Long endurance energy saving aircraft motor

Abstract

The application 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 to the aircraft body, a motor body is installed in the balance rods, and an output end of the motor body is fixedly connected with a rotating shaft. In the application, the extrusion rod intermittently extrudes the circumferentially-distributed four hemispheres in the rotating process, forces the hemispheres to push the moving rod to slide along the circular groove, and triggers the control button when the displacement of the moving rod reaches the set threshold. The control button sends a signal to the controller through the first wire, the controller activates the light bar (such as an LED array) and the buzzer (connected through the second wire) synchronously after receiving the signal. With the continuous rotation of the extrusion rod, the multiple hemispheres are triggered in sequence, the light bar is progressively lighted, and the buzzer is intermittently alarmed, so that the sound-light composite warning mechanism prompts the operator to detect the abnormal deflection state of the propeller in time.

Description

Technical Field

[0001] This invention belongs to the field of aircraft motor technology, and particularly relates to long-endurance energy-saving aircraft motors. Background Technology

[0002] An aircraft is a mechanical device capable of flying in the atmosphere or space, encompassing various types such as airplanes, helicopters, drones, and rockets. Among them, drones, with their flexibility, maneuverability, and ease of operation, are widely used in aerial photography, logistics, agricultural spraying, and emergency rescue. The core power source of drones is the electric motor, especially the brushless motor, which has become the preferred power unit for modern aircraft due to its advantages such as high efficiency, long lifespan, and low noise. The motor generates lift and thrust by driving the propeller, ensuring stable flight and the completion of various tasks. With the development of technology, aircraft and their motor systems are constantly evolving towards greater intelligence and energy efficiency.

[0003] Currently, there are two main reliability issues with drone motors during operation: First, after being impacted by external forces, the propeller mounting shaft is prone to axial or radial misalignment. If this hidden damage is not detected in time, it may lead to abnormal vibrations or even loss of control during flight. Second, if the dustproof and waterproof (IP) rating of the motor housing is insufficient, moisture and liquid may penetrate the internal windings or bearing system when operating in humid environments or under precipitation conditions, thereby causing problems such as decreased insulation performance and corrosion of metal parts, significantly shortening the motor's service life. These reliability issues directly affect the flight safety and system durability of drones.

[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 this invention is to address two issues: firstly, the problem that when a drone motor is subjected to external impact, the propeller mounting shaft is prone to axial or radial misalignment, which, if not detected in time, can lead to abnormal vibrations or even loss of control during flight; secondly, the problem that when the dustproof and waterproof (IP) rating of the motor casing is insufficient, moisture and liquid may penetrate the internal windings or bearing system when operating in humid environments or under precipitation conditions, thereby causing a decrease in insulation performance and corrosion of metal parts. Therefore, this invention proposes a long-endurance, energy-saving aircraft motor.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] The long-endurance energy-saving aircraft motor includes an aircraft body, four balance bars are fixedly connected to the outside of the aircraft body, the motor body is installed inside the balance bars, the output end of the motor body is fixedly connected to a rotating shaft, a propeller is installed outside the rotating shaft, a detection device is fixedly connected to the outside of the motor body, and a protective device is clamped on the outside of the motor body.

[0008] The detection device includes a connecting rod and a fixing block. The connecting rod is fixedly connected to the lower surface of the propeller, and a pressing rod is fixedly connected to the lower part of the connecting rod. The fixing block is fixedly connected to the motor body and sleeved on the outside of the rotating shaft. Four circular slots are opened in the fixing block, and a moving rod is installed in each of the circular slots. A return spring is fixedly connected to the lower part of the moving rod, and a circular plate is fixedly connected to the lower part of the return spring. A control button is installed on the circular plate, and a first wire is installed on one side of the control button. A controller is installed at one end of the first wire, and the controller is fixedly connected to the outside of the fixing block. A light strip is installed inside 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 pressing rod.

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

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

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

[0014] The detection device also includes a second wire and a mounting slot. The second wire is fixedly connected inside the controller, and a buzzer-type alarm is fixedly connected to one end of the second wire. The buzzer-type alarm is fixedly connected to the outside of the fixing block.

