A large oil-electric hybrid fixed-wing unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned plane, especially large -scale oil -electric hybrid power fixed wing unmanned plane, its to equipment's flight provides main body support and driving force through support device, through the landing gear to the gliding landing and the sliding take -off process of equipment support, and can be recovered to the support device inside and reduce the wind resistance in normal flight process, through the heat abstractor to the inside battery provides auxiliary heat dissipation, reduces the influence that equipment internal heat accumulation caused to equipment normal operation, including support device, landing gear and heat abstractor, landing gear installs on support device, heat abstractor installs on support device.

Description

Technical Field

[0001] This utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a large-scale hybrid electric fixed-wing UAV. Background Technology

[0002] Fixed-wing drones are unmanned aerial vehicles that rely on fixed wings to generate lift, use a propulsion system to provide forward propulsion, and can fly autonomously or remotely along a preset route. Their design is inspired by bird gliding and traditional fixed-wing aircraft, and they are one of the most widely used and technologically mature types of drones.

[0003] The existing Chinese utility model patent with application number CN201910468422.4 relates to a hybrid electric vertical take-off and landing forward-swept fixed-wing UAV, which includes a fuselage, wings, tail, propeller, tail boom and air duct, etc., and can achieve high lift vertical take-off and landing and efficient horizontal flight.

[0004] However, in actual use, the battery of the above device generates a lot of heat during continuous operation. When the ambient temperature is high, the battery needs to be cooled. In addition, the wheels of the above device do not have the ability to be retracted, which increases the wind resistance during the flight of the equipment. Utility Model Content

[0005] To address the aforementioned technical problems, this utility model provides a large hybrid electric fixed-wing UAV that uses a support device to provide main support and driving force for the flight of the device, a landing device to support the gliding landing and take-off process of the device, and can be recovered into the support device during normal flight to reduce wind resistance. It also uses a heat dissipation device to provide auxiliary heat dissipation for the internal battery, thereby reducing the impact of heat accumulation inside the device on the normal operation of the device.

[0006] This utility model discloses a large hybrid electric fixed-wing unmanned aerial vehicle (UAV); it includes a support device, a landing device, and a heat dissipation device. The landing device is mounted on the support device, and the heat dissipation device is also mounted on the support device. The support device provides the main support and driving force for the flight of the device, the landing device supports the gliding landing and take-off processes of the device, and can be retracted into the support device during normal flight to reduce wind resistance. The heat dissipation device provides auxiliary heat dissipation for the internal battery, reducing the impact of heat accumulation inside the device on the normal operation of the device.

[0007] Preferably, the support device includes a main fuselage, main wings, ailerons, a main cabin, a propeller blade, and an engine. Main wings are located on the left and right sides of the front of the main fuselage, and a set of ailerons are located on the left and right sides of the rear of the main fuselage. The main cabin is located in the middle of the main fuselage, and the propeller blade is installed at the rear of the main fuselage. The engine is installed inside the main cabin, and its output is connected to the propeller blade. Starting the engine transmits power to the propeller blade, causing it to rotate and providing power for the device's flight. The main wings and ailerons, in conjunction with the propeller blade, provide lift to the main body of the device. The main cabin supports the main components of the device, improving the device's practicality.

[0008] Preferably, it also includes spoiler blades, with a set of spoiler blades installed at the front of each of the left and right ends of the main wing and equipped with motor drive; by controlling the rotation of the two sets of spoiler blades, the induced drag during flight is reduced, the airflow generated by the rotation of the spoiler blades reduces wingtip vortices, optimizes fuel efficiency, and improves the practicality of the device.

[0009] Preferably, the landing gear includes a front support arm, a front support wheel, an arc-shaped support arm, and a rear support wheel. A retraction slot is located at the front of the main control bay, in which the front support arm is installed. A front support wheel is installed at the end of the front support arm. A set of arc-shaped support arms is installed on the left and right sides of the rear of the main control bay, with a rear support wheel installed at the end of each arc-shaped support arm. Both the front and arc-shaped support arms are rotated by a motor. The front and rear support wheels on the front and arc-shaped support arms provide support for the equipment's gliding. During flight, the motor drives the front support arm to retract into the retraction slot on the main control bay to reduce wind resistance. The motor drives the arc-shaped support arm to lie close to the side of the main control bay to further reduce wind resistance, thus improving the practicality of the device.

[0010] Preferably, the device also includes a fuel tank, a steel plate, and batteries. The fuel tank is installed at the rear of the main engine compartment, and its lower end is supported by a steel plate. A set of batteries is installed on each of the lower left and right sides of the main engine compartment. The two sets of batteries supply power to the electrical components of the device. The fuel tank stores the fuel required for flight, and the steel plate provides auxiliary support for the fuel tank. The batteries on both sides ensure a uniform weight distribution inside the main engine compartment, improving the stability of the device during flight, reducing the impact of fuel consumption on the overall stability of the device, and improving the practicality of the device.

