Aircraft

Abstract

The utility model discloses an aircraft which comprises an aircraft body and fixed wings, the fixed wings are located on the two sides of the aircraft body, the aircraft body is further provided with a rolling wing device, the rolling wing device comprises four rolling wings, two rolling wings are a first rolling wing unit and are located in front of the fixed wings in the length direction of the aircraft body, and the other rolling wing unit is located in front of the fixed wings in the length direction of the aircraft body. The other two rolling wings form a second group of rolling wing units and are positioned behind the fixed wings along the length direction of the fuselage; the four rolling wings can independently change the motion state, and the rotation directions of the two rolling wings in each group are opposite. According to the utility model, the rolling wings and the fixed wings are combined, so that seamless conversion between a vertical take-off and landing mode and a level flight mode can be realized; and meanwhile, the limitation of the aircraft in the aspect of high-speed flight is broken through based on the performance of the fixed wings, so that the aircraft has the high-speed flight capability while the vertical take-off and landing characteristics are reserved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, concretely is a novel aircraft. BACKGROUND

[0002] With the continuous progress of aircraft technology, the demand for aircraft with vertical take-off and landing (VTOL) capability is increasing. The rolling wing aircraft has a wide application prospect in the field of aircraft due to its vertical take-off and landing capability, high aerodynamic efficiency and low noise. However, in the existing aircraft scheme, although the rolling wing aircraft can generate lift and forward thrust in the vertical rotation axis plane through the cycloidal propeller adjusting mechanism, it has good maneuverability, but its cruising efficiency needs to be further improved.

[0003] The rolling wing aircraft in the prior art comprises a fuselage, a horizontal driving assembly and at least two rolling wing assemblies. The length direction of the propeller blade is parallel to the length direction of the fuselage. When the aircraft moves forward and backward under the driving of the horizontal driving assembly, the windward area of the propeller blade is small, thereby reducing the flight resistance, improving the flight speed and improving the flight efficiency. However, the propeller blade direction is only arranged horizontally, although the flight resistance is reduced, the flight efficiency is limitedly improved, and the flight time and flight stability of the aircraft are not improved. SUMMARY

[0004] The utility model aims at the deficiencies of the prior art, and provides an aircraft, which can improve the endurance and flight performance.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical scheme: 1. An aircraft, characterized by comprising a fuselage and a fixed wing, the fixed wing is located on both sides of the fuselage, the fuselage is further provided with a rolling wing device, the rolling wing device comprises four rolling wings, two rolling wings are a first group of rolling wing units, located in front of the fixed wing along the length direction of the fuselage, and the other two rolling wings are a second group of rolling wing units, located behind the fixed wing along the length direction of the fuselage; the four rolling wings can independently change the motion state, and the rotating directions of the two rolling wings in each group are opposite.

[0006] In an optional embodiment, the first group of rolling wing units and the second group of rolling wing units are arranged on the fuselage in the form of rolling wing series, and the fixed positions of the first group of rolling wing units and the second group of rolling wing units are away from the fixed wing.

[0007] In an optional embodiment, the rotating directions of the rolling wings on the same side of the fuselage of the first group of rolling wing units and the second group of rolling wing units are opposite.

[0008] In one alternative embodiment, the roll wing further includes an eccentric mechanism, which includes a rotating shaft and a plurality of blades mounted on the rotating shaft and capable of rotation, wherein the plane in which the blades are located has an adjustable angle with the direction of blade movement.

[0009] In one alternative embodiment, the eccentric mechanism includes an eccentric support shaft located at the end of the rotating shaft, an offset disk fixed to the end of the eccentric support shaft, the offset disk being hinged to a plurality of blades via a connecting rod, and the plurality of blades being arranged around the outer periphery of the rotating shaft.

[0010] In one alternative embodiment, the bias disk extends radially outward and is provided with a plurality of guide grooves, and one end of the connecting rod is placed in the guide groove.

[0011] In one alternative implementation, each of the four rollers is independently connected to a servo motor or a motor, which drives the corresponding roller to change its motion state.

