Aircraft tilting mechanism

Abstract

The utility model relates to the technical field of aircraft, and disclose a kind of aircraft tilting mechanism, comprising: wing fuselage mechanism, through the wing fuselage mechanism control nacelle mechanism tilting, control the flight direction of aircraft;Tilting mechanism, the tilting mechanism is arranged in wing fuselage mechanism, another end protrudes the wing fuselage mechanism and nacelle mechanism connection, for controlling nacelle mechanism occurs tilting, when nacelle mechanism occurs tilting, the flight state of aircraft changes;Transmission mechanism, the transmission mechanism is connected with the tilting mechanism transmission, simultaneously with the transmission mechanism along the axial direction power conversion of wing fuselage mechanism along radial direction power of wing fuselage mechanism, further control the tilting of wing fuselage mechanism.Lightweight, compact structure, low cost and high reliability, large torque and other advantages, solve the problem that control signal needs multiple conversion, control complex, structure heavy.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to an aircraft tilting mechanism. Background Technology

[0002] With the development of drone technology, tiltrotor drones, with their unique configuration, exhibit significant advantages such as high flight efficiency, low noise, strong payload capacity, high cruising speed, and long range, and are gradually becoming a research hotspot in the drone field both domestically and internationally. They possess the flight characteristics of both fixed-wing aircraft and helicopters, do not require stringent takeoff and landing site requirements, and can achieve the high-efficiency flight capabilities of fixed-wing aircraft.

[0003] Conventional worm gear tilting mechanisms typically use a stepper motor and planetary reducer as the tilting power source. However, traditional small servos cannot meet the travel requirements of more than 360° due to the physical limitations of potentiometer stops. Servos with a travel of more than 360 degrees can only rotate continuously and cannot stay at a specific angle. An encoder is required to control the stepper motor, and the control signal needs to be converted multiple times, making the control complex. At the same time, this method results in a large mechanical structure weight, which reduces the payload capacity of the UAV.

[0004] Therefore, we propose an aircraft tilting mechanism to solve the above problems. Utility Model Content

[0005] (a) Technical problems to be solved To address the shortcomings of existing technologies, this invention provides an aircraft tilting mechanism that is lightweight, compact, low-cost, highly reliable, and has high torque. It solves the problems of multiple control signal conversions, complex control, and heavy structure.

[0006] (II) Technical Solution To achieve the aforementioned goals of lightweight design, compact structure, low cost, high reliability, and high torque, this utility model provides the following technical solution: an aircraft tilting mechanism, comprising: The wing-fuselage mechanism controls the tilting of the nacelle mechanism, thereby controlling the flight direction of the aircraft. A tilting mechanism is installed inside the wing-fuselage structure, with one end extending out of the wing-fuselage structure and connecting to the nacelle mechanism. It is used to control the tilting of the nacelle mechanism. When the nacelle mechanism tilts, the flight state of the aircraft changes. A transmission mechanism is connected to the tilting mechanism, and converts the power of the transmission mechanism along the axial direction of the wing and fuselage mechanism into the power along the radial direction of the wing and fuselage mechanism, thereby controlling the tilting of the nacelle mechanism. A drive mechanism, which serves as a tilting power source and is connected to the transmission mechanism, is used to control the rotation of the transmission mechanism and further control the tilting of the nacelle through the tilting mechanism.

[0007] As a further optimization of this utility model: the wing-fuselage mechanism includes connecting pieces on both sides, which are fixedly connected by multiple connecting rods, and the connecting pieces are also provided with mounting holes.

[0008] As a further optimization of this utility model: the tilting mechanism includes a tilting nacelle connecting device, a worm gear limiting bearing, and a turbine. One end of the turbine is fixedly connected to the mounting hole of the connecting plate through the worm gear limiting bearing, and the other end is fixedly connected to the tilting nacelle connecting device. The other end of the tilting nacelle connecting device passes through the mounting hole of the connecting plate and connects to the nacelle mechanism. As a further optimization of this utility model: the transmission mechanism includes a worm bearing connecting device and a worm, one end of the worm bearing connecting device is connected to the worm, and the other end is connected to the drive mechanism, the other end of the worm meshes with the worm gear for transmission, and the worm limit bearing is used to limit the worm and worm wheel at both fixed ends.

[0009] As a further optimization of this utility model: the drive mechanism includes a magnetic encoder servo and a servo connection device, one side of the servo connection device is connected to the output shaft of the magnetic encoder servo, and the other side is connected to the worm bearing connection device.

[0010] As a further optimization of this utility model: a fixing bearing device is also provided in the connecting pieces on both sides, the fixing bearing device being used to fix the worm gear.

