Vertical take-off and landing kit for airplane and airplane

Abstract

The utility model discloses a vertical take-off and landing kit for an aircraft and the aircraft, which are used for reducing the influence of runways and weather on take-off of the aircraft and reducing the take-off and landing conditions of the aircraft. The unmanned aerial vehicle comprises a structural assembly, a propeller and a motor, the motors are arranged at the two ends of the structural assembly respectively, a battery is arranged in the structural assembly, and the battery is connected with the motors through electronic speed regulators; a rotating shaft of the motor extends upwards, and the center of the propeller is connected to the rotating shaft; a connecting assembly is arranged in the middle of the structural assembly, so that the structural assembly is connected to the lower surface of the wing through the connecting assembly.

Description

Technical Field

[0001] The present application relates to the field of aviation technology, and in particular to a vertical take-off and landing kit for an aircraft and the aircraft. Background Art

[0002] At present, general aviation manned aircraft are mainly fixed-wing aircraft, which accelerate on a long airport runway and take off by providing lift through the wings after reaching a certain speed. However, fixed-wing aircraft have high requirements for airport runways, take-off and landing weather, such as the length, width, and surface smoothness of the airport runway. In many places, the conditions for aircraft take-off and landing cannot be met, which greatly limits the popularization and application of the general aviation industry.

[0003] Therefore, multi-rotor aircraft and compound-wing UAVs have been developed to reduce the restrictions on takeoff caused by airport runways and weather. However, the new multi-rotor aircraft have low aerodynamic efficiency during takeoff and carry less weight, which greatly limits their limitations during actual use. Compound-wing UAVs are not mature, and the period for obtaining airworthiness certification is relatively long and the cost is relatively high.

[0004] Therefore, there is an urgent need for a vertical take-off and landing kit for an aircraft to solve the above problems. Utility Model Content

[0005] In order to solve the above technical problems, the present application provides a vertical take-off and landing kit for an aircraft and an aircraft, which can reduce the impact of the runway and weather on the aircraft's take-off and reduce the aircraft's take-off and landing conditions.

[0006] The first aspect of the present application provides a vertical take-off and landing kit for an aircraft, comprising:

[0007] A structural component, a propeller and a motor; the motors are respectively arranged at both ends of the structural component, a battery is arranged inside the structural component, and the battery is connected to the motor through an electronic speed regulator; the rotating shaft of the motor extends upward, and the center of the propeller is connected to the rotating shaft; a connecting component is arranged in the middle position of the structural component, so that the structural component is connected to the lower surface of the wing through the connecting component.

[0008] Optionally, two ends of the structural component are respectively fixedly connected to a power cabin, and a receiving groove is provided in the power cabin, and the size of the receiving groove matches the size of the motor.

[0009] Optionally, the power compartment is streamlined.

[0010] Optionally, the connecting component protrudes from the surface of the structural component.

[0011] Optionally, a curved surface is provided on the connecting assembly, and the curved surface is consistent with the curved surface of the lower surface of the wing.

[0012] Optionally, the connecting assembly is mechanically connected to the wing.

[0013] Optionally, the structural component is provided with a posture sensor, a direction sensor, a speed sensor and a height sensor connected to a control system, and the control system is arranged inside the structural component.

[0014] A second aspect of the present application provides an aircraft, comprising an aircraft body, wings, a tail wing, and a vertical take-off and landing kit in any optional manner in the first aspect, wherein the wings are fixed on both sides of the aircraft body, the tail wing is integrally formed at the tail of the aircraft fuselage, and the vertical take-off and landing kit is respectively located on both sides of the aircraft body and connected to the bottom of the wings.

[0015] Optionally, the vertical device kit and the wing are arranged perpendicular to each other.

[0016] It can be seen from the above technical solutions that this application has the following effects:

[0017] By arranging motors at both ends of the structural component, connecting propellers to the rotating shaft of the motor, arranging batteries inside the structural component, electrically connecting the batteries to the motor, and then arranging a connecting component in the middle position of the structural component, the structural component is connected to the lower surface of the wing of the aircraft through the connecting component. Therefore, when the aircraft needs to take off, the propeller is driven to rotate by the motor to generate a downward thrust, and the thrust acts on the ground. The present application pushes the aircraft to move upward. Therefore, 1. A very long airport runway is no longer required for the aircraft to take off, which reduces the requirements for the runway for take-off and reduces the take-off and landing conditions of the aircraft; 2. The vertical take-off and landing kit of the present application can achieve vertical ascent, which is suitable for a variety of venues and has strong applicability; 3. Compared with the prior art, the vertical take-off and landing kit only needs to be installed on the lower surface of the wing, which can reduce costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solution in the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0019] Figure 1 This is a schematic diagram of the overall structure of a vertical take-off and landing kit for an aircraft in the present application;

[0020] Figure 2This is a schematic structural diagram of a power cabin in a vertical take-off and landing kit for an aircraft in the present application;

[0021] Figure 3 This is a schematic diagram of the overall structure of an aircraft according to the present application. DETAILED DESCRIPTION

[0022] In the present utility model, the directions or positional relationships indicated by terms such as “upper”, “lower”, “left”, “right”, “front”, “back”, “top”, “bottom”, “inside”, “outside”, “middle”, “vertical”, “horizontal”, “lateral” and “longitudinal” are based on the directions or positional relationships shown in the accompanying drawings and are only used to illustrate the relative positional relationships between the components or parts, and do not particularly limit the specific installation directions of the components or parts.