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

[0016] The mounting slot is formed inside the fixed block, and the battery pack is installed inside the mounting slot.

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

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

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

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

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

[0022] The fixing groove is provided with internal threads, and the bolt and the fixing groove form a threaded connection.

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

[0024] The upper surfaces of both the first and second housings are provided with inwardly bent arcs, which are fixed to the motor body. Both the first and second housings are fixedly connected with air guide plates that facilitate heat dissipation and rain protection for the motor body.

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

[0026] Both the first and second housings are equipped with telescopic rods. The telescopic end of the telescopic rod is fixedly connected to a top plate. A buffer spring is fitted over the telescopic rod and is fixedly connected to the outside of the top plate. The top plate is secured to the outside of 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 this invention, when the aircraft body is impacted, the shaft of the motor body may deflect, causing the propeller to rotate at an angle. As the tilted propeller rotates, it drives the compression rod to move synchronously through the connecting rod. During the rotation, the compression rod intermittently compresses four circumferentially distributed hemispheres, 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 strip (such as an LED array) and the buzzer alarm (connected through the second wire). As the compression rod continues to rotate, multiple hemispheres are triggered sequentially, realizing the gradual lighting of the light strip and the intermittent alarm of the buzzer. Thus, the sound and light composite warning mechanism prompts the operator to detect the abnormal deflection of the propeller in a timely manner.

[0029] 2. In this invention, under rainy weather conditions, the split-design first and second housings are fastened to the outside of the motor body and secured with bolts on both sides, so that the top plates inside the first and second housings are tightly attached to the outer wall of the motor body. When rainwater impacts the first and second housings, the liquid is discharged along a preset path by the air guide plate, preventing it from seeping into the motor body. At the same time, the airflow channel below the air guide plate can effectively dissipate the heat generated by the motor body during operation, ensuring heat dissipation performance. When the first and second housings encounter an external collision, the buffer spring absorbs the impact energy through elastic deformation and pushes the top plate to achieve dynamic force relief. After the collision, the restoring force of the buffer spring causes the first and second housings to quickly return to their original positions, maintaining the stability of the protective structure. This design has three functions: rainproof sealing, active heat dissipation, and mechanical buffering. Attached Figure Description

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

[0031] Figure 2 This is a three-dimensional structural schematic diagram of the propeller of the long-endurance energy-saving aircraft proposed in this invention.

[0032] Figure 3 This is a three-dimensional structural schematic diagram of the motor extrusion rod for the long-endurance energy-saving aircraft proposed in this invention;

[0033] Figure 4 This is a three-dimensional cross-sectional structural diagram of the motor fixing block for long-endurance energy-saving aircraft proposed in this invention;

[0034] Figure 5 The present invention provides a long-endurance, energy-saving aircraft motor. Figure 4 Enlarged structural diagram of part A in the middle;

[0035] Figure 6 This is a schematic diagram of the structure of the motor of the long-endurance energy-saving aircraft proposed in this invention, showing the separation of the first housing and the second housing.

[0036] Figure 7 The present invention provides a long-endurance, energy-saving aircraft motor. Figure 6 Enlarged structural diagram of part B.

[0037] Legend:

[0038] 1. Aircraft body; 2. Stabilizer bar; 3. Motor body; 4. Shaft; 5. Propeller; 6. Detection device; 601. Connecting rod; 602. Compression rod; 603. Fixing 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 strip; 613. Second wire; 614. Buzzer alarm; 615. Mounting slot; 616. Battery pack; 7. Protective device; 71. First shell; 72. Second shell; 73. Long plate; 74. Bolt; 75. Fixing slot; 76. Air guide plate; 77. Telescopic rod; 78. Top plate; 79. Buffer spring. Detailed Implementation

[0039] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0040] Please see Figures 1-7The present invention provides a technical solution: a long-endurance energy-saving aircraft motor, including an aircraft body 1, four balance bars 2 are fixedly connected to the outside of the aircraft body 1, a motor body 3 is installed inside the balance bars 2, a rotating shaft 4 is fixedly connected to the output end of the motor body 3, 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 clamped on the outside of the motor body 3.

