A combined wing vertical take-off and landing aircraft

Abstract

The utility model relates to a combined-wing vertical take-off and landing aircraft, including a fuselage, a front wing, a rear wing, a propulsion power system, a tilt-rotor power system, a vertical tail and a landing gear system. The front wing, the rear wing, the propulsion power system, the tilt-rotor power system, the vertical tail and the landing gear are regularly arranged and installed on the fuselage. The aircraft of the utility model combines the characteristics of a composite wing and a multi-rotor, and adopts a design of a tilt-rotor power system plus a propulsion power system. Compared with a pure multi-rotor aircraft, the energy loss during take-off is greatly reduced, thereby increasing the endurance. At the same time, the propulsion power system can increase the insufficient forward thrust of the rotor power system, increase the forward flight speed of the aircraft, and shorten the time spent on the way. The several rotor power devices in the tilt-rotor power system in the aircraft of the utility model all adopt two sets of upper and lower propeller systems, a total of eight sets of propeller systems, which greatly increases the safety redundancy of the aircraft.

Description

Technical Field

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

[0002] In today's society, the low-altitude economy has great potential, and various companies have successively launched their own electric vertical take-off and landing aircraft. There are mainly several types: composite wings, tilt-rotor wings and multi-rotor wings.

[0003] Composite wings and tilt-rotors can take off and land vertically like helicopters, and transform into fixed-wing flight mode in the air. They have fast flight speeds, save energy, and have lower operating costs than helicopters. In addition, they have an automatic driving function, so the requirements for pilots are relatively low. However, during the flight mode conversion process, the control is more complicated and the safety is weaker than that of multi-rotors.

[0004] The multi-rotor has a simple structure and strong control safety, but it cannot fly at high speed like a fixed wing. In view of the above problem, the present invention is made to consider whether there is an aircraft that has the safety of a multi-rotor and can fly at high speed like a fixed wing. Utility Model Content

[0005] The technical problem solved by the utility model is to provide a combined-wing vertical take-off and landing aircraft which combines the characteristics of a composite wing and a multi-rotor and has stability, safety and a long flight time.

[0006] The technical solution adopted by the utility model to solve its technical problems is:

[0007] A combined-wing vertical take-off and landing aircraft, comprising:

[0008] A fuselage, wherein a cabin is arranged at the front of the fuselage, and a fuselage cabin cover which is convenient to open is arranged on the upper side of the fuselage;

[0009] Front wings, which are symmetrically fixed to the left and right sides of the lower front section of the fuselage to form left and right front wings, and are set at a larger installation angle;

[0010] The rear wing is symmetrically fixed to the left and right sides of the upper part of the rear section of the fuselage to form left and right rear wings, and is provided with a larger installation angle;

[0011] A propulsion power device, the propulsion power device is regularly arranged and installed at the tips of the left and right front wings and the left and right rear wings, and the tips of the left and right front wings and the left and right rear wings are connected to form left and right propulsion power devices, and the propulsion power devices on the left and right sides of the fuselage form a stable triangular structure with the fuselage through the front wings and the rear wings;

[0012] A plurality of rotor power devices, the plurality of rotor power devices are regularly arranged and installed on the front and rear sections of the fuselage through support frames, including a front rotor power device and a rear rotor power device, the front rotor power device is fixedly connected to the front section of the fuselage through the front support frame symmetrically and arranged forward, and the rear rotor power device is fixedly connected to the rear section of the fuselage through the rear support frame symmetrically and arranged backward;

[0013] A landing gear system is regularly arranged and installed on the lower belly of the fuselage.

[0014] Furthermore, a vertical tail is provided on the upper side of the tail of the fuselage.

[0015] Furthermore, the left and right front wings are provided with a backward sweep angle and an upward dihedral angle, and the left and right rear wings are provided with a forward sweep angle and a downward dihedral angle, the sweep angle of the backward sweep angle is 15°-19°, the forward sweep angle of the forward sweep angle is 13°-17°, the upward dihedral angle of the dihedral angle is 7°-11°, and the downward dihedral angle of the dihedral angle is 8°-12°.

