A brushless motor for a dual mode aircraft and a dual mode aircraft

Abstract

The application discloses a brushless motor for a dual-mode aircraft and the dual-mode aircraft, and the brushless motor comprises an outer rotor and a stator, the outer rotor is rotatably installed on the stator; the stator comprises a stator base and an iron core, the iron core is sleeved on the stator base, and the stator base is provided with a positioning assembly for positioning the iron core; a plurality of heat dissipation fins are integrally arranged on the inner ring wall of the iron core, and the stator base is provided with heat dissipation air ducts matched with the heat dissipation fins; the outer rotor is provided with a fan assembly, and the fan assembly can suck air flow at the lower end of the stator base into the heat dissipation air ducts and then spray out from the upper end of the stator base to take away the heat on the heat dissipation fins when the fan assembly is in operation. The application can eliminate the heat conduction gap, reduce the thermal resistance of heat conduction, and effectively improve the heat dissipation effect by integrally forming a plurality of heat dissipation fins on the inner ring wall of the iron core.

Description

Technical Field

[0001] This invention relates to the field of brushless motors and aircraft technology, specifically to a brushless motor for a dual-mode aircraft and a dual-mode aircraft. Background Technology

[0002] Dual-mode aircraft possess both visual and lidar modes, thus enabling them to have excellent environmental perception and autonomous navigation capabilities. In aircraft, the motor is a key component of the power system, determining the reliability of the aircraft.

[0003] A brushless motor consists of a motor body and a driver, and is a typical mechatronic product. Because brushless DC motors operate under self-control, they do not require an additional starting winding on the rotor like synchronous motors under heavy load starting with frequency conversion speed regulation, nor do they experience oscillations or loss of synchronization during sudden load changes. Therefore, they are widely used in various fields. The main body of an existing brushless motor includes a stator and a rotor. The rotor of a brushless motor can be configured as an external rotor or an internal rotor. Brushless motors generate heat during operation, requiring effective heat dissipation to ensure optimal operating conditions. The main heat sources during brushless motor operation are iron losses generated by the core and copper losses generated by the windings, with copper losses from the windings having the greatest impact. Typically, motor performance depends on its heat dissipation capacity; to improve power density, air cooling is usually employed.

[0004] However, existing external rotor brushless motors have the following problems: For external rotor brushless motors, there are already designs that use fins for heat dissipation inside the motor. However, the fins and stator are integrated. Due to the process requirements of motor assembly, there must be a certain gap between the inner wall of the stator outer ring wall and the outer ring wall of the stator when the inner wall of the iron core coil, the only heat source of the motor, contacts and fits with the outer ring wall of the stator. This gap directly and greatly increases the thermal resistance of heat transfer between the two walls, seriously affecting the heat transfer effect. Summary of the Invention

[0005] The problem to be solved by the present invention is to provide a brushless motor for a dual-mode aircraft and a dual-mode aircraft. By integrally forming a number of heat dissipation fins on the inner ring wall of the iron core, the heat conduction gap can be eliminated, the thermal resistance of heat transfer can be reduced, and the heat dissipation effect can be effectively improved.

[0006] The technical solution provided by the present invention to solve the above problems is as follows: a brushless motor for a dual-mode aircraft, comprising an outer rotor and a stator, wherein the outer rotor is rotatably mounted on the stator; the stator comprises a stator base and an iron core, wherein the iron core is fitted on the stator base, and the stator base is provided with a positioning component for positioning the iron core;

[0007] The inner ring wall of the iron core is integrally provided with several heat dissipation fins, and the stator base is provided with heat dissipation air ducts that cooperate with the heat dissipation fins.

[0008] The outer rotor is equipped with a fan assembly. When the fan assembly is running, it draws the airflow located at the lower end of the stator base into the heat dissipation duct and then ejects it through the upper end of the stator base, thereby carrying away the heat from the heat dissipation fins.

[0009] Preferably, a plurality of the heat dissipation fins are arranged in a ring array on the inner wall of the iron core.

[0010] Preferably, an enhanced heat dissipation ring is provided at one end of the heat dissipation fins away from the inner ring wall of the iron core.

[0011] Preferably, the heat dissipation ring and the heat dissipation fins are integrally formed.

