Aircraft power driving device

Abstract

The invention discloses a power driving device for an aircraft. The power driving device comprises wings consisting of fan blades and driving motors, the driving motor is electrically connected with a main controller of the aircraft; the device further comprises a first adjusting mechanism and a second adjusting mechanism. The wings are connected with the first adjusting mechanism through the connecting bracket; the first adjusting mechanism is used for adjusting the wing to be switched among an upward state, a forward state and a downward state; the first adjusting mechanism is connected with the second adjusting mechanism; and the second adjusting mechanism is used for adjusting the angle of the first adjusting mechanism around the axis by taking the central shaft as the axis. The first adjusting mechanism and the second adjusting mechanism are electrically connected with a main controller of the aircraft. The wings are adjusted through the first adjusting mechanism and the second adjusting mechanism, the safety of the product is improved, and meanwhile operability and interestingness are improved.

Description

Technical Field

[0001] The present invention relates to the field of aircraft power drive, and in particular to an aircraft power drive device. Background Art

[0002] Aircraft is a general term for drones, manned aircraft, toy airplanes, and more. Currently, aircraft primarily come in single-wing, twin-wing, tri-wing, and quad-wing configurations. Single-wing configurations are located on or above the aircraft's main body; twin-wing configurations are located on either side of the main body; tri-wing configurations are located on both sides and at the tail; and quad-wing configurations are arranged in pairs on either side of the main body. The wings consist of blades and drive motors. The motors are controlled by the aircraft's main controller, which adjusts the motor speed and, therefore, the flight attitude.

[0003] Once the wings in the existing technology are connected to the aircraft body, the position and direction of the wings cannot be adjusted. This means that if the aircraft encounters airflow or is in a harsh environment during flight, the operator's operating skills are very high, which in turn affects the aircraft's maneuverability, fun and safety. Summary of the Invention

[0004] To address the deficiencies of the prior art, the present invention provides an aircraft power drive device. To achieve the above objectives, the present invention employs the following technical solutions: an aircraft power drive device comprising a wing consisting of fan blades and a drive motor; the drive motor being electrically connected to the aircraft's main controller; a first adjustment mechanism and a second adjustment mechanism; the wing being connected to the first adjustment mechanism via a connecting bracket; the first adjustment mechanism being used to adjust the wing between upward, forward, and downward positions; the first adjustment mechanism being connected to the second adjustment mechanism; and the second adjustment mechanism being used to adjust the angle of the first adjustment mechanism around an axis with the central axis as the axis. The first and second adjustment mechanisms are each electrically connected to the aircraft's main controller.

[0005] Using the technical solution of this application, the first adjustment mechanism can adjust the wing to point upward, forward, or downward; the second adjustment mechanism can adjust the wing to point left or right. The second adjustment mechanism also allows for fine-tuning of the wing angle during flight based on the flight environment, allowing for better handling in complex flight conditions. This improves aircraft safety while also enhancing its operability and enjoyment.

[0006] A further improvement is that the first adjustment mechanism includes an upper shell (1), a lower shell (1), and an adjustment motor (1); the upper and lower shells (1) are fixedly connected in an openable and removable manner; a chamber (1) is provided within the space formed by the upper and lower shells to accommodate the adjustment motor (1); the adjustment motor (1) is mounted within the chamber (1) via a mounting bracket (1); a drive shaft (1) of the adjustment motor (1) is fixedly connected to one side of the connecting bracket; the other side of the connecting bracket is connected to a rotating shaft provided on the mounting bracket (1). The coordination of the drive shaft (1) and the rotating shaft allows the wing to quickly switch between upward, forward, and super three positions.

[0007] A further improvement is that a symmetrical positioning plate 1 is provided on the mounting seat 1, and a limiting plate 1 is provided in the chamber 1 to cooperate with the positioning plate 1. The cooperation between the positioning plate and the limiting plate 1 and the adjustment motor together play a reinforcing role.

[0008] A further improvement is that the second adjustment mechanism includes an upper shell (2), a lower shell (2), and an adjustment motor (2); the upper shell (2) and the lower shell (2) are fixedly connected by means of an opening and disassembly method; a chamber (2) for accommodating the adjustment motor (2) is provided within the space formed by the upper shell (2) and the lower shell (2); the adjustment motor (2) is mounted within the chamber (2) via a mounting seat (2); a connecting plate is fixed to the drive shaft (2) of the adjustment motor (2); a slot is provided within the chamber (1) corresponding to the connecting plate; the connecting plate is fixed within the slot by means of the mating connection between the upper shell (1) and the lower shell (1). The use of the connecting plate and the slot improves the stability of the aircraft's power drive device during rotation.