[0011] As a further optimization of this utility model, the connecting pieces on both sides are also provided with weight-reducing holes to reduce the weight of the tilting mechanism itself.

[0012] As a further optimization of this utility model: the reduction ratio of the turbine to the worm gear is 1:10, which has good self-locking ability. The worm gear drives the nacelle to rotate 90 degrees, and the magnetic encoder servo needs to drive the worm wheel to rotate 900 degrees. The measured torque gain can also be increased to more than 9.5 times.

[0013] As a further optimization of this utility model: the magnetic coded servo is also equipped with a multi-turn counter, which is used to calculate the number of rotations of the output shaft of the magnetic coded servo, so as to determine the rotation angle of the output shaft of the magnetic coded servo, and further calculate the rotation angle of the worm and the turbine, and determine the tilt angle.

[0014] As a further optimization of this utility model: the magnetic coded servo motor is model DS9180, which is highly responsive, has a long stroke, zero blind zone, and is compatible with remote control systems such as Futaba, JR, SANWA, and Hitec.

[0015] (III) Beneficial Effects Compared with the prior art, the present invention provides an aircraft tilting mechanism, which has the following advantages: 1. The tilting mechanism of this aircraft achieves higher precision and reliability through a worm gear mechanism with a reduction ratio of 1:10. At the same time, it utilizes the advantages of the worm gear itself to give the nacelle a certain self-locking capability. 2. The aircraft's tilting mechanism, by using a magnetic encoder instead of a potentiometer and in conjunction with a multi-turn counter, can break through the 360° rotation limit, making it lighter and cheaper. At the same time, it does not require an additional encoder to convert the control signal; the flight controller directly outputs a PWM signal to the servo, making control simpler. Compared with traditional servos, the magnetically encoded servo can rotate more than 360 degrees and can stay at a specified angle. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a schematic diagram of the exploded structure of this utility model; Figure 3 This is a schematic diagram of the second angle explosion structure of this utility model.

[0017] In the diagram: 1. Magnetic coded servo; 2. Servo connecting device; 3. Worm bearing connecting device; 4. Fixed bearing device; 5. Worm; 6. Wing, fuselage, and mainframe mechanism; 7. Tilting nacelle connecting device; 8. Worm limit bearing; 9. Worm wheel. Detailed Implementation

[0018] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0019] Please see Figure 1-3An aircraft tilting mechanism includes: a wing-fuselage mechanism for controlling the flight direction of the aircraft by tilting the wing-fuselage mechanism; a tilting mechanism disposed within the wing-fuselage mechanism, with one end extending out of the wing-fuselage mechanism and connected to a nacelle mechanism, for controlling the tilting of the wing-fuselage mechanism, thereby changing the flight state of the aircraft when the wing-fuselage mechanism tilts; a transmission mechanism connected to the tilting mechanism for converting the axial power of the transmission mechanism along the wing-fuselage mechanism into radial power along the wing-fuselage mechanism, thereby controlling the tilting of the nacelle mechanism; and a drive mechanism connected to the transmission mechanism as a tilting power source for controlling the rotation of the transmission mechanism, thereby further controlling the tilting of the nacelle through the tilting mechanism.

[0020] The wing-fuselage mechanism includes connecting plates 6 on both sides, which are fixedly connected by multiple connecting rods. The connecting plates 6 also have mounting holes. The tilting mechanism includes a tilting nacelle connecting device 7, a worm gear limiting bearing 8, and a turbine 9. One end of the turbine 9 is fixedly connected to the mounting hole of the connecting plate 6 via the worm gear limiting bearing 8, and the other end is fixedly connected to the tilting nacelle connecting device 7. The other end of the tilting nacelle connecting device 7 passes through the mounting hole of the connecting plate 6 and connects to the nacelle mechanism. The transmission mechanism includes a worm gear bearing connecting device 3 and a worm 5. One end of the worm gear bearing connecting device 3 is connected to the worm 5, and the other end is connected to the drive mechanism. The other end of the worm 5 meshes with the turbine 9 for transmission. The worm gear limiting bearing 8 serves to limit the movement of the worm 5 and the worm wheel 9 at their fixed ends. The drive mechanism includes a magnetically encoded servo motor 1 and a servo motor connecting device 2. One side of the servo motor connecting device 2 is connected to the output shaft of the magnetically encoded servo motor 1, and the other side is connected to the worm gear bearing connecting device 3.

