aircraft

Abstract

The utility model discloses an aircraft, including wing and aircraft main body, drive motor and main controller electric connection of installation in aircraft main body, wing is connected with aircraft main body through connecting arm, second adjusting device is fixed in connecting arm, first adjusting device and second adjusting device are connected, first adjusting device is connected with wing through connecting support, first adjusting device is used for adjusting wing and switches between three states of going up, going forward, going down, second adjusting device can angle regulation to first adjusting device around center axle any angle, first adjusting device and second adjusting device electric connection with main controller respectively. The technical scheme is through first adjusting device and realizes the adjustment to the flight attitude. Through second adjusting device, the wing is adjusted to 90 degrees, realizes the adjustment of direction and the slight adjustment under any angle, can better cope with the airflow and the bad environment, has promoted the interestingness, the security and the controllability of product.

Description

Technical Field

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

[0002] An aircraft is a general term encompassing drones, manned aircraft, toy airplanes, etc. The flight of an aircraft is powered by its wings, which include blades and drive motors. Currently, aircraft are mainly classified as single-wing, biplane, triplane, and quadplane. Single-wing aircraft are typically located on the top or upper part of the aircraft's body; biplane aircraft have wings on both sides of the 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 body. The wings consist of blades and drive motors, which are controlled by the aircraft's main controller to adjust their speed, thereby adjusting flight speed and attitude. The position and orientation of the wings cannot be adjusted, which means that aircraft are essentially unable to fly if they encounter turbulence or are in adverse environments.

[0003] Designing an aircraft that can enhance the enjoyment of flying while adapting to sudden turbulence or harsh flight environments is the research topic the applicant is dedicated to. Utility Model Content

[0004] In order to overcome the shortcomings of the existing technology, this utility model provides an aircraft.

[0005] To achieve the above objectives, the technical solution adopted by this utility model is as follows: an aircraft, comprising a wing composed of fan blades and a drive motor, and an aircraft body; the drive motor is electrically connected to a main controller installed in the aircraft body; the wing is connected to the aircraft body via a connecting arm; the connecting arm is provided with a first adjustment device and a second adjustment device; the second adjustment device is fixed inside the connecting arm; the first adjustment device and the second adjustment device are connected; the first adjustment device is connected to the wing via a connecting bracket; the first adjustment device is used to switch the wing between three states: upward, forward, and downward; the second adjustment device can adjust the angle of the first adjustment device around its central axis at any angle; the first adjustment device and the second adjustment device are respectively electrically connected to the main controller.

[0006] By adopting the technical solution of this application, the first adjustment device can switch between multiple states of the wing, such as pointing upwards, forwards, and downwards, thereby adjusting the flight attitude. The second adjustment device can adjust the wing direction by 90 degrees and make minor adjustments at any angle, which can better cope with airflow and harsh environments, and improve the product's fun, safety, and maneuverability.

[0007] The power unit comprises wings, connecting arms, a first adjustment device, and a second adjustment device; there are three power units. Symmetrical balance beams are located on both sides of the aircraft body, with two power units fixedly connected to the balance beams via connecting arms; the balance beams and connecting arms are integrally formed. A third power unit is fixed to the tail of the aircraft body via a connecting arm. Balance beams are located on both sides of the aircraft body; wings are positioned at both ends of the balance beams. The balance beams ensure that the center of gravity of the aircraft body does not change significantly when the wing position or angle is adjusted. This plays a crucial role in flight stability. This technical solution, while meeting the basic operational requirements of a triplane aircraft, adds the functions of flight state switching and wing angle fine-tuning, improving stability in windy and turbulent environments.

[0008] The aircraft's main body is equipped with a landing gear and flexible support feet at its bottom; the bottom surface of the flexible support feet is flat; the landing gear is located below the balance beam; the flexible support feet are located behind the landing gear; the flexible support feet and the two landing gear support feet form an isosceles triangle. This design ensures the stability of the aircraft during takeoff and landing.

[0009] The power unit comprises wings, connecting arms, a first adjustment device, and a second adjustment device; there are four power units; the four power units are symmetrically arranged on both sides of the aircraft body in pairs via connecting frames; the two connecting arms on the same side are integrally formed. This technical solution, while meeting the basic operational requirements of a quadcopter, adds the functions of flight state switching and wing angle fine-tuning, improving stability in windy and turbulent environments.

