Range extender and vertical take-off and landing aircraft comprising same

Abstract

The application relates to the field of aircraft technology and discloses a range extender and a vertical take-off and landing aircraft comprising the same. The range extender comprises a power generation module, the power generation module comprising an engine and a generator, the engine and the generator being connected through a shaft coupling, the engine being capable of driving the generator to rotate and generate power, the generator generating electric energy which is input to the aircraft; a fuel tank, the fuel tank comprising an oil outlet, the oil outlet being connected with the engine to provide fuel energy for the engine; and a shell, the shell being streamlined, the power generation module and the fuel tank being arranged in the shell. The range extender realizes modular system integration design, and greatly improves the endurance of the aircraft under the condition of temporarily increasing the same unit weight.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more particularly to a range extender and a vertical take-off and landing aircraft including the same. Background Technology

[0002] Vertical takeoff and landing aircraft, especially cargo and manned aircraft, mostly use lithium batteries as power to drive motors and 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. There is an urgent need to find a solution that can temporarily increase the endurance and achieve better endurance with the same increase in unit weight. Summary of the Invention

[0003] The purpose of this application is to provide a range extender and a vertical take-off and landing aircraft containing the same. The range extender of this application realizes a modular system integration design, which greatly improves the endurance of the aircraft while temporarily increasing the same unit weight.

[0004] To address the aforementioned technical problems, this application provides a range extender for providing additional electrical energy to an aircraft. It is characterized by comprising: a power generation module, including an engine and a generator connected via a coupling; the engine drives the generator to rotate and generate electricity, which is then input to the aircraft's battery pack; a fuel tank, including an inlet and an outlet, the outlet being connected to the engine to provide it with fuel; and a streamlined outer shell, within which the power generation module and the fuel tank are housed.

[0005] This application provides a vertical takeoff and landing (VTOL) aircraft, comprising: a fuselage; a left wing and a right wing connected to the fuselage; at least one pair of linear support members, the at least one pair of linear support members being respectively connected to the left wing and the right wing and symmetrically distributed on both sides of the fuselage, each of the linear support members being provided with at least two lift propellers; and at least one range extender, detachably connected to the aircraft and electrically connected to the aircraft to provide additional electrical power to the aircraft.

[0006] Optionally, a buffer device is provided between the power generation module and the housing, the buffer device being used to filter the vibration generated by the engine.

[0007] Optionally, the outer shell includes a head end, a middle end, and a tail end, wherein the head end is conical, the middle end is cylindrical, and the tail end includes a tail fin.

[0008] Optionally, the head end is provided with a first through hole for connecting the inner cavity of the outer shell and the outside.

[0009] Optionally, the outer casing is provided with a plurality of second through holes for discharging air that enters through the first through holes.

[0010] Optionally, the middle and tail ends are detachably connected.

[0011] Optionally, the range extender further includes a heat dissipation module for cooling the power generation module.

[0012] Optionally, the end of the first through hole that connects to the inner cavity of the outer shell is provided with a raised ring portion, the raised ring portion being higher than the inner surface of the first through hole.

[0013] Optionally, the range extender is connected to the aircraft via a rope component. The rope component contains a cable, one end of which is electrically connected to the range extender, and the other end is electrically connected to the aircraft's electrical system. The cable includes a control line and a power line. The control line is used to send control signals to the range extender to activate it before the aircraft's battery is depleted. The range extender charges the aircraft via the power line.

[0014] The range extender of this application implements a modular system integration design, which greatly improves the flight range of the aircraft by temporarily increasing the same unit weight. Attached Figure Description

[0015] Figure 1 The diagram shown is a structural schematic of the range extender according to the first embodiment of this application;

[0016] Figure 2 The diagram shown is another structural schematic of the range extender according to the first embodiment of this application;

[0017] Figure 3 The diagram shown is a structural schematic of the power generation module according to the first embodiment of this application;

[0018] Figure 4 Displayed as Figure 2 A magnified view of a portion of position A in the middle;

[0019] Figure 5 The diagram shown is a structural schematic of the vertical takeoff and landing aircraft according to the second embodiment of this application.

