Low-altitude aircraft energy-saving motor with heat dissipation structure

Abstract

The application discloses a low-altitude aircraft energy-saving motor with a heat dissipation structure and relates to the technical field of energy-saving motors. The application breaks through the technical bottleneck of traditional air cooling heat dissipation, realizes an efficient, stable and safe heat management scheme, and solves the heat dissipation problem under the current high power density, and also provides a solid foundation for the development of future high-performance electric propulsion systems.

Description

Technical Field

[0001] This invention relates to the field of energy-saving motor technology, and in particular to an energy-saving motor for low-altitude aircraft with a heat dissipation structure. Background Technology

[0002] With the rapid development of low-altitude aircraft such as electric vertical takeoff and landing (EVTOL) vehicles, the motor, as their core power component, faces unprecedented performance requirements, especially at high power densities (e.g., 300 W / cm²). 2 In operating environments, traditional air-cooled heat dissipation technology has gradually revealed problems such as low thermal conductivity (typically <50W / m·K), insufficient heat dissipation efficiency, and excessive temperature rise. Under prolonged high-load operation, the temperature rise of the aluminum casing can reach over 80℃, which not only affects motor efficiency but may also cause serious safety hazards such as magnet demagnetization, insulation failure, and shortened lifespan. Therefore, we propose an energy-saving motor for low-altitude aircraft with a heat dissipation structure to address these issues. Summary of the Invention

[0003] The purpose of this invention is to address the shortcomings of existing technologies by proposing an energy-saving motor for low-altitude aircraft with a heat dissipation structure.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] An energy-saving motor for low-altitude aircraft with a heat dissipation structure includes a protective shell, a support plate fixed inside the protective shell, a motor body mounted on the upper end of the support plate, a fixing rod fixed around the upper end of the support plate, a clamping mechanism movably connected to the fixing rod, one end of the clamping mechanism abutting against one side of the motor body, a fixing tube fixed to the lower end of the support plate, a heat-absorbing structure installed inside the fixing tube, a cooling fan provided at the lower end of the heat-absorbing structure, and the cooling fan fixed to the side wall inside the fixing tube.

[0006] Preferably, the clamping mechanism includes a movable ring that passes through the fixed rod, an arc-shaped clamping plate fixed to one side of the movable ring, a heat-absorbing block fixed to one side of the arc-shaped clamping plate, and one end of the heat-absorbing block abutting against one side of the motor body.

[0007] Preferably, a stud is provided through one side of the movable ring, and multiple threaded blind holes are provided at equal intervals along the vertical direction on one side of the fixed rod. One end of the stud is threaded into one of the threaded blind holes, and a connecting block is fixed on one side of the stud.

[0008] Preferably, the support plate has a first opening, the lower end of the motor body is engaged in the first opening, and the first opening is connected to the fixing pipe.

[0009] Preferably, the heat-absorbing structure includes a pad fixed inside a fixed tube, a first filter screen is fastened to the upper end of the pad, a heat-absorbing plate is fastened to the upper end of the first filter screen, and a second filter screen is fastened to the upper end of the heat-absorbing plate.

[0010] Preferably, the pad, the first filter screen and the heat absorption plate are provided with insertion holes on both sides, and the lower end of the second filter screen is fixed with insertion rods on both sides, with one insertion rod on the same side passing through multiple insertion holes on the same side.

[0011] Preferably, the lower end of the protective shell is provided with a third opening, and a third filter screen is installed in the third opening.

[0012] Preferably, an output shaft is mounted on the motor body, the output shaft penetrates the side wall of the protective shell and extends to the upper end of the protective shell, and a blade is fixed to the upper end of the output shaft.

[0013] Preferably, the heat absorber is made of a composite phase change material.

[0014] In this invention:

[0015] 1. Pre-set clamping mechanism: According to the size of the motor body, four clamping mechanisms are evenly set around the motor. The arc-shaped clamping plate is tightly attached to the motor shell by adjusting the studs, and the heat absorption block is in place.

[0016] 2. Start-up: After the motor starts, the heat generated during operation is quickly transferred to the heat absorption block and heat absorption plate through the contact surface;

[0017] 3. Phase change heat absorption: The composite phase change material inside the heat absorption block begins to absorb heat and undergo phase change after reaching the set temperature, which slows down the rate of temperature rise and forms a "thermal buffer" effect.

