Tilting device with balancing function

Abstract

The utility model relates to the technical field of aircraft power, and discloses a tilting device with a balancing function, which comprises a plurality of power unit extension rods, a reduction gear set, a moment balancing device and a brushless motor, the power unit extension rods are rigidly connected with a fuselage, a propeller is fixedly mounted at the output end of the brushless motor, and the moment balancing device is arranged on the fuselage. The large gear penetrates through the first left bearing and the first right bearing through carbon tubes to be connected with the motor base, the servo motor and the metal shaft, and the small gear is fixedly connected with the output end of the servo motor through the metal shaft. According to the tilting device with the balancing function, the speed reduction straight gear set is used, the torque during self-locking and driving of the servo motor is amplified, meanwhile, the servo motor controls the tilting angle of the motor more accurately, the gear is directly arranged at the tail end of the carbon rod and is convenient to disassemble, meanwhile, the shaft distance does not need to be adjusted, gears with different reduction ratios can be directly replaced, and the cost is reduced. Therefore, the design is flexible and changeable, and meanwhile, different power units used by different aircrafts can be adapted.

Description

Technical Field

[0001] This utility model relates to the field of aircraft propulsion technology, specifically a tilting device with a trim function. Background Technology

[0002] The rotor tilting mechanism is a core component for improving the performance of EVTOL aircraft. It helps to expand the flight envelope of EVTOL aircraft and improve the utilization rate of electrical energy. This invention proposes a rotor tilting mechanism at the front of the fuselage of an electric tiltrotor. This mechanism achieves self-locking through a reduction gear and a servo motor. It also uses a transmission ratio greater than 1 combined with a trim mechanism using a coil spring to amplify the torque of the servo motor and improve its control accuracy. This greatly improves the controllability and safety of the aircraft during the tilting process. The entire mechanism is easy to maintain and provides a safe and reliable technical guarantee for EVTOL aircraft.

[0003] In the prior art, there is a rotor tilting mechanism (CN205396540U) for the wingtip of an electric tiltrotor aircraft. The tilting mechanism is installed at the wingtip and the aircraft propeller is driven by a worm gear. The aircraft propeller tilting mechanism (CN205396540U) is installed at the wingtip and uses a gear transmission without a reduction ratio. The mechanical structure is placed under the motor and the servo motor rotates synchronously with the motor.

[0004] Existing technologies typically mount the tilting mechanism at the wingtip, significantly increasing the wing root bending moment and wing structural weight. This also generates substantial airflow interference at the wingtip, potentially causing wing vibration during high-speed flight. Furthermore, the self-locking mechanism relies either on a purely mechanical structure or solely on a servo motor. Mechanical self-locking without a servo motor makes precise control of the motor's tilt angle difficult, while using only a servo motor places excessively high demands on the motor, making it unsuitable for large aircraft. Additionally, the existing tilting power unit is positioned below the motor, resulting in a large distance between the motor's rotation center and center of gravity, significantly increasing the drag torque during tilting. Utility Model Content

[0005] In view of the shortcomings of the prior art, this utility model provides a tilting device with balancing function to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a tilting device with balancing function, comprising:

[0007] Multiple power unit extension rods, which are rigidly connected to the fuselage;

[0008] The system includes a reduction gear set, a torque balancing device, and a brushless motor. A propeller is fixedly installed at the output end of the brushless motor. The reduction gear set includes a large gear and a small gear.

[0009] Left bearing 1, right bearing 1 and motor base, the large gear is connected to the motor base through carbon tubes passing through left bearing 1 and right bearing 1;

[0010] A servo motor and a metal shaft, wherein the pinion is fixedly connected to the output end of the servo motor via the metal shaft;

[0011] The left bearing is fixedly installed on the inner side of the left bearing housing, and the right bearing is fixed on the inner side of the right bearing housing.

[0012] The servo motor is fixed to the outside of the left and right bearing seats by two stamped metal plates and is secured by bolts.

