Aircraft power drive

Abstract

The utility model discloses an aircraft power drive arrangement, comprising the wing that fan blade and drive motor constitute, drive motor and aircraft's host computer electric connection, still include first adjusting mechanism and second adjusting mechanism, the wing is connected with first adjusting mechanism through the connecting support, first adjusting mechanism is used for adjusting the wing and switches among three states of going up, going forward, going down, first adjusting mechanism links to each other with second adjusting mechanism, and second adjusting mechanism is used for angle adjustment with first adjusting mechanism around the shaft as the axis with the central shaft as the axis, first adjusting mechanism and second adjusting mechanism electric connection with aircraft's host computer respectively, through first adjusting mechanism and second adjusting mechanism to the wing adjustment, promote the security of product's simultaneously, also promoted operability and interesting nature.

Description

Technical Field

[0001] This utility model relates to the field of aircraft power drive, and in particular to an aircraft power drive device. Background Technology

[0002] Aircraft is a general term encompassing drones, manned aircraft, toy airplanes, etc. Currently, aircraft are mainly categorized into single-wing, biplane, triplane, and quadplane types. Single-wing aircraft are typically located on the top or upper part of the main body; biplane aircraft have wings on both sides of the main body; triplane aircraft have wings on both sides and the tail; and quadplane aircraft have two wings arranged in pairs on both sides of the main body. Each wing includes blades and a drive motor. The motor is controlled by the aircraft's main controller to adjust its speed, thereby adjusting flight speed and attitude.

[0003] In existing technologies, once the wings are connected to the main body of the aircraft, 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 skills are required to be very high, which in turn affects the aircraft's operability, fun and safety. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides an aircraft power drive device. To achieve the above objective, the technical solution adopted by this utility model is as follows: an aircraft power drive device, comprising a wing consisting of fan blades and a drive motor; the drive motor is electrically connected to the aircraft's main controller; it also includes a first adjustment mechanism and a second adjustment mechanism; the wing is connected to the first adjustment mechanism via a connecting bracket; the first adjustment mechanism is used to switch the wing 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 an axis with the central axis as the axis. The first and second adjustment mechanisms are respectively electrically connected to the aircraft's main controller.

[0005] Using the technical solution of this application, the first adjustment mechanism enables the wings to be adjusted to face upwards, forwards, or downwards; the second adjustment mechanism enables the wings to be adjusted to face left or right. The second adjustment mechanism also allows for fine-tuning of the wing angle during flight based on the flight environment, enabling better handling of complex flight conditions. This improves the safety of the aircraft while also enhancing its operability and enjoyment.

[0006] Further improvements include a first adjustment mechanism comprising an upper shell, a lower shell, and an adjustment motor. The upper shell and lower shell are fixedly connected by a detachable mechanism. A chamber is provided within the space formed by the upper and lower shells to accommodate the adjustment motor. The adjustment motor is mounted within the chamber via a mounting base. The drive shaft of the adjustment motor is fixedly connected to one side of a connecting bracket. The other side of the connecting bracket is connected to a rotating shaft mounted on the mounting base. The cooperation of the drive shaft and the rotating shaft allows the wing to quickly switch between upward, forward, and supersonic states.

[0007] Further improvements include a symmetrical positioning plate on the mounting base and a limiting plate inside the chamber that mates with the positioning plate. The mate between the positioning plate and the limiting plate reinforces the adjustment motor.

[0008] Further improvements include a second adjustment mechanism comprising an upper shell, a lower shell, and an adjustment motor. The upper and lower shells are fixedly connected by a detachable mechanism. A chamber is provided within the space formed by the upper and lower shells to accommodate the adjustment motor. The adjustment motor is mounted within the chamber via a mounting base. A connecting plate is fixed to the drive shaft of the adjustment motor. A slot is provided within the chamber corresponding to the connecting plate. The connecting plate is fixed within the slot through the cooperation of the upper and lower shells. This method of using a connecting plate and slot improves the stability of the aircraft's power drive system during rotation.

