Novel aircraft capable of vertically taking off and landing

Abstract

The utility model relates to a novel aircraft capable of vertically taking off and landing. The novel aircraft comprises a fuselage, wings, a rotor power device, an empennage, a propulsion power device and an undercarriage, according to the vertical take-off and landing aircraft, the rotor power mounting frames are mounted at the tips of the wings, and the rotor power devices are arranged on the rotor power mounting frames, so that the vertical take-off and landing of the aircraft are realized, and the requirement of the aircraft for occupying land on a runway when the aircraft runs is reduced. According to the rotor power device, a circle of rotor paddle protection structure is arranged on the periphery of the rotor paddle of the rotor power device, and the rotor paddle protection structure and the rotor paddle are integrally formed, so that the paddle tip vortex can be reduced, and the noise of the rotor power device is reduced. In addition, the existence of the rotor paddle protection can prevent ground personnel from being injured by the rotor paddle.

Description

Technical Field

[0001] The utility model relates to the field of aviation technology, in particular to a novel aircraft capable of vertical take-off and landing. Background Art

[0002] In today's society, low-altitude economy is widely used and developed, and urban aircraft will play an extremely important role in the future low-altitude economy. Pure multi-rotors are safe and reliable, but their endurance is slightly shorter; pure fixed-wing aircraft have stronger endurance, but require a larger runway area due to the need for a longer taxiing distance.

[0003] In view of the above two points, most urban aircraft are now powered by pure electric composite wings and tilt-rotors. However, composite wings will cause the rotor to stop working during flight, which will result in a certain amount of waste weight, and the structure and control of tilt-rotors are relatively complex. At the same time, research on rotor noise and safety protection is also indispensable. Utility Model Content

[0004] The technical problem solved by the utility model is to provide an aircraft capable of vertical take-off and landing with good safety performance, low rotor noise and simple control logic.

[0005] The technical solution adopted by the utility model to solve its technical problems is:

[0006] A novel aircraft capable of vertical take-off and landing, comprising a fuselage, wings, a rotor power unit, a tail wing, a propulsion power unit and a landing gear;

[0007] The wings are symmetrically arranged and installed on both sides of the upper part of the middle section of the fuselage to form left and right wings. The tips of the left and right wings are symmetrically arranged and installed with rotor power mounting frames, and rotor power batteries are arranged and installed inside the mounting frames.

[0008] The outermost end of the rotor power mounting frame is provided with a rotor power mounting platform, the rotor power device is arranged and mounted on the rotor power mounting platform, and is symmetrically arranged on the left and right sides of the fuselage through the rotor power mounting frame to form left and right rotor power devices, and the rotor power batteries inside the left and right wings respectively supply power to the left and right rotor power devices;

[0009] The tail wing is installed at the upper end of the tail of the fuselage in a left-right symmetrical and inclined arrangement to form a left and right tail wing, and the trailing edges of the left and right tail wing are symmetrically provided with tail wing control surfaces for pitch and yaw control;

[0010] The propulsion power device is arranged and installed inside the tail of the fuselage. An air inlet for the propulsion power device to inlet air is regularly arranged on the fuselage at the front end of the propulsion power device, and an ejection port for the propulsion power device to eject air is regularly arranged on the fuselage at the rear end of the propulsion power device.

[0011] The jets include a main jet at the tail end of the fuselage, upper and lower power jets on the upper and lower sides of the tail of the fuselage, and left and right power jets on the left and right sides of the tail of the fuselage.

[0012] Furthermore, the front end of the fuselage is regularly provided with a front windshield, the front side thereof is regularly provided with a cabin door, and the two sides thereof are regularly provided with a plurality of cabin glasses.

[0013] Furthermore, the rotor power device includes two sets of motors installed upper and lower and rotating coaxially in opposite directions, a rotor propeller and a rotor propeller protection. The rotor propeller protection forms a fence structure that surrounds the rotor propeller and is integrally formed with it.

[0014] Furthermore, the left and right tail wings are V-shaped tail wings, which are arranged and installed on the upper end of the tail of the fuselage and are arranged away from the upper and lower power jets and the left and right power jets.

