because of the aerodynamic requirement, the object-carrying bin 1 is located at the middle section of the whole machine.
[0026] Reference Figure 1 The wing body 2 adopts a slow airfoil, the chord length of the wing body 2 is 0.425m, the span length of the wing body 2 is 0.769m, and the aspect ratio of the wing body 2 is 8.588.
[0027] As a technical optimization scheme of the utility model, the wing body 2 adopts a slow airfoil, the chord length of the wing body 2 is 0.425m, the span length of the wing body 2 is 0.769m, and the aspect ratio of the wing body 2 is 8.588, compared with other airfoils, the slow airfoil has a larger lift coefficient Cl and a smaller drag coefficient Cd, so that the slow airfoil has a larger lift-drag ratio Cl / Cd, the flight efficiency is higher, and the slow airfoil can fly a farther distance under the same condition, the wing body 2 is built by cutting a light wood into an airfoil structure, and the wing body 2 is designed to be hollow and lightweight.
[0028] Reference Figure 1 The wing body 2 adopts a trapezoidal wing.
[0029] As a technical optimization scheme of the utility model, the wing body 2 adopts a trapezoidal wing, which has the advantages of low induced drag, good lift performance at low speed, and convenient manufacturing and processing.
[0030] The working principle and use process of the utility model: when using, the nose, the power group, the battery compartment and the fairing are all installed in the front part of the object carrying compartment 1, the power group paddle is installed in parallel with the wing body 2, the wing body 2 bearing beam is composed of 1.5mm carbon fiber plate 2-5, 5*5 carbon square tube 2-4 and PMI foam composite material, adopts the sandwich structure of carbon fiber + PMI foam composite material + carbon fiber, firstly builds the basic skeleton structure by 5*5 carbon square tube, the outermost layer of the wing body 2 bearing beam is cut into a hollow structure by 1.5 carbon fiber plate, the inside is wrapped with 5mm PMI foam composite material as support, so as to provide certain variable when landing with load, achieve the damping effect, increase the stress surface, reduce the pressure, ensure the safety of the materials and equipment, increase the torsional performance, the wing body 2 is divided into three section structures, the middle section of the wing body 2 is connected with the object carrying compartment 1 in nesting mode, has +3 degree attack angle, the middle section of the wing body 2 is connected with the outer section of the wing body 2 in mortise + bolt connection mode, meets the structural strength, can realize quick disassembly and quick assembly, the connecting part is fixed by limiting the bolt, meets the strength requirement of large load carrying flight under the premise of not damaging the aerodynamic performance;
[0031] The object carrying compartment 1 and the wing middle section 2-2 are connected and installed in the mode of clamping groove type beam, 7*22 clamping grooves are designed on the left and right of the object carrying compartment 1 respectively, and are inclined at +3 degree attack angle, so as to obtain more lift, the composite carbon beam is embedded in the object carrying compartment 1, at the same time, 2.5+2.5 aviation plate rods are inserted into the object carrying compartment 1 and the middle section composite beam respectively, so as to achieve the integrated effect, the object carrying compartment 1 is connected with the rear section and the tail of the unmanned aerial vehicle in the mode of sticking, the connection between the object carrying compartment 1 and the rear section adopts two pieces of carbon structure which have a high-precision cooperation with an error of not more than +0.1, uses high-strength throat clamp + rolling strip connection, the object carrying compartment 1 and the nose and the power group are connected and installed in the mode of screw + connection, considering that the nose is the power transmission center and bears large stress, the structural strength requirement is harsh, therefore, high-strength antiskid screws are used for fixing, four M3 threaded holes are precisely matched in the front plate of the object carrying compartment 1 and the aviation bearing plate behind the nose, and the antiskid screws are embedded, so as to achieve the ideal cooperation effect;
[0032] As above, due to the small load carrying capacity, large energy consumption and poor stability of the traditional fixed-wing unmanned aerial vehicle, the wing body 2 and the object carrying compartment 1 are designed, so as to realize the transportation of large load, reduce the energy consumption of the fixed-wing unmanned aerial vehicle, improve the use efficiency of the unmanned aerial vehicle, along with the great potential of the fixed-wing unmanned aerial vehicle in agricultural production, industrial application, plant protection, forest fire prevention, environmental quality monitoring, military exploration and astronomy, the utility model has certain industrial utilization value.
[0033] It is to be noted that, in the present document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.
[0034] While the embodiments of the present application have been illustrated and described, it will be understood by those skilled in the art that various changes, modifications, substitutions, and alterations can be made therein without departing from the spirit and scope of the application, which is defined by the appended claims and their equivalents.
Claims
1. A fixed-wing unmanned aerial vehicle wing and fuselage structure suitable for carrying objects, comprising a carrying bin (1) and a wing body (2), characterized in that: The wing body (2) comprises a wing support beam (3), the wing body (2) comprises a wing outer section (2-1), a wing middle section (2-2) and a wing connecting mechanism (2-3), the surface of the object carrying bin (1) is provided with a connecting U-shaped groove (1-2), the inside of the object carrying bin (1) is respectively provided with a 3mm basswood board (1-1) and a 3mm carbon fiber board (1-3), the wing support beam (3) comprises a 5x5 carbon square tube (2-4), a 1.5mm carbon fiber board (2-5) and a basswood board structure support (2-6), the surface of the object carrying bin (1) is provided with an object carrying bin U-shaped groove (3-4), the wing body (2) comprises a wing middle section beam (3-5) and a wing rib (3-6), and the object carrying bin U-shaped groove (3-4) is inserted with the wing middle section beam (3-5).
2. The wing and fuselage structure of claim 1, wherein: The wing connecting mechanism (2-3) comprises a wing middle section jack (3-1) arranged on the surface of the wing middle section (2-2), the surface of the wing outer section (2-1) is provided with a wing outer section carbon fiber plug (3-2), the surface of the wing outer section (2-1) is provided with a bolt hole (3-3), and the wing outer section carbon fiber plug (3-2) is inserted with the wing middle section jack (3-1).
3. The wing and fuselage structure of claim 1, wherein: The object carrying bin (1) is designed in a streamlined shape, the object carrying bin (1) comprises an inner layer and an outer layer, the inner layer is a 3mm carbon fiber board (1-3), and the outer layer is a 5mm basswood board (1-1).
4. The wing and fuselage structure of claim 1, wherein: The wing body (2) adopts a slow wing type, the chord length of the wing body (2) is 0.425m, the span length of the wing body (2) is 0.769m, and the aspect ratio of the wing body (2) is 8.
588.
5. The wing and fuselage structure of claim 1, wherein: The wing body (2) adopts a trapezoidal wing.