[0020] Figure 6 The diagram shown is a structural schematic of a vertical takeoff and landing aircraft according to another embodiment of this application.

[0021] Figure 7 The diagram shown is a structural schematic of a vertical takeoff and landing aircraft according to another embodiment of this application.

[0022] Figure 8 The diagram shown is a structural schematic of a vertical takeoff and landing aircraft according to another embodiment of this application.

[0023] Figure 9 The diagram shown is a structural schematic of a vertical takeoff and landing aircraft according to another embodiment of this application. Detailed Implementation

[0024] 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.

[0025] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections or detachable connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0026] 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.

[0027] 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.

[0028] The term "vertical takeoff and landing (VTOL) aircraft" is defined as an air transport system of any size that has at least one propeller as its propulsion source. The term "VTOL aircraft" can include both "manned" and "unmanned" air transport systems. A manned VTOL aircraft can mean an air transport system carrying one or more human passengers, none of whom have control over the VTOL aircraft. A manned VTOL 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 VTOL aircraft. An unmanned VTOL 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.

[0029] 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.

[0030] The accompanying drawings illustrate various embodiments of the vertical takeoff and landing 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.

[0031] Embodiments of this application are described below with reference to the accompanying drawings, such as Figure 1 As shown, the first embodiment of this application provides a range extender for providing additional electrical energy to an aircraft. The range extender includes a power generation module 1, a fuel tank 2, and a housing 3. The power generation module 1 includes an engine 11 and a generator 12, which are connected by a coupling 10. The engine 11 drives the generator 12 to rotate and generate electricity, which is then supplied to the aircraft 100. The fuel tank 2 includes a fuel outlet connected to the engine 11 to provide it with fuel. The housing 3 is streamlined, and the power generation module 1 and the fuel tank 2 are housed within the housing 3.

[0032] Specifically, the electrical energy generated by the generator 12 is usually regulated by a rectifier circuit before being input into the battery pack of the aircraft 100 to avoid interfering with the electronic circuits of the aircraft and affecting flight stability.

[0033] Fuel tank 2 can also be equipped with a fuel inlet, which can be connected to the outside through a through hole on the outer casing 3, allowing fuel to be filled through the through hole. Of course, fuel tank 2 can also be equipped with only one outlet, serving as both the fuel outlet and inlet. In this case, fuel tank 2 needs to be completely removed before fuel can be filled.

[0034] The power generation module 1 and the fuel tank 2 can be fixed inside the outer casing 3 by means of brackets or clips, but no specific restrictions are made here.

[0035] Furthermore, such as Figure 2As shown, the outer shell 3 includes a nose end 31, a middle end 32, and a tail end 33. The nose end 31 is preferably conical, the middle end 32 is preferably cylindrical, and the tail end 33 preferably includes a tail fin to maintain flight balance.

[0036] The outer shell 3 has a streamlined structure similar to a missile, which can minimize the impact of wind resistance during flight. In some embodiments, the tail section 33 may not have a tail fin.

[0037] In one embodiment, the head end portion 31 is provided with a first through hole 310 for connecting the inner cavity of the outer casing 3 and the outside. Preferably, the outlet of the first through hole 310 is located on the windward side of the foremost end portion 31, so that airflow can enter the inner cavity of the outer casing 3 through the first through hole 310.

[0038] Furthermore, the outer casing 3 is provided with multiple second through holes 320 for exhausting air that enters through the first through hole 310. The location and number of the second through holes 320 are not specifically limited. Airflow dissipates heat from the power generation module 1 as it passes through the first through hole 310 and the second through holes 320. In some cases, rainwater entering the outer casing 3 can also be discharged through the second through holes 320.

[0039] In one embodiment, such as Figure 2 and Figure 3 As shown, a buffer device 4 is provided between the power generation module 1 and the housing 3. Because the engine will generate a certain amount of vibration, the buffer device 4 can filter the vibration generated by the engine 11, thereby maintaining the stability of the machine. The buffer device 4 includes, but is not limited to, buffer pads or dampers.

