Energy-saving disc type motor with modularized stator for unmanned aerial vehicle

Abstract

The invention discloses an unmanned aerial vehicle energy-saving disc type motor with a modularized stator, and relates to the technical field of unmanned aerial vehicle motors, the unmanned aerial vehicle energy-saving disc type motor comprises a motor shell, an electric control push rod is arranged on the inner side of the bottom of the motor shell, and an outer stator is arranged in the motor shell. The rotating speed of the unmanned aerial vehicle can be accurately controlled through vertical displacement of the inner stator, so that the unmanned aerial vehicle has a second set of rotating speed control scheme, the operation stability of the unmanned aerial vehicle is improved, in addition, when a pressure sensor detects abnormal vibration caused by blade damage or unbalanced rotating shaft, the equipment can actively finely adjust the electric control push rod, and the vibration of the unmanned aerial vehicle is reduced. The accurate position of the inner stator in the equipment is changed, the position change of the inner stator slightly affects the uniformity and torque pulsation of a magnetic field, and the adjustment can be used for actively counteracting part of vibration frequency caused by mechanical imbalance, so that the unmanned aerial vehicle can be prevented from falling off after a fault occurs and before landing maintenance. And the flight stability and safety can still be obviously improved.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of unmanned aerial vehicle motors, in particular to an energy-saving disc motor for unmanned aerial vehicles. BACKGROUND

[0002] As an intelligent device that has rapidly developed in recent years, an unmanned aerial vehicle has been widely applied in many fields such as aerial photography surveying and mapping, agricultural plant protection, logistics distribution, emergency rescue and power inspection, and the flight performance and safety thereof directly depend on the reliability and efficiency of a power system, wherein a motor as a core driving component of the unmanned aerial vehicle directly influences the endurance, control precision and running stability of the unmanned aerial vehicle.

[0003] At present, commonly used motors of unmanned aerial vehicles mainly include brush DC motors, brushless DC motors and disc motors, the disc motor is gradually popularized in small and medium-sized unmanned aerial vehicles due to the advantages of compact structure, small axial size and high power density, however, the existing disc motor still has the following technical limitations. The stator structure is single and has poor fault tolerance: the traditional disc motor adopts an integrated stator structure, the winding and the iron core are fixed as a whole, if local damage (such as winding short circuit, insulation aging, etc.) occurs in the stator, the entire motor is often disabled and cannot continue to work, thereby reducing the reliability of the system, and the entire motor needs to be disassembled for maintenance or replacement, thereby increasing the maintenance cost and prolonging the maintenance period.

[0004] The rotation speed control depends on an electronic speed controller (ESC), and the reliability is insufficient in extreme environments: when the unmanned aerial vehicle operates in extreme environments such as high temperature, high humidity and strong electromagnetic interference, the electronic speed controller and the control circuit thereof are prone to failure, thereby causing the rotation speed to be out of control or unstable, and affecting the flight safety. The existing scheme lacks mechanical or electromagnetic backup control means when the electric control system fails.

[0005] The vibration suppression capability is limited, and the stability is poor in a fault state: when the unmanned aerial vehicle is in a fault state such as blade damage, shaft bending or imbalance, the motor will produce abnormal vibration, the traditional motor lacks an online sensing and active vibration suppression mechanism, the vibration not only affects the flight quality, but also accelerates the damage of other components, and even causes the unmanned aerial vehicle to crash.

[0006] The emergency braking mechanism is lacking, and the risk of losing control is high: when the unmanned aerial vehicle loses control and flies towards people, sensitive facilities or restricted airspace, the existing motor can only be stopped by being powered off, but the rotor continues to rotate due to inertia after being powered off, and cannot be quickly braked, and the unmanned aerial vehicle may still cause impact or secondary accidents, and a kind of active and rapid emergency braking scheme is lacking.

[0007] Therefore, there is an urgent need for a high-reliability disc motor with modular design, redundancy control capability, active vibration suppression and fast emergency braking to improve the adaptability and safety of unmanned aerial vehicles in complex environments. The present application is proposed in this background, aiming to solve the above technical problems through structural innovation and function integration. SUMMARY

[0008] The present application aims to provide an energy-saving disc motor for unmanned aerial vehicles with a modular stator to solve the problems raised in the background.