[0010] The main body of the aircraft includes a base plate, a top plate, support columns, a main controller, a transmitter and receiver plate, an antenna, a motion camera, a microphone, a horn, a lidar, and a battery. The main controller is installed in the mounting chamber formed by the base plate, top plate, and support columns. The lidar is installed at the front end of the base plate; the transmitter and receiver plate is installed at the rear end of the base plate; the battery is installed on the top plate; the motion camera is angle-adjustably mounted at the front end of the top plate; the antenna is installed at the rear end of the top plate; the antenna is electrically connected to the transmitter and receiver plate; the microphone and horn are mounted on the top plate via flexible metal hoses; the main controller is electrically connected to the battery, lidar, motion camera, transmitter and receiver plate, microphone, and horn respectively. These components are directly fixed to the top and base plates, enabling the main body of the aircraft to experiment with and test new functions.

[0011] The base plate and top plate have several pre-installed mounting holes and slots for expansion, ensuring the functionality of the aircraft's main body can be expanded.

[0012] The first adjustment device includes a front shell, a rear shell, and an adjustment motor. The front shell and the rear shell are fixedly connected by a detachable mechanism. A chamber is provided in the space formed by the front shell and the rear shell to accommodate the adjustment motor. The adjustment motor is installed in 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. Under the action of the adjustment motor, the wing can quickly switch between three states: upward, forward, and downward, through the cooperation of the drive shaft and the rotating shaft.

[0013] The second adjustment device includes a front shell, a rear shell, and an adjustment motor. The front shell and the rear shell are fixedly connected by a detachable mechanism. A chamber is provided within the space formed by the front and rear 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 front and rear shells. The cooperation between the slot and the connecting plate ensures the strength of the connection and the stability during angle adjustment.

[0014] The outer shell 1, formed by the front shell 1 and the rear shell 1, has a cylindrical rotating shaft at a position corresponding to the outer shell 2, formed by the front shell 2 and the rear shell 2. The outer shell 2 has a rotating cavity corresponding to the rotating shaft. The rotating cavity is located inside the cavity 2. The connecting plate is located inside the rotating cavity. The slot is located inside the rotating shaft. The cooperation between the rotating shaft and the rotating cavity ensures smooth angle adjustment during flight and also improves the aesthetics of the product. Attached Figure Description

[0015] Figure 1 Exploded view of the power unit.

[0016] Figure 2 This is a perspective view of the aircraft with its wings facing forward, as described in Example 1.

[0017] Figure 3 This is a perspective view of the aircraft with its wings facing upwards, as described in Example 1.

[0018] Figure 4 This is a perspective view of the aircraft in Embodiment 1 with its wings facing left.

[0019] Figure 5 This is the three-dimensional representation of the aircraft in Example 2. Figure 1 .

[0020] Figure 6 This is the three-dimensional representation of the aircraft in Example 2. Figure 2 . Detailed Implementation

[0021] The preferred embodiments of this utility model will be further described in detail below with reference to the accompanying drawings.

[0022] like Figures 1 to 6 As shown, an aircraft includes a wing composed of a fan blade 1 and a drive motor 2, and an aircraft body. The drive motor is electrically connected to a main controller 3 installed inside the aircraft body. The wing is connected to the aircraft body via a connecting arm 4. The connecting arm is provided with a first adjustment device and a second adjustment device. The second adjustment device is fixed inside the connecting arm. The first adjustment device and the second adjustment device are connected. The first adjustment device is connected to the wing via a connecting bracket 5. The first adjustment device is used to switch the wing between three states: upward, forward, and downward. The second adjustment device can adjust the angle of the first adjustment device around its central axis at any angle. The first adjustment device and the second adjustment device are respectively electrically connected to the main controller.

