Vertical take-off and landing aircraft

Abstract

The utility model provides a vertical take-off and landing aircraft, which belongs to the technical field of aircrafts, and comprises a horizontal pushing power, a vertical lifting power, a tilting propeller, a piston engine and a turbojet engine, when the tilting propeller is switched to the vertical lifting power, the turbojet engine serves as a main lifting force and drives a fuselage to lift, and the tilting propeller assists the fuselage to keep stable and balanced, so that the vertical take-off and landing of the fuselage is realized. After lifting is completed, the turbojet engine is closed; and when the tilting propellers are switched to horizontal pushing power, the fuselage is driven to fly horizontally, and the turbojet engine is turned off during horizontal flying. The tilting propeller and the turbojet engine are arranged, the piston engine provides electric power for the motor of the tilting propeller, and the turbojet engine provides main lift force for lifting of the fuselage, so that the requirement of vertical power for electric energy is reduced, the weight of a battery is reduced, the tilting propeller can work during level flight and lifting, and the service life of the aircraft is prolonged. And therefore, the waste weight is reduced, the sailing distance is increased, and the use effect is better.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, concretely relates to a vertical take-off and landing aircraft. BACKGROUND

[0002] With the development of aircraft, currently there are various aircraft schemes that can realize vertical take-off and landing and flat flight cruising, such as oil-driven tilting rotor schemes, represented by the fish hawk helicopter, and composite rotor schemes.

[0003] The aircraft adopting the composite rotor scheme relies on the rotor for vertical take-off and landing, relies on the fixed wing and the propeller generating thrust to the rear of the aircraft for maintaining the lift and horizontal thrust during flat flight, at this time the rotor responsible for vertical take-off and landing does not work, and the driving mode of the rotor is electric, the battery specially providing electric energy for vertical take-off and landing is arranged in the fuselage, when the aircraft is flat flying, this mechanism stops working, the battery and the vertical take-off and landing rotor become waste weight, which will increase the weight of the aircraft, increase the energy consumption, and reduce the effective load and the flight distance. SUMMARY

[0004] Therefore, the utility model adopts a turbojet engine + electric tilting rotor to complete vertical take-off and landing and flat flight in the mode of oil-electric hybrid power, changes the condition that the vertical take-off battery and the vertical take-off rotor do not work when the aircraft is flat flying, solves the problem that the vertical take-off battery and the vertical take-off rotor become waste weight that increases the weight of the aircraft, thereby reduces the energy consumption, and improves the effective load and the flight distance, and provides a new vertical take-off and landing mode for the vertical take-off and landing aircraft.

[0005] In order to solve the above technical problems, the utility model provides a vertical take-off and landing aircraft, which comprises a fuselage.

[0006] The tilting propeller is installed on the fuselage, when the tilting propeller is switched to vertical take-off power, the turbojet engine provides main lift for the fuselage and drives the fuselage to ascend and descend, the tilting propeller assists the fuselage to keep stable balance, after the ascending and descending is completed, the turbojet engine is turned off, when the tilting propeller is switched to horizontal thrust power, the tilting propeller drives the fuselage to flat fly, at this time the turbojet engine is turned off.

[0007] The piston engine is installed in the fuselage, the driving end of the piston engine is connected with a generator and a battery pack, the generator, the battery pack and the motor of the tilting propeller are electrically connected.

[0008] The turbojet engine is installed in the fuselage, the airflow jetted by the turbojet engine is vertically towards the lower side of the fuselage, the vertical take-off power generated by the turbojet engine serves as the main lift for driving the fuselage to ascend and descend.

[0009] Optionally, the tilting propeller comprises a tail propeller arranged at the tail of the fuselage and a wing propeller arranged at the side of the fuselage.

[0010] Optionally, the wing propeller is symmetrically arranged at the two sides of the fuselage.

[0011] Optionally, the fuselage is provided with a battery, the input end of which is electrically connected with the generator and the output end of which is electrically connected with the motor of the tilting propeller.

[0012] Optionally, the turbojet engine is symmetrically arranged in the body of the fuselage.

[0013] Optionally, the jet port of the turbojet engine is arranged downward for providing main lift, the tilting propeller assists the fuselage to keep stable balance, and the turbojet engine is turned off after take-off and landing are completed.

[0014] Optionally, the turbojet engine is horizontally arranged, and the jet end of the turbojet engine is connected with an arc-shaped jet pipe with an opening downward, which is suitable for vertical take-off and landing of a rotor aircraft, vertical take-off and landing of a fixed-wing aircraft and a fixed-wing aircraft.

[0015] Optionally, the fuselage is provided with a fuel tank for storing fuel, and the fuel enters into the piston engine and the turbojet engine through oil pipes respectively.

[0016] The technical scheme of the vertical take-off and landing aircraft has the following advantages.

