Aircraft tilting mechanism
By combining a lightweight worm gear mechanism with a magnetic coded servo motor, the problems of complex control and heavy weight of the worm gear tilting mechanism are solved, enabling lightweight and efficient flight of the UAV.
Patent Information
- Application Number
- CN202511455533.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-13
- Publication Date
- 2025-11-18
AI Technical Summary
Existing worm gear tilting mechanisms suffer from problems such as complex control signals, large structural weight, and inability to meet the 360° travel requirement, resulting in a decrease in the payload capacity of drones.
It adopts a lightweight worm gear mechanism, combined with a magnetic encoder servo and a multi-turn counter, to achieve 360° continuous rotation and stop at a specified angle. By using the worm gear reduction ratio of 1:10 and the magnetic encoder servo, the control signal is simplified and the weight of the mechanical structure is reduced.
It achieves lightweight, compact, low-cost, and highly reliable tilting mechanisms for aircraft, with simple control and high torque, thereby improving the payload capacity and flight efficiency of UAVs.
Smart Images
Figure CN120964100A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the field of aircraft technology, in particular to an aircraft tilting mechanism. BACKGROUND
[0002] With the development of unmanned aerial vehicle technology, tilt-rotor unmanned aerial vehicles have shown significant advantages such as high flight efficiency, low noise, strong load capacity, fast cruising speed, and long range due to their unique configuration, and are gradually becoming a research hotspot in the field of unmanned aerial vehicles at home and abroad. It has the flight characteristics of both fixed-wing aircraft and helicopter, and does not require strict take-off and landing site requirements, and can achieve efficient flight of fixed-wing aircraft.
[0003] The conventional worm gear tilting mechanism generally uses a stepping motor plus a planetary reducer as a tilting power source. Since the traditional small rudder cannot meet the more than 360° stroke requirement due to the physical blockage of the potentiometer, the rudder with more than 360° stroke can only rotate continuously and cannot stay at a specific angle. An encoder is needed to control the stepping motor, the control signal needs to be converted multiple times, the control is complex, and at the same time, the mechanical structure is heavy, which reduces the load capacity of the unmanned aerial vehicle.
[0004] Therefore, we propose an aircraft tilting mechanism to solve the above problems. SUMMARY
[0005] (I) Technical problems solved In view of the shortcomings of the prior art, the present application provides an aircraft tilting mechanism, which has the advantages of lightweight, compact structure, low cost, high reliability, and large torque, and solves the problems of multiple conversion of control signals, complex control, and large structure weight.
[0006] (II) Technical solutions In order to achieve the above-mentioned lightweight, compact structure, low cost, high reliability, and large torque, the present application provides the following technical solutions: an aircraft tilting mechanism, comprising: A wing-body mechanism for controlling the tilting of a nacelle mechanism and controlling the flight direction of the aircraft; A tilting mechanism arranged in the wing-body mechanism and connected to the nacelle mechanism at the other end for controlling the tilting of the nacelle mechanism, so that the flight state of the aircraft changes when the nacelle mechanism tilts; A transmission mechanism in transmission connection with the tilting mechanism, which converts the axial power of the transmission mechanism along the wing-body mechanism into radial power along the radial direction of the wing-body mechanism, thereby controlling the tilting of the nacelle mechanism; A driving mechanism is connected with the transmission mechanism as a tilting power source for controlling the rotation of the transmission mechanism, and further controls the tilting of the nacelle through the tilting mechanism.
[0007] As a further optimization of the application, the wing-body mechanism comprises two side connection plates, which are fixedly connected by a plurality of connecting rods, and mounting holes are further provided on the connection plates.
[0008] As a further optimization of the application, the tilting mechanism comprises a tilting nacelle connecting device, a worm limiting bearing, and a turbine, one end of the turbine is fixedly connected with the mounting hole of the connection plate through the worm limiting bearing, the other end is fixedly connected with the tilting nacelle connecting device, and the other end of the tilting nacelle connecting device passes through the mounting hole of the connection plate and is connected with the nacelle mechanism. As a further optimization of the application, the transmission mechanism comprises a worm bearing connecting device and a worm, one end of the worm bearing connecting device is connected with the worm, and the other end is connected with the driving mechanism, the other end of the worm is engaged with the turbine for transmission, and the worm limiting bearing is used for limiting the two ends of the worm and the worm gear.
[0009] As a further optimization of the application, the driving mechanism comprises a magnetic encoder steering engine and a steering engine connecting device, one side of the steering engine connecting device is connected with the output shaft of the magnetic encoder steering engine, and the other side is connected with the worm bearing connecting device.
[0010] As a further optimization of the application, a fixed bearing device is further provided in the two connection plates, which is used for fixing the worm.
[0011] As a further optimization of the application, lightening holes are further provided on the two connection plates for reducing the weight of the tilting mechanism.
[0012] As a further optimization of the application, the reduction ratio of the turbine to the worm is 1:10, which has good self-locking ability, the worm drives the nacelle to rotate 90 degrees, the magnetic encoder steering engine drives the worm gear to rotate 900 degrees, and the actual measured torque gain can be increased by more than 9.5 times.
[0013] As a further optimization of the application, a plurality of turn counters are further provided in the magnetic encoder steering engine, which are used for counting the number of turns of the output shaft of the magnetic encoder steering engine, facilitating the judgment of the rotation angle of the output shaft of the magnetic encoder steering engine, further calculating the rotation angle of the worm and the turbine, and judging the tilting angle.
[0014] As a further optimization of the application: the model of the magnetic encoder steering engine is DS9180, which is sensitive, has large stroke, zero blind area, and is compatible with Futaba, JR, SANWA, Hitec and other remote control systems.
