Propeller variable pitch control system, electric engine, electric propulsion device and aircraft

Abstract

The utility model provides a propeller variable pitch control system, an electric engine, an electric propulsion device and an aircraft, and relates to the technical field of aircrafts. The system comprises a variable pitch motor; the variable-pitch motor controller is connected with the variable-pitch motor; the angle sensor is connected with the variable pitch motor controller; after the aircraft is started, the angle sensor collects the propeller pitch angle of the propeller blades of the aircraft and transmits the propeller pitch angle to the variable pitch motor controller, and the variable pitch motor controller controls the propeller to change the pitch based on the propeller pitch angle. The variable-pitch motor controller is directly connected with the angle sensor, and the propeller pitch angle of the propeller blade is directly collected through the angle sensor, so that the obtained propeller pitch angle is more accurate; besides, a plurality of angle sensors are installed on the blades of the propeller in a distributed mode, tiny differences of different blades can be effectively recognized, the consistency of the blades can be adjusted and monitored more conveniently, and the reliability of controlling the variable pitch of the propeller is improved by considering the fact that the anti-interference capacity of digital signals transmitted by the angle sensors is higher.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a propeller pitch control system, an electric motor, an electric propulsion device, and an aircraft. Background Technology

[0002] Electric vertical take-off and landing (eVTOL) aircraft use electricity as their power source, offering significant advantages in safety, intelligence, economy, and environmental friendliness compared to traditional aircraft. Compared to the limitations of fixed-pitch propellers on flight speed and range, variable-pitch propellers greatly improve propeller power utilization, increase flight range, and save energy consumption. In existing technologies, eVTOL pitch control typically employs a geared variable-pitch motor to drive the pitch mechanism. This motor provides the necessary torque and speed control. The pitch control motor controller and transmission are housed within the hollow shaft of the power motor rotor. A linear displacement sensor located near the power motor indirectly detects the propeller pitch signal, transmitting the result as a small analog signal to the pitch control motor controller. The controller then uses this signal to drive the transmission and control the propeller pitch. However, the reliability of controlling propeller pitch is relatively poor.

[0003] Therefore, improving the reliability of propeller pitch control for aircraft, especially eVTOL, is a critical technical problem that urgently needs to be solved in the industry. Utility Model Content

[0004] This application provides a propeller pitch control system, an electric motor, an electric propulsion device, and an aircraft to solve the problem of poor reliability in the prior art for controlling propeller pitch.

[0005] In a first aspect, this application provides a propeller pitch control system, comprising:

[0006] Variable pitch motor;

[0007] A variable pitch motor controller, which is connected to the variable pitch motor;

[0008] Angle sensor, which is connected to the variable pitch motor controller;

[0009] After the aircraft starts up, the angle sensor collects the pitch angle of the aircraft's blades and transmits it to the variable pitch motor controller, which controls the propeller pitch based on the pitch angle.

[0010] In one possible implementation, the propeller pitch control system further includes: a transceiver and a transmission component; the transceiver and the transmission component are connected via a power line; the transmission component is also connected to the pitch motor controller; the transceiver is used to couple control signals sent to the transmission component to the power line for transmission via power line carrier technology.

[0011] In one possible implementation, the transmission assembly includes multiple sub-assemblies consisting of carbon brushes and slip rings; wherein, in each sub-assembly, the slip ring is disposed on the rotor shaft of the power motor and the carbon brush is disposed on the stator of the power motor.

[0012] In one possible implementation, the transmission component includes multiple sets of coils; wherein at least one set of coils is distributed radially along the motor and at least two sets of coils are distributed axially along the motor.

[0013] In one possible implementation, the transmission component includes multiple sets of coils; wherein at least one set of coils is distributed along the axial direction of the motor, and at least two sets of coils are distributed along the radial direction of the motor.

[0014] In one possible implementation, the angle sensor is positioned within a first preset range of the propeller blades and is adjacent to the propeller blades.

[0015] In one possible implementation, the angle sensor is located at the root of the propeller blades.

