CN218949477U

CN218949477U - Control device of variable-pitch aircraft

Info

Publication number: CN218949477U
Application number: CN202222689935.8U
Authority: CN
Inventors: 胡文生
Original assignee: Pinghu Zhifei Unmanned Aerial Vehicle Co ltd
Current assignee: Yunnan Stratospheric Technology Co ltd
Priority date: 2022-10-10
Filing date: 2022-10-10
Publication date: 2023-05-02
Anticipated expiration: 2032-10-10

Abstract

The utility model discloses a control device of a variable-pitch aircraft, and relates to the technical field of aircrafts. The device comprises a frame, the displacement device is installed respectively to the both sides of frame, the displacement device includes the motor, and the bottom of motor and the top of frame one side are fixed, the output fixedly connected with rotating member of motor, the both ends of rotating member rotate respectively and are connected with the screw, the top fixedly connected with electric putter of frame one side, electric putter's telescopic end fixedly connected with bearing, the top fixedly connected with solid fixed ring of bearing, the top fixedly connected with support frame of solid fixed ring, the inside swing joint of the top and the screw of support frame. According to the utility model, through the arrangement of the structure of the distance changing device, the telescopic end of the electric push rod can move, and the bearing, the fixed ring and the support frame move, so that the deflection angle of the propeller blade is changed, the complexity of internal parts is low, the manufacturing cost is low, and the production is convenient.

Description

Control device of variable-pitch aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a control device of a variable-pitch aircraft.

Background

The pitch-variable aircraft controls the deflection angle of the propeller blades and the magnitude of pulling force or lifting force, namely, the deflection angle of the propeller blades is changed by the motor at the same rotating speed, so that the flying speed of the aircraft is also changed.

A control device for a pitch-controlled aircraft as disclosed in application No. 201410199408.6, said control device comprising a first control lever which in a first state controls the pitch of the aircraft rotor and the rotational speed of the motor to increase synchronously; the first control rod controls the pitch of the rotor wing of the aircraft and the rotating speed of the motor to be synchronously reduced in the second state, and the application also discloses a control method of the multi-rotor wing variable-pitch aircraft. In the utility model, when the climbing pitch of the aircraft is required to be increased, the flight controller controls the motor to correspondingly increase the rotating speed and the torque force in a certain proportion, and the mode has higher relative efficiency and moderate sensitivity and is easy to control.

The variable-pitch rotor used by the device has more transmission parts involved in the process when the blades of the propeller deflect at an angle, wherein part of the transmission parts are more complex in structure and need to be processed additionally, and meanwhile, the dimensional accuracy of the transmission parts needs to be ensured, so that the production cost of the aircraft is high, and therefore, the control device of the variable-pitch aircraft is provided.

Disclosure of Invention

The utility model aims to provide a control device of a variable-pitch aircraft, which is used for solving the problems in the background art.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a controlling means of displacement aircraft, includes the frame, displacement device is installed respectively to the both sides of frame, displacement device includes the motor, and the bottom of motor and the top of frame one side are fixed, the output fixedly connected with rotating member of motor, the both ends of rotating member rotate respectively and are connected with the screw, the top fixedly connected with electric putter of frame one side, electric putter's telescopic end fixedly connected with bearing, the top fixedly connected with solid fixed ring of bearing, the top fixedly connected with support frame of solid fixed ring, the inside swing joint of the top and screw of support frame, the internally mounted of frame has control mechanism.

Preferably, a groove is formed in one end of the bottom of the propeller, and the top end of the support frame is movably connected with one end of the bottom of the propeller through the groove.

Preferably, the control mechanism comprises a control terminal, a power supply and a three-axis gyroscope, wherein the control terminal, the power supply and the three-axis gyroscope are respectively positioned on the frame, and the internal power supply is electrically connected with the control terminal and the three-axis gyroscope.

Preferably, the frame is internally provided with a signal receiver, and the signal receiver is electrically connected with the control terminal.

Preferably, a microprocessor and a GPS positioning system are arranged in the frame, and the microprocessor is electrically connected with the three-axis gyroscope and the GPS positioning system.

