Long-endurance energy-saving aircraft motor

Abstract

The invention discloses a long-endurance energy-saving aircraft motor, and belongs to the technical field of aircraft motors, the long-endurance energy-saving aircraft motor comprises an aircraft body, four balance rods are fixedly connected outside the aircraft body, a motor body is installed in the balance rods, and the output end of the motor body is fixedly connected with a rotating shaft. According to the device, an extrusion rod intermittently extrudes four hemispheroids which are uniformly distributed in the circumferential direction in the rotating process, the hemispheroids are forced to push a moving rod to slide along a circular groove, when the displacement of the moving rod reaches a set threshold value, a control button is triggered, the control button sends a signal to a controller through a first wire, and after the controller receives the signal, the controller controls the controller to move. The light bar (such as an LED array) and the buzzing alarm (connected through a second wire) are synchronously activated, and the plurality of hemispheres are sequentially triggered along with continuous rotation of the extrusion rod, so that gradual lightening of the light bar and intermittent alarm of the buzzer are realized, and an operator is prompted to detect the abnormal deflection state of the propeller in time through an acousto-optic composite warning mechanism.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft motors, and in particular relates to a long-endurance energy-saving aircraft motor. Background Art

[0002] An aircraft is a mechanical device that can fly in the atmosphere or space, including airplanes, helicopters, drones, rockets and other types. Among them, drones are widely used in aerial photography, logistics, agricultural spraying and emergency rescue due to their flexibility, maneuverability and easy operation. The core power source of drones is the motor, especially the brushless motor. Due to its high efficiency, long life and low noise, it has become the preferred power device for modern aircraft. The motor generates lift and thrust by driving the propeller to ensure the stable flight of the aircraft and complete various tasks. With the development of technology, aircraft and their motor systems are constantly evolving towards a smarter and more energy-efficient direction.

[0003] Currently, there are two major reliability risks in the operation of drone motors: First, after being hit by external forces, the propeller mounting shaft is prone to axial displacement or radial deflection. If this hidden damage is not detected in time, it may cause abnormal vibration or even loss of control during flight. Second, if the dust and water resistance (IP) rating of the motor casing is insufficient, when operating in a humid environment or precipitation conditions, water vapor and liquid may invade the internal windings or bearing systems, causing problems such as reduced insulation performance and rust of metal parts, significantly shortening the motor's service life. These reliability issues directly affect the flight safety and system durability of the drone.

[0004] Based on this, the present invention designs a long-endurance energy-saving aircraft motor to solve the above problems. Summary of the Invention

[0005] The purpose of the present invention is to solve the following problems: first, to solve the problem that the propeller mounting shaft of the current drone motor is prone to axial displacement or radial deflection after being hit by external force. If this hidden damage is not detected in time, it may cause abnormal vibration or even loss of control during flight; second, when the dust and water resistance (IP) rating of the motor housing is insufficient, when operating in a humid environment or precipitation conditions, water vapor and liquid may invade the internal winding or bearing system, thereby causing insulation performance degradation and rust of metal parts. Therefore, a long-endurance energy-saving aircraft motor is proposed.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] A long-endurance energy-saving aircraft motor includes an aircraft body, four stabilizing rods fixedly connected to the outside of the aircraft body, a motor body mounted inside the stabilizing rods, a rotating shaft fixedly connected to the output end of the motor body, a propeller mounted outside the rotating shaft, a detection device fixedly connected to the outside of the motor body, and a protective device mounted outside the motor body;

[0008] The detection device includes a connecting rod and a fixed block, the connecting rod is fixedly connected to the lower surface of the propeller, an extrusion rod is fixedly connected under the connecting rod, the fixed block is fixedly connected to the motor body and is sleeved outside the rotating shaft, four circular grooves are opened in the fixed block, a moving rod is installed in the circular groove, a reset spring is fixedly connected under the moving rod, a circular plate is fixedly connected under the reset spring, a control button is installed on the circular plate, a first wire is installed on one side of the control button, a controller is installed on one end of the first wire, the controller is fixedly connected to the outside of the fixed block, and a light bar is installed in the controller.

[0009] As a further description of the above technical solution:

[0010] A hemisphere is fixedly connected to the upper surface of the moving rod, and the height of the hemisphere is slightly lower than the height of the extrusion rod.