[0040] In one embodiment, the middle end 32 and the tail end 33 are detachably connected to facilitate opening the housing 3 to remove the power generation module 1 and the fuel tank 2 for maintenance and other operations.

[0041] In one embodiment, such as Figure 2 As shown, the range extender also includes a heat dissipation module 5, which is used to cool the power generation module 1. The heat dissipation module 5 is preferably configured as an air-cooled heat dissipation system, which exhausts the hot air generated by the power generation module to the outer casing 3 through the second through hole 320. The heat dissipation module 5 can be a fan assembly.

[0042] Furthermore, such as Figure 4 As shown, in one embodiment, the end of the first through hole 310 connected to the inner cavity of the outer shell 3 is provided with a protruding ring 30. The protruding ring 30 is higher than the inner surface of the first through hole 310, so as to block rainwater from entering the first through hole 310.

[0043] like Figure 5As shown, the second embodiment of this application provides a vertical takeoff and landing (VTOL) aircraft, which includes: a fuselage 100, a left wing 101 and a right wing 102, a pair of linear support members 200, and a range extender 300. The left wing 101 and the right wing 102 are connected to both sides of the fuselage 100. The pair of linear support members 200 are respectively connected to the left wing 101 and the right wing 102 and are symmetrically distributed on both sides of the fuselage 100. Each linear support member 200 is equipped with three lift propellers. The range extender 300 is detachably connected to the aircraft and is electrically connected to the VTOL aircraft, thereby providing additional electrical energy to the VTOL aircraft.

[0044] The range extender 300 includes a power generation module 1, a fuel tank 2, and a housing 3. The power generation module 1 includes an engine 11 and a generator 12, which are connected by a coupling 10. The engine 11 drives the generator 12 to rotate and generate electricity, which is then input to the aircraft 100. The fuel tank 2 includes a fuel outlet connected to the engine 11 to provide it with fuel. The housing 3 is streamlined, and the power generation module 1 and the fuel tank 2 are housed within the housing 3.

[0045] The Range Extender 300 can be connected to the aircraft as a single module. When a higher-power range extender is needed, there is no need to redesign the existing range extender; simply install an additional range extender module to achieve high-power supply.

[0046] The power generation module 1 converts fossil fuels in the fuel tank 2 into electrical energy. The range extender 300 is externally mounted on the vertical takeoff and landing aircraft. In one embodiment, the range extender 300 is suspended below the fuselage 100 by a pair of rope components 400, the length of which is adjustable and not specifically limited. The fixed connection between the range extender 300 and the rope components 400 can be achieved by any possible existing means.

[0047] The cable component 400 contains a cable, one end of which is electrically connected to the range extender 300, and the other end is electrically connected to the electrical system inside the aircraft. The cable includes a control line and a power line. The control line is used to send control signals to the range extender 300 to activate the range extender 300 before the aircraft's battery is depleted. The range extender 300 charges the aircraft through the power line.

[0048] In another embodiment, such as Figure 6 As shown, the range extender 300 can be directly attached to the underside of the fuselage 100. The range extender 300 can be connected via a threaded installation, which allows for convenient and quick installation and removal of the range extender, reducing installation and disassembly procedures and improving work efficiency.

[0049] It should be noted that the internal arrangement of the range extender 300 is not limited to that shown in the attached drawings. The number of linear support members 200 and the range extender 300 is not limited to those shown in the drawings. The fuselage 100 can be a pod as shown in the attached drawings, which can be used for carrying passengers or cargo; of course, the fuselage 100 may also be without a pod. The volume and dimensions of the range extender 300 can also be adjusted accordingly to adapt to different installation scenarios.

[0050] In one embodiment, each linear support 200 may be equipped with an additional number of lift propellers.

[0051] In the aircraft provided in this application, each linear support is parallel to the longitudinal axis of the fuselage 100, 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 remaining working propellers can be kept in balance, allowing the aircraft to remain in the air.