[0012] Preferably, the stator base is provided with a partition ring, which divides the interior of the stator base into an inner ring and an outer ring. The inner ring is closed, so that air only flows through the outer ring area.

[0013] Preferably, the inner ring wall of the iron core cooperates with the partition ring to form the heat dissipation duct.

[0014] Preferably, the positioning component includes an axial positioning component and a rotational positioning component, wherein the axial positioning component is used for axial positioning of the iron core, and the rotational positioning component is used for rotational positioning of the iron core.

[0015] Preferably, the rotation positioning assembly includes a plurality of slots and a plurality of positioning plates. The plurality of slots are axially disposed on the inner ring wall of the heat dissipation ring, and the plurality of positioning plates are integrally disposed on the outer ring wall of the partition ring. The end of the positioning plate away from the partition ring cooperates with the slot to achieve rotation positioning of the iron core.

[0016] Preferably, the axial positioning assembly includes a spring, a push rod, and a locking block. The upper end of the positioning plate is provided with a mounting cavity for installing the axial positioning assembly. One end of the spring is fixedly connected to the cavity wall of the mounting cavity, and the other end is fixedly connected to the push rod. The locking block is disposed on the side of the push rod away from the spring. One end of the locking block extends through the mounting cavity and out of the positioning plate. An inclined surface is provided on the upper end surface of the locking block.

[0017] The present invention also discloses a dual-mode aircraft, including a brushless motor for a dual-mode aircraft as described in any of the above claims.

[0018] Compared with the prior art, the advantages of the present invention are: by integrally forming a number of heat dissipation fins on the inner ring wall of the iron core, the present invention can eliminate the heat conduction gap, reduce the thermal resistance of heat transfer, and thus effectively improve the heat dissipation effect. Attached Figure Description

[0019] The accompanying drawings, which are provided to further illustrate the invention and constitute a part of this invention, are illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention.

[0020] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0021] Figure 2 This is a schematic diagram of the explosion mechanism of the present invention;

[0022] Figure 3 This is a top view of the iron core of the present invention;

[0023] Figure 4 This is a top view of the mating of the iron core and stator base of the present invention;

[0024] Figure 5 yes Figure 4 Enlarged structural diagram at point A;

[0025] Figure 6 This is a cross-sectional view of the axial positioning component of the present invention.

[0026] The attached diagram is labeled as follows: 1. Outer rotor, 2. Air outlet, 3. Stator base, 4. Heat dissipation fins, 5. Iron core, 6. Push rod, 7. Locking block, 8. Positioning plate, 9. Separating ring, 10. Enhanced heat dissipation ring, 11. Slot, 12. Inclined surface, 13. Heat dissipation duct, 14. Spring, 15. Mounting cavity, 16. Inner ring. Detailed Implementation

[0027] The following will describe in detail the implementation of the present invention with reference to the accompanying drawings and embodiments, so that the process of how the present invention uses technical means to solve technical problems and achieve technical effects can be fully understood and implemented accordingly.

[0028] In the description of this invention, it should be noted that the directional terms such as "center", "lateral", "longitudinal", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", and "counterclockwise" indicate the orientation and positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. They should not be construed as limiting the specific protection scope of this invention.

[0029] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features. Thus, the use of "first" and "second" to define a feature may explicitly or implicitly include one or more of that feature, and in the description of this invention, "a number" means two or more, unless otherwise explicitly specified.

[0030] In this invention, unless otherwise explicitly specified and limited, the terms "assembly," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can also refer to a mechanical connection; they can refer to a direct connection or a connection through an intermediate medium; or they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0031] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0032] It should also be understood that the terminology used in this specification of embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to limit the embodiments of the invention. As used in this specification of embodiments of the invention and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise. Example 1

[0033] like Figures 1-6 As shown, a brushless motor for a dual-mode aircraft includes an outer rotor 1 and a stator, wherein the outer rotor 1 is rotatably mounted on the stator; the stator includes a stator base 3 and an iron core 5, wherein the iron core 5 is fitted on the stator base 3, and the stator base 3 is provided with a positioning component for positioning the iron core 5.