[0016] Furthermore, the propeller planes of the plurality of rotor power devices are arranged to be tilted upward relative to the parking horizontal plane of the aircraft, and the upward tilt angle is 8°-12°.

[0017] Furthermore, the plurality of rotor power devices each include two sets of upper and lower propeller system structures, which are regularly arranged and installed at the upper and lower ends of the front end of the support frame.

[0018] Furthermore, the front rotor power device is arranged in front of the front wing through the front support frame, and the rear rotor power device is arranged behind the rear wing through the rear support frame.

[0019] Furthermore, the front rotor power unit is arranged to avoid the fuselage door rule.

[0020] Furthermore, the landing gear system includes a front landing gear and a rear landing gear, and the front landing gear and the rear landing gear are arranged symmetrically at the front and middle rear of the lower belly of the fuselage to form a four-point landing gear system.

[0021] The beneficial effects of the utility model are:

[0022] 1. The aircraft of the utility model combines the characteristics of composite wings and multi-rotors, and adopts a design of a tilt-rotor power system plus a propulsion power system. The tilt-rotor power system can provide forward flight power components and lift direction power components. The front wing and the rear wing are used to provide a certain lift for the aircraft during flight. The tilt-rotor lift direction power component and the lift provided by the front wing and the rear wing act simultaneously, which greatly reduces the energy loss during takeoff compared to pure multi-rotor aircraft, thereby increasing endurance. At the same time, the aircraft has a propulsion power system. When the vertical takeoff is switched to the level flight mode, the tilt-rotor power system continues to work, and the propulsion power system gradually increases to supplement the lack of forward thrust, increasing the forward flight speed of the aircraft, which can shorten the time consumed in transit.

[0023] 2. The several rotor power devices in the tilt-rotor power system of the aircraft of the present invention all adopt two sets of propeller systems, namely, upper and lower propeller systems, for a total of eight propeller systems, which greatly increases the safety redundancy of the aircraft.

[0024] 3. The aircraft of the utility model can increase the heading stability of the aircraft during flight by adding a vertical tail design to the tail of the fuselage. 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 aircraft of the utility model in a parked state;

[0027] Figure 3 It is a front view of the utility model;

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

[0029] Figure 5 It is a side view of the aircraft of the utility model in a level flight state;

[0030] The markings in the figure are:

[0031] 1. Fuselage, 101. Fuselage canopy, 2. Front wing, 3. Rear wing, 4. Propulsion power unit, 401. Propulsion power propeller, 5. Vertical tail, 6. Rear rotor power unit, 61. Rear support frame, 7. Front rotor power unit, 71. Front support frame, 8. Rear landing gear, 9. Front landing gear, 601. Left rear rotor power unit, 602. Right rear rotor power unit, 701. Left front rotor power unit, 702. Right front rotor power unit, 801. Fairing. DETAILED DESCRIPTION

[0032] 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.

[0033] 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.

[0034] like Figure 1-5 As shown, the utility model provides a combined-wing vertical take-off and landing aircraft, including a fuselage 1, a front wing 2, a rear wing 3, a propulsion power device 4, a vertical tail 5, a plurality of rotor power devices and a landing gear, and the front wing 2, the rear wing 3, the propulsion power device 4, the vertical tail 5, a plurality of rotor power devices and a landing gear are regularly arranged on the fuselage 1.

[0035] The fuselage 1 is a streamlined fuselage, but is not limited to a streamlined fuselage. A cabin is arranged at the front of the fuselage 1, and a fuselage canopy 101 that is convenient to open is arranged on the upper side thereof. Seats and a control module of the aircraft are regularly arranged in the cabin.

[0036] Furthermore, the front wing 2 adopts a low-speed high-lift airfoil, and the front wing 2 is symmetrically fixed to the left and right sides of the lower front section of the fuselage 1 to form left and right front wings. The front wing 2 is set to have a larger installation angle with respect to the horizontal plane, and the installation angle is 16°-20°.

[0037] Furthermore, the rear wing 3 also adopts a low-speed high-lift airfoil, and the rear wing 3 is symmetrically fixed to the left and right sides of the upper rear section of the fuselage 1 to form left and right rear wings. The rear wing 3 is also set to have a larger installation angle, which is 16°-20°.