[0015] Furthermore, a plurality of fan blade baffles are regularly arranged at the upper and lower power jet ports and the left and right power jet ports, and the plurality of fan blade baffles are driven to open and close by a motor or an electric cylinder.

[0016] Furthermore, the fan blade baffles at the upper and lower power jet ports control the opening sizes of the upper and lower power jet ports to adjust the pitch attitude of the aircraft; the fan blade baffles at the left and right power jet ports control the opening sizes of the left and right power jet ports to adjust the yaw attitude of the aircraft.

[0017] Furthermore, the landing gear includes a front landing gear and a rear landing gear, the rear landing gear is symmetrically arranged and installed in the middle part of the belly of the fuselage, and the front landing gear is arranged and installed in the front part of the belly of the fuselage, and the front landing gear and the rear landing gear form a three-point landing gear.

[0018] Furthermore, the wing and the rotor power mounting frame are both arranged to be tilted upward, with an inclination angle of 9-12° upward relative to the horizontal plane.

[0019] The beneficial effects of the utility model are:

[0020] 1. The utility model realizes vertical take-off and landing of the aircraft by installing a rotor power mounting frame at the tip of the wing and arranging and installing the rotor power device on the rotor power mounting frame, thereby reducing the need for runway space when the aircraft is taxiing.

[0021] 2. The utility model adopts a wing design, and the wing can also generate lift when the aircraft flies forward. By retaining the wing design, the energy loss of the aircraft can be reduced, thereby increasing the flight time and range of the aircraft.

[0022] 3. The utility model can save space inside the fuselage by reasonably arranging and installing the power supply battery of the rotor power device inside the wing, thereby effectively utilizing the space inside the fuselage.

[0023] 4. The utility model provides a circle of rotor blade protection structure on the periphery of the rotor blade of the rotor power device, and the rotor blade protection and the rotor blade are integrally formed, so as to reduce the blade tip vortex and reduce the noise of the rotor power device. Moreover, the existence of the rotor blade protection can prevent ground personnel from being harmed by the rotor blade.

[0024] 5. The aircraft of the present invention adopts a hybrid system of oil and electricity, which can increase the endurance of the aircraft under the current low battery energy density. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a three-dimensional structural diagram of the utility model;

[0026] Figure 2 It is a side view of the utility model;

[0027] Figure 3 This is the front view of the utility model

[0028] Figure 4 It is a top view of the utility model;

[0029] The markings in the figure are:

[0030] 1. Fuselage, 101. Front windshield, 102. Door, 103. Cabin glass, 2. Wing, 3. Rotor power mounting frame, 4. Rotor power unit, 401. Rotor propeller, 401. Rotor propeller protection, 5. Tail, 501. Tail control surface, 6. Propulsion power unit, 7. Air intake, 8. Upper and lower power jets, 9. Left and right power jets, 10. Rotor power battery, 11. Rear landing gear, 12. Front landing gear. DETAILED DESCRIPTION

[0031] In order to make the above contents, purposes and beneficial effects of the utility model more obvious and easy to understand, the specific implementation methods of the utility model are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the utility model. However, the utility model can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the utility model, so the utility model is not limited by the specific embodiments disclosed below.

[0032] It should be noted that, unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art in the technical field of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

[0033] like Figure 1-4 As shown, the utility model provides a novel aircraft capable of vertical take-off and landing, comprising a fuselage 1, wings 2, a rotor power device 4, a tail wing 5, a propulsion power 6 and a landing gear.

[0034] The fuselage 1 adopts a streamlined design, but is not limited to a streamlined fuselage. A front windshield 101 is regularly arranged at the front section of the fuselage 1, a cabin door 102 is regularly arranged at the front side thereof, and a plurality of cabin glasses 103 are regularly arranged at both sides of the middle thereof. A cockpit and a cabin are regularly arranged inside the fuselage 1, and a plurality of seats are arranged and installed respectively.

[0035] Furthermore, the wing 2 adopts a low-speed high-lift airfoil, and is symmetrically arranged and installed on both sides of the upper part of the middle section of the fuselage to form left and right wings. The tips of the left and right wings are arranged and installed with rotor power mounting frames 3, and the interior of the left and right wings is used to arrange and install rotor power batteries 10.