[0034] The inner ring wall of the iron core 5 is integrally provided with a plurality of heat dissipation fins 4, and the stator base 3 is provided with heat dissipation air ducts 13 that cooperate with the heat dissipation fins 4.

[0035] A fan assembly is provided on the outer rotor 1. When the fan assembly is running, it draws the airflow located at the lower end of the stator base 3 into the heat dissipation duct 13 and then ejects it through the upper end of the stator base 3 to remove the heat from the heat dissipation fins 4. The fan assembly specifically includes a centrifugal fan and an air outlet. Both the centrifugal fan and the air outlet are located at the upper end of the outer rotor. When the centrifugal fan rotates, it draws the airflow located at the lower end of the stator base 3 into the heat dissipation duct 13 and then ejects it through the air outlet 2 to remove the heat from the heat dissipation fins 4.

[0036] In the above scheme, by integrally forming several heat dissipation fins on the inner ring wall of the iron core (the heat generated by the iron core and the coil can be directly conducted to the heat dissipation fins), the heat conduction gap can be eliminated, the thermal resistance of heat transfer can be reduced, and the heat dissipation effect can be effectively improved.

[0037] Specifically, several of the heat dissipation fins 4 are arranged in a ring array on the inner wall of the iron core 5; and as shown in the figure Figure 2 As shown, in this embodiment, an enhanced heat dissipation ring 10 is provided at one end of the plurality of heat dissipation fins 4 away from the inner wall of the iron core 5; and the enhanced heat dissipation ring 10 and the heat dissipation fins 4 are integrally formed. It should be noted that in this solution, the iron core, heat dissipation fins and enhanced heat dissipation ring are made of the same material, which can further improve the heat transfer effect.

[0038] In the above scheme, the heat-enhancing ring 10 can, on the one hand, increase the heat dissipation area of ​​the iron core 5 as a heat dissipation component (both the inner and outer ring walls of the heat-enhancing ring 10 can serve as heat dissipation surfaces). On the other hand, the heat-enhancing ring 10 can provide a stable protection for the heat dissipation fins 4, preventing a portion of the heat dissipation fins 4 from being individually bumped and deformed during assembly, thus improving assembly stability. Furthermore, the heat-enhancing ring 10 also serves as a positioning component, achieving the positioning of the iron core 5 through the cooperation of the positioning component and the heat-enhancing ring 10.

[0039] It should be noted that the heating elements of the motor, namely the iron core and coil windings, have temperature sensors installed at multiple locations along the circumference. Multiple sensors are also installed near the motor shaft bearings, and a temperature sensor is also integrated on the outside of the motor. In this way, the operating status of the motor can be judged by combining temperature data from different locations inside the motor and atmospheric temperature data.

[0040] For example, such as Figure 3As shown, a partition ring 9 is provided on the stator base 3, which divides the interior of the stator base 3 into an inner ring 16 and an outer ring. The inner ring 16 is closed, allowing air to flow only through the outer ring area. The inner wall of the iron core 5 cooperates with the partition ring 9 to form the heat dissipation duct 13. When the centrifugal fan integrated in the outer rotor of the motor operates at high speed, air is drawn in from the heat dissipation duct 13. Before the partition ring 9 is provided, the high-speed airflow is located in the area near the inner side of the stator base 3, because the heat dissipation fins 4 cannot fill the cavity area on the stator base 3, resulting in a very low airflow velocity through the heat dissipation fins 4. The cavity area on the outer side of the partition ring 9 is the main placement area for the heat dissipation fins 4. The partition ring 9 is added to reduce the cross-sectional area of ​​the airflow channel through each cavity, and the airflow velocity through the heat dissipation fins 4 is increased after the partition ring 9 is provided, thereby increasing the heat conduction efficiency between the air and the heat dissipation fins 4.

[0041] In this embodiment, the positioning component includes an axial positioning component and a rotational positioning component. The axial positioning component is used to axially position the iron core 5, and the rotational positioning component is used to rotate the iron core 5.