[0038] Further, such as Figure 1 As shown, in the present invention, the propulsion power device 4 is arranged and installed at the tip of the front wing 2 and the rear wing 3, and connects the tip of the front wing 2 and the rear wing 3. Because the front wing 2 is fixed to the lower front part of the fuselage 1, and the rear wing 3 is fixed to the upper rear part of the fuselage 1, so Figure 1 , Figure 3 and Figure 4As shown, the front wing 2 is provided with a backward sweep angle and an upward dihedral angle, and the rear wing 3 is provided with a forward sweep angle and a downward dihedral angle.

[0039] Further, such as Figure 4 As shown, the left and right front wings 2 are arranged backward to form a swept angle, and the swept angle is 15°-19°; the left and right rear wings 3 are arranged forward to form a forward swept angle, and the forward swept angle is also 13°-17°. Figure 3 As shown, the left and right front wings 2 are arranged upward to form an anhedral angle of 7°-11°, and the left and right rear wings 3 are arranged downward to form an anhedral angle of 8°-12°. The propulsion power device 4 is fixed to the tips of the front and rear wings by the swept back and anhedral setting of the front wings 2 and the swept forward and anhedral setting of the rear wings 3, thereby forming a stable triangular structure with the fuselage.

[0040] like Figure 1 As shown, the propulsion power device 4 is arranged to be fixedly connected to the tips of the left and right front wings and the left and right rear wings on the left and right sides of the fuselage 1 to form the propulsion power system of the aircraft, providing power for the aircraft to fly forward, and a motor and an electric regulator are installed inside it, and a propulsion power propeller 401 is installed at the rear.

[0041] Further, such as Figure 2 As shown, the installation planes of the propulsion power devices 4 on the left and right sides of the fuselage 1 are arranged to be tilted downward with respect to the aircraft's parking horizontal plane, and the downward tilt angle is 8°-12°.

[0042] Further, such as Figure 1 and Figure 3 As shown, the vertical tail 5 adopts a symmetrical airfoil and is fixedly connected to the upper side of the tail of the fuselage 1. The vertical tail design can increase the stability of the heading of the aircraft during flight.

[0043] Further, such as Figure 1 As shown, a plurality of rotor power devices constitute the rotor power system of the aircraft, including a rear rotor power device 6 and a front rotor power device 7. The front and rear rotor power devices are respectively fixedly connected to the front and rear sections of the fuselage 1 through support frames.

[0044] Among them, Figure 1 and Figure 4 As shown, the rear rotor power device 6 is fixedly connected to the rear section of the fuselage 1 symmetrically via a rear support frame 61 , and the front rotor power device 7 is fixedly connected to the front section of the fuselage 1 symmetrically via a front support frame 71 .

[0045] Furthermore, the rear rotor power device 6 is arranged behind the rear wing through the rear support frame 61, and the front rotor power device 7 is arranged in front of the front wing through the front support frame 71.

[0046] Further, such as Figure 2As shown, the installation planes (propeller planes) of several rotor power devices are arranged to be tilted upward with respect to the parking horizontal plane of the aircraft, and the upward tilt angle is 8°-12°, thereby forming a tilted rotor power system.

[0047] like Figure 5 As shown, several rotor power units are arranged to tilt upward, and can provide forward flight power together with the propulsion power during the forward flight of the aircraft. While the propulsion power unit provides thrust, several rotor power units generate an upward component due to the upward tilt, thereby providing upward lift for the aircraft together with the wings.

[0048] Furthermore, several rotor power units include two sets of propeller system structures, an upper set and a lower set, and the whole machine has a total of eight propeller systems, which can greatly increase the safety redundancy of the aircraft.

[0049] like Figure 1 and Figure 2 As shown, the propellers at the upper ends of the left and right front rotor power units 7 are arranged away from the fuselage door 101, thereby further improving the safety in the cabin.

[0050] like Figure 4 As shown, in one embodiment, the propellers of the front rotor power devices on the left and right sides of the front section of the fuselage 1 rotate in opposite directions, and the propellers of the rear rotor power devices on the left and right sides of the rear section also rotate in opposite directions. The left front rotor power device 701 rotates clockwise, the right front rotor power device 702 rotates counterclockwise, the left rear rotor power device 601 rotates counterclockwise, and the right rear rotor power device 602 rotates clockwise.

