High-speed aircraft capable of vertically taking off and landing

Abstract

The utility model relates to a high-speed aircraft capable of vertically taking off and landing. The high-speed aircraft comprises a fuselage, wings, supporting wings, rotor power devices, empennages, propulsion power devices and undercarriages, the wingtip winglet structure is arranged on the tip of the wing in an upward bending mode, and the rotor wing power device is arranged on the wingtip winglet structure. Vertical take-off and landing of the high-speed aircraft are achieved through the rotor wing power devices, and therefore the requirement for a flight runway is reduced. The wing structure of a traditional aircraft is reserved, so that the aircraft has the characteristics of high speed and long endurance of the traditional aircraft. Moreover, the supporting wings are arranged at the lower ends of the wings, the wings and the fuselage are connected through the supporting wings, and the wings, the supporting wings and the fuselage form a stable triangular structure, so that the structural strength and rigidity of the wings can be enhanced, and strength and rigidity support is provided for rotor wing power arrangement at wingtips.

Description

Technical Field

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

[0002] At present, the application and development of urban aircraft has become the focus of society. There are various types of urban aircraft, including multi-rotor, composite wing, tilt-rotor and traditional aircraft. Compared with composite wing and tilt-rotor, multi-rotor has the worst maximum speed and flight time. Most composite wing and tilt-rotor urban aircraft are propelled by electric propellers, which have low propeller power efficiency and cannot reach a high flight speed due to propeller limitations.

[0003] Traditional aircraft are powerful and can reach higher speeds, but most of them take off and land on a taxiway, which requires a larger area with a runway. Utility Model Content

[0004] The technical problem solved by the utility model is to provide a high-speed aircraft capable of vertical take-off and landing.

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

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

[0007] The wings are horizontally arranged symmetrically on both sides of the middle upper part of the fuselage to form left and right wings. The middle lower part of the wing is connected and fixed to the fuselage through the supporting wing. The wing, the supporting wing and a part of the fuselage form a stable triangular structure.

[0008] The trailing edges of the left and right wings are symmetrically provided with ailerons for rolling attitude control, and the tips of the left and right wings are respectively provided with winglets that bend upwards;

[0009] The rotor power device is arranged and installed at the upper end of the winglet to form a left and right rotor power device;

[0010] The tail wing is inclined at an angle and is symmetrically arranged and installed on the upper end of the tail of the fuselage to form left and right tail wing, and the trailing edges of the left and right tail wing are also symmetrically provided with tail wing control surfaces for pitch and yaw attitude control;

[0011] The propulsion power device is installed on the upper end of the tail of the fuselage through a propulsion power mounting frame and is arranged between the left and right tail wings.

[0012] Furthermore, a front windshield is regularly arranged at the front of the fuselage, a cabin door is regularly arranged at the front side thereof, and a plurality of cabin glasses are regularly arranged at both sides of the middle thereof.

[0013] Preferably, the wing adopts a low-speed high-lift airfoil.

[0014] Furthermore, the rotor power unit adopts electric power, and the propulsion power unit adopts oil-driven turbojet power.

[0015] Furthermore, the landing gear includes a front landing gear and a rear landing gear, the rear landing gear is symmetrically arranged and installed at the rear end of the belly of the fuselage, and the front landing gear is arranged and installed at the front end of the belly of the fuselage, and the front landing gear and the rear landing gear form a three-point landing gear.

[0016] Furthermore, when the high-speed aircraft is cruising, the rotor propellers of the left and right rotor power devices are locked and stop rotating in the heading direction.

[0017] Furthermore, the rotation directions of the left and right rotor power devices are opposite.

[0018] The beneficial effects of the utility model are:

[0019] 1. The utility model has a winglet structure bent upward at the tip of the wing, and the rotor power device is arranged and installed on the winglet structure. The rotor power device realizes the vertical take-off and landing of the high-speed aircraft of the utility model, thereby reducing the demand for the flight runway.

[0020] 2. The utility model retains the wing structure of traditional aircraft, thus having the characteristics of high speed and long flight time of traditional aircraft. In addition, by arranging a support wing at the lower end of the wing, the wing and the fuselage are connected through the support wing, and the wing, the support wing and the fuselage form a stable triangular structure, thereby enhancing the structural strength and rigidity of the wing, and providing strength and rigidity support for the rotor power arranged at the wing tip. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a three-dimensional structural diagram of the utility model;

[0022] Figure 2 It is a side view of the utility model;

[0023] Figure 3 This is the front view of the utility model

[0024] Figure 4 It is a top view of the utility model;

[0025] The markings in the figure are:

[0026] 1. Fuselage, 101. Front windshield, 102. Cabin door, 103. Cabin glass, 2. Wing, 201. Aileron, 202. Winglet, 3. Support wing, 4. Rotor power unit, 5. Tail, 501. Tail control surface, 6. Propulsion power unit, 7. Propulsion power mounting frame, 8. Rear landing gear, 9. Front landing gear. DETAILED DESCRIPTION

[0027] 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.

[0028] 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.

[0029] like Figure 1-4 As shown, the utility model provides a high-speed aircraft capable of vertical take-off and landing, including a fuselage 1, wings 2, support wings 3, a rotor power device 4, a tail wing 5, a propulsion power device 6, a rear landing gear 8 and a front landing gear 9.

