Aircraft tilting mechanism

Abstract

The utility model discloses an aircraft tilting mechanism relates to unmanned helicopter rotor tilting technical field, including bottom plate and with the vertical shaft of bottom plate rotation connection, vertical shaft fixedly connected with the sleeve pipe, the sleeve pipe is rotationally arranged with the horizontal shaft, and vertical shaft and horizontal shaft one end respectively has the power component, and the sleeve pipe between power component is provided with the clamping assembly for fixing vertical shaft and horizontal shaft, and the clamping assembly is fixedly connected with the bottom plate. The application has the beneficial effect that by setting the first motor between the power component and the sleeve pipe, the horizontal shaft is arranged in the sleeve pipe and is connected with the first motor output shaft, the sleeve pipe bottom connects the vertical shaft, the second motor that drives the vertical shaft rotation is arranged below the bottom plate, the horizontal shaft rotation realizes the adjustment of rotor angle in the unmanned helicopter operation process, the vertical shaft rotation realizes the accommodation of power component, and the overall structure is compact, greatly reduces the volume of tilting mechanism, thereby reduces the accommodation space of aircraft, realizes the space utilization rate promotion.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) rotor tilting technology, and in particular to an aircraft tilting mechanism. Background Technology

[0002] The tilt mechanism of a UAV is a core component for adjusting the rotor angle, enabling the UAV to perform vertical takeoff and landing, climb, altitude reduction, in-flight turning, hovering turns, rolls, and forward and backward movements. Composed of tilt joints, a synchronous control system, and power and aerodynamic design, the UAV combines the high maneuverability of a helicopter with the efficiency of a fixed-wing aircraft. It is convenient and flexible to use and widely applied in aerial photography, military reconnaissance, scientific research, and other fields.

[0003] The weight and rotational accuracy of the tilt mechanism have a significant impact on the flight performance of a drone. Weight affects the drone's flight speed, while rotational accuracy affects its controllability. Some existing drone tilt mechanisms suffer from drawbacks such as large space requirements and low rotational accuracy, which greatly limit the drone's performance. Therefore, there is an urgent need for a compact, lightweight tilt mechanism with high rotational accuracy. Utility Model Content

[0004] The purpose of this section is to provide an aircraft tilting mechanism that can reduce the space occupied, thereby improving the overall performance of the drone.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution: an aircraft tilting mechanism, including a base plate and a vertical shaft rotatably connected to the base plate, a sleeve fixedly connected to the vertical shaft, a transverse shaft rotatably disposed inside the sleeve, a power assembly connected to one end of the transverse shaft, a clamping assembly for fixing the transverse shaft disposed between the power assembly and the sleeve, and the clamping assembly being fixedly connected to the side wall of the base plate.

[0006] In a preferred embodiment of the aircraft tilting mechanism described in this utility model, a first motor for driving the lateral axis to rotate is provided between the sleeve and the power assembly.

[0007] In a preferred embodiment of the aircraft tilting mechanism described in this utility model, the power assembly includes a turbofan and a fixed shell sleeved outside the turbofan, wherein the fixed shell is fixedly connected to a transverse shaft.

[0008] As a preferred embodiment of the aircraft tilting mechanism of this utility model, the clamping assembly includes a clamp and a moving rod that cooperates with the clamp to clamp the transverse axis.

[0009] As a preferred embodiment of the aircraft tilting mechanism of this utility model, at least two bearings are provided at one end of the transverse shaft located inside the sleeve, and an anti-loosening nut and a washer are sequentially provided on one side of one of the bearings.

[0010] As a preferred embodiment of the aircraft tilting mechanism of this utility model, the vertical shaft is provided with a bearing, a lock nut and a washer in sequence at one end located below the base plate, and a second motor for driving the vertical shaft to rotate is provided on one side of the washer.

[0011] As a preferred embodiment of the aircraft tilting mechanism of this utility model, flanges for limiting the vertical movement of the rotation shaft are provided above and below the base plate.

[0012] The beneficial effects of this utility model are:

[0013] By placing the first motor between the power assembly and the sleeve, setting the transverse shaft inside the sleeve and connecting it to the output shaft of the first motor, and connecting the bottom of the sleeve to the vertical shaft, a second motor is set below the base plate to drive the vertical shaft to rotate. The rotation of the transverse shaft enables the adjustment of the rotor angle during the operation of the UAV, and the rotation of the vertical shaft enables the storage of the power assembly. The overall structure is compact, greatly reducing the volume of the tilting mechanism, thereby reducing the storage space of the aircraft and improving space utilization. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the following description of the embodiments will be briefly introduced. The drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without any creative effort or labor. Wherein:

[0015] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0016] Figure 2 This is a partial structural schematic diagram of the present invention;

[0017] Figure 3 This is a schematic diagram of the clamping assembly of this utility model;

[0018] Figure 4 This is a schematic diagram of the second motor and the vertical shaft of this utility model;

[0019] Figure 5 This is a disassembly diagram of the vertical axis portion of this utility model;

[0020] Figures 6-12 This is a schematic diagram showing the position of the turbofan in different states of the aircraft.