[0011] Preferably, the heat dissipation device includes a control cabin, a filter, an air duct, and air outlets. The control cabin is located at the front of the main engine compartment and is isolated from the space where the battery is located. A filter is located at the lower part of the front storage compartment of the main engine compartment, and an air duct is connected to the rear of the filter. The air duct passes through the interior of the control cabin and extends to the rear of the main engine compartment. Multiple sets of air outlets are provided on the rear surface of the control cabin, and the air outlets are distributed on the upper and lower sides of the steel plate. Multiple sets of exhaust holes are provided at the rear of the main engine compartment corresponding to the multiple sets of air outlets. The control cabin provides installation space for the equipment control equipment and communication equipment, isolates them from the battery, and reduces the impact of heat generated during battery operation on the equipment components. During flight, airflow is delivered by the filter and air duct to the multiple sets of air outlets and ejected to provide auxiliary heat dissipation for the rear of the main engine compartment, reducing the impact of heat accumulation on equipment operation. The filter reduces the entry of impurities in the airflow into the equipment, improving the practicality of the device.

[0012] Preferably, it also includes an electromagnet base, with an electromagnet base installed at the front of the retraction slot at the front of the main engine compartment; the electromagnet base attracts the front of the front support arm, reducing the vibration and amplitude of the front support arm during flight and improving the stability of the device.

[0013] Compared with the prior art, the beneficial effects of this utility model are as follows: the support device provides the main support and driving force for the flight of the equipment; the take-off and landing device supports the gliding landing and take-off process of the equipment; and it can be recovered into the support device during normal flight to reduce wind resistance. The heat dissipation device provides auxiliary heat dissipation for the internal battery, reducing the impact of heat accumulation inside the equipment on the normal operation of the equipment. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the first isometric structure of this utility model; Figure 2 This is a schematic diagram of the second isometric structure of this utility model; Figure 3 This is a first cross-sectional structural diagram of the present invention; Figure 4 This is a schematic diagram of the second cross-sectional structure of this utility model; Figure 5 This is a schematic diagram of the third cross-sectional structure of this utility model; The following are labels in the attached diagram: 1. Main fuselage; 2. Main wing; 3. Aileron; 4. Main cabin; 5. Power propeller blade; 6. Engine; 7. Spoiler blade; 9. Front support arm; 10. Front support wheel; 11. Arc-shaped support arm; 12. Rear support wheel; 13. Fuel tank; 14. Steel plate; 15. Battery; 16. Control cabin; 17. Filter screen; 18. Air duct; 19. Air outlet; 20. Electromagnet base. Detailed Implementation

[0015] To facilitate understanding of this utility model, a more complete description will be given below with reference to the accompanying drawings. This utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to make the disclosure of this utility model more thorough and complete.

[0016] Example 1 Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, the lifting device is mounted on the support device, and the heat dissipation device is mounted on the support device; First, start the engine 6 to transmit power to the power blade 5 to drive the power blade 5 to rotate and provide power to the equipment. After the equipment completes the sliding and lifting, the motor drives the front support arm 9 to be retracted into the retraction slot on the main engine compartment 4 to reduce wind resistance. The motor drives the arc support arm 11 to be close to the side of the main engine compartment 4 to reduce wind resistance. The airflow is delivered by the filter screen 17 and the air duct 18 to multiple sets of air outlets 19 and sprayed out to provide auxiliary heat dissipation for the rear of the main engine compartment 4. The support device includes a main fuselage 1, a main wing 2, an auxiliary wing 3, a main cabin 4, a power propeller 5, and an engine 6. The main fuselage 1 has a main wing 2 on the left and right sides at the front, a set of auxiliary wings 3 on the left and right sides at the rear, a main cabin 4 in the middle, a power propeller 5 installed at the tail, and an engine 6 installed inside the main cabin 4. The output end of the engine 6 is connected to the power propeller 5. It also includes spoiler blades 7. A set of spoiler blades 7 is installed on the front part of the left and right ends of the main wing 2 and is equipped with a motor drive. The landing device includes a front support arm 9, a front support wheel 10, an arc-shaped support arm 11, and a rear support wheel 12. The front of the main engine compartment 4 is provided with a retraction slot, in which the front support arm 9 is installed. The front support wheel 10 is installed at the end of the front support arm 9. A set of arc-shaped support arms 11 is installed on the left and right sides of the rear of the main engine compartment 4. The rear support wheel 12 is installed at the end of the arc-shaped support arm 11. The front support arm 9 and the arc-shaped support arm 11 are both controlled by a motor to rotate. It also includes a fuel tank 13, a steel plate 14 and a battery 15. The fuel tank 13 is installed in the rear of the main engine compartment 4. The lower end of the fuel tank 13 is supported by the steel plate 14. A set of batteries 15 is installed on the left and right sides of the lower part of the main engine compartment 4. The heat dissipation device includes a control compartment 16, a filter 17, an air duct 18, and an air outlet 19. The control compartment 16 is located at the front of the main unit compartment 4 and is isolated from the space where the battery 15 is located. The filter 17 is located at the lower part of the front storage slot of the main unit compartment 4. The air duct 18 is connected to the rear of the filter 17. The air duct 18 extends through the interior of the control compartment 16 to the rear of the main unit compartment 4. Multiple sets of air outlets 19 are provided on the rear end face of the control compartment 16. The air outlets 19 are distributed on the upper and lower sides of the steel plate 14. Multiple sets of exhaust holes are provided at the rear of the main unit compartment 4 corresponding to the positions of the multiple sets of air outlets 19. It also includes an electromagnet base 20. The electromagnet base 20 is installed in the front of the retraction slot at the front of the main engine compartment 4. It provides the main support and driving force for the flight of the equipment through the support device, supports the gliding landing and take-off process of the equipment through the landing device, and can be retracted into the support device during normal flight to reduce wind resistance. It provides auxiliary heat dissipation for the internal battery through the heat dissipation device to reduce the impact of heat accumulation inside the equipment on the normal operation of the equipment.