[0018] 4. Heat conduction and forced convection: The heat absorption plate conducts heat from the bottom to the fixed tube, and the cooling fan starts to exhaust the heat from the third opening, forming a forced convection heat dissipation path;

[0019] 5. Multi-layer filtration protection: Each layer of filter screen ensures efficient air circulation while effectively blocking dust and impurities, preventing blockage and pollution.

[0020] This invention achieves a dual heat dissipation mode of "passive plus active": initially, heat is absorbed by phase change materials to reduce the heat load, and later, heat is dissipated by forced cooling by fans. Under high temperature or high load operation, the "thermal buffer" effect of phase change materials can reduce the instantaneous temperature rise of the motor, avoiding power drop or protective shutdown due to overheating. The overall system design significantly improves the thermal stability and operating efficiency of the motor, thereby extending the flight time of the aircraft and achieving the goal of energy saving.

[0021] This invention is applicable to new low-altitude flight platforms such as unmanned aerial vehicles, vertical takeoff and landing aircraft (eVTOL), and urban air traffic (UAM). It can maintain stable operation even in harsh environments such as high temperature, high humidity, and dust. It is suitable for various mission scenarios such as fire fighting, rescue, inspection, and logistics. It can also be extended to fields with high thermal management requirements, such as electric aircraft power systems and vehicle motor systems.

[0022] The present invention has the following advantages:

[0023] 1. The heat absorption block uses phase change material, which can absorb a large amount of heat within a specific temperature range without significant temperature rise, thus achieving "thermal energy buffering". Compared with traditional metal materials, it has higher heat capacity and controllable thermal response capability.

[0024] 2. The upper clamp absorbs heat, the bottom heat absorption plate conducts heat, and the side fan forces convection, thus constructing a "three-dimensional heat dissipation" system. The multi-point contact design avoids local overheating and improves the overall thermal uniformity.

[0025] 3. Each heat absorption structure is connected to the insertion holes via insertion rods, making it easy to disassemble and replace. The filter design takes into account both heat dissipation and protection, extending the service life of the system.

[0026] 4. The adjusting structure of the moving ring and stud can be adapted to motors of different sizes, improving versatility and adaptability;

[0027] In summary, this invention breaks through the technical bottleneck of traditional air-cooled heat dissipation and realizes an efficient, stable and safe thermal management solution. Its application in the field of low-altitude aircraft motors not only solves the current heat dissipation problem under high power density, but also provides a solid foundation for the development of future high-performance electric propulsion systems. It can absorb a large amount of heat within a specific temperature range without significant temperature rise, achieving "thermal energy buffering". Compared with traditional metal materials, it has higher heat capacity and controllable thermal response capability. Attached Figure Description

[0028] Figure 1 This is a diagram of the internal structure of the present invention;

[0029] Figure 2 A structural diagram showing the clamping mechanism of the present invention;

[0030] Figure 3 This is a structural diagram showing the heat absorption plate and cooling fan of the present invention;

[0031] Figure 4 This is a diagram of the external structure of the present invention;

[0032] Figure 5 This is a diagram showing the insertion structure of the first filter screen and the heat absorption plate of the present invention;

[0033] Figure 6 A structural diagram of the third filter screen of the present invention.

[0034] In the diagram: 1. Arc-shaped clamping plate, 2. Fixing rod, 3. Moving ring, 4. Bearing plate, 5. Fixing tube, 6. Threaded blind hole, 7. Stud, 8. First opening, 9. Blade, 10. Protective shell, 11. Motor body, 12. Heat absorption block, 13. Pad, 14. First filter screen, 15. Heat absorption plate, 16. Second filter screen, 17. Insert rod, 18. Second opening, 19. Cooling fan, 20. Insertion hole, 21. Third filter screen, 22. Connecting block, 23. Third opening. Detailed Implementation

[0035] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0036] Reference Figure 1-6 An energy-saving motor for low-altitude aircraft with a heat dissipation structure includes a protective shell 10. The protective shell not only provides protection but also structural support and airflow guidance for the motor. The support plate 4 is made of high-strength lightweight alloy material (such as aerospace aluminum) and has a first opening 8 to facilitate the stable embedding of the motor body 11. At the same time, it realizes the heat conduction path with the heat absorption structure below. This through-type design makes the heat transfer path shorter and the heat conduction efficiency higher.