[0013] Two mounting brackets are provided on the outside of the servo motor and are used to fix the left bearing and the right bearing.

[0014] The torque balancing device includes a large gear, a limit buckle, a coil spring, and a limit bar.

[0015] Preferably, the limiting buckle is used to fix the coil spring, one end of the coil spring is locked with the gear integrated limiting protrusion, and the other end is locked with the left bearing integrated limiting bar.

[0016] Preferably, the brushless motor is indirectly powered by the servo motor through a reduction gear set, and the brushless motor and the torque balancing device are located on both sides of the power unit extension rod.

[0017] Preferably, the reduction gear set, torque balancing device, and brushless motor are connected together with the saddle clamp, power unit extension rod, and aircraft as a whole via the left and right bearing seats.

[0018] Preferably, both the large gear and the small gear are spur gears, and they have the same module.

[0019] Preferably, the power unit extension rod has a hole drilled at its end for bolts to pass through and fix it to the saddle clip, and the power unit extension rod is located far from the propeller's mounting position on the brushless motor when the brushless motor rotates to a horizontal position.

[0020] Preferably, the servo motor controls the maximum rotation angle of the motor mount to be 90 degrees after being reduced in speed by a reduction gear set.

[0021] Preferably, the carbon tube is prevented from sliding left and right by a large gear on the motor mount.

[0022] Compared with the prior art, the beneficial effects of this utility model are:

[0023] 1. This tilting device with balancing function uses a reduction spur gear set, which amplifies the torque of the servo motor during self-locking and driving, and at the same time makes the servo motor's control of the tilting angle of the motor more precise. The gears are directly arranged at the end of the carbon rod, which is easy to disassemble. At the same time, there is no need to adjust the wheelbase, and different reduction ratio gears can be directly replaced to meet the requirements of flexible design and adaptability to different power groups used in different aircraft.

[0024] 2. This tilting device with balancing function connects the left and right parts in series through a carbon rod. The motor and gear simultaneously serve to fix the carbon rod, while the carbon rod passes through the bearing, which further reduces the resistance during rotation.

[0025] 3. The tilting device with trim function is connected to the aircraft via an extension rod connected to the fuselage. The lift and mass distribution of the aircraft can be adjusted by selecting different lengths of the extension rod. At the same time, the tilting device is far away from the aerodynamic components of the aircraft and hardly interferes with the original structure of the aircraft, thus preserving the design performance of the aircraft and reducing the structural weight.

[0026] 4. The tilting device with balancing function uses a coil spring balancing device, and the torque provided by the balancing device is always less than or equal to the torque generated by the motor's gravity. When the motor rotates, the coil spring counteracts the torque generated by the motor's gravity. When turning from vertical to horizontal, the existing torque can naturally drive the motor to tilt. When turning from horizontal to vertical, the servo motor needs to generate torque, but at this time the torque generated by the coil spring has a promoting effect on the servo motor's torque, which is less than the self-locking torque required without the balancing device. Similarly, when self-locking, it is less than the self-locking torque required without the balancing device. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the left and right bearing housings of this utility model;

[0028] Figure 2 This is a three-dimensional schematic diagram of the overall structure of this utility model;

[0029] Figure 3 This is a front view schematic diagram of the structure of this utility model;

[0030] Figure 4 This is a side view of the structure of this utility model.

[0031] In the diagram: 1. Reduction gear set; 2. Large gear; 3. Left bearing 1; 4. Right bearing 1; 5. Motor mount; 6. Small gear; 7. Left bearing mount; 8. Right bearing mount; 9. Stamped metal sheet; 10. Saddle clip; 11. Power unit extension rod; 12. Torque balancing device; 13. Limit buckle; 14. Coil spring; 15. Limit bar; 16. Brushless motor; 17. Servo motor; 18. Propeller; 19. Limit protrusion. Detailed Implementation

[0032] 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.

[0033] Example:

[0034] Please refer to Figures 1-4.