Preferably, the bearing comprises an outer ring frame and an inner ring frame, the top end of the inner ring frame is fixed with the bottom end of the fixing ring, the bottom end of the outer ring frame is fixed with the telescopic end of the electric push rod, a gap is reserved between the inner wall of the inner ring frame and the output shaft of the motor, and the inner wall of the fixing ring is in sliding connection with the output shaft of the motor.

Preferably, the outer wall of the output shaft of the motor is provided with a sliding groove, and the inner wall of the fixed ring is movably connected with the outer wall of the output shaft of the motor through the sliding groove.

Compared with the prior art, the utility model has the beneficial effects that:

according to the control device of the pitch-variable aircraft, through the arrangement of the structure of the pitch-variable device, the telescopic end of the electric push rod can be moved, and the bearing, the fixed ring and the support frame can be moved, so that the deflection angle of the propeller blade is changed, the complexity of internal parts is low, the manufacturing cost is low, and the production is convenient.

This control device of pitch-changing aircraft, through the setting of bearing, when the screw rotates, the part that links to each other with it all can not influence the rotation of screw, and solid fixed ring and support frame rotate along with the rotation of screw, make this rotation do not have the influence to electric putter through the bearing for electric putter can normally work, has improved the practicality of this pitch-changing device.

Drawings

FIG. 1 is an isometric view of the present utility model;

FIG. 2 is an isometric view of a pitch device of the present utility model;

fig. 3 is a partial cross-sectional view of the propeller of the present utility model.

In the figure: 1. a frame; 2. a motor; 3. a rotating member; 4. a propeller; 5. a support frame; 6. a fixing ring; 7. a bearing; 8. an electric push rod.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

It should be noted that, in the description of the present utility model, the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, only for convenience in describing the present utility model and simplifying the description, and do not indicate or imply that the apparatus or elements to be referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present utility model.

Furthermore, it should be understood that the dimensions of the various elements shown in the figures are not drawn to actual scale, e.g., the thickness or width of some layers may be exaggerated relative to other layers for ease of description.

It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once an item is defined or illustrated in one figure, no further detailed discussion or description thereof will be necessary in the following description of the figures.

As shown in fig. 1-3, the present utility model provides a technical solution: the utility model provides a controlling means of displacement aircraft, including frame 1, displacement device is installed respectively to frame 1's both sides, displacement device includes motor 2, motor 2's bottom and the top of frame 1 one side are fixed, motor 2's output fixedly connected with rotating member 3, rotating member 3's both ends are the rotation respectively and are connected with screw 4, frame 1's top fixedly connected with electric putter 8, electric putter 8's telescopic end fixedly connected with bearing 7, bearing 7's top fixedly connected with solid fixed ring 6, guy fixed ring 6's top fixedly connected with support frame 5, the inside swing joint of support frame 5's top and screw 4, frame 1's internally mounted has control mechanism.

One end of the bottom of the screw 4 is provided with a groove, and the top end of the supporting frame 5 is movably connected with one end of the bottom of the screw 4 through the groove.

The control mechanism comprises a control terminal, a power supply and a three-axis gyroscope, wherein the control terminal, the power supply and the three-axis gyroscope are respectively positioned on the frame 1, and the internal power supply is electrically connected with the control terminal and the three-axis gyroscope.

The frame 1 is internally provided with a signal receiver which is electrically connected with a control terminal.

The frame 1 is internally provided with a microprocessor and a GPS positioning system, and the microprocessor is electrically connected with the triaxial gyroscope and the GPS positioning system.

The bearing 7 comprises an outer ring frame and an inner ring frame, the top end of the inner ring frame is fixed with the bottom end of the fixed ring 6, the bottom end of the outer ring frame is fixed with the telescopic end of the electric push rod 8, a gap is reserved between the inner wall of the inner ring frame and the output shaft of the motor 2, and the inner wall of the fixed ring 6 is in sliding connection with the output shaft of the motor 2.

The outer wall of the output shaft of the motor 2 is provided with a sliding groove, and the inner wall of the fixed ring 6 is movably connected with the outer wall of the output shaft of the motor 2 through the sliding groove.