[0030] 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 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.

[0031] Furthermore, the wing 2 adopts a low-speed high-lift airfoil, which can ensure that the aircraft has the characteristics of high-speed flight and long flight time. The wing 2 is horizontally arranged and installed on both sides of the middle upper part of the fuselage 1 in a left-right symmetrical manner, forming left and right wings.

[0032] Furthermore, ailerons 201 for roll attitude control are symmetrically arranged at the trailing edges of the left and right wings.

[0033] Furthermore, the tips of the left and right wings are respectively provided with upwardly curved winglets 202. The rotor power device 4 is arranged and installed on the upper end of the winglet 202 to form a left and right rotor power device.

[0034] In one embodiment, the rotor power device 4 is driven by electric power. The rotor structure adopts a helicopter rotor design and is provided with a tilting disk, so that the propeller disk posture can be slightly adjusted.

[0035] The utility model provides upward lift through the left and right rotor power devices, thereby realizing the vertical take-off and landing of the aircraft in situ without the need for a long runway.

[0036] Further, such as Figure 4 As shown, the rotation directions of the left rotor power unit and the right rotor power unit are opposite.

[0037] Further, such as Figure 3 As shown, when the aircraft is cruising in level flight, the left and right rotor power devices lock the rotors in the heading direction and stop rotating, thereby reducing flight resistance.

[0038] Further, such as Figure 1 and Figure 3 As shown, the middle lower part of the left and right wings is connected and fixed to the fuselage 1 through the support wing 3. The wing 2, the support wing 3 and a part of the fuselage 1 form a stable triangular structure, thereby enhancing the structural strength and rigidity of the wing and providing strength and rigidity support for the wingtip arrangement of the rotor power.

[0039] Furthermore, the tail 5 adopts a symmetrical airfoil, and the tail is inclined at an angle and is symmetrically arranged on the upper end of the tail of the fuselage to form left and right tails, and the left and right tails are in a V-shaped tail layout.

[0040] Furthermore, the trailing edges of the left and right tail wings are symmetrically provided with tail wing control surfaces 501 for pitch and yaw attitude control.

[0041] Furthermore, the propulsion power device 6 is arranged and installed at the upper end of the tail of the fuselage through the propulsion power mounting frame 7, and is arranged between the left and right tail wings.

[0042] In one embodiment, the propulsion power device 6 adopts oil-driven turbojet power. The oil-driven turbojet power is used as the propulsion power, thereby ensuring the high-speed flight of the aircraft.

[0043] Further, such as Figure 1 As shown, the rear landing gear 8 and the front landing gear 9 are respectively arranged and installed at the rear end and the front end of the belly of the fuselage.

[0044] Among them, the rear landing gear 8 is symmetrically arranged and installed on the rear section of the fuselage belly, and the front landing gear 9 is installed on the front section of the fuselage belly. The front and rear landing gears form a three-point landing gear.

[0045] Furthermore, the rear landing gear and the front landing gear both include a power unit, a folding assembly and wheels. When the aircraft is in a level flight cruise, the power unit 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.

[0046] 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 high-speed aircraft capable of vertical take-off and landing, characterized in that: It includes fuselage, wings, support wings, rotor power unit, tail wing, propulsion power unit and landing gear; The wings are horizontally arranged symmetrically on both sides of the middle upper part of the fuselage to form left and right wings. The middle lower part of the wing is connected and fixed to the fuselage through the supporting wing. The wing, the supporting wing and a part of the fuselage form a stable triangular structure. The trailing edges of the left and right wings are symmetrically provided with ailerons for rolling attitude control, and the tips of the left and right wings are respectively provided with winglets that bend upwards; The rotor power device is arranged and installed at the upper end of the winglet to form a left and right rotor power device; The tail wing is inclined at an angle and is symmetrically arranged and installed on the upper end of the tail of the fuselage to form left and right tail wing, and the trailing edges of the left and right tail wing are also symmetrically provided with tail wing control surfaces for pitch and yaw attitude control; The propulsion power device is installed on the upper end of the tail of the fuselage through a propulsion power mounting frame and is arranged between the left and right tail wings.

2. The high-speed aircraft capable of vertical take-off and landing as claimed in claim 1, characterized in that: The front part 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 part thereof are regularly provided with a plurality of cabin glasses.

3. The high-speed aircraft capable of vertical take-off and landing as claimed in claim 1, characterized in that: The wing adopts a low-speed high-lift airfoil.

4. The high-speed aircraft capable of vertical take-off and landing as claimed in claim 1, characterized in that: The rotor power unit adopts electric power, and the propulsion power unit adopts oil-driven turbojet power.

5. The high-speed aircraft capable of vertical take-off and landing according to any one of claims 1 to 4, 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 rear end of the belly of the fuselage, and the front landing gear is arranged and installed at the front end of the belly of the fuselage, and the front landing gear and the rear landing gear form a three-point landing gear.

6. The high-speed aircraft capable of vertical take-off and landing as claimed in claim 5, characterized in that: When the high-speed aircraft is cruising, the rotor propellers of the left and right rotor power devices are locked and stop rotating in the heading direction.

7. The high-speed aircraft capable of vertical take-off and landing as claimed in claim 6, characterized in that: The rotation directions of the left and right rotor power devices are opposite.

Images