[0035] A tilting device with balancing function, comprising:

[0036] Multiple power unit extension rods 11 are rigidly connected to the fuselage;

[0037] The gear set 1 includes a reduction gear set 1, a torque balancing device 12, and a brushless motor 16. A propeller 18 is fixedly installed at the output end of the brushless motor 16. The reduction gear set 1 includes a large gear 2 and a small gear 6.

[0038] Left bearing 3, right bearing 4 and motor base 5, large gear 2 is connected to motor base 5 by passing through left bearing 3 and right bearing 4 via carbon tubes;

[0039] The servo motor 17 and the metal shaft, and the pinion 6 are fixedly connected to the output end of the servo motor 17 through the metal shaft;

[0040] Left bearing 3 is fixedly installed on the inside of the left bearing housing, and right bearing 4 is fixed on the inside of the right bearing housing 8.

[0041] The servo motor 17 is fixed to the outside of the left bearing housing 7 and the right bearing housing 8 by two stamped metal pieces 9 and is fixed by bolts;

[0042] Two saddle clamps 10 are located on the outside of the servo motor 17 and are used to fix the left bearing 3 and the right bearing 4.

[0043] The torque balancing device 12 includes a large gear 2, a limit buckle 13, a coil spring 14, and a limit bar 15;

[0044] The limit buckle 13 is used to fix the coil spring 14. One end of the coil spring 14 is locked to the gear integrated limit protrusion 19, and the other end is locked to the limit rod 15 of the left bearing 3 body.

[0045] The brushless motor 16 is indirectly powered by the servo motor 17 through the reduction gear set 1. The brushless motor 16 and the torque balancing device 12 are located on both sides of the power set extension rod 11.

[0046] The reduction gear set 1 and torque balancing device 12, and the brushless motor 16 are connected together with the saddle clamp 10, the power group extension rod 11 and the entire aircraft through the left bearing seat 7, the right bearing seat 8 and the saddle clamp 10, the power group extension rod 11 and the aircraft as a whole.

[0047] The power unit extension rod 11 has a hole drilled at the end and a bolt is used to pass through and fix it to the saddle clip 10. At the same time, the power unit extension rod 11 is far away from the propeller 18 on the brushless motor 16 when the brushless motor 16 is rotated to the horizontal position.

[0048] After being reduced in speed by the reduction gear set 1, the servo motor 17 controls the maximum rotation angle of the motor base 5 to be 90 degrees.

[0049] The carbon tube is prevented from sliding left and right by the large gear 2 of the motor mount 5.

[0050] The tilting device uses a reduction spur gear set, which amplifies the torque of the servo motor 17 during self-locking and driving, and at the same time makes the servo motor 17 more precise in controlling the tilting angle of the motor. The gear is directly arranged at the end of the carbon rod, which is easy to disassemble. At the same time, there is no need to adjust the wheelbase, and different reduction ratio gears can be directly replaced to meet the requirements of flexible design and adaptability to different power groups used by different aircraft.

[0051] The tilting device uses a coil spring 14 for balancing, and the torque provided by the balancing device is always less than or equal to the torque generated by the motor's gravity. When the motor rotates, the coil spring 14 counteracts the torque generated by the motor's gravity. When turning from vertical to horizontal, the existing torque can naturally drive the motor to tilt. When turning from horizontal to vertical, the servo motor 17 needs to generate torque, but at this time the torque generated by the coil spring 14 has a promoting effect on the force of the servo motor 17, which is less than the self-locking torque required without the balancing device. Similarly, when self-locking, it is less than the self-locking torque required without the balancing device.

[0052] The tilting device places the tilting power unit and the motor on both sides, allowing the motor to be placed closer to the center of rotation, further reducing the motor's gravitational torque and further reducing the torque required by the servo motor 17.

[0053] The tilting device connects the left and right parts in series via a carbon rod. The motor and gears simultaneously serve to fix the carbon rod, while the carbon rod passes through a bearing, which further reduces the resistance during rotation.