[0009] As a further improvement, symmetrical limiting plates are provided at the corresponding locations of chamber 2 and mounting base 2; a positioning plate is provided on top of mounting base 2; and a limiting groove is provided within chamber 2 to limit the positioning plate. The combination of positioning plate 2 and limiting groove 1 provides a secondary fixation for adjusting motor 2.

[0010] A further improvement is that the first housing, formed by the first upper housing and the first lower housing, is provided with a cylindrical rotating shaft at a position corresponding to the second housing, formed by the second upper housing and the second lower housing. The second housing has a rotating chamber corresponding to the rotating shaft, which is located within the second chamber. The connecting plate is located within the rotating chamber, and the slot is located within the rotating shaft. This design ensures that the aircraft power drive device rotates while also improving the product's aesthetics.

[0011] As a further improvement, the wing is fixedly connected to the connecting bracket via a mounting seat 3. With the help of the mounting seat 3, the firmness of the connection and the stability during flight are guaranteed.

[0012] A further improvement includes a protective cover having a second limiting groove at its center axis and a limiting block below the mounting seat that cooperates with the second limiting groove. The cooperation between the second limiting groove and the limiting block ensures the stability of the protective cover during flight.

[0013] As a further improvement, the limiting groove is triangular and the limiting block is triangular. The stability of the triangle improves the stability of the protective cover connection.

[0014] A further improvement is that the retaining groove has an arc-shaped groove at the vertex of the triangle, and an inward-protruding arc-shaped protrusion is located between the two vertices of the triangle. The retaining block has an arc-shaped retaining post corresponding to the arc-shaped groove, and an inward-concave arc-shaped surface corresponding to the arc-shaped protrusion. This design adds a double guarantee to the stability of the protective cover. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a three-dimensional diagram of the aircraft power drive device with the wings facing forward.

[0016] Figure 2 This is an exploded view of the aircraft's power drive unit with its wings facing upward.

[0017] Figure 3 This is a three-dimensional diagram when the wings are facing upward and the first adjustment mechanism is deflected 90 degrees relative to the second adjustment mechanism.

[0018] Figure 4 This is an exploded view of the protective cover and the aircraft's power drive unit.

[0019] Figure 5 yes Figure 2 A partial enlarged view of .

[0020] Figure 6 Reference to the application of aircraft power drive devices to aircraft in the prior art Figure 1 .

[0021] Figure 7 Reference to the application of aircraft power drive devices to aircraft in the prior art Figure 2 .

[0022] Figure 8 Reference to the application of aircraft power drive devices to aircraft in the prior art Figure 3 . DETAILED DESCRIPTION

[0023] The preferred embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0024] like Figures 1 to 8As shown, an aircraft power drive device includes a wing consisting of a fan blade 1 and a drive motor 2; it also includes a first adjustment mechanism 3 and a second adjustment mechanism 4; the drive motor, the first adjustment mechanism, and the second adjustment mechanism are respectively electrically connected to the main controller of the aircraft. The wing is connected to the first adjustment mechanism via a connecting bracket 5; the first adjustment mechanism is used to adjust the wing to switch between three states: upward, forward, and downward; the first adjustment mechanism is connected to the second adjustment mechanism; the second adjustment mechanism is used to adjust the angle of the first adjustment mechanism around the axis with the central axis as the axis. The wing is fixedly connected to the connecting bracket via a third mounting seat 27. It also includes a protective cover 28; a second limit groove 29 is provided at the center axis of the protective cover; a limit block 30 is provided below the third mounting seat to cooperate with the second limit groove. The limit groove is triangular in shape; the limit block is triangular in shape. The limiting groove has an arc groove 31 at the vertex of the triangle, and an inward-protruding arc protrusion 32 is provided between the two vertices of the triangle; the limiting block has an arc limiting column 33 corresponding to the arc groove, and an inward-concave arc surface 34 corresponding to the arc protrusion.

[0025] The first adjustment mechanism includes an upper shell 6, a lower shell 7, and an adjustment motor 8. The upper shell 1 and the lower shell 1 are fixedly connected in an open and disassembled manner. In this application, screws and screw holes are used for fixation. Of course, other removable fixing methods such as snaps and slots can also be used. The space formed by the upper shell 1 and the lower shell 1 is provided with a chamber 9 for accommodating the adjustment motor 1. The adjustment motor 1 is installed in the chamber 1 via a mounting seat 10. The transmission shaft 11 of the adjustment motor 1 is fixedly connected to one side of the connecting bracket; the other side of the connecting bracket is connected to a rotating shaft 12 provided on the mounting seat 1. A symmetrical positioning plate 13 is provided on the mounting seat 1; and a limit plate 14 is provided in the chamber 1 to cooperate with the positioning plate 1.