[0016] In one possible implementation, the variable pitch motor controller is located within a second preset range of the variable pitch motor and is adjacent to the variable pitch motor.

[0017] In one possible implementation, the variable pitch motor controller is located at the shaft end of the variable pitch motor.

[0018] In one possible implementation, at least one of the pitch motor controller, pitch motor, and angle sensor is configured as dual-redundant.

[0019] In one possible implementation, the propeller pitch control system further includes: an absolute angle sensor; the absolute angle sensor is disposed on the central shaft of the pitch motor and connected to the pitch motor controller, and is used to acquire the motor angle of the pitch motor.

[0020] In one possible implementation, the absolute angle sensor includes at least two types, each of which is a dual-redundant setting.

[0021] Secondly, this application provides an electric motor, including the propeller pitch control system described in any one of the first aspects.

[0022] Thirdly, this application provides an electric propulsion device, comprising: the electric motor described in the second aspect.

[0023] Fourthly, this application provides an aircraft, including: an aircraft body and the electric propulsion device described in the third aspect.

[0024] The propeller pitch control system provided in this application includes: a pitch motor; a pitch motor controller connected to the pitch motor; and an angle sensor connected to the pitch motor controller. After the aircraft starts, the angle sensor acquires the pitch angle of the propeller blades and transmits it to the pitch motor controller, which then controls the propeller pitch based on the pitch angle. This application directly connects the pitch motor controller to the angle sensor, allowing for direct acquisition of the propeller blade pitch angle after aircraft startup, resulting in a more accurate pitch angle. By distributing multiple angle sensors across the propeller blades, subtle differences between blades can be effectively identified, reducing process requirements and manufacturing difficulty. This facilitates easier adjustment and monitoring of blade consistency. Furthermore, considering the stronger anti-interference capability of the digital signals transmitted by the angle sensors, the reliability of propeller pitch control is improved. Attached Figure Description

[0025] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0026] Figure 1 A schematic diagram of a propeller pitch control system provided as an exemplary embodiment of this application;

[0027] Figure 2 A schematic diagram of the communication process of a propeller pitch control system provided as an exemplary embodiment of this application;

[0028] Figure 3 A cross-sectional schematic diagram of a propeller pitch control system provided as an exemplary embodiment of this application;

[0029] Figure 4 Another cross-sectional schematic diagram of a propeller pitch control system provided as an exemplary embodiment of this application;

[0030] Figure 5 Another cross-sectional schematic diagram of a propeller pitch control system provided for an exemplary embodiment of this application.

[0031] Figure label:

[0032] 10. Propeller pitch control system; 11. Pitch motor; 12. Pitch motor controller; 13. Angle sensor.

[0033] The accompanying drawings illustrate specific embodiments of this application, which will be described in more detail below. These drawings and descriptions are not intended to limit the scope of the concept in any way, but rather to illustrate the concept of this application to those skilled in the art through reference to particular embodiments. Detailed Implementation

[0034] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0035] The terms “first,” “second,” etc., used in the specification and claims of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented, for example, in orders other than those illustrated or described herein. Furthermore, the terms “comprising” and “having,” and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, products, or apparatus.

[0036] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, data stored, data displayed, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties. Furthermore, the collection, use and processing of the relevant data must comply with relevant laws, regulations and standards, and corresponding operation entry points are provided for users to choose to authorize or refuse.

[0037] In the prior art, when the propeller pitch signal is indirectly detected by a single linear displacement sensor, the transmitted signal is a small analog signal and the linear displacement sensor is located near the power motor. This makes the transmitted signal susceptible to electromagnetic interference and makes it impossible to identify the consistency of multiple blades, thereby reducing the reliability of controlling the propeller pitch.

[0038] To address the aforementioned issues, this application provides a propeller pitch control scheme. By distributing multiple angle sensors on the propeller blades and directly connecting the pitch motor controller to the angle sensors, subtle differences between different blades can be effectively identified, thereby reducing process requirements and manufacturing difficulty. This makes it easier to adjust and monitor blade consistency. Furthermore, considering the stronger anti-interference capability of the digital signals transmitted by the angle sensors, the reliability of controlling propeller pitch is further improved.