The receiver receives the command, the motor 2 of the aircraft is started, the output end of the motor 2 rotates, the rotating piece 3 rotates, the propeller 4 rotates by taking the central shaft of the rotating piece 3 as the rotation center, the lifting of the aircraft can be realized, the telescopic end of the electric push rod 8 moves, the bearing 7 moves, the fixed ring 6 moves, the supporting frame 5 moves, the top end of the supporting frame 5 and the position inside the propeller 4 change, the supporting frame 5 and the propeller 4 are movably connected, but when the supporting frame 5 moves, the top of the supporting frame 5 contacts with the inside of the propeller 4 and applies force to the propeller 4, under the action of the force, the deflection angle of the blades of the propeller 4 changes, the rotating speed of the motor 2 does not change, but the pulling force or lifting force generated by the propeller 4 changes, so as to control the pulling force or lifting force of each distance-changing device, thus controlling the balance of the whole aircraft, the signal receiver receives control signals, the aircraft is controlled to move through the control terminal according to the signals, the triaxial gyroscope can simultaneously measure the positions, the movement track and the acceleration of 6 directions, when the aircraft is unnecessarily inclined in the flight process, the triaxial gyroscope can detect the inclination and send signals to the microprocessor, the microprocessor processes the signals and adjusts through the variable-pitch device of the control terminal control part, the telescopic end of the electric push rod 8 moves, the deflection angle of the blades of the propeller 4 which is not in transmission changes, the lift force of the propeller 4 is sequentially changed, so that the lift force on one side is high, the lift force on the other side is low, the inclination angle is adjusted, the telescopic end of the electric push rod 8 moves through the arrangement of the variable-pitch device structure, the bearing 7, the fixed ring 6 and the support frame 5 move, make the deflection angle of the paddle of screw 4 change, the internals complexity is not high, low in manufacturing cost, the production of being convenient for, through the setting of bearing 7, when screw 4 rotates, the part that links to each other with it all can not influence the rotation of screw 4, solid fixed ring and support frame 5 rotate along with the rotation of screw 4, make this rotation do not have the influence to electric putter 8 through bearing 7 for electric putter 8 can normally work, has improved the practicality of this displacement device.

Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. Control device for a pitch-variable aircraft, comprising a frame (1), characterized in that: the utility model provides a motor variable-pitch device is installed respectively to both sides of frame (1), variable-pitch device includes motor (2), and the bottom of motor (2) is fixed with the top of frame (1) one side, the output fixedly connected with rotating member (3) of motor (2), the both ends of rotating member (3) rotate respectively and are connected with screw (4), the top fixedly connected with electric putter (8) of frame (1) one side, the telescopic end fixedly connected with bearing (7) of electric putter (8), the top fixedly connected with solid fixed ring (6) of bearing (7), the top fixedly connected with support frame (5) of solid fixed ring (6), the inside swing joint of the top and screw (4) of support frame (5), the internally mounted of frame (1) has control mechanism.

2. A control device for a pitch-varying aircraft according to claim 1, characterized in that: the one end of screw (4) bottom is seted up flutedly, and the one end swing joint of screw (4) bottom of recess is passed through on the top of support frame (5).

3. A control device for a pitch-varying aircraft according to claim 1, characterized in that: the control mechanism comprises a control terminal, a power supply and a three-axis gyroscope, wherein the control terminal, the power supply and the three-axis gyroscope are respectively positioned on the frame (1), and the internal power supply is electrically connected with the control terminal and the three-axis gyroscope.

4. A control device for a pitch-varying aircraft according to claim 1, characterized in that: the frame (1) is internally provided with a signal receiver which is electrically connected with the control terminal.

5. A control device for a pitch-varying aircraft according to claim 1, characterized in that: the microprocessor and the three-axis gyroscope are electrically connected with the GPS positioning system.

6. A control device for a pitch-varying aircraft according to claim 1, characterized in that: the bearing (7) comprises an outer ring frame and an inner ring frame, the top end of the inner ring frame is fixed with the bottom end of the fixed ring (6), the bottom end of the outer ring frame is fixed with the telescopic end of the electric push rod (8), a gap is reserved between the inner wall of the inner ring frame and the output shaft of the motor (2), and the inner wall of the fixed ring (6) is in sliding connection with the output shaft of the motor (2).

7. A control device for a pitch-varying aircraft according to claim 1, characterized in that: the outer wall of the output shaft of the motor (2) is provided with a sliding groove, and the inner wall of the fixed ring (6) is movably connected with the outer wall of the output shaft of the motor (2) through the sliding groove.