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

[0042] 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 at one end of the first wire 610. The controller 611 is fixedly connected to the outside of the fixing block 603. A light strip 612 is installed inside the controller 611.

[0043] Specifically, such as Figures 2-5 As shown, a hemisphere 606 is fixedly connected to the upper surface of the moving rod 605. The height of the hemisphere 606 is slightly lower than the height of the pressing rod 602. The contact surface between the rotating motion of the pressing rod 602 and the hemisphere 606 adopts a height difference design (the hemisphere 606 is slightly lower than the pressing rod 602) to ensure that there is no interference between the two when the propeller 5 is running normally. The hemisphere 606 is only triggered when the rotating shaft 4 is tilted, causing the pressing rod 602 to press down. This dynamic contact mechanism can avoid false triggering and respond quickly when tilting occurs. The arc surface of the hemisphere 606 and the linear contact with the pressing rod 602 can disperse the impact force and reduce wear. At the same time, the sliding cooperation 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 the moving rod 605 and the circular groove 604 form a sliding connection. The detection device 6 also includes a second wire 613 and a mounting groove 615. The second wire 613 is fixedly connected inside the controller 611. One end of the second wire 613 is fixedly connected to a buzzer 614. The buzzer 614 is fixedly connected outside the fixing block 603. The mounting groove 615 is opened inside the fixing 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 strip 612.

[0045] Specifically, such as Figures 6-7 As shown, the protective device 7 includes a first housing 71 and a second housing 72. Long plates 73 are symmetrically installed on the outside of both the first housing 71 and the second housing 72. A fixing groove 75 is formed within the long plate 73, and a bolt 74 for sealing is fitted into one of the fixing grooves 75. The fixing groove 75 has an internal thread, and the bolt 74 and the fixing groove 75 form a threaded connection. The upper surfaces of both the first housing 71 and the second housing 72 have inwardly bent arcs, which are fitted onto the outside of the motor body 3. Both the first housing 71 and the second housing 72 are fixedly connected to a wind guide plate 76 for heat dissipation and rain protection of the motor body 3. The tilt angle of the wind guide plate 76 forms a continuous curved surface with the edge of the housing, guiding rainwater to flow quickly along the plate surface during rainy weather, preventing water from seeping into the motor. Simultaneously, its bottom opening forms an airflow channel, utilizing the natural convection of hot air generated during motor operation to achieve passive heat dissipation. The geometry of the wind guide plate 76 balances fluid guidance and structural strength, simultaneously resolving the conflicting needs of rain protection and heat dissipation without additional power.

[0046] Both the first housing 71 and the second housing 72 are equipped with telescopic rods 77. The telescopic end of the telescopic rod 77 is fixedly connected to a top plate 78. A buffer spring 79 is sleeved on the telescopic rod 77. When a collision occurs, the spring absorbs the instantaneous impact energy through compression, while the telescopic rod 77 restricts the lateral deformation of the spring, ensuring that the top plate 78 moves only axially. The combination of the elastic deformation of the spring and the rigid guidance of the telescopic rod 77 not only achieves the flexible dissipation of the collision force, but also prevents the housing from failing to seal due to excessive displacement, 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 clipped onto the outside of the motor body 3.

[0048] Working principle and usage: When the aircraft body 1 is impacted, the shaft 4 of the motor body 3 may deflect, causing the propeller 5 to rotate at an angle. As the propeller 5 rotates, it drives the compression rod 602 to move synchronously via the connecting rod 601. During rotation, the compression rod 602 intermittently compresses four circumferentially distributed hemispheres 606, forcing them to push the moving rod 605 to slide along the circular groove 604. When the displacement of the moving rod 605 reaches a set threshold, it triggers the control button 609. The control button 609 sends a signal to the controller 611 via the first wire 610. Upon receiving the signal, the controller 611 synchronously activates the light strip 612 (such as an LED array) and the buzzer alarm 614 (connected via the second wire 613). As the compression rod 602 continues to rotate, multiple hemispheres 606 are triggered sequentially, achieving gradual lighting of the light strip 612 and intermittent audible alarm 614. In rainy weather, the first and second housings, designed as separate units, are fastened to the outside of the motor body 3 and secured with bolts 74 on both sides. This ensures that the top plates 78 inside the first and second housings 71 and 72 are tightly fitted against the outer wall of the motor body 3. When rainwater impacts the first and second housings 71 and 72, the liquid is guided by the air guide plate 76 and discharged along a preset path, preventing it from seeping into the motor. At the same time, the airflow channel below the air guide plate 76 can effectively dissipate the heat generated during the operation of the motor body 3, ensuring heat dissipation performance. When the first and second housings 71 and 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 relief. After the collision, the restoring force of the buffer spring 79 causes the first and second housings 71 and 72 to quickly return to their original positions, maintaining the stability of the protective structure. This completes the protection of the motor body 3 and the detection of the propeller 5.