[0023] The first adjustment device includes a front shell 22, a rear shell 23, and an adjustment motor 24. The front shell and the rear shell are fixedly connected by a detachable mechanism. A chamber 1 for accommodating the adjustment motor 1 is provided in the space formed by the front shell and the rear shell. The adjustment motor 1 is installed in the chamber 1 via a mounting base 1. The drive shaft 25 of the adjustment motor 1 is fixedly connected to one side of a connecting bracket. The other side of the connecting bracket is connected to a rotating shaft provided on the mounting base 1. The second adjustment device includes a front shell 26, a rear shell 27, and an adjustment motor 28. The front shell 2 and the rear shell 2 are fixedly connected by a detachable mechanism. A chamber 2 for accommodating the adjustment motor 2 is provided in the space formed by the front shell 2 and the rear shell 2. The adjustment motor 2 is installed in the chamber 2 via a mounting base 2. A connecting plate 29 is fixed on the drive shaft 2 of the adjustment motor 2. A slot 30 is provided in the chamber 1 corresponding to the connecting plate. The connecting plate is fixed in the slot by the cooperation of the front shell and the rear shell. The outer shell 1 formed by the front shell 1 and the rear shell 1 has a cylindrical rotating shaft at a position corresponding to the outer shell 2 formed by the front shell 2 and the rear shell 2; the outer shell 2 has a rotating cavity corresponding to the rotating shaft; the rotating cavity is located inside the chamber 2; the connecting plate is located inside the rotating cavity; and the slot is located inside the rotating shaft. Example

[0024] The aircraft is a triplane, specifically, the power unit consists of wings, connecting arms, a first adjustment device, and a second adjustment device; there are three power units. Symmetrical balance beams 6 are located on both sides of the aircraft body, and two power units are fixedly connected to the balance beams via connecting arms; the balance beams and connecting arms are integrally formed; the third power unit is fixed to the tail of the aircraft body via a connecting arm. The bottom of the aircraft body is equipped with landing gear 7 and elastic support feet 8; the bottom surface of the elastic support feet is flat; the landing gear is located below the balance beams; the elastic support feet are located behind the landing gear; the elastic support feet and the two landing gear support feet form an isosceles triangle. Example

[0025] like Figure 5 and Figure 6As shown, the aircraft is a quadcopter. The power unit consists of wings, connecting arms, a first adjustment device, and a second adjustment device. There are four power units; each power unit is symmetrically arranged on both sides of the aircraft body via connecting frames 9. The two connecting arms on the same side are integrally formed. The aircraft body includes a base plate 10, a top plate 11, a support column 12, a main controller, a transmitter and receiver plate 13, an antenna 13, a motion camera 15, a microphone 15, a horn 17, a lidar 18, and a battery 19. The main controller is installed in the mounting chamber formed by the base plate, top plate, and support column. The lidar is installed at the front end of the base plate; the transmitter and receiver plate is installed at the rear end of the base plate; the battery is installed on the top plate; the motion camera is angle-adjustably installed at the front end of the top plate; the antenna is installed at the rear end of the top plate; the antenna is electrically connected to the transmitter and receiver plate; the microphone and horn are installed on the top plate via flexible metal hoses; the main controller is electrically connected to the battery, lidar, motion camera, transmitter and receiver plate, microphone, and horn. Several mounting holes 20 and mounting slots 21 for expansion are pre-installed on the base plate and top plate. The aircraft in this application focuses more on a concept aircraft designed for the future, while the modified aircraft emphasizes more on the personalized customization of functions. This also facilitates the testing of various functional templates of the aircraft during the development process.

[0026] To better illustrate the technical solution of this application, the use of the aircraft of this application will be further explained.

[0027] The aircraft is connected to the player's remote control in the same way as existing connection methods on the market. The aircraft described in this application is essentially the same in basic function as common triplane and quadplane aircraft on the market.

[0028] The differences between this application and commercially available triplane and quadplane aircraft are as follows: During horizontal flight, adjusting motor one can adjust the front wing (default forward direction is considered forward) to face forward and the rear wing to face backward (please refer to [reference needed] for wing orientation). Figure 2 At this point, both the front and rear wings can generate forward thrust. When flying backward, the main control can switch the direction of the fan blade rotation to ensure that both the front and rear wings generate backward thrust. When flying to the left or right, first adjust the connecting bracket via motor one to change the wing's orientation from forward to upward (please refer to [reference] for wing orientation). Figure 3 Then, by adjusting motor two, rotate the left wing 90 degrees clockwise and the right wing 90 degrees counterclockwise to face right; when the aircraft is a triplane, rotate the rear wing 90 degrees clockwise to face left or counterclockwise to face right (please refer to the wing orientation guide). Figure 4After the wings are synchronized, when the aircraft needs to fly to the left, both the front and rear wings generate a traction force to the left; when the aircraft needs to fly to the right, both the front and rear wings generate a traction force to the right.