[0037] A support plate 4 is fixed inside the protective shell 10. The motor body 11 is installed on the upper end of the support plate 4. A fixing rod 2 is fixed around the upper end of the support plate 4. A clamping mechanism is movably connected to the fixing rod 2. The clamping mechanism adopts a modular design, supports quick installation and replacement, and is suitable for motor bodies 11 of different sizes.

[0038] One end of the clamping mechanism abuts against one side of the motor body 11. A fixing tube 5 is fixed to the lower end of the bearing plate 4. A heat-absorbing structure is installed inside the fixing tube 5. A cooling fan 19 is provided at the lower end of the heat-absorbing structure and is fixed to the side wall inside the fixing tube 5. The cooling fan 19 is a high-efficiency DC brushless fan. The DC brushless fan has the following characteristics:

[0039] Low power consumption, low noise, and long lifespan;

[0040] Intelligent speed control: The fan speed is automatically adjusted through a temperature feedback module;

[0041] Dustproof and waterproof design: suitable for dusty and humid environments;

[0042] Suitable for the complex environment of low-altitude aircraft, the third opening 23 is designed at the bottom of the protective shell, forming a heat dissipation path that combines natural convection and forced convection with bottom air intake and top air exhaust, improving the overall heat dissipation efficiency. Combined with the airflow effect during the flight of the aircraft, the third opening 23 can also serve as an aerodynamic auxiliary heat dissipation port to further enhance the heat dissipation capacity.

[0043] The clamping mechanism includes a movable ring 3 that runs through the fixed rod 2. An arc-shaped clamping plate 1 is fixed to one side of the movable ring 3, and a heat-absorbing block 12 is fixed to one side of the arc-shaped clamping plate 1. The heat-absorbing block 12 is filled with a composite phase change material (such as paraffin + metal foam composite material), which has high heat capacity and good thermal conductivity. When the motor generates heat during operation, the heat-absorbing block quickly absorbs the heat and undergoes a phase change (such as changing from solid to liquid), realizing a "thermal buffer" effect, delaying the sudden rise in motor temperature, and improving the stability of motor operation. The selection of phase change material can be customized according to the operating temperature range of the motor to achieve the best thermal management effect.

[0044] One end of the heat-absorbing block 12 abuts against one side of the motor body 11. The curvature design of the arc-shaped clamping plate 1 matches the contour of the motor housing, enhancing clamping stability and thermal contact area.

[0045] A stud 7 is provided through one side of the moving ring 3, and multiple threaded blind holes 6 are provided at equal intervals along the vertical direction on one side of the fixed rod 2. One end of the stud 7 is threaded into one of the threaded blind holes 6. A connecting block 22 is fixed on one side of the stud 7. By adjusting the fit between the stud 7 and the multiple threaded blind holes 6, a precise fit to the motor housing can be achieved, ensuring that there is no gap between the heat absorption block 12 and the motor surface, thereby improving the heat conduction efficiency.

[0046] The support plate 4 has a first opening 8, and the lower end of the motor body 11 is snapped into the first opening 8. The first opening 8 is connected to the fixing pipe 5. The fan control circuit is equipped with a temperature feedback control module, which can automatically adjust the fan speed according to the motor temperature to achieve dual optimization of energy saving and noise reduction.

[0047] The load-bearing plate and the protective shell are fixed by a combination of silicone pads and bolts, which not only ensures structural strength but also has a certain shock absorption and buffering effect to prevent the motor from loosening due to flight vibration.