[0039] The technical solution of this application and how the technical solution of this application solves the above-mentioned technical problems are described in detail below with specific embodiments. These specific embodiments can be combined with each other, and the same or similar concepts or processes may not be described again in some embodiments. The embodiments of this application will now be described with reference to the accompanying drawings.

[0040] Figure 1 A schematic diagram of a propeller pitch control system provided as an exemplary embodiment of this application. Figure 1 As shown, the propeller pitch control system 10 includes: a pitch motor 11; a pitch motor controller 12 connected to the pitch motor 11; and an angle sensor 13 connected to the pitch motor controller 12. After the aircraft starts, the angle sensor 13 collects the pitch angle of the aircraft's propeller blades and transmits it to the pitch motor controller 12, which controls the propeller pitch based on the pitch angle.

[0041] For example, an angle sensor 13 is installed on each blade of the propeller. The angle sensor 13 collects the pitch angle of the propeller blades in real time and transmits the collected pitch angle to the variable pitch motor controller 12. Correspondingly, after receiving the pitch angle, the variable pitch motor controller 12 controls the propeller pitch according to its internal control algorithm or preset judgment rules. For example, the control algorithm built into the variable pitch motor controller 12 calculates the required pitch angle adjustment based on the received pitch angle data and preset flight parameters (such as flight speed, flight altitude, electric motor speed, etc.). Further, the variable pitch motor controller 12 sends a control command carrying the pitch angle adjustment amount to the variable pitch motor 11. This control command is used to drive the variable pitch motor 11 to adjust the blade angle so that the propeller reaches the required pitch. In this way, the propeller pitch control system can dynamically adjust the pitch angle during the flight of the aircraft, thereby improving the energy efficiency and flight performance of the aircraft. For example, during takeoff and climb, the propeller pitch control system can increase the pitch angle to obtain greater thrust; during cruise, the propeller pitch control system can decrease the pitch angle to reduce energy consumption.

[0042] The propeller pitch control system provided in this application directly connects the pitch motor controller to the angle sensor. After the aircraft starts, the angle sensor directly collects the pitch angle of the propeller blades, making the obtained pitch angle more accurate. By distributing multiple angle sensors on the propeller blades, it can effectively identify subtle differences between different blades, thereby reducing process requirements and manufacturing difficulty. This makes it easier to adjust and monitor blade consistency. Furthermore, considering that the digital signals transmitted by the angle sensors have stronger anti-interference capabilities, the reliability of controlling the propeller pitch is improved.

[0043] In some embodiments, the angle sensor is positioned within a first preset range of the propeller blades and is adjacent to the propeller blades.

[0044] Optionally, the first preset range can refer to a distance extending outward from the root of the blade, such as a region between 10% and 30% of the blade length. For example, setting the angle sensor within this region ensures that the sensor can directly detect changes in blade angle without being affected by excessive centrifugal force from the high-speed rotation of the blade tip. This configuration allows the angle sensor to provide high-precision pitch angle data, thereby improving the reliability of propeller pitch control.

[0045] In some embodiments, the angle sensor is located at the root of the propeller blades.

[0046] For example, an angle sensor is placed at the root of each propeller blade. The root location is typically the area where the blade connects to the shaft, close to the hub. By placing the angle sensor at the root, the rotation angle of the blade can be directly measured using the mechanical connection between the blade and the shaft, resulting in an accurate and reliable pitch angle, thus improving the reliability of propeller pitch control. Furthermore, the root location is generally less affected by external environmental factors (such as wind and rain), which also enhances the sensor's durability and reliability.