[0021] Reference numerals in the attached drawings: 1. Base plate; 2. Vertical shaft; 3. Sleeve; 4. Horizontal shaft; 501. Turbine fan; 502. Fixed shell; 601. Clamp; 602. Moving rod; 7. First motor; 8. Bearing; 9. Anti-loosening nut; 10. Washer; 11. Second motor; 12. Flange. Detailed Implementation

[0022] To make the above-mentioned objectives, features and advantages of this utility model more easily understood, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0023] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways than those described herein. The term "embodiment" as used herein refers to a particular feature, structure, or characteristic that may be included in at least one implementation of the present invention.

[0024] Example

[0025] Reference Figures 1-9 This embodiment provides an aircraft tilting mechanism, specifically including a base plate 1 and a vertical shaft 2 rotatably connected to the base plate 1. A sleeve 3 is fixedly connected to the vertical shaft 2, and a transverse shaft 4 is rotatably disposed within the sleeve 3. One end of the transverse shaft 4 is connected to a power assembly. A clamping assembly for fixing the transverse shaft 4 is disposed between the power assembly and the sleeve 3, and the clamping assembly is fixedly connected to the side wall of the base plate 1. A first motor 7 for driving the transverse shaft 4 to rotate is disposed between the sleeve 3 and the power assembly. The power assembly includes a turbofan 501 and a fixed housing 502 sleeved outside the turbofan 501, and the fixed housing 502 is fixedly connected to the transverse shaft 4. The clamping assembly includes a clamp 601 and a moving rod 602 that cooperates with the clamp 601 to clamp the transverse shaft 4. At least two bearings 8 are disposed at one end of the transverse shaft 4 located inside the sleeve, and an anti-loosening nut 9 and a washer 10 are sequentially disposed on one side of one of the bearings 8.

[0026] A power assembly is connected to one end of the vertical shaft 2 and the horizontal shaft 4. A clamping assembly for fixing the vertical shaft 2 and the horizontal shaft 4 is provided between the power assembly and the sleeve 3.

[0027] The movable rod 602 is a square column pin.

[0028] The sleeve 3 is arranged horizontally and has a circular protrusion in the middle of its inner wall. The circular protrusion is in contact with the horizontal shaft 4. The inner wall of the sleeve 3 near the two ends (i.e. the part without the circular protrusion) is in contact with the bearing 8 sleeved on the horizontal shaft 4.

[0029] One end of the transverse shaft 4 is flush with the sleeve 3, and the other end is located outside the sleeve 3. The bearing 8 on the transverse shaft 4 near the first motor 7 is fitted with bushings to restrict the sliding of the bearing 8. The other bearing 8 on the transverse shaft 4 is restricted from sliding by a ring protrusion and a lock nut 9. A washer 10 is fitted on the outside of the lock nut 9.

[0030] The portion of the transverse shaft 4 located outside the sleeve 3 is provided with teeth, which cooperate with the first motor 7 to drive the transverse shaft 4 to rotate along the axis of the sleeve 3.

[0031] The clamp 601 and the moving rod 602 are common clamping fit methods in the prior art. The specific structure will not be described in detail in the instruction manual. The transverse shaft 4 is rotatably connected to the inner wall of the clamp 601. The moving rod 602 moves upward to cooperate with the clamp 601 to clamp the transverse shaft 4 and prevent the transverse shaft 4 from shifting position. At this time, the transverse shaft 4 can rotate along the axis of the sleeve 3 under the drive of the first motor 7.

[0032] A bearing 8, a lock nut 9, and a washer 10 are sequentially installed at the end of the vertical shaft 2 located below the base plate 1. A second motor 11 for driving the rotation of the vertical shaft 2 is installed on one side of the washer 10. Flanges 12 for limiting the vertical movement of the rotating shaft are installed above and below the base plate 1.

[0033] The inner wall of the flange 12 located above the base plate 1 is also equipped with a bearing 8. Under the restriction of the two flanges 12, the vertical shaft 2 can only rotate along its own axis. The rotation of the vertical shaft 2 is used to store or extend the power component.