[0048] The heat absorption structure includes a pad 13 fixed inside the fixed tube 5. A first filter screen 14 is fastened to the upper end of the pad 13. A heat absorption plate 15 is fastened to the upper end of the first filter screen 14. A second filter screen 16 is fastened to the upper end of the heat absorption plate 15. The heat absorption plate 15 is made of a high thermal conductivity alloy material (copper-aluminum composite plate). Its surface can be designed with microchannels to increase the heat conduction area. The pad 13 plays a supporting and heat insulation role to prevent the bottom heat from being conducted back to the aircraft structure. The insertion method of the plug rod 17 and the plug hole 20 is easy to disassemble and replace, which is convenient for later maintenance and cleaning. The multi-layer filter design not only improves the air circulation efficiency, but also effectively prevents dust and impurities from entering the core heat dissipation system and extends the service life of the equipment.

[0049] The pad 13, the first filter screen 14 and the heat absorption plate 15 are provided with insertion holes 20 on both sides. The lower end of the second filter screen 16 is fixed with insertion rods 17 on both sides. One insertion rod 17 on the same side passes through multiple insertion holes 20 on the same side. The first filter screen 14 and the second filter screen 16 adopt a composite structure of stainless steel mesh and activated carbon.

[0050] The third filter 21 uses a honeycomb porous metal mesh and can be equipped with an electrostatic dust removal layer or a nano-photocatalytic coating to adsorb pollutants such as PM2.5 particles and harmful gases.

[0051] The lower end of the protective shell 10 is provided with a third opening 23, and a third filter 21 is installed in the third opening 23. The filter uses a porous metal mesh or honeycomb structure filter material, which has both high permeability and high filtration efficiency. An electrostatic dust removal layer or an activated carbon adsorption layer can be selected to adsorb fine particulate matter or harmful gases inhaled during flight. Regular cleaning or replacement of the filter can maintain the long-term high-efficiency operation of the system, which is especially suitable for urban low-altitude flight environment and prevents dust accumulation from affecting heat dissipation performance.

[0052] An output shaft is mounted on the motor body 11. The output shaft passes through the side wall of the protective shell 10 and extends to the upper end of the protective shell 10. A blade 9 is fixed at the upper end of the output shaft. The output shaft is supported by high-precision bearings to reduce operating friction and heat generation. The blade 9 is made of carbon fiber composite material, which has high strength, lightweight and low wind resistance characteristics, improving the overall efficiency of the aircraft. The connection structure between the output shaft and the blade should have a dynamic balance design to prevent structural fatigue and uneven heat distribution caused by operating vibration.

[0053] The heat absorber block 12 is made of composite phase change material (paraffin + metal foam composite material), which has high heat capacity and good thermal conductivity. It quickly absorbs heat in the early stage of motor start-up, realizing a "thermal buffer" effect and preventing a sudden temperature rise.

[0054] It has the following benefits:

[0055] High heat capacity: rapidly absorbs heat during the initial startup phase of the motor;

[0056] Controllable phase change temperature: Phase change materials can be customized according to the motor's operating temperature (such as adding graphene to improve thermal conductivity);

[0057] Buffer temperature rise: Prevents the motor from degrading due to a sudden increase in temperature;

[0058] Modular replacement: facilitates later maintenance and material upgrades.

[0059] In this invention:

[0060] 1. Pre-set clamping mechanism: According to the size of the motor body 11, four clamping mechanisms are evenly arranged around the motor. By adjusting the studs 7, the arc-shaped clamping plate 1 is tightly attached to the motor shell, and the heat absorption block 12 is in contact with the motor.

[0061] 2. Start-up: After the motor starts, the heat generated during operation is quickly transferred to the heat absorption block 12 and the heat absorption plate 15 through the contact surface;

[0062] 3. Phase change heat absorption: The composite phase change material inside the heat absorption block 12 begins to absorb heat and undergo phase change after reaching the set temperature, which slows down the rate of temperature rise and forms a "thermal buffer" effect.

[0063] 4. Heat conduction and forced convection: The heat absorption plate 15 conducts heat from the bottom to the fixed tube 5, and the cooling fan 19 starts to exhaust the heat from the third opening 23, forming a forced convection heat dissipation path.

[0064] 5. Multi-layer filtration protection: Each layer of filter screen ensures efficient air circulation while effectively blocking dust and impurities, preventing blockage and pollution.