[0029] The greatest advantage of this application lies in the fact that during flight, aircraft often encounter turbulence or harsh environments caused by airflow. Therefore, by adjusting the wing angle through motor two, the aircraft can be kept in an optimal stable state at all times. These are the two biggest advantages of this application. Compared with the existing technology that uses the speed difference of the wing's drive motor for deflection, this represents a substantial change in both control effect and functional expansion.

[0030] 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 comprising a wing consisting of a fan blade (1) and a drive motor (2) and an aircraft body; the drive motor being electrically connected to a main controller (3) installed within the aircraft body; characterized in that: The wing is connected to the main body of the aircraft via a connecting arm (4); the connecting arm is equipped with a first adjustment device and a second adjustment device; the second adjustment device is fixed inside the connecting arm; the first adjustment device and the second adjustment device are connected; the first adjustment device is connected to the wing via a connecting bracket (5); the first adjustment device is used to adjust the wing to switch between three states: upward, forward, and downward; the second adjustment device can adjust the angle of the first adjustment device around the central axis at any angle; the wing, the connecting arm, the first adjustment device, and the second adjustment device constitute a power unit; the first adjustment device and the second adjustment device are electrically connected to the main controller respectively.

2. The aircraft according to claim 1, characterized in that: There are three power units; symmetrical balance beams (6) are provided on both sides of the main body of the aircraft. Two power units are fixedly connected to the balance beams through connecting arms; the balance beams and connecting arms are integrally formed; the other power unit is fixed to the tail of the main body of the aircraft through connecting arms.

3. The aircraft according to claim 2, characterized in that: The aircraft body is equipped with a landing gear (7) and an elastic support foot (8) at the bottom; the bottom surface of the elastic support foot is a plane; the landing gear is located below the balance beam; the elastic support foot is located behind the landing gear; the elastic support foot and the two landing support feet of the landing gear form an isosceles triangle.

4. The aircraft according to claim 1, characterized in that: There are four power units; the four power units are symmetrically arranged on both sides of the aircraft body through connecting frames (9); the two connecting arms on the same side are integrally formed.

5. The aircraft according to claim 4, characterized in that: The main body of the aircraft includes a base plate (10), a top plate (11), a support column (12), a main controller, a transmitter and receiver plate (13), an antenna (14), a motion camera (15), a microphone (16), a horn (17), a lidar (18), and a battery (19). The main controller is installed in the mounting chamber formed by the base plate, the top plate, and the support column. The lidar is installed at the front end of the base plate. The transmitter and receiver plate is installed at the rear end of the base plate. The battery is installed on the top plate. The motion camera is installed at the front end of the top plate with adjustable angle. The antenna is installed at the rear end of the top plate. The antenna is electrically connected to the transmitter and receiver plate. The microphone and horn are installed on the top plate through metal hoses. The main controller is electrically connected to the battery, lidar, motion camera, transmitter and receiver plate, microphone, and horn, respectively.

6. The aircraft according to claim 5, characterized in that: The bottom plate and top plate are pre-installed with several mounting holes (20) and mounting slots (21) for expansion.

7. The aircraft according to claim 3 or 6, characterized in that: The first adjustment device includes a front shell (22), a rear shell (23), and an adjustment motor (24); the front shell and the rear shell are fixedly connected by a detachable method; a chamber is provided in the space formed by the front shell and the rear shell to accommodate the adjustment motor; the adjustment motor is installed in the chamber through a mounting seat; the drive shaft (25) 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 provided on the mounting seat.

8. The aircraft according to claim 7, characterized in that: The second adjustment device includes a front shell (26), a rear shell (27), and an adjustment motor (28). The front shell and the rear shell are fixedly connected by a detachable method. The space formed by the front shell and the rear shell is provided with a chamber for accommodating the adjustment motor. The adjustment motor is installed in the chamber through a mounting seat. A connecting plate (29) is fixed on the drive shaft of the adjustment motor. A slot (30) is provided in the chamber corresponding to the connecting plate. The connecting plate is fixed in the slot by the cooperation of the front shell and the rear shell.

9. The aircraft according to claim 8, characterized in that: The outer shell 1 formed by the front shell 1 and the rear shell 1 has a cylindrical rotating shaft at a position corresponding to the outer shell 2 formed by the front shell 2 and the rear shell 2; the outer shell 2 has a rotating cavity corresponding to the rotating shaft; the rotating cavity is located inside the chamber 2; the connecting plate is located inside the rotating cavity; and the slot is located inside the rotating shaft.

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