[0042] Specifically, such as Figure 4 , Figure 5 and Figure 6 As shown, the rotation positioning assembly includes several slots 11 and several positioning plates 8. The slots 11 are axially arranged on the inner wall of the heat dissipation ring 10, and the positioning plates 8 are integrally arranged on the outer wall of the partition ring 9. The end of the positioning plate 8 away from the partition ring 9 cooperates with the slot 11 to achieve rotational positioning of the iron core 5. The axial positioning assembly includes a spring 14, a push rod 6, and a locking block 7. The upper end of the positioning plate 8 is provided with a mounting cavity 15 for installing the axial positioning assembly. One end of the spring 14 is fixedly connected to the cavity wall of the mounting cavity 15, and the other end is fixedly connected to the push rod 6. The locking block 7 is arranged on the side of the push rod 6 away from the spring 14. One end of the locking block 7 extends through the mounting cavity 15 and out of the positioning plate 8. An inclined surface 12 is provided on the upper surface of the locking block 7. In this scheme, the cooperation between the positioning plate 8 on the separator ring 9 and the slot 11 on the heat dissipation ring 10 can achieve the rotational positioning of the iron core 5. On the other hand, through the contact between the positioning plate 8 and the heat dissipation ring 10, a part of the heat on the heat dissipation ring 10 can be conducted to the separator ring 9 and the positioning plate 8. The outer wall of the separator ring 9 and the positioning plate 8 are also within the heat dissipation channel 13. Therefore, the heat dissipation performance of the iron core 5 and the coil can be further improved.

[0043] In the above scheme, the specific disassembly and assembly process of the iron core 5 is as follows: During installation, first align the slot 11 of the heat-dissipating ring 10 on the iron core 5 with the positioning plate 8 on the stator seat 3, and then insert the iron core 5 from top to bottom onto the stator seat 3 (during the insertion of the iron core 5, the lower end of the heat-dissipating ring 10 contacts the inclined surface 12 of the upper end face of the locking block 7, pressing the locking block 7 into the mounting cavity 15), until the lower end of the iron core 5 contacts the positioning step at the lower end of the stator seat 3. At this time, the locking block 7 is no longer held by the inner ring wall of the heat-dissipating ring 10. Under the action of the spring 14, the locking block 7 extends out from the mounting cavity 15 and abuts against the upper end face of the heat-dissipating ring 10, thereby completing the axial positioning of the iron core 5; During disassembly, first press the push rod 6 and push the push rod 6 in the direction of compressing the spring 14 until the locking block 7 is completely retracted into the mounting cavity 15, and then the iron core 5 can be removed.

[0044] The heat dissipation method of the present invention can significantly improve contact thermal resistance, make the temperature uniformly distributed, reduce the temperature gradient difference between the circumferential and axial directions, and eliminate local high-temperature dead zones. Compared with conventional passive heat dissipation schemes and indirect contact heat dissipation module heat dissipation schemes, the heat dissipation capacity is greatly improved.

[0045] In this embodiment, an independently temperature-controlled cooling fan is integrated at the lower part of the stator base. The fan's outlet faces upwards, directly opposite the cooling duct on the stator base. The cooling fan's speed is controllably adjusted based on atmospheric temperature data and temperature data from multiple areas within the motor. When the temperature is high, it automatically increases its speed to deliver more airflow into the motor, assisting in the cooling of the centrifugal fan blades at the top of the motor. After the motor stops running, if there is still a relatively high residual temperature inside, the centrifugal fan at the top of the motor will stop working because the motor has stopped rotating. However, the cooling fan can continue to deliver airflow until the internal temperature of the motor drops to an acceptable range, thereby reducing the time the motor's internal temperature remains high. Example 2

[0046] This embodiment discloses a dual-mode aircraft, including a brushless motor for the dual-mode aircraft as described in Embodiment 1. Because the dual-mode aircraft is equipped with the brushless motor, the dual-mode aircraft has good heat dissipation performance, thereby ensuring working efficiency.

[0047] Specifically, in this embodiment, the "dual-mode" of the dual-mode aircraft typically refers to two main environmental perception and navigation modes, namely:

[0048] 1. Visual modality (camera)

[0049] - Principle: Capture images or videos in the visible light band using an optical camera (such as an RGB, binocular, or multi-lens camera).

[0050] - Features: Provides rich texture and color information, and supports tasks such as target recognition, scene understanding, and SLAM (simultaneous localization and mapping).

[0051] - Advantages: Low cost, intuitive data, suitable for well-lit environments.