[0012] In one alternative embodiment, the leading edge of the fixed wing is provided with an upwardly tilted portion to provide additional lift and rectification during high-speed flight.

[0013] In one alternative embodiment, the fuselage is made of carbon fiber composite material.

[0014] In one alternative embodiment, the tail section of the fuselage is further provided with a tail fin.

[0015] Compared with the prior art, the aircraft provided by this utility model combines a roll wing and a fixed wing, enabling seamless switching between vertical take-off and landing and level flight modes; at the same time, based on the performance of the fixed wing, it breaks through the limitations of the aircraft in high-speed flight, enabling the aircraft to retain the characteristics of vertical take-off and landing while having the ability to fly at high speed. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of the aircraft in this utility model.

[0017] Figure 2 This is a schematic diagram of the rotation direction of the roller in this utility model.

[0018] Figure 3 This is a schematic diagram of the structure of the rolling vane in this utility model.

[0019] Figure 4 This is a schematic diagram of the structure of an aircraft according to the present invention.

[0020] Reference numerals: 1. Fuselage; 2. Roller assembly; 3. Fixed wing; 4. Roller; 5. Tail fin; 21. Shaft; 22. Blade; 23. Offset disk; 24. Connecting rod; 25. Eccentric support shaft; 26. Guide groove. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] Please see Figures 1 to 4 This utility model provides an aircraft, including a fuselage 1, a roll wing device 2, and fixed wings 3. The fuselage 1 features a streamlined design to reduce drag and is made of carbon fiber composite material to ensure high strength and lightweight characteristics while improving performance; for example, carbon fiber reinforced metal matrix composite material can be used. A cabin can be installed on the fuselage 1, providing piloting, passenger, and storage space. The fixed wings 3 are located on both sides of the fuselage 1 along its length, i.e., two fixed wings 3 are provided.

[0023] like Figure 1 As shown, the leading edge of the fixed wing 3 is provided with an upward tilting portion, which is used to provide additional lift and rectification function during high-speed flight. The roll wing device 2 is also fixed to both sides of the fuselage 1, but is set away from the fixed wing 3, which can avoid interference between the fixed wing 3 and the roll wing 4 caused by the roll wing device 2 being set together with the fixed wing 3.

[0024] Please see Figure 1 and Figure 2 As shown, the rolling wing device 2 includes four rolling wings 4, with two rolling wings 4 forming a group. The two rolling wings 4 located in front of the fuselage 1 constitute the first group of rolling wing units, which are fixed in front of the fixed wing 3 along the length of the fuselage 1. The other two rolling wings 4 constitute the second group of rolling wing units, which are located behind the fixed wing 3 along the length of the fuselage 1.

[0025] In some embodiments, each of the four rollers 4 is independently connected to a motor, and the four motors drive the corresponding four rollers 4 respectively. By controlling the four motors, the motion state of the rollers 4 can be changed to achieve pitch oscillation motion.

[0026] In other embodiments, each of the four roll vanes 4 is independently connected to a servo motor, and the four servo motors drive the corresponding four roll vanes 4 respectively. By controlling the four servo motors, the motion state of the roll vanes 4 can be changed to achieve pitch oscillation motion.

[0027] With the above two implementation manners, the rotation speed of each roll wing 4 motor or steering engine can be independently adjusted for optimizing power distribution in different flight states, and the aircraft transmission system is omitted.

[0028] In the utility model, four roll wings 4 can independently change the motion state, and the flight direction of the fuselage 1 can be changed through different motion states of the four roll wings 4, and 360 full vector propulsion is realized. The rotation directions of the two roll wings 4 of each group are opposite. Figure 2 As shown in the embodiment of the application, the rotation directions of the roll wings 4 on the same side of the fuselage 1 of the first group of roll wing units and the second group of roll wing units are opposite. Figure 2 In the embodiment, one of the two roll wings 4 on the left front side (i.e. the first group of roll wing units) rotates clockwise, and the other rotates counterclockwise; one of the two roll wings 4 on the right rear side (i.e. the second group of roll wing units) rotates counterclockwise, and the other rotates clockwise. One of the two roll wings 4 on the right side of the fuselage 1 rotates counterclockwise, and the other rotates clockwise; one of the two roll wings 4 on the left side of the fuselage 1 rotates clockwise, and the other rotates counterclockwise.