[0023] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0024] In addition, the terms "installed", "set", "provided with", "connected", and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be an internal connection between two devices, elements, or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0025] In addition, the structures, proportions, sizes, etc. drawn in the drawings in the present application are only used to match the contents disclosed in the specification so as to facilitate the understanding and reading of those skilled in the art, and are not used to limit the restrictive conditions under which the present application can be implemented. Therefore, they have no substantive technical significance. Any structural modification, change in proportional relationship or adjustment of size should still fall within the scope of the technical contents disclosed in the present application without affecting the effects and purposes that can be achieved by the present application.

[0026] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0027] The present application provides a vertical take-off and landing kit for an aircraft and an aircraft, which is used to reduce the impact of runways and weather on aircraft take-off and reduce aircraft take-off and landing conditions. The specific implementation process of the present application is described as follows.

[0028] See also Figure 1 and Figure 2 , a vertical take-off and landing kit for an aircraft provided in the present application comprises:

[0029] A structural component 1, a propeller 2 and a motor 3; the motors 3 are respectively arranged at both ends of the structural component 1, a battery is arranged inside the structural component 1, the battery is connected to the electronic speed regulator, and the electronic speed regulator is connected to the motor 3; the rotating shaft of the motor 3 extends upward, and the center of the propeller 2 is connected to the rotating shaft; a connecting component 5 is arranged in the middle position of the structural component 1, so that the structural component 1 is connected to the lower surface of the wing 7 through the connecting component 5.

[0030] The battery and the electronic speed regulator are both located inside the structural component 1. The battery is connected to the motor 3 at both ends through wires. The electronic speed regulator is connected to the battery and the motor 3 respectively. The electronic speed regulator is used to control the speed of the motor 3. The wires are also located inside the structural component 1. A control system is also provided inside the structural component 1. The control system is connected to the battery and the motor 3 respectively, so that the control system controls the motor 3.

[0031] The propellers 2 on both ends of the structural component 1 are of the same size and shape, and are at the same distance from the motor 3. The connecting component 5 is located in the middle of the structural component 1. When connected to the wing 7, the connecting component 5 contacts and connects with the wing 7, thereby fixing the structural component 1 on the lower surface of the wing 7.

[0032] The propellers 2 at both ends are located on both sides of the wing 7. In actual use, the motor 3 drives the propeller 2 to rotate through the rotating shaft, so that the propeller 2 generates a downward thrust. The propeller 2 and the structural component 1 are subjected to a reaction force, thereby generating an upward thrust on the wing 7. Therefore, when the rotation speed of the motor 3 is gradually increased and the thrust generated by the propeller 3 exceeds the requirement for the aircraft to take off, the aircraft can take off on the spot. Similarly, when the aircraft lands, the rotation speed of the motor 3 is gradually reduced.

[0033] In this embodiment, a vertical take-off and landing kit consisting of a structural component 1, a propeller 2 and a motor 3 is provided, and a vertical take-off and landing kit is installed on the lower surface of a wing 7, wherein the structural component 1 is connected to the wing 7 through a connecting component 5, the motor 3 is connected to the propeller 2, and the motor 2 is fixedly connected to both ends of the structural component 1, thereby, the propeller 2 is driven to rotate by the motor 3, and the vertical upward take-off and landing of the aircraft is realized. Compared with traditional aircraft in the prior art, the aircraft equipped with the vertical take-off and landing kit of the present application is less affected by the runway and weather, and the requirements for the runway length, flatness, etc. are also reduced, thereby reducing the take-off and landing conditions of the aircraft.

[0034] In addition, vertical take-off and landing can be achieved without additional design of the wing structure, thus reducing costs.

[0035] Optionally, in a feasible manner, both ends of the structural component 1 are respectively fixedly connected with a power cabin 4, and a receiving groove is provided in the power cabin 4. The size of the receiving groove matches the size of the motor 3, and the receiving groove is used to accommodate the motor 3. In practice, the opening of the receiving groove faces upward, and the motor 3 is embedded in the receiving groove from top to bottom, and the motor 3 is fixedly connected to the power cabin 4, and the motor shaft of the motor 3 protrudes upward from the upper surface of the power cabin 4.

[0036] Optionally, in another practicable manner, the power cabin 4 is cylindrical in shape, wherein the shape of the receiving slot is the same as that of the motor 3. Figure 2 The exterior of the power compartment 4 and the structural component 1 are streamlined, and the streamlined arrangement can reduce air resistance.