[0015] (Three) beneficial effects Compared with the prior art, the application provides a flight vehicle tilting mechanism, which has the following beneficial effects: 1. The flight vehicle tilting mechanism realizes higher precision and reliability through the speed reduction ratio 1:10 worm gear mechanism, and utilizes the advantages of the worm gear itself to enable the short nacelle to have certain self-locking ability. 2. The flight vehicle tilting mechanism uses a magnetic encoder to replace a potentiometer, cooperates with a multi-turn counter to break through the 360° rotation limit, is more lightweight and has lower cost, does not need to additionally increase an encoder conversion control signal, directly outputs a PWM signal of a flight control to a steering engine, and is more simple in control. BRIEF DESCRIPTION OF DRAWINGS
[0016] Fig. 1 is a schematic diagram of the overall structure of the application; Fig. 2 is a schematic diagram of the explosion structure of the application; Fig. 3 is a schematic diagram of the explosion structure of the second angle of the application.
[0017] In the figure: 1, magnetic encoder steering engine; 2, steering engine connecting device; 3, worm shaft bearing connecting device; 4, fixed bearing device; 5, worm shaft; 6, wing body mechanism; 7, tilting short nacelle connecting device; 8, worm shaft limiting bearing; 9, worm gear. DETAILED DESCRIPTION
[0018] The technical solutions in the embodiments of the application will be described clearly and completely below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the application.
[0019] Please refer to Figs. 1-3The application relates to a kind of aircraft tilting mechanism, comprising: wing-body mechanism, the flight direction of aircraft is controlled by tilting wing-body mechanism;Tilting mechanism, tilting mechanism is arranged in wing-body mechanism, and the other end of tilting mechanism is connected with nacelle mechanism outside wing-body mechanism, for controlling wing-body mechanism to tilt, when wing-body mechanism tilts, the flight state of aircraft changes;Transmission mechanism, transmission mechanism is drivingly connected with tilting mechanism, and simultaneously, transmission mechanism is converted into power along the radial direction of wing-body mechanism along the axial direction of wing-body mechanism, and then controls the tilting of nacelle mechanism;Driving mechanism, driving mechanism is connected with transmission mechanism as tilting power source, for controlling transmission mechanism to rotate, further controls the tilting of nacelle through tilting mechanism.
[0020] The wing-body mechanism comprises two side connection plates 6, the two side connection plates 6 are fixedly connected through a plurality of connecting rods, and mounting holes are further arranged on the connection plates 6. The tilting mechanism comprises a tilting nacelle connecting device 7, a worm limiting bearing 8 and a turbine 9, one end of the turbine 9 is fixedly connected with the mounting hole of the connection plate 6 through the worm limiting bearing 8, the other end is fixedly connected with the tilting nacelle connecting device 7, and the other end of the tilting nacelle connecting device 7 penetrates through the mounting hole of the connection plate 6 and is connected with the nacelle mechanism. The transmission mechanism comprises a worm bearing connecting device 3 and a worm 5, one end of the worm bearing connecting device 3 is connected with the worm 5, and the other end is connected with the driving mechanism, the other end of the worm 5 is engaged with the turbine 9 in transmission, and the worm limiting bearing 8 is used for limiting the two ends of the worm 5 and the turbine 9. The driving mechanism comprises a magnetic encoder steering engine 1 and a steering engine connecting device 2, one side of the steering engine connecting device 2 is connected with the output shaft of the magnetic encoder steering engine 1, and the other side is connected with the worm bearing connecting device 3.
[0021] The two side connection plates 6 are further provided with a fixed bearing device 4, and the fixed bearing device 4 is used for fixing the worm 5. The two side connection plates 6 are further provided with lightening holes for reducing the weight of the tilting mechanism. The speed reduction ratio of the turbine 9 and the worm 5 is 1:10, has good self-locking ability, the worm 5 drives the nacelle mechanism to rotate by 90 degrees, the magnetic encoder steering engine 1 drives the turbine 9 to rotate by 900 degrees, and the actual measured torque gain can be increased by more than 9.5 times. A multi-turn counter is further arranged in the magnetic encoder steering engine 1, the multi-turn counter is used for counting the number of turns of the output shaft of the magnetic encoder steering engine 1, the rotation angle of the output shaft of the magnetic encoder steering engine 1 is conveniently judged, the rotation angles of the worm 5 and the turbine 9 can be further calculated, and the tilting angle is judged. The model of the magnetic encoder steering engine 1 is DS9180, the model has sensitive response, large stroke and zero blind area, and is compatible with Futaba, JR, SANWA, Hitec and other remote control systems.
[0022] Working principle: the device is connected with the wing body mechanism and the wing of the tilt rotor unmanned aerial vehicle, the worm 5 is connected with the output end of the magnetic code steering engine 1, so that when the magnetic code steering engine 1 starts, the output shaft drives the worm 5 part to rotate, the tilt nacelle connecting device 7 and the worm limiting bearing 8 are driven to rotate, and then the driven realizes the rotation of the whole tilt mechanism movable part; For example, when controlling the short nacelle to tilt 90 degrees, the flight control sends a 1000us PWM signal, the magnetic code steering engine 1 is at the initial position, and the short nacelle mechanism is vertical; the flight control sends a 1500us PWM signal, the magnetic code steering engine 1 rotates 450 degrees, and the short nacelle mechanism tilts 45 degrees; the flight control sends a 200us PWM signal, the magnetic code steering engine rotates to 900 degrees, and the short nacelle mechanism tilts 90 degrees.
[0023] Although the embodiments of the present application have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to the embodiments without departing from the principles and spirits of the present application, and the scope of the present application 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.