[0036] Furthermore, the rotor power mounting frame 3 adopts a streamlined design, thereby reducing flight resistance. The outermost end thereof is provided with a rotor power mounting platform for mounting the rotor power device 4.

[0037] Furthermore, the rotor power device 4 is arranged and installed on the outermost rotor power mounting platform of the rotor power mounting frame 3, and is symmetrically arranged on the left and right sides of the fuselage 1 through the rotor power mounting frame 3 to form left and right rotor power devices. The left and right rotor power devices 4 are powered by the rotor power batteries 10 inside the left and right wings 2 respectively.

[0038] Furthermore, the rotor power device 4 includes two sets of motors installed coaxially and rotating in opposite directions, a rotor blade 401 and a rotor blade protection 402. The rotor blade 401 and the rotor blade protection 402 are integrally formed and arranged together, and the rotor blade protection 402 forms a fence structure to surround and protect the rotor blade 401.

[0039] By providing a rotor blade protection 402 at the tip of the rotor blade 401 to surround it, the tip vortex of the rotor blade can be reduced, thereby reducing the noise generated when the rotor power device rotates. At the same time, the existence of the rotor blade protection 402 can prevent ground personnel from being harmed by the propeller.

[0040] like Figure 3 As shown, in one embodiment, the left and right wings 2 and the rotor power mounting frame 3 are arranged at an angle tilted upward, and the angle with the horizontal plane is 9-12°.

[0041] Furthermore, the tail 5 adopts a symmetrical airfoil, and is installed at the upper end of the tail of the fuselage 1 in a symmetrical and inclined arrangement to form left and right tails. The trailing edges of the left and right tails are also symmetrically provided with tail control surfaces 501 for pitch and yaw control.

[0042] Furthermore, the left and right tail fins are V-shaped tail fins and are arranged and installed at the upper end of the tail of the fuselage.

[0043] Further, such as Figure 1 As shown, the propulsion power device 6 is arranged and installed inside the tail of the fuselage 1. The propulsion power device 6 adopts oil-driven turbine power and is propelled by jet.

[0044] Furthermore, an air inlet 7 is regularly arranged on the fuselage at the front end of the propulsion power device 6, and the air inlet 7 connects the propulsion power device with the outside world and is used for the air intake of the propulsion power device. Figure 1 As shown, in one embodiment, the air inlet 7 is regularly arranged at the upper end of the tail of the fuselage 1. The tail end of the fuselage 1 is provided with a main jet port for jet propulsion of the propulsion power unit 6.

[0045] Furthermore, upper and lower power jets 8 and left and right power jets 9 are regularly arranged on the fuselage at the rear end of the propulsion power unit 6. The upper and lower power jets 8 are regularly arranged on the upper and lower sides of the tail of the fuselage, and the left and right power jets 9 are regularly arranged on the left and right sides of the tail of the fuselage. The upper and lower power jets and the left and right power jets are connected to the air outlet of the propulsion power unit through the exhaust channel inside the fuselage.

[0046] Furthermore, a plurality of fan blade baffles rotating around an axis are regularly arranged at the upper and lower power jet ports and the left and right power jet ports. The plurality of fan blade baffles are driven to rotate by a motor or an electric cylinder, so that the opening size of the upper and lower power jet ports and the left and right power jet ports can be adjusted by adjusting the opening and closing size of the plurality of fan blade baffles.

[0047] Therefore, the pitch attitude of the aircraft is adjusted by adjusting the fan blade baffles at the upper and lower power jet ports; and the yaw attitude of the aircraft is adjusted by adjusting the fan blade baffles at the left and right power jet ports.

[0048] Furthermore, a turbine generator is arranged and installed inside the fuselage 1, so as to generate electricity through the turbine generator to charge and supply power to the rotor power battery 10 inside the wing and the corresponding modules of the system.