[0047] In existing technologies, the pitch motor and pitch motor controller are typically arranged separately, possibly on different sides of the drive motor or even further away. This layout results in long drive lines between the pitch motor and the controller, making signal transmission susceptible to interference, especially electromagnetic interference from the drive motor. This not only affects signal stability but can also lead to signal attenuation and errors. To address this issue, this application integrates the pitch motor controller with the pitch motor, significantly shortening the physical distance and signal transmission path between them. This reduces intermediate connection points and cable lengths, effectively shortening the control loop length and reducing the likelihood of electromagnetic interference. Furthermore, the shorter control loop ensures more stable signal transmission, minimizing signal attenuation and interference caused by long-distance transmission, thereby improving the reliability of propeller pitch control.

[0048] Therefore, in some embodiments, the variable pitch motor controller is located within a second preset range of the variable pitch motor and is adjacent to the variable pitch motor.

[0049] For example, the pitch motor controller is adjacent to the pitch motor, and the physical distance between them meets the minimum electrical clearance requirements, thus tightly arranging the pitch motor controller and the pitch motor within a small area. Furthermore, the pitch motor controller and the pitch motor are designed as a single integrated housing. Simultaneously, the angle sensor is mounted near the propeller hub or blade root to ensure accurate detection of changes in the blade pitch angle.

[0050] In this embodiment, by setting the variable pitch motor controller within a second preset range of the variable pitch motor and adjacent to it, and by placing the angle sensor near the propeller blades, the drive circuit between the variable pitch motor controller and the variable pitch motor is significantly shortened. This effectively shortens the length of the control loop, reduces the possibility of electromagnetic interference, and the shorter control loop makes signal transmission more stable, reducing signal attenuation and interference problems caused by long-distance transmission, thereby improving the reliability of controlling the propeller pitch.

[0051] In some embodiments, at least one of the pitch motor controller, pitch motor, and angle sensor is configured as dual-redundant.

[0052] In the first implementation, any one of the pitch motor controller, pitch motor, and angle sensor is configured with dual redundancy. For example, the pitch motor controller is configured with dual redundancy.

[0053] In the second implementation, any combination of the pitch motor controller, the pitch motor, and the angle sensor is a dual-redundant configuration. For example, both the pitch motor controller and the pitch motor are dual-redundant, or the pitch motor controller, the pitch motor, and the angle sensor are all dual-redundant.

[0054] In the third implementation, any one of the pitch motor controller, pitch motor, and angle sensor is configured as redundant. For example, the pitch motor controller can be configured as triple-redundant or quadruple-redundant.

[0055] In the fourth implementation, any combination of the pitch motor controller, pitch motor, and angle sensor is a redundant configuration. For example, both the pitch motor controller and the pitch motor are triple-redundant, or all three components (pitch motor controller, pitch motor, and angle sensor) are triple-redundant.

[0056] In this embodiment, by configuring the pitch motor controller, pitch motor, and angle sensor with dual redundancy, it can be ensured that even if a single component fails, the redundant components can still operate normally, thereby ensuring that the pitch function is not affected, further improving the reliability of controlling the propeller pitch, and significantly reducing the risk of system failure, ensuring the safety of the aircraft under various conditions.

[0057] In some embodiments, the variable pitch motor controller is located at the shaft end of the variable pitch motor.

[0058] In one implementation, the dual-redundant variable pitch motor controllers are respectively set on one end face of the dual-redundant variable pitch motor.

[0059] In another implementation, the dual-redundant variable pitch motor controllers are respectively set on both ends of the dual-redundant variable pitch motor.

[0060] In this embodiment, by placing the variable pitch motor controller at the shaft end of the variable pitch motor, the physical distance and signal transmission path between the controller and the motor are shortened, further improving the reliability of the propeller variable pitch control system. Simultaneously, the entire system can be made more compact, reducing the required installation space, which is particularly important for applications with limited space.

[0061] In existing technologies, electrical energy and control signals are transmitted separately through lines located near the motor. Due to susceptibility to interference from the motor, separate filtering circuits are required for interference suppression, leading to complex electromagnetic interference handling and the risk of power and control signal failure. To address this issue, some embodiments of the propeller pitch control system further include: a transceiver and a transmission component; the transceiver and the transmission component are connected via a power line; the transmission component is also connected to the pitch motor controller; the transceiver is used to couple control signals sent to the transmission component to the power line for transmission via power line carrier technology.