[0017] 1. The vertical take-off and landing aircraft provided by the utility model takes the turbojet engine as the main lift to drive the fuselage to ascend and descend, and keeps the fuselage posture stable and balanced through the electric tilting propeller during the ascending and descending process, and turns off the turbojet engine after the vertical take-off and landing are completed.

[0018] The self-generating system of the piston engine provides power for the motor of the tilting propeller, the turbojet engine provides main lift for the ascending and descending of the fuselage, the demand of the vertical take-off power for electric energy is reduced, the weight of the battery is reduced, the tilting propeller can work during the ascending and descending and the flat flight, the tilting propeller is fully utilized, the waste weight is reduced, the navigation distance is improved, and the use effect is better.

[0019] 2. The vertical take-off and landing aircraft provided by the utility model is driven by the electric tilting propeller, the rotating speed of the tilting propeller is improved, the use is more sensitive, and the use effect is better.

[0020] 3. The vertical take-off and landing aircraft, when the piston engine is running, the battery can be charged through the generator, so as to store the excess electric energy, when needed, the motor of the tilting propeller can be provided with power, and the battery is not the energy storage component for providing the main lift, so that the volume and weight are relatively low, thereby reducing the weight of the fuselage, effectively improving the payload and navigation distance.

[0021] 4. The vertical take-off and landing aircraft, the piston engine and the turbojet engine share an oil tank, the fuel in the oil tank is consumed by the two engines at the same time, the corresponding weight of the fuel consumption is reduced, and the aircraft becomes lighter, thereby effectively reducing the burden of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed in the specific embodiments or the prior art description will be briefly introduced as follows. Obviously, the drawings in the following description are some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0023] Figure 1 is a front view of the vertical take-off and landing aircraft provided in the first embodiment of the present application;

[0024] Figure 2 is Figure 1 another side view;

[0025] Figure 3 is Figure 1 a sectional view of

[0026] Figure 4 is a front view of the vertical take-off and landing aircraft provided in the second embodiment of the present application;

[0027] Figure 5 is Figure 4 another side view;

[0028] Figure 6 is Figure 4 a sectional view of

[0029] BRIEF DESCRIPTION OF DRAWINGS

[0030] 1, fuselage; 2, tilting propeller; 3, turbojet engine; 4, tail push propeller; 5, wing propeller; 6, wing; 7, arc-shaped jet pipe. DETAILED DESCRIPTION

[0031] The technical solutions of the present application will be described clearly and completely in connection with the drawings. Obviously, the described embodiments are some of the embodiments of the present application, but not all the embodiments. Based on the embodiments of the present application, all the other embodiments obtained by those skilled in the art without creative labor fall within the scope of the present application.

[0032] In the description of the present application, it should be noted that the directions or position relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like are based on the directions or position relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0033] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, or the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0034] In addition, the technical features involved in the different embodiments of the present application described below can be combined with each other as long as there is no conflict.

[0035] For example, the first and second embodiments can be combined with each other. Figures 1 to 6As shown in the figure, the vertical take-off and landing aircraft provided by the embodiment includes a fuselage 1, a tilting propeller 2, a piston engine, and a turbojet engine 3. The actuator of the tilting propeller 2 is mounted on the fuselage 1. When the tilting propeller 2 is switched to vertical take-off power, the turbojet engine 3 provides the fuselage 1 with main lift and drives the fuselage 1 to ascend and descend, and the tilting propeller 2 assists the fuselage 1 to keep stable balance. After the ascending and descending are completed, the turbojet engine 3 is turned off. When the tilting propeller 2 is switched to horizontal thrust power, the fuselage 1 is driven to fly horizontally, and the turbojet engine 3 is turned off at this time. The piston engine is mounted in the fuselage 1. The driving end of the piston engine is connected with a generator and a battery pack (not shown in the figure). The generator and the battery pack are electrically connected with the motor of the tilting propeller 2. The turbojet engine 3 is mounted in the fuselage 1. The airflow jetted by the turbojet engine 3 is vertically directed to the lower side of the fuselage 1. The vertical take-off power generated by the turbojet engine 3 is used to drive the fuselage 1 to ascend and descend. In the embodiment, the piston engine (not shown in the figure) and the turbojet engine 3 are embeddedly mounted. The number of the turbojet engines 3 is not fixed. The number of the turbojet engines 3 can be adjusted according to the take-off weight. The power sources of the piston engine and the turbojet engine 3 are all fuel.