[0017] like Figures 1 to 4 As shown, this utility model discloses a large hybrid electric fixed-wing UAV. When in operation, the engine 6 is first started to transmit power to the propeller 5, which drives the propeller 5 to rotate and thus provide power to the equipment. After the equipment completes the gliding and lifting, the front support arm 9 is driven by the motor to be retracted into the retraction slot on the main body 4 to reduce wind resistance. The arc-shaped support arm 11 is driven by the motor to be close to the side of the main body 4 to reduce wind resistance. The airflow is delivered by the filter screen 17 and the air duct 18 to multiple sets of air outlets 19 and sprayed out to provide auxiliary heat dissipation for the rear of the main body 4.

[0018] The engine 6 and battery 15 of this large hybrid electric fixed-wing UAV are commercially available. Technical personnel in this industry only need to install and operate them according to the accompanying instruction manual, without requiring any creative work from those skilled in the art.

[0019] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.

Claims

1. A large hybrid electric fixed-wing unmanned aerial vehicle; characterized in that, It includes a support device, a landing device and a heat dissipation device. The landing device is installed on the support device and the heat dissipation device is installed on the support device. The heat dissipation device includes a control compartment (16), a filter screen (17), an air duct (18) and an air outlet (19). The control compartment (16) is located at the front of the main unit compartment (4). The control compartment (16) is isolated from the space where the battery (15) is located. The filter screen (17) is located at the lower part of the front loading and unloading slot of the main unit compartment (4). The air duct (18) is connected to the rear of the filter screen (17). The air duct (18) extends through the interior of the control compartment (16) to the rear of the main unit compartment (4). Multiple sets of air outlets (19) are provided on the rear end face of the control compartment (16). The air outlets (19) are distributed on the upper and lower sides of the steel plate (14). Multiple sets of exhaust holes are provided at the rear of the main unit compartment (4) corresponding to the multiple sets of air outlets (19).

2. The large hybrid electric fixed-wing UAV as described in claim 1, characterized in that, The support device includes a main fuselage (1), a main wing (2), an auxiliary wing (3), a main cabin (4), a power propeller (5), and an engine (6). The main fuselage (1) has a main wing (2) on the left and right sides at the front, a set of auxiliary wings (3) on the left and right sides at the rear, a main cabin (4) in the middle, a power propeller (5) at the tail, and an engine (6) inside the main cabin (4). The output end of the engine (6) is connected to the power propeller (5).

3. A large hybrid electric fixed-wing UAV as described in claim 2, characterized in that, It also includes spoiler blades (7), with a set of spoiler blades (7) installed on the front of the left and right ends of the main wing (2) and equipped with motor drive.

4. A large hybrid electric fixed-wing UAV as described in claim 3, characterized in that, The landing device includes a front support arm (9), a front support wheel (10), an arc-shaped support arm (11), and a rear support wheel (12). The front of the main engine compartment (4) is provided with a retraction slot, in which the front support arm (9) is installed. The front support wheel (10) is installed at the end of the front support arm (9). A set of arc-shaped support arms (11) is installed on the left and right sides of the rear of the main engine compartment (4). The rear support wheel (12) is installed at the end of the arc-shaped support arm (11). The front support arm (9) and the arc-shaped support arm (11) are both controlled by a motor to rotate.

5. A large hybrid electric fixed-wing UAV as described in claim 4, characterized in that, It also includes a fuel tank (13), a steel plate (14) and a battery (15). The fuel tank (13) is installed in the rear of the main engine compartment (4). The lower end of the fuel tank (13) is supported by a steel plate (14). A set of batteries (15) is installed on the left and right sides of the lower part of the main engine compartment (4).

6. A large hybrid electric fixed-wing UAV as described in claim 5, characterized in that, It also includes an electromagnet base (20), which is installed at the front of the storage slot at the front of the main engine compartment (4).

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