[0062] Power line carrier technology is a technique that uses existing power lines for data transmission. This technology transmits data by superimposing high-frequency signals onto the power lines, thus eliminating the need for additional dedicated data transmission lines.

[0063] For example, the transceiver is connected to both the power supply unit and the aircraft's control system. The internal coupler of the transceiver couples the electrical energy supplied by the power supply unit with the control signals sent by the control system, generating a coupled analog and digital signal. This coupled signal is transmitted via a power line to a transmission component, which then passes through the propeller section on the stator and rotor sides of the power motor, ultimately transmitting it to the pitch motor controller. Inside the pitch motor controller, the transceiver decouples the received coupled signal, separating the electrical energy from the control signal. The separated electrical energy is used to continuously power the pitch motor controller, while the control signal is used to control the rotation of the pitch motor, thereby achieving pitch regulation of the propeller.

[0064] In this embodiment, power line carrier technology is used to couple control signals to the power line via a collinear transmission method. This reduces the number of wires passing through the motor, simplifies the wiring structure, and lowers the risk of wire failure, thereby further improving the reliability of the propeller pitch control system. Furthermore, by using collinear transmission, power and control signals can share an anti-interference circuit, saving space and further optimizing the overall system layout.

[0065] Based on the above embodiments, in some embodiments, the transmission component is also used to send the propeller pitch status to the control system.

[0066] For example, Figure 2 This is a schematic diagram of the communication flow of a propeller pitch control system provided for an exemplary embodiment of this application. For example, as shown... Figure 2As shown, in the entire propeller pitch control system, the coupler transceiver in the transceiver unit, the power line between the transceiver unit and the transmission component, the transmission line between the transmission component and the controller, the coupler transceiver inside the pitch motor controller, the pitch motor controller and the pitch motor can all be configured with dual redundancy. In this transceiver unit, a dual-redundant coupled transceiver couples the electrical energy supplied by the power supply unit and the control signal sent by the control system to generate a coupled signal. This coupled signal is transmitted to the transmission component via the power line, and then to the dual-redundant variable-pitch motor controller via the transmission component. The dual-redundant coupled transceiver inside the dual-redundant variable-pitch motor controller decouples the received coupled signal, separating the electrical energy and the control signal. The separated electrical energy is used to continuously supply power to the variable-pitch motor controller, while the control signal is used to control the rotation of the variable-pitch motor, thereby realizing the variable-pitch adjustment of the propeller. Correspondingly, the dual-redundant variable-pitch motor controller acquires the blade pitch angle collected by the angle sensor and controls the propeller pitch according to the pitch angle. Further, the dual-redundant variable-pitch motor controller transmits the propeller pitch state in reverse to the transceiver unit via the transmission component, and then the transceiver unit transmits it to the control system.

[0067] In this embodiment of the application, the propeller pitch status is sent to the control system via a transmission component, which helps the control system to adjust the control strategy in a timely manner, thereby improving the system's response speed and accuracy.

[0068] Based on the above embodiments, in some embodiments, the propeller pitch control system further includes: an absolute angle sensor; the absolute angle sensor is disposed on the central shaft of the pitch motor and connected to the pitch motor controller, and is used to collect the motor angle of the pitch motor.

[0069] For example, an absolute angle sensor is mounted on the central shaft of the variable-pitch motor and connected to the variable-pitch motor controller. The absolute angle sensor acquires the angle of the variable-pitch motor in real time and transmits the acquired data to the variable-pitch motor controller; correspondingly, the variable-pitch motor controller receives the angle of the variable-pitch motor acquired by the absolute angle sensor. Furthermore, the variable-pitch motor controller controls the propeller pitch according to the angle of the variable-pitch motor.

