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

Abstract

The invention discloses a low-altitude aircraft energy-saving motor with a heat dissipation structure, and relates to the technical field of energy-saving motors, the low-altitude aircraft energy-saving motor comprises a protective shell, a bearing plate is fixed in the protective shell, a motor body is mounted at the upper end of the bearing plate, a fixing rod is fixed on the periphery of the upper end of the bearing plate, and a clamping mechanism is movably connected to the fixing rod; one end of the clamping mechanism abuts against one side of the motor body, a fixing pipe is fixed to the lower end of the bearing plate, and a heat absorption structure is installed in the fixing pipe. The technical bottleneck of traditional air cooling heat dissipation is broken through, an efficient, stable and safe heat management scheme is achieved, the heat dissipation problem under the current high power density is solved by applying the heat dissipation device to the field of low-altitude aircraft motors, a solid foundation is provided for development of a high-performance electric propulsion system in the future, and the application range is wide. The composite material can absorb a large amount of heat in a specific temperature range without obvious temperature rise, achieves heat energy buffering, and has higher heat capacity and controllable thermal response capacity compared with a traditional metal material.

Description

Technical Field

[0001] The present invention relates to the technical field of energy-saving motors, and in particular to an energy-saving motor for low-altitude aircraft with a heat dissipation structure. Background Art

[0002] With the rapid development of low-altitude aircraft such as electric vertical take-off and landing aircraft, motors, as their core power components, are facing unprecedented performance requirements. Especially in high power density (such as 300W / cm 2 Under these operating conditions, traditional air-cooling technology has gradually exposed problems such as low thermal conductivity (typically <50W / m·K), insufficient heat dissipation efficiency, and excessive temperature rise. The aluminum housing can heat up to over 80°C under prolonged, high-load operation. This not only affects motor efficiency but can also lead to serious safety hazards such as magnetic demagnetization, insulation failure, and shortened lifespan. To address these issues, we have proposed an energy-saving motor with a heat dissipation structure for low-altitude aircraft. Summary of the Invention

[0003] The purpose of the present invention is to solve the shortcomings of the prior art and to propose an energy-saving motor for low-altitude aircraft with a heat dissipation structure.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions:

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

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

[0007] Preferably, a stud is provided through one side of the movable ring, a plurality of 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, a first opening is provided on the supporting plate, the lower end of the motor body is clamped in the first opening, and the first opening is communicated with the fixing pipe.

[0009] Preferably, the heat absorption structure includes a pad fixed in the fixed tube, the upper end of the pad is buckled with a first filter, the upper end of the first filter is buckled with a heat absorption plate, and the upper end of the heat absorption plate is buckled with a second filter.

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

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

[0012] Preferably, an output shaft is mounted on the motor body, the output shaft passes through 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 absorption block is made of composite phase change material.

[0014] In the present invention:

[0015] 1. Preset clamping mechanism: According to the size of the motor body, four clamping mechanisms are evenly arranged around the motor. By adjusting the studs, the arc-shaped clamping plate is tightly fitted to the motor housing and the heat absorption block is in place;

[0016] 2. Start running: After the motor starts, the heat generated during operation is quickly transferred to the heat absorbing block and the heat absorbing 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 phase change after reaching the set temperature, slowing down the temperature rise rate and forming a "thermal buffer" effect;

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

[0019] 5. Multi-layer filtration protection: Each layer of filter not only ensures the air circulation efficiency, but also effectively blocks dust and impurities to prevent blockage and pollution.

[0020] The present invention realizes a dual heat dissipation mode of "passive plus active": in the initial stage, heat load is reduced by absorbing heat through phase change materials, and in the later stage, heat is discharged through forced heat dissipation by fans. Under high temperature or high load operating conditions, the "thermal buffering" effect of the phase change material 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 purpose of energy saving.

[0021] The present invention is suitable for new low-altitude flight platforms such as drones, vertical take-off and landing vehicles (eVTOL), and urban air traffic (UAM). It can maintain stable operation in harsh environments such as high temperature, high humidity, and dust. It is suitable for various mission scenarios such as firefighting, rescue, inspection, and logistics. It can be expanded to areas with high thermal management requirements such as electric aircraft power systems and vehicle-mounted motor systems.

[0022] The present invention has the following advantages:

[0023] 1. The heat absorption block adopts phase change material, which can absorb a large amount of heat within a specific temperature range without significant temperature increase, realizing "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 absorbing plate conducts heat, and the side fan forces convection, building a "three-dimensional heat dissipation" system. The multi-point contact design avoids local overheating and improves overall thermal uniformity.

[0025] 3. Each layer of heat absorption structure is connected by a plug-in rod and a socket, which is convenient for disassembly and replacement. The filter design takes into account both heat dissipation and protection, thus extending the service life of the system.