[0026] The second adjustment mechanism includes an upper shell 2 15, a lower shell 2 16, and an adjustment motor 2 17; the upper shell 2 and the lower shell 2 are fixedly connected in an open and disassembled manner; in this application, screws and screw holes are used for fixation, but other detachable fixation methods such as snaps and slots can also be used. The space formed by the upper shell 2 and the lower shell 2 is provided with a chamber 2 18 for accommodating the adjustment motor 2; the adjustment motor 2 is arranged in the chamber 2 via a mounting seat 2 19; a connecting plate 20 is fixed to the transmission shaft 2 of the adjustment motor 2; a slot 21 is provided in the chamber 1 corresponding to the connecting plate; the connecting plate is fixed in the slot by the cooperation of the upper shell 1 and the lower shell 1. A symmetrical limiting plate 22 is provided at the corresponding position of the chamber 2 and the mounting seat 2; a positioning plate 23 is provided on the top of the mounting seat 2; and a limiting slot 1 24 is provided in the chamber 2 to limit the positioning plate 2. Shell 1 formed by upper shell 1 and lower shell 1 is provided with a cylindrical rotating shaft 25 at a position corresponding to shell 2 formed by upper shell 2 and lower shell 2; shell 2 is provided with a rotating cavity 26 corresponding to the rotating shaft; the rotating cavity is arranged in chamber 2; the connecting plate is arranged in the rotating cavity; and the card slot is arranged inside the rotating shaft.

[0027] To better illustrate the technical solution of this application, the aircraft power drive device of this application is applied to a quadcopter. In this embodiment, the nose is set as the front end, and the tail is set as the rear end. The terms front and rear are for convenience only and do not limit the technical solution.

[0028] Under normal operation, that is, the first regulating mechanism and the second regulating mechanism are not working, the quadcopter using the aircraft power drive device is controlled in the same manner as other aircraft on the market, and will not be described in detail.

[0029] Fly forward or backward (e.g. Figure 6 (as shown): The aircraft's main controller controls adjustment motor 1, which drives the connecting bracket to adjust the front wing to face forward and the rear wing to face backward. During forward flight, the front wing provides forward traction, while the rear wing also provides forward traction. When the aircraft flies backward, the rear wing also provides backward traction, while the front wing also provides backward traction.

[0030] Vertically pointing up, down, or hovering: The aircraft's main controller controls motor 1, which drives the connecting brackets to synchronously adjust the front and rear wings to point upward or downward. Regardless of whether the wings are pointing up or down, they provide upward traction or downward thrust. Figure 7 Only the upward position is shown.

[0031] When flying to the left or right: the aircraft's main controller controls the adjustment motor 1, which drives the connecting bracket to adjust the front and rear wings to face upward or downward synchronously. Figure 8 As shown, when the wings are facing upward, the first adjustment mechanism is rotated 90 degrees by adjusting motor 2; the front and rear ends of the left wing are adjusted to the left; the front and rear ends of the right wing are adjusted to the right; when flying to the left, the left wing is set to provide traction to the left, and the right wing is set to provide traction to the left. When flying to the right, the right wing is set to provide traction to the right, and the left wing is set to provide traction to the right. If there is enough space, when flying to the left, the right wing can also be adjusted to the left; when flying to the right, the left wing can also be adjusted to the right.

[0032] When encountering turbulence or performing a flip, fine-tune the wing angle by adjusting Motor 2, ensuring the aircraft always maintains optimal stability. Adjusting the angle of Motor 2 allows for flips forward, backward, left, and right. Compared to existing technologies that rely on speed differences between the wing drive motors, this system offers substantial improvements in both control effectiveness and functionality. Functional features of aircraft power drive device:

[0033] 1. When used on a manned drone, the fuselage can remain horizontal and motionless during forward, backward, left, and right flight. Direction of travel is altered by changing the orientation and deflection angle of the wings, and simultaneously by changing the direction of the wind blades' traction. This solves the problem of traditional aircraft using the entire aircraft to change direction of movement. The advantage is that the fuselage remains horizontal during flight or in the event of turbulence, without noticeable oscillation.

[0034] 2. During flight, the fuselage does not need to tilt left or right, front or back, greatly reducing the large area of ​​the fuselage facing the wind. This structure can reduce wind resistance when facing the wind from the side, making the flight more stable and sensitive. When hovering, regardless of the wind blowing from the front, back, left or right, the second adjustment structure will adjust the wing angle in real time according to the data fed back by the main controller to balance the aircraft and ensure the fuselage is stable.

[0035] 3. When applied to drone photography, the real-time fine-tuning of the four wing angles through the second adjustment structure can keep the fuselage stable and reduce the shaking of the camera, and can replace the original three-axis gimbal.

[0036] 4. The horizontal movement of the fuselage during driving reduces the large surface area of ​​the fuselage facing the wind, thereby improving flight efficiency and being more energy-efficient. Since the four wings can provide traction in the same direction at the same time, the flight time or load-bearing capacity can be increased.