[0034] In use, the second motor 11 is activated to extend the power unit, which is then rotated until the horizontal shaft 4 is flush with the inner wall of the clamp 601, and then fixed by the moving rod 602. The angle of the power unit is then adjusted by the driving force of the first motor 7, thereby controlling the drone's flight mode.

[0035] The rotor and power assembly of this application are separately configured, allowing for convenient flight attitude conversion and a shift in power from vertical lift to sustained thrust, resulting in a longer flight time. The side of the WS-501 with the protective shield is the air inlet, and the side without the protective shield is the air outlet, which is the direction in which thrust is generated.

[0036] When the aircraft is in standby mode, all WS-501 turbofans are hidden to improve space utilization.

[0037] vertical takeoff state of the aircraft ( Figure 6 All turbofan 501 units generate thrust vertically downwards (arrows indicate airflow direction);

[0038] Aircraft climb status ( Figure 7 All 501 turbofan engines generate thrust backward and downward;

[0039] Aircraft cruise status ( Figure 8 All 501 turbofan engines generate thrust directly backward;

[0040] Aircraft roll state ( Figure 9 One of the turbofan 501s on one side generates thrust directly downwards, while the other turbofan 501 generates thrust directly upwards, causing the aircraft to roll laterally.

[0041] Aircraft in backward state ( Figure 10 All 501 turbofans generate thrust forward and downward to achieve backward flight. During forward flight, all 501 turbofans generate thrust forward and downward to decelerate at a relatively high forward speed.

[0042] During a turn in flight, the two turbofan engines 501 at the rear of the aircraft generate thrust directly backward, producing forward propulsion. The two turbofan engines 501 at the front of the aircraft generate thrust in opposite directions: one generates thrust downward and backward, while the other generates thrust downward and forward, enabling the aircraft to make a left turn during flight. Figure 11 ) or turn right ( Figure 12 ).

[0043] When the aircraft is hovering, after vertical takeoff, all the WS-501 turbines on one side generate thrust downwards and backwards, while all the WS-501 turbines on the other side generate thrust downwards and forwards, enabling the aircraft to make a left or right turn while hovering.

[0044] Other states of the aircraft and the rotor engagement methods are the same as those commonly used in the prior art, and will not be described in detail in this specification.

[0045] Importantly, although only a few embodiments are described in detail in this disclosure, those who consult this disclosure will readily understand that many modifications are possible without substantially departing from the subject matter described in this application, such as changes in the size, structure, shape, and proportion of various elements, as well as variations in temperature, pressure, installation arrangement, material use, color, orientation, etc.; for example, an element shown as integrally formed may be composed of multiple parts or elements, and the position of the elements may be inverted or otherwise altered; therefore, all such modifications should be included within the scope of this invention, and other substitutions, modifications, alterations, and omissions may be made in the design, operation, and arrangement of the exemplary embodiments without departing from the scope of this invention.

Claims

1. An aircraft tilting mechanism, characterized in that, It includes a base plate (1) and a vertical shaft (2) rotatably connected to the base plate (1). The vertical shaft (2) is fixedly connected to a sleeve (3). A transverse shaft (4) is rotatably arranged inside the sleeve (3). One end of the transverse shaft (4) is connected to a power assembly. A clamping assembly for fixing the transverse shaft (4) is provided between the power assembly and the sleeve (3). The clamping assembly is fixedly connected to the side wall of the base plate (1).

2. The aircraft tilting mechanism as described in claim 1, characterized in that, A first motor (7) for driving the rotation of the transverse shaft (4) is provided between the sleeve (3) and the power assembly.

3. The aircraft tilting mechanism as described in claim 1, characterized in that, The power assembly includes a turbofan (501) and a fixed shell (502) sleeved on the outside of the turbofan (501), the fixed shell (502) being fixedly connected to the transverse shaft (4).

4. The aircraft tilting mechanism as described in claim 1, characterized in that, The clamping assembly includes a clamp (601) and a cooperating clamp (601) for clamping a moving rod (602) that clamps the transverse shaft (4).

5. The aircraft tilting mechanism as described in claim 1, characterized in that, The transverse shaft (4) is provided with at least two bearings (8) at one end inside the sleeve, and a lock nut (9) and a washer (10) are provided on one side of one of the bearings (8).

6. The aircraft tilting mechanism as described in claim 1, characterized in that, The vertical shaft (2) is provided with a bearing (8), a lock nut (9) and a washer (10) in sequence at one end below the base plate (1). A second motor (11) for driving the vertical shaft (2) to rotate is provided on one side of the washer (10).

7. The aircraft tilting mechanism as described in claim 1, characterized in that, Flanges (12) for limiting the vertical movement of the rotating shaft are provided above and below the base plate (1).

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