[0009] To achieve the above-mentioned purpose, the present application provides the following technical solution: an energy-saving disc motor for unmanned aerial vehicles with a modular stator, comprising a motor housing, an electric control push rod is arranged on the inner side of the bottom of the motor housing, an outer stator is arranged in the interior of the motor housing, an inner stator is arranged on the inner ring of the outer stator, a rotor assembly is arranged on the top outer end of the outer stator and the inner stator, the rotor assembly comprises a rotor seat, magnets are annularly distributed on the bottom outer end of the rotor seat, a rotating shaft is arranged on the top outer end of the rotor seat, a centrifugal disc is arranged on the outer end of the rotating shaft, a tension spring is arranged in the interior of the centrifugal disc, a speed reduction block is arranged on the outer end of the tension spring, a guide seat is arranged on the top outer end of the motor housing, an electromagnet is arranged on the top bottom end of the guide seat, an emergency stop assembly is arranged on the inner side of the rotating shaft, and a return spring is arranged between the emergency stop assembly and the guide seat.

[0010] Further, the electric control push rod is fixedly connected with the inner stator, and the inner stator and the outer stator are concentrically distributed.

[0011] Further, the electric control push rod drives the inner stator to ascend and descend in the interior of the motor housing, and the rotor seat rotates through the outer stator and the inner stator.

[0012] Further, the speed reduction block is annularly distributed with four groups in the interior of the centrifugal disc, and the speed reduction block is elastically connected with the tension spring.

[0013] Further, the emergency stop assembly comprises a docking disc, a permanent magnet is arranged on the inner side of the bottom of the docking disc, a sliding seat is arranged on the outer end of the docking disc, a pressure spring is arranged in the interior of the sliding seat, a pressure sensor is arranged in the interior of the sliding seat, a fitting seat is arranged in the interior of the sliding seat, an armature is arranged on the top outer end of the docking disc, a first sliding groove is arranged at the joint of the docking disc, the guide seat and the return spring, a second sliding groove is arranged at the joint of the armature and the sliding seat.

[0014] Further, the docking disc is connected with the rotating shaft, and the docking disc is elastically connected with the guide seat through the return spring.

[0015] Further, the speed reduction block is electromagnetically attracted to the permanent magnet, and the armature is electromagnetically attracted to the electromagnet.

[0016] Further, the outer surface of the sliding seat is attached to the inner surface of the guide seat, and the outer surface of the attaching seat is attached to the inner surface of the guide seat.

[0017] Further, the attaching seat is elastically connected to the sliding seat through a pressure spring, and the end of the attaching seat away from the guide seat is attached to the pressure sensor.

[0018] Further, the reset spring slides through the first sliding groove, and the armature slides through the second sliding groove.

[0019] The application provides an unmanned aerial vehicle (UAV) energy-saving disc motor with a modular stator. 1. During the flight of the UAV, the inner stator is driven to move downward by the electric control push rod, so that the magnetic induction between the inner stator and the rotor seat changes, which allows the speed of the rotor seat to be adjusted. Since the UAV often operates in extreme environments, the electric control system is prone to failure in extreme environments. By displacing the inner stator up and down, the speed of the UAV can be accurately controlled, which allows the UAV to have a second speed control scheme, thereby improving the stability of the UAV operation. In addition, when the pressure sensor detects abnormal vibration caused by damaged blades or unbalanced shafts, the device can actively fine-tune the electric control push rod to change the precise position of the inner stator inside the device. Since the position change of the inner stator will slightly affect the uniformity of the magnetic field and the torque ripple, this adjustment can be used to actively offset part of the vibration frequency caused by mechanical imbalance, which allows the UAV to significantly improve flight stability and safety before landing and maintenance after failure. Since the outer stator and the inner stator are independent units that can be separately assembled, they are not a single iron core winding that is integrally formed in traditional motors, but each has an independent iron core, winding and insulation structure, which allows the structural design of the outer stator and the inner stator to modularize the stator. When a single stator is damaged, the other stator can still work, which further improves the stability of the device.