[0070] In some embodiments, the variable pitch motor controller is also used to control the propeller pitch according to the angle of the variable pitch motor when the detection accuracy of the angle sensor and the absolute angle sensor is consistent; and to control the propeller pitch according to the mechanical parameters of the transmission device, the pitch angle and the angle of the variable pitch motor when the detection accuracy of the angle sensor and the absolute angle sensor is inconsistent.

[0071] For example, assuming both the angle sensor and the absolute angle sensor are functioning correctly, and if their detection accuracies are consistent, the variable pitch motor controller directly calculates the blade pitch angle based on the angle data from the variable pitch motor and the transmission ratio. Assuming the transmission ratio is 1000 and the initial angles are all 0°, when the variable pitch motor angle is 1000°, the blade pitch angle can be determined to be 1° based on the transmission ratio, and the propeller pitch can be controlled accordingly. If the angle sensor and the absolute angle sensor have inconsistent detection accuracies, the variable pitch motor controller can control the propeller pitch based on the mechanical properties of the transmission device, the blade pitch angle, and the angle of the variable pitch motor. The mechanical properties include delay, hysteresis, and dead zone. For example, based on the angle data transmitted by the angle sensor and the absolute angle sensor, and considering the effects of delay, hysteresis, and dead zone on the blade pitch angle, the blade pitch angle is determined according to the degree of influence, and the propeller pitch is further controlled based on the blade pitch angle.

[0072] This embodiment of the application uses a dual-redundancy detection method, employing an absolute angle sensor mounted on the central shaft of the variable-pitch motor and an angle sensor located at the root of the propeller blades, to accurately determine the blade pitch angle. This ensures that the angle accurately reflects the actual situation and improves the system's adaptability under complex operating conditions. Furthermore, by utilizing both absolute and angle sensors, common-mode faults can be effectively eliminated, further enhancing the system's reliability, stability, and safety.

[0073] In some embodiments, the absolute angle sensor includes at least two types, each of which is a dual-redundant configuration.

[0074] For example, a Type 1 absolute angle sensor and a Type 2 absolute angle sensor are installed on the central shaft of the variable pitch motor. The Type 1 and Type 2 absolute angle sensors are of different types, and both are configured with dual redundancy.

[0075] In this embodiment, by setting at least two absolute angle sensors and implementing a dual-redundancy configuration, even if one of the absolute angle sensors fails, the system can still rely on the other absolute angle sensor for angle detection, thereby improving the system's reliability and fault tolerance. In addition, by using different types of absolute angle sensors, common-mode faults caused by the same reason are effectively eliminated, thereby reducing the risk of system downtime due to single-point failures and further improving the system's reliability, security, and stability.

[0076] Based on the above embodiments, in some embodiments, the transmission component includes multiple sub-components composed of carbon brushes and slip rings; wherein, in each sub-component, the slip ring is disposed on the rotor shaft of the power motor and the carbon brush is disposed on the stator of the power motor.

[0077] For example, Figure 3 A cross-sectional schematic diagram of a propeller pitch control system provided as an exemplary embodiment of this application. Figure 3 As shown, each propeller blade is equipped with a Type 1 angle sensor and a Type 2 angle sensor at its root. The central shaft of the variable-pitch motor is equipped with a dual-redundant Type 1 absolute angle sensor and a dual-redundant Type 2 absolute angle sensor. The dual-redundant variable-pitch motor controller is located on both sides of the dual-redundant variable-pitch motor and above the drive motor. The transmission assembly between the dual-redundant variable-pitch motor controller and the transceiver includes a sub-assembly consisting of carbon brushes and slip rings. The slip rings in the sub-assembly are mounted on the rotor shaft of the drive motor, and the carbon brushes are mounted on the stator of the drive motor. Correspondingly, the transceiver generates a coupling signal, which is transmitted to the carbon brushes and slip rings via a power line. The signal then passes through the stator and the propeller section on the rotor side of the drive motor, and is finally transmitted to the dual-redundant variable-pitch motor controller. It should be noted that... Figure 3 The example shown is that the slip rings in the sub-assembly are placed on the rotor shaft of the power motor and the carbon brushes are placed on the stator of the power motor. In actual applications, multiple sub-assemblies consisting of carbon brushes and slip rings can be deployed according to application requirements. The number of sub-assemblies consisting of carbon brushes and slip rings deployed is not limited here.

