Compound wing aircraft

Abstract

The application relates to the technical field of aircrafts, and discloses a compound wing aircraft. The compound wing aircraft comprises a fuselage, a left wing and a right wing connected to the fuselage, at least one pair of linear support members, each pair of linear support members being connected to the left wing and the right wing respectively, the linear support members being arranged with multiple lift propellers, and a nacelle attached to the fuselage, the nacelle being provided with a thrust module, a power generation module and a battery module, the thrust module and the power generation module being arranged at the tail of the nacelle, the thrust module comprising an engine and a thrust propeller, the thrust propeller being driven to rotate by the engine so as to provide aircraft thrust, the power generation module comprising a power generator connected with the engine and generating power when the engine rotates, and the power being stored in the battery module. The compound wing aircraft greatly improves the endurance.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to a compound wing aircraft. Background Technology

[0002] Vertical takeoff and landing aircraft, especially cargo and manned aircraft, mostly use lithium batteries as motor power to drive propellers to obtain lift and thrust. However, due to the low energy density of lithium batteries, the flight load capacity and flight duration are relatively short. Simply adding batteries will increase the load on the aircraft and reduce flight efficiency. Therefore, there is an urgent need to find a solution that can increase the flight range. Utility Model Content

[0003] The purpose of this application is to provide a compound wing aircraft that greatly improves endurance.

[0004] To address the aforementioned technical problems, this application provides a compound wing aircraft, comprising: a fuselage; a left wing and a right wing connected to the fuselage; at least one pair of linear support members, each pair of linear support members being connected to the left wing and the right wing respectively, the linear support members being arranged with multiple lift propellers; a pod attached to the fuselage, the pod being provided with a thrust module, a power generation module, and a battery module, the thrust module and the power generation module being disposed at the tail of the pod, the thrust module including an engine and a thrust propeller, the thrust propeller being driven to rotate by the engine to provide thrust to the aircraft; the power generation module including a generator, the generator being connected to the engine and generating electricity as the engine rotates, which is then stored in the battery module.

[0005] Optionally, the engine and the generator are covered by a tail cover, which has a plurality of first air intake holes. The first air intake holes form a guide channel towards the engine, wherein the plurality of first air intake holes face the airflow direction, and the airflow enters the first air intake holes and then passes through the guide channel to dissipate heat from the engine.

[0006] Optionally, the flow channel extends in an S-shape.

[0007] Optionally, the engine includes a cylinder block, each side of which is provided with a plurality of cylinder heads. The plurality of cylinder heads are covered by a cylinder head cover, which is connected to the airflow channel. Airflow entering from the first air intake port enters the cylinder head cover through the airflow channel and dissipates heat from the cylinder heads.

[0008] Optionally, it also includes a heat sink assembly with internal flow channels, which are connected to the engine lubrication flow path to form a closed loop.

[0009] Optionally, the tail cover is provided with a second air inlet facing the heat sink assembly, the second air inlet facing the airflow direction, for dissipating heat from the heat sink assembly.

[0010] Optionally, a pressure pump is provided in the engine lubrication flow path to accelerate the flow of lubricating fluid.

[0011] Optionally, the heat sink assembly includes multiple layers of parallel fins, with air convection channels formed between adjacent fins.

[0012] Optionally, it also includes a fuel tank, which is located at the bottom of the pod and communicates with the engine.

[0013] Optionally, the tail cover is also provided with multiple air vents.

[0014] The compound wing aircraft of this application uses an engine that consumes chemical energy as the power source for the thrust propeller, which can greatly improve the range compared to lithium battery drive with lower energy density. Attached Figure Description

[0015] Figure 1 The diagram shown is a structural schematic of a compound wing aircraft according to an embodiment of this application. Figure 2 The diagram shown is a structural schematic of a compound wing aircraft according to an embodiment of this application. Figure 3 The image shown is a side sectional view of the composite wing aircraft pod according to an embodiment of this application; Figure 4 show Figure 2 A magnified view of a portion of position A in the middle; Figure 5 The diagram shown is a schematic representation of the flow channel in an embodiment of this application. Figure 6 The diagram shown is a structural schematic of the heat sink assembly in an embodiment of this application. Figure 7 The diagram shown is a structural schematic of the thrust module in an embodiment of this application. Detailed Implementation

[0016] The following embodiments further illustrate the technical solutions of this application. It should be understood that the specific embodiments described herein are merely for explaining this application. Furthermore, it should be noted that, for ease of description, only the parts relevant to this application are shown in the accompanying drawings, not all of them.