[0037] Optionally, the connecting component 5 protrudes from the surface of the structural component 1. Specifically, the connecting component 5 is located on the outside of the structural component 1, and the connecting component 5 protrudes vertically upward. When connected, the surface of the structural component 1 does not contact the wing 7, and the structural component 1 is connected to the wing 7 through the connecting component 5.

[0038] Optionally, a curved surface is provided on the connecting component 5, and the curved surface is consistent with the curved surface of the lower surface of the wing 7. Specifically, in order to realize take-off and flight of the aircraft, the lower surface of the wing 7 is provided with a curved surface, and in order to ensure that the heights of the two ends of the structural component 1 are consistent, the same curved surface is provided on the upper surface of the connecting component 5.

[0039] Optionally, the connection assembly 5 and the wing 7 are mechanically connected, and the mechanical connection may be a bolt connection, a screw connection, a threaded connection, etc.

[0040] Optionally, a direction sensor, a speed sensor and an altitude sensor connected to a control system are provided on the structural component 1. The control system is arranged inside the structural component 1, and the direction sensor, the speed sensor and the altitude sensor are all arranged inside the structural component 1. The state of the aircraft is acquired through these sensors, and the aircraft state information (including flight speed, flight posture, height from the ground, heading, etc.) is acquired. The control system collects and analyzes the information, and outputs control information for the vertical take-off and landing kit and display information of the aircraft state, so as to achieve the purpose of vertical take-off and landing of the aircraft.

[0041] In another feasible manner, the control system in the structural component 1 can also obtain aircraft status information (including flight speed, flight attitude, altitude above the ground, heading, etc.) from the aircraft system, and then control the vertical take-off and landing kit.

[0042] Optionally, in one achievable manner, the propeller 2 includes two integrally formed blades, which are arranged 180 degrees apart. In other achievable manners, the propeller may be composed of multiple blades, or may be composed of upper and lower layers of blades. The specific propeller structure is not limited here, and is subject to actual achievable configurations.

[0043] Please continue reading Figure 3 The second aspect of the present application provides an aircraft, the aircraft comprising an aircraft body 6, wings 7, a tail and Figure 1 and Figure 2 In any of the embodiments, the vertical take-off and landing kit, the wing 7 is fixed on both sides of the aircraft body 6, the tail wing is integrally formed and arranged at the tail of the aircraft body 6, the vertical take-off and landing kit is respectively located on both sides of the aircraft body and connected to the bottom of the wing 7, wherein the vertical take-off and landing kit is connected to the lower surface of the wing 7 through the connecting component 5 on the structural component 1.

[0044] Optionally, the vertical device kit and the wing 7 are arranged perpendicular to each other. Specifically, the structural component 1 in the vertical take-off and landing kit and the wing 7 are arranged perpendicular to each other.

[0045] It should be noted that the above description of the disclosed embodiments enables professionals and technicians in the field to implement or use the present application. Various modifications to these embodiments will be apparent to professionals and technicians in the field, and the general principles defined herein can be implemented in other embodiments without departing from the scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but should conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A vertical take-off and landing kit for an aircraft, It is characterized in that include: Structural components, propellers, and motors; The motors are respectively arranged at both ends of the structural assembly, a battery is arranged inside the structural assembly, and the battery is connected to the motor via an electronic speed regulator; The rotating shaft of the motor extends upward, and the center of the propeller is connected to the rotating shaft; A connecting assembly is arranged at the middle position of the structural assembly, so that the structural assembly is connected to the lower surface of the wing through the connecting assembly.

2. The vertical take-off and landing kit according to claim 1, It is characterized in that Both ends of the structural component are respectively fixedly connected with a power cabin, and a receiving groove is arranged in the power cabin, and the size of the receiving groove matches the size of the motor.

3. The vertical take-off and landing kit according to claim 2, It is characterized in that The power cabin is streamlined.

4. The vertical take-off and landing kit according to any one of claims 1 to 3, It is characterized in that The connecting component protrudes from the surface of the structural component.

5. The vertical take-off and landing kit according to any one of claims 1 to 3, It is characterized in that The connection assembly is provided with a curved surface, and the curved surface is consistent with the curved surface of the lower surface of the wing.

6. The vertical take-off and landing kit according to any one of claims 1 to 3, It is characterized in that The connection assembly is mechanically connected to the wing.

7. The vertical take-off and landing kit according to any one of claims 1 to 3, It is characterized in that The structural component is provided with a posture sensor, a direction sensor, a speed sensor and a height sensor connected with a control system, and the control system is arranged in the structural component.

8. An aircraft, It is characterized in that It comprises an aircraft fuselage, wings, a tail and a vertical take-off and landing kit as described in any one of claims 1 to 7, wherein the wings are fixed on both sides of the aircraft fuselage, the tail is integrally formed and arranged at the tail of the aircraft fuselage, and the vertical take-off and landing kit is respectively located on both sides of the aircraft fuselage and connected to the bottom of the wings.

9. The aircraft according to claim 8, It is characterized in that The vertical take-off and landing kit and the wing are arranged perpendicular to each other.

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