[0029] The fixed positions of the first group of roll wing units and the second group of roll wing units are away from the fixed wing 3, and the independent driving structure with opposite rotation directions is arranged, so that the coupling problem of roll and pitch caused by the existence of two roll wings 4 on one side of the fuselage 1 can be overcome, and good flight performance is achieved; the influence of the pitch angle after being disturbed by a small pitch is small, and good maneuverability and stability are achieved.

[0030] The first group of roll wing units and the second group of roll wing units are arranged on the fuselage 1 in a roll wing tandem manner; that is, the front and rear wings are arranged along the axis of the fuselage 1. Compared with the traditional single-wing or double-wing layout, this layout form has the following obvious characteristics:

[0031] Optimized lift distribution: the front and rear wings can bear different stages of lift demand respectively, which helps to improve the overall lift efficiency.

[0032] Stability enhancement: the aerodynamic coupling effect between the front and rear wings can enhance the flight stability of the unmanned aerial vehicle and reduce the influence of turbulence.

[0033] Flexible load distribution: according to task requirements, equipment can be arranged at different positions of the front and rear wings or the fuselage 1 to realize flexible configuration of loads.

[0034] Aerodynamic resistance control: by adjusting the distance, area and angle of the front and rear wings, the aerodynamic resistance of the unmanned aerial vehicle can be effectively controlled, and the flight performance is optimized.

[0035] Please refer to Figure 3, the rolling wing 4 further comprises an eccentric mechanism, the eccentric mechanism comprises a rotating shaft 21 and a plurality of blades 22 arranged on the rotating shaft 21 and capable of rotating, the plane where the blades 22 are located has an angle-adjustable included angle with the movement direction of the blades 22, and the pitch movement of the blades 22 can be controlled by adjusting the included angle.

[0036] Specifically, the axial direction of the rotating shaft 21 is perpendicular to the length direction of the fuselage 1, that is, one end of the rotating shaft 21 is fixed on the fuselage 1, and the other end is away from the fuselage 1. The eccentric support shaft 25 is arranged at the end of the rotating shaft 21, the end of the eccentric support shaft 25 is further fixed with a biasing disc 23, and a plurality of guide grooves 26 are arranged on the biasing disc 23 and extend outward in the radial direction. The plurality of guide grooves 26 of the biasing disc 23 are hinged to the plurality of blades 22 through connecting rods 24, one end of the connecting rod 24 is arranged in the guide groove 26, the connecting rod 24 can slide and change position along the guide groove 26, and the plane where the blades 22 are located has an angle-adjustable included angle with the movement direction of the blades 22. The plurality of blades 22 are uniformly arranged around the outer periphery of the rotating shaft 21, the rotation of the rolling wing 4 realizes the vertical take-off and landing of the aircraft, the fixed wing 3 realizes the flat flight mode, and finally the seamless conversion of the vertical take-off and landing and the flat flight mode is achieved.

[0037] In some embodiments, the blades 22 adopt NACA0015 airfoils, the span length of the blades is 1m, the chord length is 0.3m, and there are 6 blades in total. The blades 22 realize the pitch oscillation movement through the connecting rods 24 and the eccentric mechanism.

[0038] Further, please refer to Figure 4 As shown in the figure, the tail of the fuselage 1 is further provided with a tail wing 5, and the tail wing 5 can ensure that the aircraft obtains the necessary stability and maneuverability in all possible states. The tail wing 5 enhances flight stability and reduces flight resistance when the aircraft flies at high speed, and in addition, a large-thrust engine can be installed to provide the required thrust for high-speed flight.