[0011] As a further description of the above technical solution:

[0012] The cross section of the moving rod is slightly smaller than the inner diameter of the circular groove, and a sliding connection is formed between the moving rod and the circular groove.

[0013] As a further description of the above technical solution:

[0014] The detection device further includes a second wire and a mounting slot. The second wire is fixedly connected to the controller. One end of the second wire is fixedly connected to a buzzer alarm, and the buzzer alarm is fixedly connected to the outside of the fixed block.

[0015] As a further description of the above technical solution:

[0016] The installation slot is provided in the fixing block, and a battery pack is installed in the installation slot.

[0017] As a further description of the above technical solution:

[0018] The battery pack is electrically connected to the controller and the light bar.

[0019] As a further description of the above technical solution:

[0020] The protective device includes a first shell and a second shell. Long plates are symmetrically installed on the outside of the first shell and the second shell. Fixing grooves are opened in the long plates, and a bolt for sealing is clamped in one of the fixing grooves.

[0021] As a further description of the above technical solution:

[0022] An internal thread is provided in the fixing groove, and a threaded connection is formed between the bolt and the fixing groove.

[0023] As a further description of the above technical solution:

[0024] The upper surfaces of the first shell and the second shell are both provided with an inwardly bent arc, and the arc is clamped outside the motor body. The first shell and the second shell are both fixedly connected to the bottom with a wind deflector that is convenient for dissipating heat from the motor body and protecting from rain.

[0025] As a further description of the above technical solution:

[0026] A telescopic rod is installed in both the first shell and the second shell. The telescopic end of the telescopic rod is fixedly connected to the top plate. A buffer spring is provided on the outer sleeve of the telescopic rod. The buffer spring is fixedly connected to the outside of the top plate. The top plate is clamped outside the motor body.

[0027] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0028] 1. In the present invention, when the aircraft body is hit, the rotating shaft of the motor body may be deflected, and the propeller may be driven to rotate tilted. When the tilted propeller rotates, the extrusion rod is driven to move synchronously through the connecting rod. During the rotation process, the extrusion rod intermittently squeezes four hemispheres evenly distributed circumferentially, forcing the hemispheres to push the moving rod to slide along the circular groove. When the displacement of the moving rod reaches a set threshold, the control button is triggered. The control button sends a signal to the controller through the first wire. After receiving the signal, the controller synchronously activates the light bar (such as an LED array) and the buzzer alarm (connected by the second wire). As the extrusion rod continues to rotate, multiple hemispheres are triggered in sequence, realizing the progressive lighting of the light bar and the intermittent alarm of the buzzer, thereby prompting the operator to promptly detect the abnormal deflection state of the propeller through the sound and light composite warning mechanism.

[0029] 2. In the present invention, under rainy weather conditions, the split-design first shell and the second shell are buckled onto the outside of the motor body and fastened with double-sided bolts so that the top plates inside the first shell and the second shell are tightly fitted to the outer wall of the motor body. When rainwater hits the first shell and the second shell, the liquid is discharged along a preset path by the drainage effect of the wind guide plate to avoid seeping into the interior of the motor body. At the same time, the air flow channel under the wind guide plate can effectively discharge the heat generated by the motor body during operation, ensuring the heat dissipation performance. When the first shell and the second shell encounter an external collision, the buffer spring absorbs the impact energy through elastic deformation and pushes the top plate to achieve dynamic force release. After the collision, the restoring force of the buffer spring causes the first shell and the second shell to quickly reset, maintaining the stability of the protective structure. This design has the triple functions of rainproof sealing, active heat dissipation and mechanical buffering. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 This is a three-dimensional structural diagram of the long-endurance energy-saving aircraft motor proposed by the present invention;

[0031] Figure 2 This is a three-dimensional structural diagram of the long-endurance energy-saving aircraft motor propeller proposed by the present invention;

[0032] Figure 3 This is a three-dimensional structural diagram of the extruded rod of the motor of the long-endurance energy-saving aircraft proposed by the present invention;

[0033] Figure 4 This is a schematic diagram of the three-dimensional cross-sectional structure of the motor fixing block of the long-endurance energy-saving aircraft proposed by the present invention;

[0034] Figure 5 The long-endurance energy-saving aircraft motor proposed by the present invention Figure 4 A schematic diagram of the structure of the enlarged part A;

[0035] Figure 6 This is a schematic diagram of the structure of the long-endurance energy-saving aircraft motor separated from the second housing proposed by the present invention;

[0036] Figure 7 The long-endurance energy-saving aircraft motor proposed by the present invention Figure 6 Schematic diagram of the enlarged structure of part B.