[0078] In this embodiment, communication between the transceiver and the variable-pitch motor controller is achieved through a sub-assembly composed of carbon brushes and slip rings, avoiding interference caused by rotor rotation and thus ensuring the stability of power or signal transmission. Furthermore, the configuration of multiple sub-assemblies composed of carbon brushes and slip rings provides redundancy; even if one sub-assembly fails, the system can still rely on other sub-assemblies for transmission, further improving system reliability and fault tolerance.

[0079] In some embodiments, the transmission component includes multiple sets of coils; wherein at least one set of coils is distributed radially along the motor and at least two sets of coils are distributed axially along the motor.

[0080] For example, Figure 4 Another cross-sectional schematic diagram of a propeller pitch control system provided for an exemplary embodiment of this application. (See diagram below.) Figure 4 As shown, one set of coils is distributed radially along the motor, and two sets of coils are distributed axially along the motor.

[0081] In some embodiments, the transmission component includes multiple sets of coils; wherein at least one set of coils is distributed along the axial direction of the motor and at least two sets of coils are distributed along the radial direction of the motor.

[0082] For example, Figure 5 This is another cross-sectional schematic diagram of a propeller pitch control system provided as an exemplary embodiment of this application. (See attached diagram.) Figure 5 As shown, one set of coils is distributed along the axial direction of the motor, and two sets of coils are distributed along the radial direction of the motor.

[0083] Accordingly, Figure 4 and Figure 5 The system generates a coupling signal via a transceiver device. This signal is transmitted to the coil via the power line, then through the coil to the stator and rotor of the motor, and finally to the dual-redundant variable-pitch motor controller. It should be noted that... Figure 4 and Figure 5 The arrangement of the coil is only one example. In actual applications, multiple sets of coils can be deployed along different directions of the motor according to application requirements. There are no restrictions on the arrangement of the coils (including but not limited to direction and number).

[0084] In this embodiment, by distributing the coils radially and axially along the motor, the internal space of the motor is effectively utilized, and the heat dissipation performance of the coils is improved. This further reduces losses during power transmission, thereby enhancing the stability of power and control signal transmission and ensuring stable system operation under high loads and complex conditions. Furthermore, through different distribution methods of multiple coils, the system can better adapt to different working environments and conditions, further improving system reliability and fault tolerance.

[0085] In some embodiments, the variable pitch motor controller is also used to store process data, including pre-calibrated angle data and operational process data. Furthermore, the process data is periodically exported via an onboard maintenance interface or other means, and the exported data is used as a lifecycle management asset for system performance analysis, fault diagnosis, maintenance plan development, etc., further enhancing the system's maintainability and reliability.

[0086] In summary, this application has at least the following advantages:

[0087] First, by directly connecting the variable pitch motor controller to the angle sensor, the pitch angle of the propeller blades can be directly acquired through the angle sensor after the aircraft starts, making the obtained pitch angle more accurate. By distributing multiple angle sensors on the propeller blades, subtle differences between different blades can be effectively identified, thereby reducing process requirements and manufacturing difficulty, making it easier to adjust and monitor blade consistency. Furthermore, considering that the digital signal transmitted by the angle sensor has stronger anti-interference capability, the reliability of controlling the propeller pitch is improved.

[0088] Second, by setting the variable pitch motor controller within the preset range of the variable pitch motor and adjacent to it, and placing the angle sensor near the propeller blades, the drive line between the variable pitch motor controller and the variable pitch motor is significantly shortened, thereby effectively shortening the length of the control loop, reducing the possibility of electromagnetic interference, and the shorter control loop makes the signal transmission more stable, reducing signal attenuation and interference problems caused by long-distance transmission, thus improving the reliability of the propeller variable pitch control system.