[0017] The terms used in this specification to describe the various embodiments are to be understood not only in their commonly defined meanings, but also, by their specific definitions in this specification, to include structures, materials, or actions that extend beyond their commonly defined meanings. Therefore, if an element is to be understood in the context of this specification to include more than one meaning, its use in the claims must be understood to apply universally to all possible meanings supported by the specification and by its own terminology. In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0018] The term "aircraft" is defined as an air transport system of any size having at least one lift propeller as its propulsion source. The term "aircraft" can include both "manned" and "unmanned" air transport systems. A manned aircraft can mean an air transport system carrying one or more human passengers, none of whom have control over the aircraft. A manned aircraft can also mean an air transport system carrying one or more human passengers, some of whom, or one of whom, has partial or full control over the aircraft. An unmanned aircraft can mean an air transport system that does not carry any human passengers and flies autonomously or is remotely controlled by someone at a distance.

[0019] The term "compound wing aircraft" is defined as an air transport system of any size that has at least one propeller as its propulsion source. The term "compound wing aircraft" can include both "manned" and "unmanned" air transport systems. A manned compound wing aircraft can refer to an air transport system carrying one or more human passengers, none of whom have control over the compound wing aircraft. A manned compound wing aircraft can also refer to an air transport system carrying one or more human passengers, some of whom, or one of whom, has partial or full control over the compound wing aircraft. An unmanned compound wing aircraft can refer to an air transport system that does not carry any human passengers and flies autonomously or is remotely controlled by someone at a distance.

[0020] The term "fixed wing" is defined as a non-rotating wing on an aircraft that generates lift due to the forward airspeed of the aircraft and the shape of the fixed wing.

[0021] The accompanying drawings illustrate various embodiments of the compound wing aircraft. It should be noted, in particular, that other types of aircraft are envisioned to implement many of the inventive features described herein, in addition to those shown in the drawings.

[0022] like Figure 1 As shown, this application provides a compound wing aircraft, including: a fuselage 10, a left wing 11 and a right wing 12 connected to the fuselage 10, and two pairs of linear support members 13. The left wing 11 and the right wing 12 are symmetrically arranged on both sides of the fuselage 10 along the longitudinal axis of the fuselage 10. The left wing 11 and the right wing 12 are non-rotatable relative to the fuselage 10 and provide lift for the aircraft during level flight.

[0023] In this embodiment, the two pairs of linear support members 13 include a pair of outer linear support members 13 and a pair of inner linear support members 13. The two pairs of linear support members 13 are symmetrically arranged on both sides of the fuselage 10 and are respectively connected to the left wing 11 and the right wing 12. Each inner linear support member 13 is equipped with three lift propellers 14, and each outer linear support member 13 is equipped with two lift propellers 14.

[0024] The lift propeller 14 is driven by a motor housed inside the linear support 13, and each motor can be independently powered by a battery, avoiding adverse effects on the aircraft system from the failure of a single motor. However, it is understandable that several motors can also be connected in series as a group for power supply.

[0025] In some embodiments, each linear support 13 may be equipped with more lift propellers 14 to increase load capacity, or in some embodiments, the lift propellers 14 may have different sizes.

[0026] In this embodiment, the front ends of the inner pair of linear support members 13 are connected by a canard 15. Control surfaces can be provided on the canard 15 for controlling the pitch of the aircraft. The rear end of each inner linear support member 13 is also provided with a propeller 16 for providing thrust; both propellers 16 are driven by an electric motor. In another embodiment, the propellers 16 may also be driven by an engine.