[0009] Further improvements include symmetrical limiting plates 2 corresponding to the second chamber and the second mounting base; a positioning plate 2 is provided on the top of the second mounting base; and a limiting groove 1 is provided inside the second chamber to limit the positioning plate 2. The cooperation between the positioning plate 2 and the limiting groove 1 provides a secondary fixing function for the second adjusting motor.

[0010] Further improvements include a cylindrical rotating shaft on the outer shell 1 formed by the upper shell 1 and lower shell 1, corresponding to the outer shell 2 formed by the upper shell 2 and lower shell 2; a rotating cavity corresponding to the rotating shaft on the outer shell 2; the rotating cavity being located within the cavity 2; a connecting plate being located within the rotating cavity; and a slot being located inside the rotating shaft. This design ensures that the aircraft's power drive unit rotates while also enhancing the product's aesthetics.

[0011] Further improvements include a wing that is securely connected to the connecting bracket via mounting base three. Mounting base three ensures a robust connection and stability during flight.

[0012] Further improvements include a protective shield; a second limiting groove is provided at the central axis of the protective shield; and a limiting block that mates with the second limiting groove is provided below the mounting base three. The cooperation between the second limiting groove and the limiting block ensures the stability of the protective shield during flight.

[0013] Further improvements include a triangular limiting groove and a triangular limiting block. The stability of the protective cover connection is enhanced by the stability of the triangle.

[0014] Further improvements include an arc-shaped groove at the apex of the triangle and an inwardly bulging arc-shaped protrusion between the two apexes of the triangle; the limiting block has an arc-shaped limiting post corresponding to the arc-shaped groove and an inwardly concave arc-shaped surface corresponding to the arc-shaped protrusion. This design adds two more layers of protection to the stability of the protective cover. Attached Figure Description

[0015] Figure 1 It is a 3D view of the aircraft's power drive system with the wings facing forward.

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

[0017] Figure 3 It is a three-dimensional view with the wings pointing upwards and the first adjustment mechanism deflected 90 degrees relative to the second adjustment mechanism.

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

[0019] Figure 5 yes Figure 2 A magnified view of a portion of the image.

[0020] Figure 6 Reference for aircraft that apply aircraft propulsion devices to existing technology Figure 1 .

[0021] Figure 7 Reference for aircraft that apply aircraft propulsion devices to existing technology Figure 2 .

[0022] Figure 8 Reference for aircraft that apply aircraft propulsion devices to existing technology Figure 3 . Detailed Implementation

[0023] The preferred embodiments of this utility model will be 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 composed 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 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 switch the wing 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 central axis. The wing is fixedly connected to the connecting bracket via a mounting base 3 27. It also includes a protective cover 28; a limiting groove 29 is provided at the central axis of the protective cover; a limiting block 30 that cooperates with the limiting groove 2 is provided below the mounting base 3. The limiting groove is triangular; the limiting block is triangular. The limiting groove has an arc-shaped groove 31 at the vertex of the triangle, and an inwardly raised arc-shaped protrusion 32 between the two vertices of the triangle; the limiting block has an arc-shaped limiting post 33 corresponding to the arc-shaped groove, and an inwardly recessed arc-shaped surface 34 corresponding to the arc-shaped protrusion.

[0025] 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 by a detachable mechanism. In this application, screws and screw holes are used for fixing, but other detachable fixing methods such as clips and slots can also be used. The space formed by the upper shell and the lower shell has a chamber 9 for accommodating the adjustment motor. The adjustment motor is installed in the chamber through a mounting base 10. The drive shaft 11 of the adjustment motor is fixedly connected to one side of a connecting bracket. The other side of the connecting bracket is connected to a rotating shaft 12 set on the mounting base. The mounting base has symmetrical positioning plates 13. The chamber has a limiting plate 14 that cooperates with the positioning plates.