[0054] The coil spring 14 retainer on the large gear 2 is fixed by screws, and the appropriate coil spring 14 can be quickly replaced for different motors;

[0055] The device is connected to the aircraft via an extension rod attached to the fuselage. The lift and mass distribution of the aircraft can be adjusted by selecting different extension rod lengths. At the same time, the tilting device is far away from the aerodynamic components of the aircraft and hardly interferes with the original structure of the aircraft, thus preserving the design performance of the aircraft and reducing the structural weight.

[0056] In this embodiment: the servo motor 17 and the brushless motor 16 are existing structures, and the control circuit can be implemented by those skilled in the art through simple programming. They are common knowledge in the art and are only used without modification. Therefore, the control method and circuit connection will not be described in detail.

[0057] Working principle: This tilting device uses a reduction spur gear set, which amplifies the torque of the servo motor 17 during self-locking and driving, and at the same time makes the servo motor 17 more precise in controlling the tilting angle of the motor. The gear is directly arranged at the end of the carbon rod, which is easy to disassemble. At the same time, there is no need to adjust the wheelbase, and different reduction ratio gears can be directly replaced to meet the requirements of flexible design and adaptability to different power groups used by different aircraft.

[0058] 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. A tilting device with balancing function, characterized in that, include: Multiple power unit extension rods (11) are rigidly connected to the fuselage; The gear set (1), torque balancing device (12) and brushless motor (16) are provided. A propeller (18) is fixedly installed at the output end of the brushless motor (16). The gear set (1) includes a large gear (2) and a small gear (6). Left bearing 1 (3), right bearing 1 (4) and motor base (5), the large gear (2) is connected to the motor base (5) through a carbon tube passing through the left bearing 1 (3) and the right bearing 1 (4); The servo motor (17) and the metal shaft, wherein the pinion (6) is fixedly connected to the output end of the servo motor (17) via the metal shaft; The left bearing (3) is fixedly installed on the inner side of the left bearing seat, and the right bearing (4) is fixed on the inner side of the right bearing seat (8). The servo motor (17) is fixed to the outside of the left bearing seat (7) and the right bearing seat (8) by two stamped metal pieces (9) and is fixed by bolts; Two saddle clips (10) are provided on the outside of the servo motor (17) and are used to fix the left bearing (3) and the right bearing (4). The torque balancing device (12) includes a large gear (2), a limit buckle (13), a coil spring (14), and a limit bar (15).

2. A tilting device with balancing function according to claim 1, characterized in that: The limiting buckle (13) is used to fix the coil spring (14). One end of the coil spring (14) is locked to the gear integral limiting protrusion (19), and the other end is locked to the limiting rod (15) of the main left bearing (3).

3. A tilting device with balancing function according to claim 1, characterized in that: The brushless motor (16) is indirectly powered by the servo motor (17) through the reduction gear set (1). The brushless motor (16) and the torque balancing device (12) are located on both sides of the power group extension rod (11).

4. A tilting device with balancing function according to claim 1, characterized in that: The reduction gear set (1) and torque balancing device (12), the brushless motor (16) are connected together with the riding card (10), the power group extension rod (11) and the aircraft as a whole through the left bearing seat (7) and the right bearing seat (8).

5. A tilting device with balancing function according to claim 1, characterized in that: Both the large gear (2) and the small gear (6) are spur gears, and they have the same module.

6. A tilting device with balancing function according to claim 1, characterized in that: The power unit extension rod (11) has a hole drilled at the end and is fixed to the saddle clip (10) by bolts. At the same time, the power unit extension rod (11) is far from the mounting position of the propeller (18) on the brushless motor (16) when the brushless motor (16) is rotated to the horizontal position.

7. A tilting device with balancing function according to claim 1, characterized in that: The servo motor (17) is decelerated by the reduction gear set (1) and the maximum rotation angle of the motor base (5) is 90 degrees.

8. A tilting device with balancing function according to claim 1, characterized in that: The carbon tube is prevented from sliding left and right by the large gear (2) of the motor mount (5).

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