[0052] 2. LiDAR (Light Detection and Ranging) Mode

[0053] - Principle: High-precision three-dimensional point cloud data is generated by emitting laser pulses and measuring the reflection time.

[0054] - Functions: Accurate distance measurement, construction of 3D environmental models, suitable for obstacle avoidance, terrain modeling, and navigation in low-light conditions.

[0055] - Advantages: Unaffected by lighting conditions, providing accurate distance and structural information.

[0056] The significance of bimodal fusion:

[0057] - Complementarity: Vision compensates for the lack of texture information in LiDAR, while LiDAR solves the limitations of vision in low-light or dynamic scenes.

[0058] - Robustness enhancement: For example, in complex urban environments, visual recognition of traffic signs and LiDAR detection of obstacles work together to improve the safety of autonomous flight.

[0059] - Application scenarios: Fields requiring high-precision environmental interaction, such as logistics and distribution, agricultural monitoring, and search and rescue missions.

[0060] It should be noted that the remaining structural components of the dual-mode aircraft in this embodiment are existing technologies, and those skilled in the art can design them as needed. Therefore, they will not be described in detail in this embodiment.

[0061] In the description of this specification, references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0062] The above description only illustrates the preferred embodiments of the present invention and should not be construed as limiting the scope of the claims. The present invention is not limited to the above embodiments, and variations in its specific structure are permitted. All modifications made within the scope of the independent claims of this invention are also within the scope of protection of this invention.

Claims

1. A brushless motor for a dual-mode aircraft, comprising an outer rotor (1) and a stator, the outer rotor (1) being rotatably mounted on the stator; characterized in that: The stator includes a stator base (3) and an iron core (5). The iron core (5) is fitted onto the stator base (3). The stator base (3) is provided with a positioning component for positioning the iron core (5). The inner ring wall of the iron core (5) is integrally provided with a number of heat dissipation fins (4), and the stator base (3) is provided with heat dissipation air ducts (13) that cooperate with the heat dissipation fins (4). The outer rotor (1) is provided with a fan assembly. When the fan assembly is running, it draws the airflow located at the lower end of the stator base (3) into the heat dissipation duct (13) and then sprays it out through the upper end of the stator base (3) to take away the heat on the heat dissipation fins (4). An enhanced heat dissipation ring (10) is provided at one end of the inner ring wall of several heat dissipation fins (4) away from the iron core (5). The enhanced heat dissipation ring (10) and the heat dissipation fins (4) are integrally formed; The stator base (3) is provided with a partition ring (9), which divides the interior of the stator base (3) into an inner ring (16) and an outer ring. The inner ring (16) is in a closed state, so that air only flows through the outer ring area. The inner ring wall of the iron core (5) and the partition ring (9) cooperate to form the heat dissipation air duct (13). The positioning assembly includes an axial positioning assembly and a rotational positioning assembly. The axial positioning assembly is used to axially position the iron core (5), and the rotational positioning assembly is used to rotate the iron core (5). The rotation positioning assembly includes several slots (11) and several positioning plates (8). Several slots (11) are axially arranged on the inner ring wall of the heat dissipation ring (10), and several positioning plates (8) are integrally arranged on the outer ring wall of the partition ring (9). The end of the positioning plate (8) away from the partition ring (9) cooperates with the slot (11) to realize the rotation positioning of the iron core (5). The axial positioning assembly includes a spring (14), a push rod (6), and a locking block (7). The upper end of the positioning plate (8) is provided with a mounting cavity (15) for installing the axial positioning assembly. One end of the spring (14) is fixedly connected to the cavity wall of the mounting cavity (15), and the other end is fixedly connected to the push rod (6). The locking block (7) is located on the side of the push rod (6) away from the spring (14). One end of the locking block (7) extends through the mounting cavity (15) and out of the positioning plate (8). An inclined surface (12) is provided on the upper surface of the locking block (7).

2. The brushless motor for a dual-mode aircraft according to claim 1, characterized in that: Several of the heat dissipation fins (4) are arranged in a ring array on the inner wall of the iron core (5).

3. A dual-mode aircraft, characterized in that: Includes a brushless motor for a dual-mode aircraft as described in any one of claims 1-2.

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