[0039] The rolling wing device 2 can rotate along the horizontal axis to provide forward and upward power for the aircraft. In the take-off stage, the rolling wing device 2 controls the thrust direction to generate upward thrust, the aircraft is vertically taken off by the rolling wing device 2 providing all lift. After the aircraft reaches the predetermined height, the rolling wing device 2 is controlled to provide lift and thrust at the same time, so that the aircraft enters the flat flight mode, and the fixed wing 3 and the rolling wing device 2 provide lift at the same time. During the flat flight, the rolling speed and eccentric distance of each rolling wing 4 are adjusted to change the thrust size and direction of each rolling wing 4, so that the flight attitude can be controlled. When reaching the predetermined location in the air to prepare for landing, all lift is provided by the rolling wing 4, and the aircraft is vertically landed.

[0040] The aircraft provided by the utility model combines the rolling wing and the fixed wing, can realize seamless conversion of vertical take-off and landing and flat flying mode, and breaks through the limitation of the aircraft in high-speed flight based on the performance of the fixed wing, so that the aircraft has the ability of high-speed flight while retaining the vertical take-off characteristics.

[0041] The utility model drives by motor or rudder, omits the aircraft transmission system, in addition, the arrangement mode of rolling wing string further improves the load, the fixed wing improves the navigation time, so that the aircraft has good flight performance, the rolling wing has high reliability, light weight, small noise, safe and comfortable performance, the utility model breaks through the application limitation of traditional aircraft in multi-task scene, has high efficiency, high mobility and multi-scene adaptability, is especially suitable for application scene such as city short-distance transportation, long navigation time cruise, complex task operation, and has good application prospect.

[0042] Finally, it should be noted that: the above only for the preferred embodiments of the utility model, and does not limit the utility model, although the utility model has been described in detail with reference to the foregoing embodiments, for the person skilled in the art, it still can modify the technical scheme recorded in foregoing each embodiment, or equivalent replacement for part of technical features. Any modification, equivalent replacement, improvement etc. within the spirit and principle of the utility model, should be included in the protection scope of the utility model.

Claims

1. An aircraft, characterized in that: The aircraft comprises a fuselage and fixed wings on both sides of the fuselage, and a rolling wing device on the fuselage, which comprises four rolling wings, two of which are a first group of rolling wing units, located in front of the fixed wings along the length direction of the fuselage, and the other two are a second group of rolling wing units, located behind the fixed wings along the length direction of the fuselage; the four rolling wings can independently change the motion state, and the rotating directions of the two rolling wings in each group are opposite.

2. An aircraft as claimed in claim 1, characterised in that: The first group of rolling wing units and the second group of rolling wing units are arranged on the fuselage in the form of rolling wing series, and the fixed positions of the first group of rolling wing units and the second group of rolling wing units are away from the fixed wings.

3. An aircraft as claimed in claim 2, characterised in that: The rotating directions of the rolling wings on the same side of the fuselage of the first group of rolling wing units and the second group of rolling wing units are opposite.

4. The aircraft of claim 1, wherein: The rolling wing further comprises an eccentric mechanism, which comprises a rotating shaft and a plurality of paddles arranged on the rotating shaft and capable of rotating, and the plane of the paddle has an angle-adjustable included angle with the movement direction of the paddle.

5. An aircraft as claimed in claim 4, characterised in that: The eccentric mechanism comprises an eccentric support shaft arranged at the end of the rotating shaft, and the end of the eccentric support shaft is fixed with a biasing disc, the biasing disc is hinged with a plurality of paddles through a connecting rod, and a plurality of paddles are arranged around the outer periphery of the rotating shaft.

6. An aircraft as claimed in claim 5, characterised in that: The biasing disc is provided with a plurality of guide grooves extending radially outward, and one end of the connecting rod is placed in the guide groove.

7. The aircraft of claim 1, wherein: The four rolling wings are respectively independently connected with a rudder or a motor, and the rudder or the motor is used to drive the corresponding rolling wing to change the motion state.

8. An aircraft according to any one of claims 1 to 7, characterised in that: The leading edge of the fixed wing is provided with an upward inclined part for providing additional lift and fairing function when flying at high speed.

9. An aircraft as claimed in any one of claims 1 to 7, characterised in that: The fuselage is made of carbon fiber composite material.

10. An aircraft as claimed in any one of claims 1 to 7, characterised in that: The tail of the fuselage is further provided with a tail wing to enhance the flight stability.

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