[0021] The connecting plates 6 on both sides are also equipped with fixed bearing devices 4, which are used to fix the worm gear 5. Lightening holes are also provided on the connecting plates 6 on both sides to reduce the weight of the tilting mechanism itself. The reduction ratio between the worm wheel 9 and the worm gear 5 is 1:10, providing good self-locking capability. For the worm gear 5 to drive the nacelle mechanism to rotate 90 degrees, the magnetic encoder servo 1 needs to drive the worm wheel 9 to rotate 900 degrees. The measured torque gain can be increased to over 9.5 times. The magnetic encoder servo 1 also contains a multi-turn counter, which is used to calculate the number of rotations of the output shaft of the magnetic encoder servo 1, facilitating the determination of the rotation angle of the output shaft. This allows for the calculation of the rotation angles of the worm gear 5 and worm wheel 9, thus determining the tilt angle. The magnetic encoder servo 1 is model DS9180, which is highly responsive, has a large stroke, zero blind zone, and is compatible with remote control systems such as Futaba, JR, SANWA, and Hitec.

[0022] Working principle: This device is connected to the wing of the tiltrotor UAV through the wing-fuselage mechanism. The worm 5 is connected to the output end of the magnetic encoder servo 1. When the magnetic encoder servo 1 is started, the output shaft drives the worm 5 to rotate. The tilt nacelle connecting device 7 and the worm limit bearing 8 are driven to rotate, thereby realizing the rotation of the moving parts of the entire tilt mechanism. For example, when controlling the nacelle to tilt 90 degrees, the flight controller sends a 1000us PWM signal, and the magnetic coded servo 1 is in the initial position, with the nacelle mechanism vertical; the flight controller sends a 1500us PWM signal, and the magnetic coded servo 1 rotates 450 degrees, with the nacelle mechanism tilting 45 degrees; the flight controller sends a 200us PWM signal, and the magnetic coded servo rotates to 900 degrees, with the nacelle mechanism tilting 90 degrees.

[0023] Although embodiments of the present invention 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 to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An aircraft tilting mechanism, characterized in that, include: The wing-fuselage mechanism controls the tilting of the nacelle mechanism, thereby controlling the flight direction of the aircraft. A tilting mechanism is installed inside the wing-fuselage structure, with one end extending out of the wing-fuselage structure and connecting to the nacelle mechanism. It is used to control the tilting of the nacelle mechanism. When the nacelle mechanism tilts, the flight state of the aircraft changes. A transmission mechanism is connected to the tilting mechanism, and converts the power of the transmission mechanism along the axial direction of the wing and fuselage mechanism into the power along the radial direction of the wing and fuselage mechanism, thereby controlling the tilting of the nacelle mechanism. A drive mechanism, which serves as a tilting power source and is connected to the transmission mechanism, is used to control the rotation of the transmission mechanism and further control the tilting of the nacelle mechanism through the tilting mechanism.

2. The aircraft tilting mechanism according to claim 1, characterized in that: The wing-fuselage mechanism includes connecting pieces (6) on both sides, which are fixedly connected by multiple connecting rods. The connecting pieces (6) are also provided with mounting holes.

3. The aircraft tilting mechanism according to claim 1, characterized in that: The tilting mechanism includes a tilting nacelle connecting device (7), a worm gear limiting bearing (8), and a turbine (9). One end of the turbine (9) is fixedly connected to the mounting hole of the connecting piece (6) through the worm gear limiting bearing (8), and the other end is fixedly connected to the tilting nacelle connecting device (7). The other end of the tilting nacelle connecting device (7) passes through the mounting hole of the connecting piece (6) and is connected to the nacelle mechanism.

4. The aircraft tilting mechanism according to claim 3, characterized in that: The transmission mechanism includes a worm bearing connecting device (3) and a worm (5). One end of the worm bearing connecting device (3) is connected to the worm (5), and the other end is connected to the drive mechanism. The other end of the worm (5) meshes with the turbine (9) for transmission.

5. The aircraft tilting mechanism according to claim 4, characterized in that: The drive mechanism includes a magnetic encoder servo (1) and a servo connection device (2). One side of the servo connection device (2) is connected to the output shaft of the magnetic encoder servo (1), and the other side is connected to the worm bearing connection device (3).

6. The aircraft tilting mechanism according to claim 4, characterized in that: The connecting pieces (6) on both sides are also provided with a fixed bearing device (4), which is used to fix the worm (5).

7. The aircraft tilting mechanism according to claim 2, characterized in that: The connecting pieces (6) on both sides are also provided with light-reducing holes.

8. The aircraft tilting mechanism according to claim 4, characterized in that: The reduction ratio between the turbine (9) and the worm (5) is 1:

10.

9. The aircraft tilting mechanism according to claim 5, characterized in that: The magnetic encoder servo (1) is also equipped with a multi-turn counter, which is used to calculate the number of rotations of the output shaft of the magnetic encoder servo (1).

10. The aircraft tilting mechanism according to claim 5, characterized in that: The magnetic coded servo motor (1) is model DS9180.

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