[0027] In one embodiment, the linear support 13 extends forward beyond the canard 15. In this way, the canard 15 connects the front end of the linear support 13, which can improve the structural integrity of the aircraft, increase structural strength, and enhance safety and reliability. The canard 15 is not connected to the fuselage 10. In another embodiment, a canard 15 may also be provided at the rear of the fuselage 10; this application does not impose specific limitations.

[0028] like Figure 2 As shown, a pod 20 is attached to the lower part of the fuselage 10. The pod 20 is used for carrying passengers or cargo. In addition, it can also carry other functions, such as installing other recording devices, delivery devices, or other instruments and equipment.

[0029] like Figure 3 As shown, the pod 20 is equipped with a thrust module 21, a power generation module 22, and a battery module 23. The thrust module 21 and the power generation module 22 are located at the tail of the pod 20. The thrust module 21 includes an engine 210 and a thrust propeller 211. The thrust propeller 211 is driven by the engine 210 to rotate, thereby providing thrust to the aircraft in the fixed-wing flight mode of the compound wing aircraft.

[0030] In addition, the bottom of the pod 20 is equipped with a fuel tank 25 for the engine 210. The fuel tank 25 is connected to the engine 210 and provides it with fossil fuels. The engine 210 is powered by the fossil fuels stored in the fuel tank 25. Compared with electric motor drive, lithium batteries have a lower energy density, so carrying the same weight of fossil fuels can achieve a greater flight range. However, it is understood that the fuel tank 25 can also be installed in other locations on the aircraft, and no specific restrictions are made here.

[0031] The power generation module 22 includes a generator 220, which is connected to the engine 210 and generates electricity as the engine 210 rotates. The generated electricity is stored in the battery module 23 via a cable (not shown). The battery module 23 can power the control system and other equipment such as the lift motor. The battery module 23 is located in... Figure 3 The image shown is for illustrative purposes only; it can actually be placed anywhere inside the aircraft.

[0032] The generator 220 and the engine 210 can be connected coaxially, via a coupling, or via a clutch; they can be selectively connected or disconnected. For example, when the battery module 23 is fully loaded, the generator 220 can be disconnected from the engine 210. When charging the battery module 23 is required, the two can be connected via the clutch, thereby charging the battery module 23 during engine rotation. This embodiment of the application, by connecting the engine and the generator, can convert some of the engine's kinetic energy into electrical energy, thereby increasing the driving range and supplying power to the overall control system or other electrical equipment, such as lift motors.

[0033] like Figure 3 and Figure 4 As shown, the engine 210 and generator 220 are covered by a tail cover 24, which has two first air intakes 241, respectively located on both sides of the tail cover 24.

[0034] like Figure 5 As shown, a guide channel 40 is formed from the first air intake 241 towards the engine 210, with the first air intake 241 facing the airflow direction. After the airflow enters the first air intake 241, it passes through the guide channel 40 to dissipate heat from the engine 210. It should be noted that the airflow direction mentioned in this embodiment refers to the airflow direction flowing across the surface of the aircraft.

[0035] In one embodiment, such as Figure 5 As shown, the flow channel 40 extends in an S-shape, which can effectively prevent the generation of whistling noise.

[0036] In one embodiment, the flow channel 40 may have other streamlined configurations, which are not specifically limited here.

[0037] In one embodiment, such as Figure 3 As shown, a heat sink assembly 30 is also installed inside the tail cover 24 of the pod 20. Correspondingly, as... Figure 4 As shown, a second air inlet 242 is provided on the tail cover 24, facing the heat sink assembly 30. The second air inlet 242 is directly opposite the airflow direction. After the airflow enters the second air inlet 242, it passes through an air duct and then directly faces the heat sink assembly 30 for heat dissipation, thereby achieving a large heat dissipation efficiency. It should be noted that the airflow direction mentioned in this embodiment refers to the airflow direction flowing across the surface of the aircraft.

[0038] The heat sink assembly 30 has internal flow channels (not shown in the figure), which are connected to the engine lubrication flow path to form a closed loop. For example... Figure 3 As shown, a pressure pump 31 is also installed in the engine lubrication flow path to accelerate the flow of lubricating fluid. The flow of lubricating fluid transfers heat to the heat sink for heat dissipation. Figure 6 As shown, the heat sink assembly 30 includes multiple layers of parallel fins 301, and air convection channels are formed between adjacent fins 301 to improve heat dissipation efficiency.