[0020] 2、The present application can make the inner stator not participate in the rotation of the rotor seat by driving the inner stator to quickly move down through the electric control push rod, at this time the rotor seat will quickly slow down, the rotor seat speed reduction will reduce the centrifugal force of the centrifugal disc, which makes the stretching spring pull back the speed reduction block, at the same time the electromagnet loses power and makes the return spring rebound, in the process of the return spring rebound, the abutment disc will be lowered through the displacement of the sliding seat in the guide seat, and after the abutment disc moves down, the permanent magnet will move down to the same height as the speed reduction block, which makes the speed reduction block and the permanent magnet realize electromagnetic adsorption to achieve the emergency stop of the rotating shaft, when the unmanned aerial vehicle uncontrollably flies towards the crowd due to failure or operation error, and the operator has judged that it is impossible to avoid collision through normal control, the emergency stop can be triggered to make the unmanned aerial vehicle fall in the unmanned area, and when inspecting high-voltage lines, chemical plants, data centers and other sensitive environments, if the unmanned aerial vehicle loses control and may collide with key equipment to cause a major accident, the power is immediately cut off to make it fall vertically, so as to minimize the damage, through the above design, the safety of the unmanned aerial vehicle operation can be greatly improved.

[0021] 3、In the process of the blade rotation, the abutment disc can be moved to the highest point through the electromagnetic iron power-on attraction of the armature, and the abutment disc can be moved to the bottom end through the electromagnetic iron power-off and the reset of the return spring, because the abutment disc is connected with the rotating shaft, when the unmanned aerial vehicle blade is damaged, or the rotating shaft is deformed due to the impact in the operation process of the unmanned aerial vehicle, the vibration at the high place of the rotating shaft will be greater than that at the low place, and the abutment disc can sense the vibration and transmit the vibration force to the sliding seat, when the sliding seat senses the vibration force, it can offset the vibration force by extruding the pressure spring, and when the pressure spring is extruded, the abutment seat extrudes the pressure sensor to sense the pressure, the equipment can judge whether the blade or the rotating shaft is damaged through the pressure sensing frequency of the pressure sensor, because the armature can be displaced in a small range through the second sliding groove, and the return spring can be displaced in a small range through the first sliding groove, so the two will not interfere with the vibration swing of the abutment disc. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 It is a whole three-dimensional structure schematic view of the energy-saving disc type motor for unmanned aerial vehicle with modular stator; Figure 2 It is an internal structure schematic view of the motor shell of the energy-saving disc type motor for unmanned aerial vehicle with modular stator; Figure 3 It is a structure schematic view of the rotor assembly of the energy-saving disc type motor for unmanned aerial vehicle with modular stator; Figure 4 It is a structure schematic view of the emergency stop assembly of the energy-saving disc type motor for unmanned aerial vehicle with modular stator; Figure 5 It is an internal structure schematic view of the guide seat of the energy-saving disc type motor for unmanned aerial vehicle with modular stator; Figure 6 Figure 1 is a schematic diagram of the structure of the inner stator of the energy-saving disc type motor for the unmanned aerial vehicle with modular stator according to the present application; Figure 7 Figure 2 is a schematic diagram of the overall cross-sectional structure of the energy-saving disc type motor for the unmanned aerial vehicle with modular stator according to the present application; Figure 8 Figure 3 is a schematic diagram of the overall cross-sectional structure of the energy-saving disc type motor for the unmanned aerial vehicle with modular stator according to the present application; Figure 9 Figure 4 is a schematic diagram of the structure of the inner stator of the energy-saving disc type motor for the unmanned aerial vehicle with modular stator according to the present application; Figure 7 Figure 5 is a schematic diagram of the enlarged structure at position A of the inner stator of the energy-saving disc type motor for the unmanned aerial vehicle with modular stator according to the present application; Figure 10 Figure 6 is a schematic diagram of the structure of the first sliding groove and the second sliding groove of the energy-saving disc type motor for the unmanned aerial vehicle with modular stator according to the present application.

[0023] In the figure: 1, motor housing; 2, electric control push rod; 3, outer stator; 4, inner stator; 5, rotor assembly; 501, rotor seat; 502, magnet; 503, rotating shaft; 504, centrifugal disc; 505, tension spring; 506, speed reduction block; 6, guide seat; 7, electromagnet; 8, emergency stop assembly; 801, docking disc; 802, permanent magnet; 803, sliding seat; 804, pressure spring; 805, pressure sensor; 806, fitting seat; 807, armature; 9, return spring; 10, first sliding groove; 11, second sliding groove. DETAILED DESCRIPTION