[0052] In one embodiment, the range extender 300 is built into the housing 100. The range extender 300 can be directly fixed inside the housing 100, thus ensuring its stability and avoiding adverse effects caused by shaking.

[0053] In another embodiment, such as Figure 7 As shown, there is a pair of range extenders 300, corresponding to a pair of linear support members 200. A fixing mechanism is designed below the linear support member 200, and the range extender 300 is detachably mounted below the linear support member 200 through the fixing mechanism. Of course, the number of range extenders 300 can also be other, and the number should be the same as the number of linear support members 200. In addition, the dimensions of the range extender 300 in the attached figure are for illustrative purposes only and do not constitute actual dimensions.

[0054] In another embodiment, such as Figure 8 As shown, there is a pair of range extenders 300 and a pair of corresponding linear support members 200. The pair of range extenders 300 are respectively externally attached to the fuselage 100 and the pair of linear support members 200 in the lower middle area by ropes, which can achieve good mounting stability.

[0055] In another embodiment, such as Figure 9 As shown, the range extender 300 can be designed to be miniaturized and can be built into the linear support 200 and close to the lift propeller, serving as an additional charging device for the lift propeller.

[0056] The range extension device of the extended-range vertical takeoff and landing aircraft of this application can better increase the aircraft's endurance by temporarily adding the same unit weight, compared to directly mounting the same weight of batteries.

[0057] 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 range extender for providing additional electrical power to an aircraft, characterized in that, include: The power generation module (1) includes an engine (11) and a generator (12), which are connected by a coupling (10). The engine (11) can drive the generator (12) to rotate and generate electricity, which is then input into the aircraft. The fuel tank (2) includes an outlet, which is connected to the engine (11) to provide it with fuel energy. The outer shell (3) is streamlined, and the power generation module (1) and the fuel tank (2) are disposed inside the outer shell (3).

2. The range extender according to claim 1, characterized in that, A buffer device (4) is provided between the power generation module (1) and the outer casing (3), and the buffer device (4) is used to filter the vibration generated by the engine (11).

3. The range extender according to claim 1, characterized in that, The outer shell (3) includes a head end (31), a middle end (32) and a tail end (33). The head end (31) is conical, the middle end (32) is cylindrical, and the tail end (33) includes a tail fin.

4. The range extender according to claim 3, characterized in that, The head end (31) is provided with a first through hole (310) for connecting the inner cavity of the outer shell (3) and the outside.

5. The range extender according to claim 4, characterized in that, The outer casing (3) is provided with a plurality of second through holes (320) for discharging air that enters through the first through hole (310).

6. The range extender according to claim 3, characterized in that, The middle end (32) and the tail end (33) are detachably connected.

7. The range extender according to claim 1, characterized in that, It also includes a heat dissipation module (5) for cooling the power generation module (1).

8. The range extender according to claim 4, characterized in that, The first through hole (310) is connected to the inner cavity of the outer shell (3) at one end, and the protruding ring (30) is higher than the inner surface of the first through hole (310).

9. A vertical takeoff and landing aircraft, characterized in that, include: The fuselage (100), the left wing (101) and the right wing (102) connected to the fuselage; At least one pair of linear support members (200), which are respectively connected to the left wing (101) and the right wing (102) and are symmetrically distributed on both sides of the fuselage (100), and at least two lift propellers are arranged on each of the linear support members (200); at least one range extender (300), which is detachably connected to the aircraft and electrically connected to the aircraft to provide additional power to the aircraft.

10. The vertical takeoff and landing aircraft according to claim 9, characterized in that, The range extender (300) is connected to the aircraft via a rope component (400). The rope component (400) contains a cable. One end of the cable is electrically connected to the range extender (300), and the other end is electrically connected to the electrical system inside the aircraft. The cable includes a control line and a power line. The control line is used to send control signals to the range extender (300) to activate the range extender (300) before the aircraft's battery is depleted. The range extender (300) charges the aircraft via the power line.

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