[0039] In addition, such as Figure 4 As shown, multiple vents 243 are also provided on both sides of the tail cover 24 to carry the airflow after heat exchange out of the tail cover 24, so as to prevent heat from being unable to be properly discharged inside the tail cover 24. There are no specific restrictions on the shape, number and position of the vents 243.

[0040] Furthermore, the tail cover 24 and the pod 20 are detachably connected, facilitating maintenance and replacement.

[0041] In one embodiment, the fuselage 10 is detachably connected to the left wing 11 and the right wing 12, which facilitates maintenance and replacement.

[0042] In one embodiment, the fuselage 10 is integrally formed with the left wing 11 and the right wing 12, which can improve structural integrity.

[0043] In some embodiments, such as Figure 1 As shown, two pairs of linear support members 13 are arranged parallel to the fuselage 10 and symmetrically on both sides of the fuselage 10. The length of the inner linear support member 13 is greater than the length of the pod 20. The two pairs of linear support members 13 are arranged longitudinally parallel to each other.

[0044] In some embodiments, the installation position and orientation of the lift motor are not limited. In this embodiment, the lift propellers 14 are all disposed on the top of the linear support member 13; in one embodiment, they may also be disposed on the bottom of the linear support member 13.

[0045] In one embodiment, such as Figure 2 As shown, a vertical stabilizer 130 is provided at the rear end of each inner linear support 13, and a pair of vertical stabilizers 130 are arranged in parallel relative to each other. Each pair of vertical stabilizers is provided with a steering surface, which can serve as a control unit for steering. In this embodiment, the pair of vertical stabilizers extends downwards. In another embodiment, the vertical stabilizers may also be configured to extend upwards.

[0046] In one embodiment, such as Figure 7 As shown, the engine 210 includes a cylinder block 2101 and multiple cylinder heads 212. Three cylinder heads 212 are provided on each side of the cylinder block 2101, and the three cylinder heads 212 are covered by a cylinder head cover 213. The cylinder head cover 213 is not a completely sealed structure; it has multiple openings. The cylinder head cover 213 communicates with a guide channel 40 within the first air intake port 241. When airflow enters through the first air intake port 241, it enters the cylinder head cover 213 through the guide channel 40 and dissipates heat from the cylinder heads 212. Because the cold airflow can have a delayed residence time within the cylinder head cover 213, it allows for sufficient contact between the cold airflow and the cylinder heads, thereby improving heat dissipation efficiency.

[0047] In another embodiment of this application, there are three pairs of linear support members 13. The compound wing aircraft includes: a fuselage 10, a left wing 11 and a right wing 12 connected to the fuselage 10, three pairs of linear support members 13, and a canard wing 15. The left wing 11 and the right wing 12 are symmetrically arranged on both sides of the fuselage 10 along the longitudinal axis of the fuselage 10. The left wing 11 and the right wing 12 are non-rotatable relative to the fuselage 10 and provide lift for the aircraft during level flight. Each pair of linear support members 13 is symmetrically arranged on both sides of the fuselage 10 and is connected to the left wing 11 and the right wing 12 respectively. Each linear support member 13 is equipped with multiple lift propellers 14, all of which are driven by motors, and each motor is independently powered by a rechargeable battery.

[0048] The fuselage of the aircraft provided in this application is preferably made of carbon fiber material, which has a certain degree of ductility and toughness. While enhancing the strength of the fuselage, carbon fiber material itself has a certain degree of toughness and ductility, which can be used to resist some of the torque and air resistance applied to the fuselage during flight.

[0049] Each linear support component can be made of suitable materials to withstand the physical demands of flight and resist the torsion caused by various pressures generated during flight. Such materials include natural and synthetic polymers, various metals and metal alloys, natural materials, textile fibers, glass, and ceramic materials.