[0049] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. Long endurance energy saving aircraft motor, comprising an aircraft body (1), characterized in that, The aircraft body (1) is externally connected with four balance bars (2), the balance bar (2) is internally provided with a motor body (3), the output end of the motor body (3) is fixedly connected with a rotating shaft (4), the rotating shaft (4) is externally provided with a propeller (5), the motor body (3) is externally fixedly connected with a detection device (6), and the motor body (3) is externally clamped with a protection device (7). The detection device (6) comprises 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 lower end of the connecting rod (601) is fixedly connected with a pressing rod (602), the fixed block (603) is fixedly connected to the motor body (3) and is sleeved outside the rotating shaft (4), four circular grooves (604) are formed in the fixed block (603), the moving rod (605) is installed in the circular groove (604), the lower end of the moving rod (605) is fixedly connected with a reset spring (607), the lower end of the reset spring (607) is fixedly connected with a circular plate (608), the circular plate (608) is installed with a control button (609), one side of the control button (609) is installed with a first lead wire (610), one end of the first lead wire (610) is installed with a controller (611), the controller (611) is fixedly connected to the outside of the fixed block (603), and the controller (611) is internally installed with a light bar (612). The upper surface of the moving rod (605) is fixedly connected with a hemispherical body (606), and the height of the hemispherical body (606) is slightly lower than the height of the pressing rod (602). The cross section of the moving rod (605) is slightly smaller than the inner diameter of the circular groove (604), and the moving rod (605) and the circular groove (604) are in sliding connection. The detection device (6) further comprises a second lead wire (613) and a mounting groove (615), the second lead wire (613) is fixedly connected in the controller (611), one end of the second lead wire (613) is fixedly connected with a buzzer alarm (614), and the buzzer alarm (614) is fixedly connected to the outside of the fixed block (603).

2. The long endurance energy saving aircraft motor of claim 1, wherein, The mounting groove (615) is formed in the fixed block (603), and the mounting groove (615) is internally installed with a battery pack (616).

3. The long endurance energy saving aircraft motor of claim 2, wherein, The battery pack (616) is electrically connected with the controller (611) and the light bar (612).

4. The long endurance energy saving aircraft motor of claim 1, wherein, The protection device (7) comprises a first shell (71) and a second shell (72), the first shell (71) and the second shell (72) are symmetrically installed with a long plate (73) outside, the long plate (73) is internally provided with a fixed groove (75), and one of the fixed grooves (75) is clamped with a bolt (74) for sealing.

5. The long endurance energy saving aircraft motor of claim 4, wherein, The fixed groove (75) is internally provided with an internal thread, and the bolt (74) and the fixed groove (75) are in threaded connection.

6. The long endurance energy saving aircraft motor of claim 4, wherein, The upper surfaces of the first shell (71) and the second shell (72) are provided with inwardly bent arcs, and the arcs are clamped outside the motor body (3), and the lower surfaces of the first shell (71) and the second shell (72) are fixedly connected with air deflectors (76) facilitating heat dissipation and rain shielding of the motor body (3).

7. The long endurance energy saving aircraft motor of claim 4, wherein, The first shell (71) and the second shell (72) are provided with telescopic rods (77) inside, the telescopic ends of the telescopic rods (77) are fixedly connected with top plates (78), the telescopic rods (77) are provided with buffer springs (79) outside, the buffer springs (79) are fixedly connected outside the top plates (78), and the top plates (78) are clamped outside the motor body (3).

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