Composite wing unmanned aerial vehicle with heavy-load function
By combining fixed-wing and rotary-wing configurations and using tilt-rotor servo design, the contradiction between increased payload and endurance of UAVs and flight performance was resolved, enabling the design of UAVs with large payload and long endurance, and improving flight safety and power efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-23
- Publication Date
- 2026-04-03
AI Technical Summary
With the addition of payload capacity, existing drones have difficulty balancing endurance, flight performance, and safety risks. The traditional combination of fixed-wing and rotary-wing designs is difficult to effectively integrate, making it impossible to achieve both high payload and long endurance at the same time.
It adopts a hybrid layout of fixed wing and rotor, with the main wing providing lift, the rotor structure enabling vertical take-off and landing and hovering, and the tilt servo achieving synchronous tilting of the rotor through the servo linkage. Combined with the box-type load-bearing structure and distributed rib design, the load distribution is optimized.
It has achieved the core competitiveness of heavy payload and long endurance, avoided runway dependence, and improved power utilization and flight safety.
Smart Images
Figure CN224075775U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a compound-wing UAV with a large payload capacity. Background Technology
[0002] With the continuous development of drone technology, drones in the traditional sense can be divided into two main categories: rotary-wing drones and fixed-wing drones. Fixed-wing drones generate lift by using their wings and fluid, resulting in high flight speed and long endurance. They are generally used for long-duration and long-distance missions, such as surveying and patrolling. However, due to their aerodynamic configuration, they cannot hover. Also, due to differences in aircraft design, different configurations of fixed-wing drones have different requirements for takeoff and landing distances. Rotary-wing drones, based on their kinematics and dynamics equations, can achieve vertical takeoff and landing and hovering, and are flexible in operation. They are generally used for aerial photography. Their flight time and range are shorter than those of fixed-wing drones. As an effective carrier of unmanned systems, drones are increasingly being used in fields such as inspection and monitoring. However, increasing the payload design poses a new challenge to the endurance, flight performance, safety, and reliability of drones.
[0003] Even when combining traditional fixed-wing and rotary-wing technologies, the design process still presents significant challenges. Continuous exploration and learning are needed to fully leverage the characteristics of both fixed-wing and rotary-wing systems, effectively integrate these two completely different structures, achieve excellent load-bearing capacity, and overcome the contradictions between drone performance and flight characteristics. Utility Model Content
[0004] The purpose of this invention is to provide a compound wing UAV with a large payload capacity, which adopts a "fixed wing + rotor" compound layout, perfectly supporting the UAV's core competitiveness of "large payload + long endurance".
[0005] To achieve the above objectives, this utility model provides a compound wing unmanned aerial vehicle (UAV) with a large payload capacity, comprising a fuselage. The top of the fuselage, from front to back, is provided with a pitot tube, a first dorsal antenna radome, a second dorsal antenna radome, and a V-tail. The main wings, rotor structures, and main landing gear are symmetrically arranged on both sides of the middle position of the fuselage. The rotor structures are symmetrically arranged on the main wings. The main landing gear is symmetrically arranged on the bottom of the fuselage below the main wings. A wingtip plate is provided at the end of the main wing away from the fuselage. The bottom of the fuselage, from front to back, is provided with an electro-optical pod, a nose landing gear, and a payload rack.
[0006] Preferably, the main wing includes a wing body, the wing body is connected to a control surface aileron, the control surface aileron is electrically connected to an aileron servo, the aileron servo is located at the bottom of the wing body, the wing body is provided with a hidden through-type wing spars, the wing spars are connected to the fuselage, the wing body is provided with wing secondary spars, the wing secondary spars are provided with a plurality of wing ribs, and each wing rib is provided with a fixing hole for connecting to the wing main spars.
[0007] Preferably, both ends of the rotor structure are provided with rotor assemblies. The rotor assembly is provided with a rotor blade, a rotor motor, a motor mount, a tilt servo, and a servo mount from top to bottom. The tilt servo is connected to a servo linkage through the servo mount. The servo linkage passes through the main wing and connects to the rotor assembly at the other end.
[0008] Preferably, the rotor blades are fixed-pitch propulsion blades, including a long-endurance 18×16 two-bladed rotor blade and a high-power 20×16 two-bladed propeller.
[0009] Preferably, the fuselage contains, from front to back, an airspeed sensor, a radar transceiver, a GPS inertial navigation system, a Ku-band satellite communication antenna, a video encoder, a control module, an equipment cooling fan, a first accessory bay, an airborne antenna bracket, a main battery, a secondary battery, a second accessory bay, and a backup battery.
[0010] Preferably, the control module internally includes a flight control unit, an airborne RTK, a remote control transceiver, and a communication processor.