[0065] This invention achieves a dual heat dissipation mode of "passive plus active": initially, heat is absorbed by phase change materials to reduce the heat load, and later, heat is dissipated by forced heat dissipation through fans. Under high temperature or high load operation, the "thermal buffer" effect of phase change materials can reduce the instantaneous temperature rise of the motor, avoid power drop or protective shutdown due to overheating. The overall system design significantly improves the thermal stability and operating efficiency of the motor, thereby extending the flight time of the aircraft and achieving the purpose of energy saving.

[0066] This invention is applicable to new low-altitude flight platforms such as unmanned aerial vehicles, vertical takeoff and landing aircraft (eVTOL), and urban air traffic (UAM). It can maintain stable operation even in harsh environments such as high temperature, high humidity, and dust. It is suitable for various mission scenarios such as fire fighting, rescue, inspection, and logistics. It can also be extended to fields with high thermal management requirements, such as electric aircraft power systems and vehicle motor systems.

[0067] This invention not only introduces a combined heat dissipation structure of clamped heat-absorbing block + bottom heat-absorbing plate + fan in its structural design, but also uses composite phase change material as the key heat-absorbing element, achieving a "thermal buffering" effect and overcoming the limitations of traditional metal fin + fan heat dissipation. Therefore, this invention has significant advantages in terms of heat capacity, thermal response control, and temperature rise suppression.

[0068] The above are merely preferred embodiments 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 solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A low-altitude aircraft energy-saving motor with a heat dissipation structure, comprising a protective shell (10), characterized in that, The protective shell (10) has a bearing plate (4) fixed inside. The upper end of the bearing plate (4) is equipped with a motor body (11). A fixing rod (2) is fixed around the upper end of the bearing plate (4). A clamping mechanism is movably connected to the fixing rod (2). One end of the clamping mechanism abuts against one side of the motor body (11). A fixing tube (5) is fixed at the lower end of the bearing plate (4). A heat-absorbing structure is installed inside the fixing tube (5). A cooling fan (19) is provided at the lower end of the heat-absorbing structure. The cooling fan (19) is fixed on the side wall inside the fixing tube (5). The clamping mechanism includes a movable ring (3) that passes through the fixed rod (2), an arc-shaped clamping plate (1) is fixed on one side of the movable ring (3), a heat-absorbing block (12) is fixed on one side of the arc-shaped clamping plate (1), and one end of the heat-absorbing block (12) abuts against one side of the motor body (11). A stud (7) is provided through one side of the moving ring (3), and a plurality of threaded blind holes (6) are provided at equal intervals along the vertical direction on one side of the fixed rod (2). One end of the stud (7) is threaded into one of the threaded blind holes (6), and a connecting block (22) is fixed on one side of the stud (7). The heat absorption structure includes a pad (13) fixed inside the fixed tube (5), a first filter screen (14) is fastened to the upper end of the pad (13), a heat absorption plate (15) is fastened to the upper end of the first filter screen (14), and a second filter screen (16) is fastened to the upper end of the heat absorption plate (15). The heat absorber (12) is made of composite phase change material.

2. The energy-saving motor of the low-altitude aircraft with the heat-dissipation structure according to claim 1, characterized in that: The bearing plate (4) is provided with a first opening (8), and the lower end of the motor body (11) is engaged in the first opening (8). The first opening (8) is connected to the fixing tube (5).

3. The energy-saving motor of the low-altitude aircraft with the heat-dissipation structure according to claim 1, characterized in that: The pad (13), the first filter screen (14) and the heat absorption plate (15) are provided with insertion holes (20) on both sides. The lower end of the second filter screen (16) is fixed with insertion rods (17) on both sides. One insertion rod (17) on the same side passes through multiple insertion holes (20) on the same side.

4. The energy-saving motor of a low-altitude aerial vehicle with a heat dissipation structure according to claim 1, characterized in that: The lower end of the protective shell (10) is provided with a third opening (23), and a third filter screen (21) is installed in the third opening (23).

5. The energy-saving motor of a low-altitude aerial vehicle with a heat dissipation structure according to claim 1, characterized in that: An output shaft is installed on the motor body (11). The output shaft passes through the side wall of the protective shell (10) and extends to the upper end of the protective shell (10). A blade (9) is fixed to the upper end of the output shaft.

Images