[0026] The second adjustment mechanism includes an upper shell 15, a lower shell 16, and an adjustment motor 17. The upper shell and lower shell are fixedly connected by a detachable mechanism. In this application, screws and screw holes are used for fixing, but other detachable fixing methods such as clips and slots can also be used. A chamber 18 for accommodating the adjustment motor 17 is provided in the space formed by the upper and lower shells. The adjustment motor 17 is mounted in the chamber 17 via a mounting base 19. A connecting plate 20 is fixed to the drive shaft 2 of the adjustment motor 17. A slot 21 is provided in the chamber 17 corresponding to the connecting plate. The connecting plate is fixed in the slot by the cooperation of the upper and lower shells. Symmetrical limiting plates 22 are provided in the chamber 17 corresponding to the mounting base 27. A positioning plate 23 is provided on the top of the mounting base 27. A limiting groove 24 for limiting the positioning plate 27 is provided in the chamber 17. The outer shell 1 formed by the upper shell 1 and the lower shell 1 has a cylindrical rotating shaft 25 at a position corresponding to the outer shell 2 formed by the upper shell 2 and the lower shell 2; the outer shell 2 has a rotating cavity 26 corresponding to the rotating shaft; the rotating cavity is located inside the cavity 2; the connecting plate is located inside the rotating cavity; and the slot is located inside the rotating shaft.

[0027] To better illustrate the technical solution of this application, the aircraft power drive device of this application is described using a quadcopter. In this embodiment, the nose is designated as the front end and the tail as the rear end. The front and rear designations are for illustrative purposes only and do not limit the technical solution.

[0028] Under normal operation, the first and second adjustment mechanisms are not in operation. At this time, the quadcopter, powered by the aircraft's own propulsion system, operates in the same way as other aircraft on the market, and will not be described further.

[0029] Flying forward or backward (e.g.) Figure 6 (As shown): The main controller of the aircraft controls the first adjustment motor, which drives the connecting bracket to adjust the front wing to face forward and the rear wing to face backward. When flying forward, the front wing provides forward traction, and the rear wing simultaneously provides forward traction. When the aircraft flies backward, the rear wing provides backward traction, and the front wing simultaneously provides backward traction.

[0030] Vertical upward, downward, or hovering: The main controller of the aircraft controls the adjustment motor one, which drives the connecting bracket to synchronously adjust the front and rear wings to point upward or downward. Regardless of whether the wings are pointing upward or downward, they can provide either upward traction or downward thrust. Figure 7 Only the upward-facing state is shown.

[0031] When flying to the left or right: The main controller of the aircraft controls the adjustment motor one, which drives the connecting bracket to synchronously adjust the front and rear wings to face upwards or downwards. For example... Figure 8 As shown, when the wings are pointing upwards, the first adjustment mechanism is rotated 90 degrees by adjusting motor two; the left front and rear wings are adjusted to face left; the right front and rear wings are adjusted to face 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. Provided there is sufficient space, when flying to the left, the right wing can also be adjusted to face left; when flying to the right, the left wing can also be adjusted to face right.

[0032] When encountering turbulence or performing a roll: Fine-tuning the wing angle by adjusting motor two ensures the aircraft remains in optimal stability. Adjusting the angle of motor two allows for forward, backward, left, and right rolls. Compared to existing technologies that rely on the speed difference of the wing's drive motors for deflection, this represents a substantial improvement in both control effectiveness and functional expansion.

[0033] 1. Functional characteristics of aircraft propulsion systems:

[0034] When used on manned drones, the aircraft can remain level during forward, backward, left, and right flight. The direction of travel is changed by altering the orientation and yaw angle of the wings, as well as the direction of the wind turbine's traction, thus overcoming the traditional method of using the entire aircraft to tilt to change direction. The advantage is that the aircraft remains level during flight or in turbulent airflow, preventing noticeable swaying.