[0036] The vertical take-off and landing aircraft provided by the embodiment drives the fuselage 1 to fly horizontally by the tilting propeller 2, drives the fuselage 1 to ascend and descend by the tilting propeller 2 and the turbojet engine 3, and provides the motor of the tilting propeller 2 with power by the self-power generation system of the piston engine. The turbojet engine 3 provides the fuselage 1 with main lift for ascending and descending. After the vertical take-off and landing are completed, the turbojet engine 3 is turned off. The use of the turbojet engine 3 as the main lift reduces the demand of the vertical take-off power for electric energy, reduces the weight of the battery, and makes the tilting propeller 2 work in the horizontal flight and the ascending and descending, so that the tilting propeller 2 is fully utilized, the waste weight is reduced, the navigation distance is improved, and the use effect is better.

[0037] As shown in the figure, Figure 1 , Figure 2 In the vertical take-off and landing aircraft provided by the embodiment, the tilting propeller 2 includes a tail propeller 4 and a side wing propeller 5. The tail propeller 4 is arranged at the tail of the fuselage 1. The side wing propeller 5 is arranged at the side of the fuselage 1. The tail propeller 4 can provide the aircraft with horizontal thrust power. The side wing propeller 5 can assist the turbojet engine 3 to provide the aircraft with stable balanced power.

[0038] As shown in the figure, Figure 1 , Figure 2As shown, in the vertical take-off and landing aircraft provided in this embodiment, there are at least two side propellers 5 symmetrically arranged on both sides of the fuselage 1. In this embodiment, when the fuselage 1 has wings 6, the number of the side propellers 5 is two, and when the fuselage 1 does not have wings 6, the number of the side propellers 5 is four. The side propellers 5 can make the fuselage 1 evenly stressed and more stable during flight.

[0039] like Figure 1 、 Figure 2 As shown, in the vertical take-off and landing aircraft provided by this embodiment, a battery (not shown in the figure) is provided in the fuselage 1, the input end of which is electrically connected to the generator, and the output end of which is electrically connected to the motor of the tilting propeller 2. When the piston generator is running, the battery can be charged by the generator, thereby storing excess electrical energy. When needed, it can provide power to the motor of the tilting propeller 2. Moreover, the battery is not a main lift power storage component, so its volume and weight are correspondingly low, thereby making the weight of the fuselage 1 lower and effectively increasing the cruising distance.

[0040] like Figures 1 to 3 As shown, in the vertical take-off and landing aircraft provided in this embodiment, the turbojet engine 3 is symmetrically arranged in the body of the fuselage 1. Specifically, when the fuselage 1 does not have wings 6, the turbojet engine 3 is arranged in the body of the fuselage 1. The turbojet engine 3 is symmetrically arranged to ensure uniform weight distribution and improve the stability of the fuselage 1.

[0041] like Figures 4 to 6 As shown, in the vertical take-off and landing aircraft provided by this embodiment, the jet outlet of the turbojet engine 3 is set downward to provide the main lift, and the tilt propeller 2 assists the fuselage 1 in rising and falling. When performing level flight, the tilt propeller 2 provides horizontal power to enable the fuselage 1 to fly level. The turbojet engine 3 provides the main lift and drives the fuselage 1 to rise and fall together with the tilt propeller 2, making the rising and falling of the fuselage 1 more stable and energy-saving, and having a better use effect.

[0042] like Figure 3 、 Figure 6 As shown, in the vertical take-off and landing aircraft provided by this embodiment, the turbojet engine 3 is arranged horizontally, and the jet end of the turbojet engine 3 is connected to a curved jet pipe 7 with the opening facing downward. Since the turbojet engine 3 is relatively long, in order to ensure that it can be installed smoothly, it is arranged horizontally, which can save vertical space. It is suitable for vertical rotorcraft, vertical fixed-wing aircraft and fixed-wing aircraft.

[0043] like Figure 1 、 Figure 2As shown, the vertical take-off and landing aircraft provided by the embodiment has an oil tank (not shown in the figure) in the fuselage 1 for storing fuel, the fuel enters the piston engine and turbojet 3 through the oil pipe respectively, the piston engine and turbojet 3 share an oil tank, the fuel in the oil tank is consumed by the two driving members at the same time, the aircraft becomes lighter and lighter, and the corresponding weight is reduced, thereby reducing the burden of the aircraft.

[0044] In the embodiment of the utility model, for fish eagle type tilt rotor aircraft, because the rotor diameter of fish eagle type tilt rotor aircraft is larger, when cruising, it will cause greater insecurity, affect the cruising of fish eagle type tilt rotor aircraft, the embodiment provides auxiliary lift for it through turbojet 3, can shorten the rotor of fish eagle type tilt rotor aircraft, at the same time, also does not reduce the lift, completely solves the safety problem of fish eagle aircraft.

[0045] In the embodiment of the utility model, for electric non-tilt rotor aircraft, when the electric non-tilt rotor aircraft takes off vertically, it needs larger motor power, and then leads to larger motor weight, and when cruising, the rotor cannot be tilted, and is pushed by the tail, and then the rotor becomes waste weight, the embodiment provides lift for the fuselage 1 through the setting turbojet 3, and the tilt propeller 2 only assists the fuselage 1, makes it keep stable balance in the lifting process, and then needs smaller motor power, and the motor and battery pack are lighter.