[0024] Referring to Figures 1 to 10 The present application provides a technical solution: an energy-saving disc type motor for unmanned aerial vehicle with modular stator, comprising a motor housing 1, an electric control push rod 2 is arranged on the inner side of the bottom of the motor housing 1, an outer stator 3 is arranged in the inner part of the motor housing 1, and an inner stator 4 is arranged in the inner circle of the outer stator 3, a rotor assembly 5 is arranged on the top outer end of the outer stator 3 and the inner stator 4, the rotor assembly 5 comprises a rotor seat 501, magnets 502 are annularly distributed on the bottom outer end of the rotor seat 501, and a rotating shaft 503 is arranged on the top outer end of the rotor seat 501, a centrifugal disc 504 is arranged on the outer end of the rotating shaft 503, a tension spring 505 is arranged in the inner part of the centrifugal disc 504, a speed reduction block 506 is arranged on the outer end of the tension spring 505, the electric control push rod 2 is fixedly connected with the inner stator 4, and the inner stator 4 and the outer stator 3 are concentrically distributed, the electric control push rod 2 drives the inner stator 4 to ascend and descend in the inner part of the motor housing 1, and the rotor seat 501 rotates through the outer stator 3 and the inner stator 4; The specific operation is as follows, after the device is installed in the unmanned aerial vehicle, the device needs to be powered on to connect with the power connector of the unmanned aerial vehicle to realize power on, and the fan of the unmanned aerial vehicle can be connected with the rotating shaft 503. During the use of the unmanned aerial vehicle, the device can supply power to the unmanned aerial vehicle. The outer stator 3 and the inner stator 4 are both wound with power coils (not shown in the figure). When the unmanned aerial vehicle passes the current in the winding of the outer stator 3 and the inner stator 4 in a certain order, a rotating magnetic field will be generated in the stator. The annular magnet 502 installed at the bottom of the rotor base 501 provides a permanent magnetic field. When the permanent magnetic field is attracted and repelled by the rotating magnetic field of the outer stator 3 and the inner stator 4, an electromagnetic torque will be generated. The torque will drive the rotor base 501 and the rotating shaft 503 rigidly connected thereto to start rotating, and then drive the unmanned aerial vehicle fan installed on the rotating shaft 503 to work, thereby realizing the flight of the unmanned aerial vehicle. During the flight of the unmanned aerial vehicle, the inner stator 4 is driven downward by the electric control push rod 2, so that the magnetic induction between the inner stator 4 and the rotor base 501 changes, which enables the speed of the rotor base 501 to be adjusted. Since the unmanned aerial vehicle often operates in extreme environments, the electric control system is prone to failure in extreme environments. By displacing the inner stator 4 upward and downward, the speed of the unmanned aerial vehicle can be accurately controlled, which enables the unmanned aerial vehicle to have a second speed control scheme, thereby improving the stability of the unmanned aerial vehicle operation. In addition, when the pressure sensor 805 detects abnormal vibration caused by blade damage or unbalance of the rotating shaft 503, the device can actively adjust the electric control push rod 2 to change the accurate position of the inner stator 4 in the device. Since the position change of the inner stator 4 will slightly affect the uniformity of the magnetic field and the torque pulsation, this adjustment can be used to actively offset part of the vibration frequency caused by mechanical imbalance, which enables the unmanned aerial vehicle to still significantly improve the flight stability and safety before landing and maintenance after failure. Since the outer stator 3 and the inner stator 4 are independent units manufactured and separable assembled, they are not a single iron core winding integrally formed in the traditional motor, but each has an independent iron core, winding and insulation structure, which enables the structure design of the outer stator 3 and the inner stator 4 to be modularized. Under the modularized design, when a single stator is damaged, the other stator can still work, which further improves the running stability of the device.