[0050] In the aircraft provided in this application, each linear support is parallel to the longitudinal axis of the fuselage, so that the propellers arranged on each linear support are parallel to each other, thereby providing optimal stability and redundancy. When a propeller on a linear support fails, it is only necessary to shut down the corresponding propeller on the other linear support opposite the failed propeller, so that the working propellers are kept in balance and the aircraft remains in the air.

[0051] In one embodiment, such as Figure 1 As shown, an airspeed meter 17 is installed at the forward-facing end of the canard 15. In addition, an airspeed meter (not shown in the figure) can also be installed at the front of the linear support 13. Multiple airspeed meters can ensure system redundancy and improve safety and reliability.

[0052] The linear support component of this application embodiment has two propellers 16 and a thrust propeller 211 at the tail of the pod 20. By changing the thrust, asymmetrical thrust can be generated. The asymmetrical thrust can control the active yaw of the aircraft, thereby adding another yaw control channel. When the yaw control of the lift motor cannot be guaranteed, it can be achieved by multiple thrust propellers, which increases control redundancy and improves safety and reliability.

[0053] The above embodiments are merely illustrative of the principles and effects of this application. Any person skilled in the art can modify or alter the above embodiments without departing from the purpose of this application. Therefore, all equivalent modifications or alterations made by those skilled in the art without departing from the purpose disclosed in this application should still be covered by the claims of this application.

Claims

1. A compound wing aircraft, characterized in that, include: Fuselage (10); left wing (11) and right wing (12) connected to said fuselage (10); At least one pair of linear support members (13), each pair of linear support members (13) is connected to the left wing (11) and the right wing (12) respectively, and the linear support members (13) are arranged with multiple lift propellers (14). A pod (20) is attached to the fuselage (10). The pod (20) is provided with a thrust module (21), a power generation module (22) and a battery module (23). The thrust module (21) and the power generation module (22) are located at the tail of the pod (20). The thrust module (21) includes an engine (210) and a thrust propeller (211). The thrust propeller (211) is driven by the engine (210) to rotate, thereby providing thrust to the aircraft. The power generation module (22) includes a generator (220). The generator (220) is connected to the engine (210) and generates electricity as the engine (210) rotates, which is then stored in the battery module (23).

2. The compound wing aircraft according to claim 1, characterized in that, The engine (210) and the generator (220) are covered by a tail cover (24), which has a plurality of first air intake holes (241). The first air intake holes (241) form a guide channel (40) towards the engine. The plurality of first air intake holes (241) face the airflow direction. After the airflow enters the first air intake holes (241), it dissipates heat from the engine (210) through the guide channel (40).

3. The compound wing aircraft according to claim 2, characterized in that, The flow channel (40) extends in an S-shape.

4. The compound wing aircraft according to claim 2, characterized in that, The engine (210) includes a cylinder block (2101), and each side of the cylinder block (2101) is provided with a plurality of cylinder heads (212). The plurality of cylinder heads (212) are covered by a cylinder head cover (213). The cylinder head cover (213) is connected to the air guide channel (40). The airflow entering from the first air intake hole (241) enters the cylinder head cover (213) through the air guide channel (40) and dissipates heat from the cylinder heads (212).

5. The compound wing aircraft according to claim 2, characterized in that, It also includes a heat sink assembly (30) with internal flow channels, which are connected to the engine lubrication flow path to form a closed loop.

6. The compound wing aircraft according to claim 5, characterized in that, The tail cover (24) is provided with a second air inlet (242) facing the heat sink assembly (30). The second air inlet (242) is directly facing the airflow direction and is used to dissipate heat from the heat sink assembly (30).

7. The compound wing aircraft according to claim 5, characterized in that, A pressure pump (31) is provided in the engine lubrication flow path to accelerate the flow of lubricating fluid.

8. The compound wing aircraft according to claim 5, characterized in that, The heat sink assembly (30) includes multiple layers of parallel fins (301), with air convection channels formed between adjacent fins (301).

9. The compound wing aircraft according to claim 1, characterized in that, It also includes a fuel tank (25), which is located at the bottom of the pod (20) and communicates with the engine (210).

10. The compound wing aircraft according to claim 2, characterized in that, The tail cover (24) is also provided with multiple air vents (243).

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