[0046] In the embodiment of the utility model, for electric tilt rotor aircraft, it is through electric tilt rotor as main lift, leads to larger required motor power, and the energy storage and weight of battery are increased, therefore, the battery pack can only take off and land once, and the embodiment sets turbojet 3, uses fuel as fuel, can take off and land multiple times, makes the use of aircraft more convenient.

[0047] Of course, although the turbojet 3 is powerful, it is fuel-consuming and unstable, when encountering crosswind, the attitude is adjusted slowly, and the embodiment sets the tilt propeller 2, keeps the stable balance of the attitude of the fuselage 1 through the tilt propeller 2.

[0048] The working process of the vertical take-off and landing aircraft provided by the embodiment is as follows:

[0049] When the aircraft needs to take off vertically, the tilt propeller 2 is switched to vertical take-off power, the turbojet engine 3 is started and the piston engine generates electricity, the turbojet engine 3 provides upward lift for the fuselage 1, the tilt propeller 2 assists the fuselage 1 to keep stable balance, the aircraft performs vertical ascending operation, when the aircraft vertical ascending is completed and needs to fly horizontally, the turbojet engine 3 is closed, the tilt propeller 2 is switched to horizontal thrust power, the tilt propeller 2 provides horizontal thrust for the fuselage 1, the aircraft performs horizontal flying operation; when the aircraft needs to descend, the turbojet engine 3 is started again, and the tilt propeller 2 is switched to vertical take-off power, the aircraft performs descending operation, and then the vertical take-off and horizontal flying operation process of the aircraft is completed.

[0050] Obviously, the above embodiments are only examples for clearly illustrating but not limiting the embodiments. Based on the above description, other different forms of changes or variations can be made by those skilled in the art. All the embodiments do not need to be exhausted here. The obvious changes or variations derived therefrom are still within the protection scope of the present application.

Claims

1. A vertical take-off and landing aircraft characterised in that, Include: The fuselage (1); The tilting propeller (2) is mounted on the fuselage (1), when the tilting propeller (2) is switched to vertical take-off power, the turbojet engine (3) provides the main lift for the fuselage (1) and drives the fuselage (1) to take off and land, the tilting propeller (2) assists the fuselage (1) to keep stable balance, and the turbojet engine (3) is closed after landing; When the tilting propeller (2) is switched to horizontal thrust, it drives the fuselage (1) to fly horizontally, and the turbojet engine (3) is closed at this time; The piston engine is installed in the fuselage (1), the driving end of the piston engine is connected with the generator and the battery pack, and the generator, the battery pack and the motor of the tilting propeller (2) are electrically connected; The turbojet engine (3) is installed in the fuselage (1), the airflow ejected by the turbojet engine (3) is vertically directed downward of the fuselage (1), and the vertical take-off power generated by the turbojet engine (3) serves as the main lift for driving the fuselage (1) to take off and land.

2. The vertical take-off and landing aircraft of claim 1, wherein, The tilting propeller (2) includes: tail push propeller (4) and wing propeller (5), the tail push propeller (4) is arranged at the tail of the fuselage (1), and the wing propeller (5) is arranged on the side of the fuselage (1).

3. The vertical take-off and landing aircraft of claim 2, wherein, The wing propeller (5) is symmetrically arranged on both sides of the fuselage (1).

4. The vertical takeoff and landing aircraft of claim 1, wherein, The fuselage (1) has a battery inside, the input end is electrically connected with the generator, and the output end is electrically connected with the motor of the tilting propeller (2).

5. The vertical takeoff and landing aircraft of claim 1, wherein, The turbojet engine (3) is symmetrically arranged in the body of the fuselage (1).

6. The vertical take-off and landing aircraft of claim 5, wherein, The jet port of the turbojet engine (3) is downwardly arranged for providing main lift, the tilting propeller (2) assists the fuselage (1) to keep stable balance, the turbojet engine (3) is closed after take-off and landing, when flying horizontally, the tilting propeller (2) is tilted to provide horizontal power to make the fuselage (1) fly horizontally, and the turbojet engine (3) is closed.

7. The vertical take-off and landing aircraft of claim 5 or 6, wherein, The turbojet engine (3) is horizontally arranged, and the jet end of the turbojet engine (3) is connected with an arc-shaped jet pipe (7) with downward opening, which is suitable for vertical take-off rotor aircraft, vertical take-off fixed wing aircraft and fixed wing aircraft.

8. The vertical take-off and landing aircraft of any one of claims 1-6, wherein, The fuselage (1) has a fuel tank for storing fuel, and the fuel enters the piston engine and the turbojet engine (3) through oil pipes respectively.

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