[0025] Please refer to Figures 1 to 10The top outer end of the motor housing 1 is provided with a guide seat 6, and the top inner end of the guide seat 6 is provided with an electromagnet 7. The inner side of the rotating shaft 503 is provided with an emergency stop assembly 8. The emergency stop assembly 8 and the guide seat 6 are provided with a return spring 9. Four groups of speed reduction blocks 506 are annularly distributed inside the centrifugal disc 504, and the speed reduction blocks 506 are elastically connected with the tension spring 505. The emergency stop assembly 8 comprises a butt joint disc 801. The inner bottom side of the butt joint disc 801 is provided with a permanent magnet 802. The outer end of the butt joint disc 801 is provided with a sliding seat 803. The inner side of the sliding seat 803 is provided with a pressure spring 804. The inner side of the sliding seat 803 is provided with a pressure sensor 805. The inner side of the sliding seat 803 is provided with a fitting seat 806. The top outer end of the butt joint disc 801 is provided with an armature 807. The butt joint disc 801, the guide seat 6 and the return spring 9 are provided with a first sliding groove 10. The armature 807 and the sliding seat 803 are provided with a second sliding groove 11. The butt joint disc 801 is sleeved with the rotating shaft 503. The butt joint disc 801 is elastically connected with the guide seat 6 through the return spring 9. The speed reduction block 506 is electromagnetically adsorbed with the permanent magnet 802. The armature 807 is electromagnetically adsorbed with the electromagnet 7. The outer surface of the sliding seat 803 is fitted with the inner surface of the guide seat 6. The outer surface of the fitting seat 806 is fitted with the inner surface of the guide seat 6. The fitting seat 806 is elastically connected with the sliding seat 803 through the pressure spring 804. The end of the fitting seat 806 away from the guide seat 6 is fitted with the pressure sensor 805. The return spring 9 slides through the first sliding groove 10. The armature 807 slides through the second sliding groove 11. The specific operation is as follows: in the process of flight of the unmanned aerial vehicle, when the motor needs to be stopped urgently to avoid danger, the inner stator 4 is quickly lowered by the electric control push rod 2, so that the inner stator 4 does not participate in the rotation of the rotor seat 501, at this time the rotor seat 501 will quickly slow down, the centrifugal force of the centrifugal disc 504 will be reduced, which makes the tension spring 505 pull back the speed reduction block 506, at the same time the electromagnet 7 loses power and makes the return spring 9 rebound, in the process of rebounding of the return spring 9, the displacement of the docking disc 801 in the guide seat 6 is realized by the sliding seat 803, and after the docking disc 801 moves downward, the permanent magnet 802 moves to the same height as the speed reduction block 506, which makes the speed reduction block 506 and the permanent magnet 802 realize electromagnetic adsorption to realize the emergency stop of the rotating shaft 503, when the unmanned aerial vehicle uncontrollably flies towards the crowd due to failure or operation error, and the operator judges that it is impossible to avoid collision by normal control, the emergency stop can be triggered to make the unmanned aerial vehicle fall on the spot in the unmanned area, and when inspecting high-voltage lines, chemical plants, data centers and other sensitive environments, once the unmanned aerial vehicle loses control and may collide with key equipment to cause a major accident, the power is immediately cut off to make it fall vertically, so as to minimize the damage, through the above design, the safety of the unmanned aerial vehicle operation can be greatly improved, the rotating shaft 503 is connected with the unmanned aerial vehicle blade, in the process of rotation of the blade, the docking disc 801 is moved to the highest point by the electromagnetic attraction of the electromagnet 7, and the electromagnet 7 loses power, the return spring 9 resets, which makes the docking disc 801 move to the bottom end, because the docking disc 801 is connected with the rotating shaft 503, when the unmanned aerial vehicle blade is damaged or the rotating shaft 503 is deformed due to collision in the process of unmanned aerial vehicle operation, the vibration at the high position of the rotating shaft 503 will be greater than that at the low position, and the docking disc 801 can sense the vibration and transmit the vibration force to the sliding seat 803, when the sliding seat 803 senses the vibration force, it will offset the vibration force by extruding the pressure spring 804, and when the pressure spring 804 is extruded, the pressure sensor 805 will be extruded by the abutting seat 806, the equipment can judge whether the blade or the rotating shaft 503 is damaged by sensing the pressure frequency of the pressure sensor 805, because the armature 807 can move in a small range through the second sliding groove 11, and the return spring 9 can move in a small range through the first sliding groove 10, so the two will not interfere with the vibration of the docking disc 801.