[0037] Legend:

[0038] 1. Aircraft body; 2. Balance bar; 3. Motor body; 4. Rotating shaft; 5. Propeller; 6. Detection device; 601. Connecting rod; 602. Extrusion rod; 603. Fixed block; 604. Circular groove; 605. Moving rod; 606. Hemisphere; 607. Return spring; 608. Circular plate; 609. Control button; 610. First wire; 611. Controller; 612. Light bar; 613. Second wire; 614. Buzzer alarm; 615. Mounting slot; 616. Battery pack; 7. Protective device; 71. First shell; 72. Second shell; 73. Long board; 74. Bolt; 75. Fixed slot; 76. Wind deflector; 77. Telescopic rod; 78. Top plate; 79. Buffer spring. DETAILED DESCRIPTION

[0039] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0040] See also Figure 1-Figure 7The present invention provides a technical solution: a long-endurance energy-saving aircraft motor, comprising an aircraft body 1, four balancing rods 2 fixedly connected to the outside of the aircraft body 1, a motor body 3 installed inside the balancing rods 2, an output end of the motor body 3 fixedly connected to a rotating shaft 4, a propeller 5 installed outside the rotating shaft 4, a detection device 6 fixedly connected to the outside of the motor body 3, and a protective device 7 provided on the outside of the motor body 3;

[0041] The detection device 6 includes a connecting rod 601 and a fixed block 603. The connecting rod 601 is fixedly connected to the lower surface of the propeller 5. The extrusion rod 602 is fixedly connected to the lower surface of the connecting rod 601. The fixed block 603 is fixedly connected to the motor body 3 and is sleeved on the outside of the rotating shaft 4. Four circular grooves 604 are opened in the fixed block 603. The circular grooves 604 are installed in the moving rod 605. The moving rod 605 is fixedly connected to the lower surface of the return spring 607. The return spring 607 is fixedly connected to the lower surface of the circular plate 608. The return spring 607 is pre-set. In the compressed state, it is fixed between the circular plate 608 and the fixed block 603. When the extrusion rod 602 releases the pressure on the hemisphere 606, the elastic restoring force of the spring pushes the circular plate 608 and the movable rod 605 to quickly reset, preparing for the next triggering. The circular plate 608 acts as a force-bearing platform, evenly transmitting the linear restoring force of the spring to the movable rod 605, avoiding unilateral jamming. This combination not only ensures the recyclability of the detection device 6, but also reduces the risk of damage to the control button 609 due to mechanical impact through the buffering effect of the spring.

[0042] A control button 609 is mounted on the circular plate 608 , a first wire 610 is mounted on one side of the control button 609 , a controller 611 is mounted on one end of the first wire 610 , the controller 611 is fixedly connected to the outside of the fixed block 603 , and a light bar 612 is mounted inside the controller 611 .

[0043] Specifically, such as Figure 2-Figure 5 As shown, the upper surface of the moving rod 605 is fixedly connected to a hemispherical body 606, and the height of the hemispherical body 606 is slightly lower than that of the extrusion rod 602. The contact surface between the rotational movement of the extrusion rod 602 and the hemispherical body 606 adopts a height difference design (the hemispherical body 606 is slightly lower than the extrusion rod 602), ensuring that there is no interference between the two when the propeller 5 is operating normally. The hemispherical body 606 is triggered only when the extrusion rod 602 is pressed downward due to the deflection of the rotating shaft 4. This dynamic contact mechanism can avoid false triggering and respond quickly when tilt occurs. The linear contact between the curved surface of the hemispherical body 606 and the extrusion rod 602 can disperse the impact force and reduce wear. At the same time, the sliding fit between the moving rod 605 and the circular groove 604 ensures the smoothness of the triggering process, making the pressing action of the control button 609 accurate and reliable.