[0035] 2. During flight, the fuselage does not need to tilt to the left, right, front, or back, greatly reducing the large area of ​​the fuselage facing the wind. This structure allows for lateral wind resistance, reducing speed and making flight more stable and agile. When hovering, regardless of wind blowing from the front, back, left, or right, the second adjustment structure will adjust the wing angle in real time based on data feedback from the main controller to balance the aircraft and ensure its stability.

[0036] 3. When applied to shooting drones, the real-time fine-tuning of the four wing angles through the second adjustment structure can keep the fuselage stable and reduce camera shake, thus replacing the three-axis gimbal.

[0037] 4. The horizontal movement of the fuselage during flight reduces the large area of ​​the fuselage facing the wind, thereby improving flight efficiency and energy saving. Since the four wings can provide traction in the same direction at the same time, the flight time or payload capacity can be increased.

[0038] 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 demonstration flights of cranes in the front, back, left, and right. (3) When performing demonstration flights of cranes in the front, back, left, and right, the aircraft can also fly backwards by changing the direction of the traction force of the wings.

[0039] 6. When used on a humanoid aircraft, the main controller will adjust the angle of the wings in real time based on the detected environmental data, which can enable various aerobatic performances such as forward, backward, left, right, and side-to-side vertical flight and rolls.

[0040] The above embodiments are merely preferred embodiments of this utility model, but this embodiment is not limited to the above embodiments. Any changes, modifications, substitutions, combinations, or simplifications made without departing from the spirit and principle of this utility model shall be considered equivalent substitutions and shall fall within the protection scope of this utility model.

Claims

1. An aircraft power drive device, comprising a wing consisting of fan blades (1) and a drive motor (2); the drive motor is electrically connected to the main controller of the aircraft; characterized in that: It 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 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 central axis; the first adjustment mechanism and the second adjustment mechanism are 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 by a detachable method; a chamber (9) is provided in the space formed by the upper shell and the lower shell to accommodate the adjustment motor; the adjustment motor is installed in the chamber through a mounting base (10); the drive shaft (11) of the adjustment motor 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 base.

3. The aircraft power drive device according to claim 2, characterized in that: The mounting base is provided with a symmetrical positioning plate (13); the chamber is provided with a limiting plate (14) that cooperates 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 (15), a lower shell (16), and an adjustment motor (17). The upper shell and the lower shell are fixedly connected by a detachable method. The space formed by the upper shell and the lower shell is provided with a chamber (18) for accommodating the adjustment motor. The adjustment motor is installed in the chamber through a mounting base (19). A connecting plate (20) is fixed on the drive shaft of the adjustment motor. A slot (21) is provided in the chamber corresponding to the connecting plate. The connecting plate is fixed in the slot by the cooperation of the upper shell and the lower shell.

5. The aircraft power drive device according to claim 4, characterized in that: The chamber 2 and the mounting base 2 are provided with symmetrical limiting plates 2 (22); the top of the mounting base 2 is provided with positioning plate 2 (23); the chamber 2 is provided with limiting groove 1 (24) to limit the positioning plate 2.

6. The aircraft power drive device according to claim 5, characterized in that: The outer shell 1 formed by the upper shell 1 and the lower shell 1 has a cylindrical rotating shaft (25) at the corresponding position of the outer shell 2 formed by the upper shell 2 and the lower shell 2; the outer shell 2 has a rotating cavity (26) corresponding to the rotating shaft; the rotating cavity is located in the chamber 2; the connecting plate is located in the rotating cavity; and the slot is located 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 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 limiting groove 2 (29) is provided at the central axis of the protective cover; and a limiting block (30) that cooperates with the limiting groove 2 is provided below the mounting base 3.

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 has an arc-shaped groove (31) at the vertex of the triangle, and an inwardly raised arc-shaped protrusion (32) between the two vertices of the triangle; the limiting block has an arc-shaped limiting post (33) corresponding to the arc-shaped groove, and an inwardly recessed arc-shaped surface (34) corresponding to the arc-shaped protrusion.

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