[0037] 5. More special stunt functions have been added to the model aircraft and drones. (1) They can fly horizontally and vertically. (2) By changing the direction of the wings, they can perform forward, backward, left, and right crane demonstrations. (3) When performing forward, backward, left, and right crane demonstrations, the aircraft can also be made to fly upside down by changing the direction of the wing's traction force.

[0038] 6. When used on a humanoid aircraft, the main controller will adjust the angle of the wings in real time according to the detected environmental data, so that various stunts such as forward, backward, left, right, sideways flying and rolling can be performed.

[0039] The above-mentioned embodiment is only a preferred embodiment of the present invention, but the present embodiment is not limited by the above-mentioned embodiment. Any other changes, modifications, replacements, combinations, and simplifications made without departing from the spirit and principles of the present invention should be equivalent replacement methods and fall within the scope of protection of the present invention.

Claims

1. An aircraft power drive device, comprising a wing composed of a fan blade (1) and a drive motor (2); the drive motor is electrically connected to a main controller of the aircraft; and is characterized in that: The invention also includes a first adjustment mechanism (3) and a second adjustment mechanism (4); the wing is connected to the first adjustment mechanism via a connecting bracket (5); the first adjustment mechanism is used to adjust the wing to switch between the three states of upward, forward, and downward; the first adjustment mechanism is connected to the second adjustment mechanism; the second adjustment mechanism is used to adjust the angle of the first adjustment mechanism around the axis with the central axis as the axis; the first adjustment mechanism and the second adjustment mechanism are respectively electrically connected to the main controller of the aircraft.

2. The aircraft power drive device according to claim 1, characterized in that: The first adjustment mechanism includes an upper shell (6), a lower shell (7) and an adjustment motor (8); the upper shell and the lower shell are fixedly connected in an opening and disassembly manner; a chamber (9) for accommodating the adjustment motor is provided in the space formed by the upper shell and the lower shell; the adjustment motor is installed in the chamber through a mounting seat (10); a transmission shaft (11) of the adjustment motor is fixedly connected to one side of the connecting bracket; and the other side of the connecting bracket is connected to a rotating shaft (12) provided on the mounting seat.

3. The aircraft power drive device according to claim 2, characterized in that: A symmetrical positioning plate (13) is provided on the mounting seat; a limiting plate (14) is provided in the chamber to cooperate with the positioning plate.

4. The aircraft power drive device according to claim 3, characterized in that: The second adjustment mechanism includes an upper shell 2 (15), a lower shell 2 (16) and an adjustment motor 2 (17); the upper shell 2 and the lower shell 2 are fixedly connected in an opening and disassembly manner; a chamber 2 (18) for accommodating the adjustment motor 2 is provided in the space formed by the upper shell 2 and the lower shell 2; the adjustment motor 2 is arranged in the chamber 2 through a mounting seat 2 (19); a connecting plate (20) is fixed on the transmission shaft 2 of the adjustment motor 2; a slot (21) is provided in the chamber 1 corresponding to the connecting plate; the connecting plate is fixed in the slot through the cooperation of the upper shell 1 and the lower shell 1.

5. The aircraft power drive device according to claim 4, characterized in that: A symmetrical limiting plate 2 (22) is provided at the corresponding position of the chamber 2 and the mounting seat 2; a positioning plate 2 (23) is provided on the top of the mounting seat 2; and a limiting groove 1 (24) for limiting the positioning plate 2 is provided in the chamber 2.

6. The aircraft power drive device according to claim 5, characterized in that: Shell 1 formed by upper shell 1 and lower shell 1 is provided with a cylindrical rotating shaft (25) at a position corresponding to shell 2 formed by upper shell 2 and lower shell 2; shell 2 is provided with a rotating cavity (26) corresponding to the rotating shaft; the rotating cavity is arranged in chamber 2; the connecting plate is arranged in the rotating cavity; and the card slot is arranged inside the rotating shaft.

7. The aircraft power drive device according to any one of claims 1 to 6, characterized in that: The wing is fixedly connected to the connecting bracket via the mounting seat three (27).

8. The aircraft power drive device according to claim 7, characterized in that: It also includes a protective cover (28); a second limiting groove (29) is provided at the central axis of the protective cover; and a limiting block (30) is provided below the mounting seat 3 and is matched with the second limiting groove.

9. The aircraft power drive device according to claim 8, characterized in that: The limiting groove is triangular; the limiting block is triangular.

10. The aircraft power drive device according to claim 9, characterized in that: The limiting groove is provided with an arc groove (31) at the vertex of the triangle, and an inwardly raised arc protrusion (32) is provided between the two vertices of the triangle; the limiting block is provided with an arc limiting column (33) corresponding to the arc groove, and an inwardly recessed arc surface (34) corresponding to the arc protrusion.

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