[0044] The cross-section of the moving rod 605 is slightly smaller than the inner diameter of the circular groove 604, and a sliding connection is formed between the moving rod 605 and the circular groove 604. The detection device 6 also includes a second wire 613 and a mounting groove 615. The second wire 613 is fixedly connected to the controller 611. One end of the second wire 613 is fixedly connected to a buzzer alarm 614. The buzzer alarm 614 is fixedly connected to the outside of the fixed block 603. The mounting groove 615 is opened in the fixed block 603. A battery pack 616 is installed in the mounting groove 615. The battery pack 616 is electrically connected to the controller 611 and the light bar 612.

[0045] Specifically, such as Figure 6-Figure 7 As shown, the protective device 7 includes a first shell 71 and a second shell 72. Long plates 73 are symmetrically installed on the outside of the first shell 71 and the second shell 72. Fixing grooves 75 are opened in the long plates 73, and a bolt 74 for sealing is clamped in one of the fixing grooves 75. The fixing grooves 75 are provided with internal threads, and a threaded connection is formed between the bolt 74 and the fixing grooves 75. The upper surfaces of the first shell 71 and the second shell 72 are provided with an arc bent inward, and the arc is clamped on the outside of the motor body 3. The first shell 71 and the second shell 72 are fixedly connected to the bottom with an air guide plate 76 that is convenient for dissipating heat from the motor body 3 and keeping out rain. The inclination angle of the air guide plate 76 forms a continuous curved surface with the edge of the shell. On rainy days, rainwater is guided to flow quickly along the plate surface to prevent accumulated water from seeping into the motor. At the same time, the bottom opening thereof constitutes an air flow channel, which utilizes the natural convection of hot air generated when the motor is running to achieve passive heat dissipation. The geometric shape of the air guide plate 76 takes into account both fluid guidance and structural strength, and can simultaneously solve the conflicting needs of rain protection and heat dissipation without additional power.

[0046] A telescopic rod 77 is installed in both the first shell 71 and the second shell 72. The telescopic end of the telescopic rod 77 is fixedly connected to the top plate 78. A buffer spring 79 is provided on the outer sleeve of the telescopic rod 77. The buffer spring 79 is sleeved on the outside of the telescopic rod 77. During a collision, the spring absorbs instantaneous impact energy by compression, while the telescopic rod 77 limits the lateral deformation of the spring, ensuring that the top plate 78 moves only in the axial direction. The elastic deformation of the spring and the rigid guidance of the telescopic rod 77 are combined to achieve flexible dissipation of the collision force and prevent the seal from failing due to excessive displacement of the shell, thereby improving the durability of the protective device 7.

[0047] The buffer spring 79 is fixedly connected to the outside of the top plate 78 , and the top plate 78 is clamped outside the motor body 3 .

[0048] Working principle, when in use: when the aircraft body 1 is hit, the rotating shaft 4 of the motor body 3 may be deflected, and drive the propeller 5 to rotate tilted. When the tilted propeller 5 rotates, it drives the extrusion rod 602 to move synchronously through the connecting rod 601. During the rotation process, the extrusion rod 602 intermittently squeezes the four hemispheres 606 evenly distributed around the circumference, forcing the hemispheres 606 to push the moving rod 605 to slide along the circular groove 604. When the displacement of the moving rod 605 reaches the set threshold, the control button 609 is triggered. The control button 609 sends a signal to the controller 611 through the first wire 610. After receiving the signal, the controller 611 synchronously activates the light bar 612 (such as an LED array) and the buzzer alarm 614 (connected by the second wire 613). As the extrusion rod 602 continues to rotate, multiple hemispheres 606 are triggered in turn, realizing the progressive lighting of the light bar 612 and the intermittent lighting of the buzzer alarm 614. Alarm. In rainy weather conditions, the split-design first shell 71 and the second shell 72 are snapped onto the outside of the motor body 3 and fastened with double-sided bolts 74, so that the top plates 78 inside the first shell 71 and the second shell 72 are tightly fitted to the outer wall of the motor body 3. When rainwater hits the first shell 71 and the second shell 72, the liquid is discharged along the preset path under the drainage effect of the wind guide plate 76 to avoid seeping into the interior of the motor. At the same time, the air flow channel under the wind guide plate 76 can effectively discharge the heat of the motor body 3 during operation to ensure the heat dissipation performance. When the first shell 71 and the second shell 72 encounter an external collision, the buffer spring 79 absorbs the impact energy through elastic deformation and pushes the top plate 78 to achieve dynamic force release; after the collision, the restoring force of the buffer spring 79 causes the first shell 71 and the second shell 72 to quickly reset, maintaining the stability of the protective structure, thereby completing the protection of the motor body 3 and the detection of the propeller 5.