[0011] Therefore, the composite-wing UAV with a large payload capacity that adopts the above-mentioned structure has the following advantages compared with the prior art:
[0012] 1. In the design of this utility model UAV, the main wing beam and the secondary wing beam form a box-shaped load-bearing structure and the distributed wing rib design allows the wing ribs to evenly distribute the load through the fixing holes, which perfectly supports the core competitiveness of the UAV of "large payload + long endurance".
[0013] 2. This utility model adopts a "fixed wing + rotor" composite layout: the main wing provides lift for fixed wing flight, and the rotor structure realizes vertical take-off and landing and hovering capabilities. The combination of the two not only ensures the aerodynamic efficiency required for long-endurance flight, but also eliminates runway dependence; the tilt servo achieves synchronous tilting of the rotor through the servo linkage, providing lift during vertical take-off and landing, and can be converted into propulsion during cruise, effectively improving power utilization.
[0014] The technical solution of this utility model will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description
[0015] Figure 1This is a top view of an embodiment of a compound-wing unmanned aerial vehicle with a large payload capacity according to this utility model;
[0016] Figure 2 This is a front view of an embodiment of a compound-wing unmanned aerial vehicle with a large payload capacity according to the present invention;
[0017] Figure 3 This is a side view of an embodiment of a compound-wing unmanned aerial vehicle with a large payload capacity according to this utility model;
[0018] Figure 4 This is a bottom view of the main wing of an embodiment of a compound wing UAV with a large payload capacity according to this utility model;
[0019] Figure 5 This is the internal structure of the main wing of a compound wing UAV with high payload capacity according to an embodiment of the present invention;
[0020] Figure Labels
[0021] 1. Fuselage; 2. Pitot tube; 3. First dorsal antenna fairing; 4. Second dorsal antenna fairing; 5. V-tail; 6. Main wing; 7. Rotor structure; 8. Main landing gear; 9. Wingtip plate; 10. Electro-optical pod; 11. Nose landing gear; 12. Payload pylon; 61. Wing body; 62. Aileron control surfaces; 63. Aileron servo; 64. Wing spars; 65. Wing ailerons; 66. Wing ribs; 67. Mounting holes; 71. Rotor assembly; 72. Rotor; 73. Rotor motor; 74. Motor mount; 75. Tilting servo; 76. Servo mount; 77. Servo linkage. Detailed Implementation
[0022] Example
[0023] In the description of this utility model, it should be noted that the terms "upper", "lower", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship that the utility model product is usually placed in during use. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.
[0024] like Figures 1-5As shown, this utility model discloses a compound-wing unmanned aerial vehicle (UAV) with a large payload capacity, comprising a fuselage 1. From front to back, the top of the fuselage 1 is sequentially equipped with a pitot tube 2, a first dorsal antenna fairing 3, a second dorsal antenna fairing 4, and a V-tail fin 5. Symmetrically arranged on both sides of the middle of the fuselage 1 are main wings 6, rotor structures 7, and main landing gear 8. The rotor structures 7 are symmetrically arranged on the main wings 6, and the main landing gear 8 is symmetrically arranged on the bottom of the fuselage 1 below the main wings 6. A wingtip plate 9 is provided at the end of the main wing 6 furthest from the fuselage 1. From front to back, the bottom of the fuselage 1 is sequentially equipped with... The aircraft is equipped with an electro-optical pod 10, a nose landing gear 11, and a payload rack 12. The overall length of the aircraft is 2500mm, the stopping height is 735mm, and the wingspan is 5000mm. The fuselage 1 is constructed of carbon fiber laminate. Compared to the traditional vertical and horizontal tail, the V-tail 5 reduces air resistance (approximately 15-20% weight reduction) while also providing pitch and yaw control functions, simplifying the structure. The wingtip plate 9 effectively reduces wingtip vortex energy loss, improves the lift-to-drag ratio (typically 5-8%), and increases range and endurance, making it particularly suitable for long-endurance reconnaissance missions.
[0025] The main wing 6 includes a wing body 61, with ailerons 62 connected to the wing body 61. Ailerons 62 are electrically connected to aileron servos 63, which are located at the bottom of the wing body 61. The wing body 61 has a concealed, through-type wing spars 64 connected to the fuselage 1. Aileron spars 65 are located inside the wing body 61, and several ribs 66 are provided on the wing spars 65. Each rib 66 has a fixing hole 67 for connecting to the wing spars 64. The wing body is covered with a skin. The specific design details of the main wing are shown in Table 1.