[0026] In summary, the modular stator of the unmanned aerial vehicle energy-saving disc type motor, in use, first, the equipment is installed in the unmanned aerial vehicle, and the equipment needs to be powered on and connected with the power connector of the unmanned aerial vehicle to realize power on. The fan of the unmanned aerial vehicle can be connected with the rotating shaft 503. The unmanned aerial vehicle can supply power to the equipment during use. The outer stator 3 and the inner stator 4 are both wound with power coils (not shown in the figure). When the unmanned aerial vehicle passes a certain order of current to the winding of the outer stator 3 and the inner stator 4, a rotating magnetic field will be generated in the stator. The annular magnet 502 installed at the bottom of the rotor base 501 provides a permanent magnetic field. When the permanent magnetic field is attracted and repelled by the rotating magnetic field of the outer stator 3 and the inner stator 4, an electromagnetic torque will be generated. The torque will drive the rotor base 501 and the rotating shaft 503 rigidly connected thereto to start rotating, thereby driving the unmanned aerial vehicle fan installed on the rotating shaft 503 to work, thereby realizing the flight of the unmanned aerial vehicle. Then, during the flight of the unmanned aerial vehicle, the inner stator 4 is moved downward by the electric control push rod 2, which can change the magnetic induction between the inner stator 4 and the rotor base 501, which can adjust the rotating speed of the rotor base 501. Since the unmanned aerial vehicle often operates in extreme environments, the electric control system is prone to failure in extreme environments. By moving the inner stator 4 up and down, the rotating speed of the unmanned aerial vehicle can be accurately controlled, which provides a second rotating speed control scheme for the unmanned aerial vehicle, thereby improving the stability of the unmanned aerial vehicle. In addition, when the pressure sensor 805 detects abnormal vibration caused by blade damage or unbalance of the rotating shaft 503, the equipment can actively adjust the electric control push rod 2 to change the precise position of the inner stator 4 inside the equipment. Since the position change of the inner stator 4 will slightly affect the uniformity of the magnetic field and the torque pulsation, this adjustment can be used to actively offset part of the vibration frequency caused by mechanical imbalance, which can significantly improve the flight stability and safety of the unmanned aerial vehicle before failure and before landing for repair. Since the outer stator 3 and the inner stator 4 are independently manufactured and separable units, they are not a single iron core winding formed integrally in the traditional motor, but each has an independent iron core, winding and insulation structure, which makes the structure design of the outer stator 3 and the inner stator 4 modular. When a single stator is damaged, the other stator can still work, which further improves the stability of the equipment. When the UAV needs to avoid danger and the motor needs to be stopped during flight, the inner stator 4 is quickly lowered by the electric control push rod 2, so that the inner stator 4 does not participate in the rotation of the rotor seat 501, at this time the rotor seat 501 will quickly slow down, the rotor seat 501 will slow down, which will reduce the centrifugal force of the centrifugal disc 504, which will cause the tension spring 505 to pull back the speed reduction block 506, and the electromagnetic iron 7 will lose power, which will cause the reset spring 9 to rebound. During the process of rebounding of the reset spring 9, the displacement of the docking disc 801 in the guide seat 6 will be realized by the sliding seat 803, and after the docking disc 801 is lowered, the permanent magnet 802 will be lowered to the same height as the speed reduction block 506, which will cause the speed reduction block 506 and the permanent magnet 802 to be electromagnetically attracted to achieve the emergency stop of the rotating shaft 503. When the UAV uncontrollably flies towards the crowd due to failure or operation error, and the operator judges that it is impossible to avoid collision by normal control, the emergency stop can be triggered to make the UAV fall in an unmanned area, and when inspecting high-voltage lines, chemical plants, data centers and other sensitive environments, if the UAV loses control and may collide with critical equipment, the power is immediately cut off to make it fall vertically, minimizing damage. Through the above design, the safety of the UAV operation can be greatly improved. During the rotation of the last blade, the electromagnetic iron 7 is powered to attract the armature 807, which can move the docking disc 801 to the highest point, and the electromagnetic iron 7 loses power, and the reset spring 9 resets, which will move the docking disc 801 to the bottom end. Because the docking disc 801 is connected with the rotating shaft 503, when the UAV blade is damaged or the rotating shaft 503 is deformed due to collision during the operation of the UAV, the vibration at the high position of the rotating shaft 503 will be greater than that at the low position, and the docking disc 801 can sense the vibration and transmit the vibration force to the sliding seat 803. When the sliding seat 803 senses the vibration force, it will offset the vibration force by pressing the pressure spring 804, and when the pressure spring 804 is pressed, the pressure sensor 805 will be pressed by the abutting seat 806. The device can judge whether the blade or the rotating shaft 503 is damaged by sensing the pressure frequency of the pressure sensor 805. Because the armature 807 can move in a small range through the second sliding groove 11, and the reset spring 9 can move in a small range through the first sliding groove 10, the two will not interfere with the vibration of the docking disc 801.

[0027] It should be noted that in this text, the terms "include", "contain" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or includes elements inherent to such process, method, article or device.