[0049] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solution of the present invention, should be covered by the scope of protection of the present invention.

Claims

1. A long-endurance energy-saving aircraft motor, comprising an aircraft body (1), characterized in that: The aircraft body (1) is fixedly connected to four balancing rods (2) on the outside, a motor body (3) is installed inside the balancing rods (2), an output end of the motor body (3) is fixedly connected to a rotating shaft (4), a propeller (5) is installed outside the rotating shaft (4), a detection device (6) is fixedly connected to the outside of the motor body (3), and a protective device (7) is provided on the outside of the motor body (3); The detection device (6) comprises a connecting rod (601) and a fixed block (603), wherein the connecting rod (601) is fixedly connected to the lower surface of the propeller (5), and an extrusion rod (602) is fixedly connected to the lower surface of the connecting rod (601), and the fixed block (603) is fixedly connected to the motor body (3) and sleeved outside the rotating shaft (4), and four circular grooves (604) are opened in the fixed block (603), and a moving rod (605) is installed in the circular groove (604), and the moving rod (605) is fixedly connected to the lower surface of the propeller (5). 05) is fixedly connected to a return spring (607), a circular plate (608) is fixedly connected to the return spring (607), a control button (609) is installed on the circular plate (608), a first wire (610) is installed on one side of the control button (609), a controller (611) is installed on one end of the first wire (610), the controller (611) is fixedly connected to the outside of the fixed block (603), and a light bar (612) is installed in the controller (611).

2. The long-endurance energy-saving aircraft motor according to claim 1, characterized in that: A hemisphere (606) is fixedly connected to the upper surface of the moving rod (605), and the height of the hemisphere (606) is slightly lower than the height of the extrusion rod (602).

3. The long-endurance energy-saving aircraft motor according to claim 1, characterized in that: The cross section of the moving rod (605) is slightly smaller than the inner diameter of the circular groove (604), and a sliding connection is formed between the moving rod (605) and the circular groove (604).

4. The long-endurance energy-saving aircraft motor according to claim 1, characterized in that: The detection device (6) further comprises a second wire (613) and a mounting slot (615); the second wire (613) is fixedly connected to the controller (611); one end of the second wire (613) is fixedly connected to a buzzer alarm (614); and the buzzer alarm (614) is fixedly connected to the outside of the fixed block (603).

5. The long-endurance energy-saving aircraft motor according to claim 4, characterized in that: The installation slot (615) is opened in the fixed block (603), and a battery pack (616) is installed in the installation slot (615).

6. The long-endurance energy-saving aircraft motor according to claim 5, characterized in that: The battery pack (616) is electrically connected to the controller (611) and the light bar (612).

7. The long-endurance energy-saving aircraft motor according to claim 1, characterized in that: The protective device (7) comprises a first shell (71) and a second shell (72), wherein long plates (73) are symmetrically mounted on the outside of the first shell (71) and the second shell (72), wherein fixing grooves (75) are provided in the long plates (73), and a bolt (74) for sealing is clamped in one of the fixing grooves (75).

8. The long-endurance energy-saving aircraft motor according to claim 7, characterized in that: An internal thread is provided in the fixing groove (75), and a threaded connection is formed between the bolt (74) and the fixing groove (75).

9. The long-endurance energy-saving aircraft motor according to claim 7, characterized in that: The upper surfaces of the first shell (71) and the second shell (72) are both provided with an arc bent inward, and the arc is clamped outside the motor body (3). The first shell (71) and the second shell (72) are both fixedly connected to the bottom with a wind deflector (76) that is convenient for dissipating heat from the motor body (3) and protecting from rain.

10. The long-endurance energy-saving aircraft motor according to claim 7, characterized in that: A telescopic rod (77) is installed in both the first shell (71) and the second shell (72), the telescopic end of the telescopic rod (77) is fixedly connected to a top plate (78), a buffer spring (79) is provided on the outer sleeve of the telescopic rod (77), the buffer spring (79) is fixedly connected to the outside of the top plate (78), and the top plate (78) is clamped outside the motor body (3).

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