[0051] like Figure 5 As shown, this is a state diagram of the aircraft in level flight mode. When the aircraft is in level flight mode, several multi-rotor power units continue to work, and the propulsion power unit gradually increases power to supplement the lack of forward thrust, increase the forward flight speed of the aircraft, and shorten the time consumed in transit.

[0052] Further, such as Figure 1 and Figure 2 As shown, the landing gear includes a front landing gear 9 and a rear landing gear 7. The front landing gear 9 and the rear landing gear 7 are both arranged symmetrically at the front and middle rear of the lower abdomen of the fuselage 1. The front landing gear and the rear landing gear form a four-point landing gear system.

[0053] Furthermore, a fairing 801 is regularly arranged on the landing gear.

[0054] 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 combined-wing vertical take-off and landing aircraft, characterized in that: include: A fuselage, wherein a cabin is arranged at the front of the fuselage, and a fuselage cabin cover which is convenient to open is arranged on the upper side of the fuselage; A front wing, the front wing is symmetrically fixed to the left and right sides of the lower part of the front section of the fuselage to form a left and right front wing, and is set at an installation angle of 16°-20°; The rear wing is symmetrically fixed to the left and right sides of the upper part of the rear section of the fuselage to form left and right rear wings, and is set at an installation angle of 16°-20°; A propulsion power device, the propulsion power device is regularly arranged and installed at the tips of the left and right front wings and the left and right rear wings, and the tips of the left and right front wings and the left and right rear wings are connected to form left and right propulsion power devices, and the propulsion power devices on the left and right sides of the fuselage form a stable triangular structure with the fuselage through the front wings and the rear wings; A plurality of rotor power devices, the plurality of rotor power devices are regularly arranged and installed on the front and rear sections of the fuselage through support frames, including a front rotor power device and a rear rotor power device, the front rotor power device is fixedly connected to the front section of the fuselage through the front support frame symmetrically and arranged forward, and the rear rotor power device is fixedly connected to the rear section of the fuselage through the rear support frame symmetrically and arranged backward; A landing gear system is regularly arranged and installed on the lower belly of the fuselage.

2. A combined-wing vertical take-off and landing aircraft as claimed in claim 1, characterized in that: A vertical tail is also arranged on the upper side of the tail of the fuselage.

3. A combined-wing vertical take-off and landing aircraft as claimed in claim 1 or 2, characterized in that: The left and right front wings are provided with a backward sweep angle and an upward dihedral angle, and the left and right rear wings are provided with a forward sweep angle and a downward dihedral angle. The sweep angle of the backward sweep angle is 15°-19°, the forward sweep angle of the forward sweep angle is 13°-17°, the upward dihedral angle of the dihedral angle is 7°-11°, and the downward dihedral angle of the dihedral angle is 8°-12°.

4. A combined-wing vertical take-off and landing aircraft as claimed in claim 1 or 2, characterized in that: The propeller planes of the plurality of rotor power devices are arranged to be tilted upwardly with respect to the parking horizontal plane of the aircraft, and the upward tilt angle is 8°-12°.

5. A combined-wing vertical take-off and landing aircraft as claimed in claim 1 or 2, characterized in that: The plurality of rotor power devices each include two sets of upper and lower propeller system structures, which are regularly arranged and installed at the upper and lower ends of the front end of the support frame.

6. A combined-wing vertical take-off and landing aircraft as claimed in claim 1 or 2, characterized in that: The front rotor power device is arranged in front of the front wing through the front support frame, and the rear rotor power device is arranged behind the rear wing through the rear support frame.

7. A combined-wing vertical take-off and landing aircraft as claimed in claim 1 or 2, characterized in that: The front rotor power device is arranged to avoid the fuselage door rule.

8. A combined-wing vertical take-off and landing aircraft as claimed in claim 1 or 2, characterized in that: The landing gear system comprises a front landing gear and a rear landing gear, and the front landing gear and the rear landing gear are both arranged bilaterally symmetrically at the front and middle rear of the lower belly of the fuselage to form a four-point landing gear system.

Images