[0028] The principles and implementation manners of the present application are described by using specific examples in the present application, and the above examples are only used to help understand the method of the present application and its core idea. The above description is only the preferred implementation manner of the present application, and it should be noted that, due to the limited expression of the text, there are objectively infinite specific structures, and for ordinary skilled persons in the technical field, some improvements, refinements or changes can be made without departing from the principles of the present application, and the above technical features can also be combined in an appropriate manner; the improvements, refinements, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, shall be regarded as the protection scope of the present application.

Claims

1. An energy-saving disc motor for unmanned aerial vehicles with a modular stator, characterized in that, The system includes a motor housing (1), an electrically controlled push rod (2) is disposed on the inner bottom side of the motor housing (1), an outer stator (3) is disposed inside the motor housing (1), and an inner stator (4) is disposed on the inner ring of the outer stator (3). A rotor assembly (5) is disposed on the outer top of the outer stator (3) and the inner stator (4). The rotor assembly (5) includes a rotor seat (501), magnets (502) are distributed in a ring at the outer bottom of the rotor seat (501), and a rotating shaft (502) is disposed on the outer top of the rotor seat (501). 03), a centrifugal disc (504) is provided at the outer end of the rotating shaft (503), a tension spring (505) is arranged inside the centrifugal disc (504), a speed reduction block (506) is arranged at the outer end of the tension spring (505), a guide seat (6) is arranged at the top outer end of the motor housing (1), and an electromagnet (7) is arranged at the top bottom end of the guide seat (6), an emergency stop assembly (8) is arranged on the inner side of the rotating shaft (503), and a reset spring (9) is arranged between the emergency stop assembly (8) and the guide seat (6).

2. The modular stator-type energy-saving disc motor for UAVs according to claim 1, characterized in that, The electric control push rod (2) is fixedly connected to the inner stator (4), and the inner stator (4) and the outer stator (3) are concentrically distributed.

3. The modular stator-type energy-saving disc motor for UAVs according to claim 1, characterized in that, The electric control push rod (2) drives the inner stator (4) to rise and fall inside the motor housing (1), and the rotor seat (501) rotates through the outer stator (3) and the inner stator (4).

4. The modular stator-type energy-saving disc motor for UAVs according to claim 1, characterized in that, The deceleration blocks (506) are arranged in four groups in a ring inside the centrifugal disc (504), and the deceleration blocks (506) are elastically connected to the tension spring (505).

5. The modular stator-type energy-saving disc motor for UAVs according to claim 1, characterized in that, The emergency stop assembly (8) includes a docking plate (801), a permanent magnet (802) is disposed on the inner side of the bottom of the docking plate (801), a sliding seat (803) is disposed at the outer end of the docking plate (801), a pressure spring (804) is disposed inside the sliding seat (803), a pressure sensor (805) is disposed inside the sliding seat (803), and a fitting seat (806) is disposed inside the sliding seat (803). An armature (807) is disposed at the outer top end of the docking plate (801). A first groove (10) is provided at the connection between the docking plate (801), the guide seat (6) and the reset spring (9), and a second groove (11) is provided at the connection between the armature (807) and the sliding seat (803).

6. The modular stator-type energy-saving disc motor for UAVs according to claim 5, characterized in that, The docking plate (801) is sleeved and connected to the rotating shaft (503), and the docking plate (801) is elastically connected to the guide seat (6) through the return spring (9).

7. The modular stator-type energy-saving disc motor for UAVs according to claim 5, characterized in that, The deceleration block (506) is electromagnetically attracted to the permanent magnet (802), and the armature (807) is electromagnetically attracted to the electromagnet (7).

8. The modular stator-type energy-saving disc motor for UAVs according to claim 5, characterized in that, The outer surface of the sliding seat (803) is in contact with the inner surface of the guide seat (6), and the outer surface of the fitting seat (806) is in contact with the inner surface of the guide seat (6).

9. An energy-saving disc motor for UAVs with a modular stator according to claim 5, characterized in that, The fitting seat (806) is elastically connected to the sliding seat (803) via a pressure spring (804), and the end of the fitting seat (806) away from the guide seat (6) is in contact with the pressure sensor (805).

10. An energy-saving disc motor for UAVs with a modular stator according to claim 5, characterized in that, The reset spring (9) slides through the first slide groove (10), and the armature (807) slides through the second slide groove (11).

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