[0026] 4. The movable ring and stud adjustment structure can adapt to motors of different sizes, improving versatility and adaptability;

[0027] In summary, the present 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 increase, realizing "thermal energy buffering". Compared with traditional metal materials, it has higher heat capacity and controllable thermal response capabilities. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0029] Figure 2 It is a structural diagram of the clamping mechanism of the present invention;

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

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

[0032] Figure 5 This is a diagram showing the plug-in structure of the first filter screen and the heat absorbing plate of the present invention;

[0033] Figure 6 This is a structural diagram of the third filter screen of the present invention.

[0034] In the figure: 1 arc-shaped clamping plate, 2 fixing rod, 3 movable 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 absorbing block, 13 backing plate, 14 first filter, 15 heat absorbing plate, 16 second filter, 17 insertion rod, 18 second opening, 19 cooling fan, 20 jack, 21 third filter, 22 connecting block, 23 third opening. DETAILED DESCRIPTION

[0035] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0036] Reference Figure 1-6 An energy-saving motor for low-altitude aircraft with a heat dissipation structure includes a protective shell 10, which not only protects the motor but also provides structural support and airflow guidance. A carrier plate 4, made of a high-strength, lightweight alloy (such as aviation aluminum), is provided with a first opening 8, which facilitates the secure insertion of the motor body 11 and establishes a heat conduction path with the underlying heat-absorbing structure. This top-to-bottom design shortens the heat transfer path and improves heat conduction efficiency.

[0037] A carrier plate 4 is fixed inside the protective shell 10, and a motor body 11 is mounted on the upper end of the carrier plate 4. A fixing rod 2 is fixed around the upper end of the carrier 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 contacts one side of the motor body 11. A fixed tube 5 is fixed to the lower end of the carrier plate 4. A heat absorbing structure is installed in the fixed tube 5. A cooling fan 19 is provided at the lower end of the heat absorbing structure. The cooling fan 19 is fixed to the side wall of the fixed tube 5. The cooling fan 19 is a high-efficiency DC brushless fan with the following characteristics:

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

[0040] Intelligent speed control: automatic adjustment of fan speed is achieved through temperature feedback module;

[0041] Dust-proof and waterproof design: suitable for dusty and humid environments;

[0042] Suitable for the complex environments of low-altitude aircraft, the third opening 23 is designed to be located at the bottom of the protective shell, forming a heat dissipation path that combines natural convection with forced convection, with air entering from the bottom and exhausting from the top, thereby improving overall heat dissipation efficiency. Combined with the airflow effect during flight, the third opening 23 can also serve as an aerodynamic auxiliary heat dissipation vent, further enhancing heat dissipation capacity.

[0043] The clamping mechanism includes a movable ring 3 that is arranged on 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) with 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 from solid to liquid), achieving 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 optimal thermal management effect;

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

[0045] A stud 7 is provided through one side of the movable 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 screwed into one of the threaded blind holes 6, and a connecting block 22 is fixed to one side of the stud 7. By adjusting the coordination between the stud 7 and the plurality of threaded blind holes 6, a precise fit with the motor housing can be achieved, ensuring gapless contact between the heat absorbing block 12 and the motor surface, thereby improving heat conduction efficiency.

[0046] The carrier plate 4 is provided with a first opening 8, and the lower end of the motor body 11 is clamped in the first opening 8. The first opening 8 is connected to the fixing tube 5. The fan control circuit is provided with a temperature feedback control module, which can automatically adjust the fan speed according to the motor temperature, thereby achieving dual optimization of energy saving and noise reduction.

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

[0048] The heat absorption structure includes a pad 13 fixed in the fixed tube 5, the upper end of the pad 13 is buckled with a first filter 14, the upper end of the first filter 14 is buckled with a heat absorbing plate 15, and the upper end of the heat absorbing plate 15 is buckled with a second filter 16. The heat absorbing plate 15 is made of a high thermal conductivity alloy material (copper-aluminum composite plate), and its surface can be designed with microchannels to increase the heat conduction area. The pad 13 plays a supporting and heat-insulating role to prevent the bottom heat from being reversely conducted to the aircraft structure. The plug-in connection method of the plug rod 17 and the socket 20 is convenient for disassembly and replacement, and facilitates subsequent 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, thereby extending the service life of the equipment.