[0026] Table 1 Detailed Design of Main Wing
[0027]
[0028] Both ends of the rotor structure 7 are equipped with rotor assemblies 71. The rotor assembly 71 is provided with rotor blades 72, rotor motors 73, motor mounts 74, tilt servos 75 and servo mounts 76 from top to bottom. The tilt servos 75 is connected to a servo linkage 77 through the servo mount 76. The servo linkage 77 passes through the main wing 6 and connects to the rotor assembly 71 at the other end. The rotor blades 72 adopt fixed-pitch propulsion blades, including a long-endurance 18×16 two-bladed rotor blade 72 and a high-power 20×16 two-bladed propeller.
[0029] The rotor structure 7 is structurally deeply coupled with the main wing 6, and the tilting function of the rotor is achieved by using a servo linkage 77 mechanism. On the one hand, the servo linkage 77 mechanism can make the two rotor assemblies 71 on the same main wing 6 tilt synchronously without damaging the structure of the main wing 6. On the other hand, since the servo linkage 77 mechanism can usually only be installed inside the fuselage 1, and with the rotor arm that runs through the fuselage 1, the space inside the fuselage 1 will be significantly compressed, and the built-in servo mechanism is more difficult to adjust and maintain. The synchronous tilting function provided has a better effect in simplifying control design and improving flight safety.
[0030] The fuselage interior, from front to back, houses an airspeed sensor, radar transceiver, GPS inertial navigation system, Ku-band satellite communication antenna, video encoder, control module, equipment cooling fan, first accessory bay, airborne antenna bracket, main battery, auxiliary battery, second accessory bay, and backup battery. The control module contains a flight control unit, airborne RTK, remote transceiver, and communication processor. The first fairing (usually forward) with its frequency band separation design houses the Ku-band satellite communication antenna (12-18GHz), while the second fairing (rear) mounts the UHF / VHF airborne radio antenna (30MHz-1GHz). This physical isolation reduces interference between high-frequency and low-frequency signals, with measured results showing a signal-to-noise ratio (SNR) improvement of over 6dB. Furthermore, the front fairing antenna uses right-hand circular polarization (RHCP), while the rear fairing uses vertical polarization, achieving an antenna isolation of 30dB between satellite communication and ground control links, thus preventing signal intermodulation distortion during full-load flight.
[0031] Therefore, the present invention is a composite wing UAV with a large payload capacity that adopts the above-mentioned structure. It adopts a "fixed wing + rotor" composite layout, which perfectly supports the core competitiveness of the UAV in "large payload + long endurance".
[0032] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of this utility model and not to limit it. Although the utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solution of this utility model, and these modifications or equivalent substitutions cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of this utility model.
Claims
1. A compound wing unmanned aerial vehicle with large load-carrying function, characterized in that: The fuselage top is sequentially provided with an air speed pipe, a first dorsal antenna fairing, a second dorsal antenna fairing and a V-tail from front to rear, the fuselage is symmetrically provided with a main wing, a rotor structure and a main landing gear at the middle position, the rotor structure is symmetrically arranged on the main wing, the main landing gear is symmetrically arranged on the bottom of the fuselage below the main wing, the main wing is provided with a wing tip plate at the end away from the fuselage, and the bottom of the fuselage is sequentially provided with a photoelectric pod, a front landing gear and a load hanger from front to rear.
2. The composite wing unmanned aerial vehicle with large load capacity of claim 1, wherein: The main wing comprises a wing body connected with a rudder surface aileron, the rudder surface aileron is electrically connected with an aileron steering engine, the aileron steering engine is arranged at the bottom of the wing body, the wing body is provided with a hidden through-type wing main beam connected with the fuselage, the wing body is internally provided with a wing secondary beam, a plurality of wing ribs are arranged on the wing secondary beam, and fixed holes connected with the wing main beam are arranged on the wing ribs.
3. The composite wing unmanned aerial vehicle with large load capacity of claim 2, wherein: Both ends of the rotor structure are provided with rotor assemblies, the rotor assemblies are sequentially provided with rotor blades, rotor motors, motor seats, tilt steering engines and steering engine seats from top to bottom, the tilt steering engines are connected with steering engine connecting rods through the steering engine seats, and the steering engine connecting rods are connected with the rotor assemblies at the other end through the main wing.
4. The composite wing unmanned aerial vehicle with large load capacity of claim 3, wherein: The rotor blades adopt fixed-pitch propeller blades, including a long-time 18x16 two-blade rotor blade and a high-power 20x16 two-blade propeller.
5. The composite winged UAV with large load capacity of claim 4, wherein: The inside of the fuselage is sequentially provided with an air speed sensor, a radar transceiver, a GPS inertial navigation, a Ku-band satellite communication antenna, a video encoder, a control module, an equipment cooling fan, a first accessory cabin, an airborne antenna support, a main battery, a secondary battery, a second accessory cabin and a standby battery from front to rear.
6. The composite winged UAV with large load capacity of claim 5, wherein: The control module is internally provided with a flight control unit, an airborne RTK, a remote control transceiver and a communication processor.