[0049] Further, the landing gear includes a rear landing gear 11 and a front landing gear 12. Figure 1 and Figure 3 As shown, the rear landing gear 11 is symmetrically arranged and installed on the middle section of the belly of the fuselage, and the front landing gear 12 is arranged and installed on the front section of the belly of the fuselage, thereby forming a three-point landing gear.

[0050] Further, the rear landing gear 11 and the front landing gear 12 both include a power device, a folding assembly and wheels. When the aircraft is in a level flight cruise, the power device drives the folding assembly to be retracted into the fuselage, thereby retracting the front and rear landing gears into the fuselage to reduce flight resistance.

[0051] The specific embodiments described above further illustrate the purpose, technical solutions and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A novel aircraft capable of vertical take-off and landing, characterized in that: Includes fuselage, wings, rotor power unit, tail, propulsion power unit and landing gear; The wings are symmetrically arranged and installed on both sides of the upper part of the middle section of the fuselage to form left and right wings. The tips of the left and right wings are symmetrically arranged and installed with rotor power mounting frames, and rotor power batteries are arranged and installed inside the mounting frames. The outermost end of the rotor power mounting frame is provided with a rotor power mounting platform, the rotor power device is arranged and mounted on the rotor power mounting platform, and is symmetrically arranged on the left and right sides of the fuselage through the rotor power mounting frame to form left and right rotor power devices, and the rotor power batteries inside the left and right wings respectively supply power to the left and right rotor power devices; The tail wing is installed at the upper end of the tail of the fuselage in a left-right symmetrical and inclined arrangement to form a left and right tail wing, and the trailing edges of the left and right tail wing are symmetrically provided with tail wing control surfaces for pitch and yaw control; The propulsion power device is arranged and installed inside the tail of the fuselage. An air inlet for the propulsion power device to inlet air is regularly arranged on the fuselage at the front end of the propulsion power device, and an ejection port for the propulsion power device to eject air is regularly arranged on the fuselage at the rear end of the propulsion power device. The jets include a main jet at the tail end of the fuselage, upper and lower power jets on the upper and lower sides of the tail of the fuselage, and left and right power jets on the left and right sides of the tail of the fuselage.

2. A novel vertical take-off and landing aircraft as claimed in claim 1, characterized in that: The front end of the fuselage is regularly provided with a front windshield, the front side thereof is regularly provided with a cabin door, and the two sides of the middle thereof are regularly provided with a plurality of cabin glasses.

3. A novel vertical take-off and landing aircraft as claimed in claim 1, characterized in that: The rotor power device includes two sets of motors installed up and down and rotating coaxially in opposite directions, a rotor propeller and a rotor propeller protection. The rotor propeller protection forms a fence structure to surround the rotor propeller and is integrally formed with it.

4. The novel vertical take-off and landing aircraft according to claim 1, characterized in that: The left and right tail wings are V-shaped tail wings, which are arranged and installed on the upper end of the tail of the fuselage and are arranged away from the upper and lower power jet ports and the left and right power jet ports.

5. The novel vertical take-off and landing aircraft according to claim 1, characterized in that: A plurality of fan blade baffles are regularly arranged at the upper and lower power jet ports and the left and right power jet ports, and the plurality of fan blade baffles are driven to open and close by a motor or an electric cylinder.

6. A novel vertical take-off and landing aircraft as claimed in claim 5, characterized in that: The fan blade baffles at the upper and lower power jet ports control the opening sizes of the upper and lower power jet ports to adjust the pitch attitude of the aircraft; the fan blade baffles at the left and right power jet ports control the opening sizes of the left and right power jet ports to adjust the yaw attitude of the aircraft.

7. The novel vertical take-off and landing aircraft according to claim 1, characterized in that: The landing gear comprises a front landing gear and a rear landing gear, wherein the rear landing gear is symmetrically arranged and installed at the middle part of the belly of the fuselage, and the front landing gear is arranged and installed at the front part of the belly of the fuselage, and the front landing gear and the rear landing gear form a three-point landing gear.

8. A novel vertical take-off and landing aircraft according to any one of claims 1 to 7, characterized in that: The wing and the rotor power mounting frame are both arranged to be tilted upward, with an inclination angle of 9-12° upward relative to the horizontal plane.

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