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

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

[0051] A third opening 23 is provided at the lower end of the protective shell 10. A third filter 21 is installed in the third opening 23. The filter is made of porous metal mesh or honeycomb structure filter material, which has both high permeability and high filtration efficiency. An electrostatic dust removal layer or activated carbon adsorption layer can be optionally provided to absorb fine particles or harmful gases inhaled during flight. Regular cleaning or replacement of the filter can maintain the long-term and efficient operation of the system. It is particularly suitable for low-altitude flight environments in cities to prevent 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. The upper end of the output shaft is fixed with a blade 9. The output shaft is supported by a high-precision bearing to reduce operating friction and heat generation. The blade 9 is made of carbon fiber composite material, which has high strength, light weight and low wind resistance, thereby 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 absorbing block 12 is made of composite phase change material (paraffin + metal foam composite material), which has high heat capacity and good thermal conductivity. It absorbs heat quickly at the initial start-up of the motor, achieving a "thermal buffer" effect to prevent a sudden temperature rise:

[0054] It has the following benefits:

[0055] High thermal capacity: quickly absorbs heat at the initial start-up 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] Buffering temperature rise: Preventing motor performance degradation due to sudden temperature rise;

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

[0059] In the present invention:

[0060] 1. Preset 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 fitted to the motor housing and the heat absorbing block 12 is in contact with the motor housing.

[0061] 2. Start operation: After the motor starts, the heat generated during operation is quickly transferred to the heat absorbing block 12 and the heat absorbing 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 phase change after reaching the set temperature, slowing down the temperature rise rate and forming a "thermal buffer" effect;

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

[0064] 5. Multi-layer filtration protection: Each layer of filter not only ensures the air circulation efficiency, but also effectively blocks dust and impurities to prevent blockage and pollution.

[0065] The present invention achieves a dual "passive plus active" heat dissipation mode: initially, heat is absorbed by the phase change material to reduce the thermal load, and later, heat is forced out through the fan. Under high-temperature or high-load operating conditions, the "thermal buffer" effect of the phase change material can reduce the instantaneous temperature rise of the motor, avoiding power reduction 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 energy conservation.

[0066] The present invention is suitable for new low-altitude flight platforms such as drones, vertical take-off and landing vehicles (eVTOL), and urban air traffic (UAM). It can maintain stable operation in harsh environments such as high temperature, high humidity, and dust. It is suitable for various mission scenarios such as firefighting, rescue, inspection, and logistics. It can be expanded to areas with high thermal management requirements such as electric aircraft power systems and vehicle-mounted motor systems.

[0067] This invention not only incorporates a combined heat dissipation structure of a clamped heat sink, a bottom heat absorbing plate, and a fan, but also utilizes a composite phase-change material as a key heat-absorbing element, achieving a "thermal buffering" effect and overcoming the limitations of traditional metal fins and fan heat dissipation. As a result, this invention offers significant advantages in terms of heat capacity, thermal response control, and temperature rise suppression.

[0068] The above are only preferred specific embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field, within the technical scope disclosed by the present invention, who makes equivalent replacements or changes based on the technical solutions and inventive concepts of the present invention, should be covered by 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: A carrying plate (4) is fixed in the protective shell (10), a motor body (11) is installed on the upper end of the carrying plate (4), a fixing rod (2) is fixed around the upper end of the carrying 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 carrying plate (4), a heat absorption structure is installed in the fixing tube (5), a cooling fan (19) is provided at the lower end of the heat absorption structure, and the cooling fan (19) is fixed on the side wall inside the fixing tube (5).

2. The low-altitude aircraft energy-saving motor with a heat dissipation structure according to claim 1, characterized in that: The clamping mechanism comprises a moving ring (3) penetrating and arranged on a fixed rod (2); an arc-shaped clamping plate (1) is fixed on one side of the moving 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).

3. The low-altitude aircraft energy-saving motor with a heat dissipation structure according to claim 2, characterized in that: A stud (7) is provided through one side of the movable 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 threadedly screwed into one of the threaded blind holes (6), and a connecting block (22) is fixed on one side of the stud (7).

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

5. The low-altitude aircraft energy-saving motor with a heat dissipation structure according to claim 1, characterized in that: The heat absorption structure comprises a backing plate (13) fixed in the fixed tube (5), the upper end of the backing plate (13) is buckled with a first filter (14), the upper end of the first filter (14) is buckled with a heat absorption plate (15), and the upper end of the heat absorption plate (15) is buckled with a second filter (16).

6. The energy-saving motor for low-altitude aircraft with a heat dissipation structure according to claim 5, characterized in that: Insertion holes (20) are provided on both sides of the backing plate (13), the first filter screen (14) and the heat absorbing plate (15); insertion rods (17) are fixed on both sides of the lower end of the second filter screen (16); and one insertion rod (17) on the same side passes through multiple insertion holes (20) on the same side.

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

8. The low-altitude aircraft energy-saving motor with a heat dissipation structure according to claim 1, characterized in that: 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), and a blade (9) is fixed to the upper end of the output shaft.

9. The low-altitude aircraft energy-saving motor with a heat dissipation structure according to claim 2, characterized in that: The heat absorption block (12) is made of composite phase change material.

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