[0089] Third, by configuring the pitch motor controller, pitch motor and angle sensor with dual redundancy, it can be ensured that even if a single component fails, the redundant components can still work normally, thus ensuring that the pitch function is not affected. This further improves the reliability of controlling the propeller pitch and significantly reduces the risk of system failure, ensuring the safety of the aircraft under various conditions.

[0090] Fourth, by employing power line carrier technology and using a co-line transmission method, control signals are coupled to the power lines, reducing the number of wires passing through the motor, simplifying the wiring structure, and thus lowering the risk of wire failure, thereby further improving the reliability of the propeller pitch control system. Furthermore, by using co-line transmission, electrical energy and control signals can share anti-interference circuitry, thereby saving layout space and further optimizing the overall system layout.

[0091] Fifth, by using a dual-redundancy detection system—one with an absolute angle sensor mounted on the central shaft of the variable-pitch motor and the other with an angle sensor located at the root of the propeller blades—the blade pitch angle can be accurately determined, ensuring that it accurately reflects the actual situation and improving the system's adaptability under complex operating conditions. Furthermore, by utilizing both absolute and angle sensors, common-mode faults can be effectively eliminated, further enhancing the system's reliability, stability, and safety.

[0092] This application also provides an electric motor, including: a propeller pitch control system as described in the above embodiments.

[0093] An electric motor is a system composed of an electric motor, a motor controller, a propeller pitch control system, cables, and accessories, which can convert electrical energy into mechanical energy. In practice, an electric motor can also be called an electric propulsion system.

[0094] The lift / thrust assembly consists of an electric motor, a propeller, and its accessories.

[0095] This application embodiment achieves precise control of the propeller pitch in the electric motor through a propeller pitch control system, thereby optimizing the performance of the lift / thrust components. Specifically, the propeller pitch control system can dynamically adjust the propeller pitch angle according to the real-time flight status of the aircraft and preset flight parameters. This adjustment not only improves the efficiency of the aircraft in different flight phases (such as takeoff, cruise, and landing) but also reduces energy consumption and extends the aircraft's endurance. By integrating the propeller pitch control system into the electric motor, the system can quickly respond to changes in flight conditions and provide the required thrust or lift, which is particularly important for aircraft that need to frequently change their flight status (such as UAVs and VTOL aircraft). In addition, the high-precision control capability of this system also helps to improve the stability and safety of the aircraft.

[0096] This application also provides an electric propulsion device, including: the electric motor described in the above embodiments.

[0097] The electric propulsion system consists of a power battery, an electric motor, a propeller, and accessories. The propeller includes variable-pitch propellers and fixed-pitch propellers.

[0098] In this embodiment, the electric motor, as part of the electric propulsion system, can effectively convert electrical energy into mechanical energy to drive the propeller and generate thrust. Through optimized control of the propeller pitch control system, the electric motor can maintain optimal performance under various flight conditions, thereby better meeting the needs of different missions.

[0099] In addition, this application also provides an aircraft, including: an aircraft body and an electric propulsion device as described in the above embodiments.

[0100] In this embodiment, the propeller pitch control system in the electric propulsion device can adjust the propeller pitch angle in real time according to the flight status, thereby optimizing thrust output. This optimization can significantly improve energy utilization efficiency, reduce power consumption, and extend the aircraft's endurance. Furthermore, by precisely controlling the propeller pitch, the aircraft can maintain optimal performance in different flight phases (such as takeoff, cruise, and landing), enabling the aircraft to respond more quickly to changes in flight conditions, thereby improving the aircraft's safety and flexibility.

[0101] Other embodiments of this application will readily occur to those skilled in the art upon consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein. The specification and examples are to be considered exemplary only, and the true scope and spirit of this application are indicated by the following claims.

[0102] It should be understood that this application is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope. The scope of this application is limited only by the appended claims.

Claims

1. A propeller pitch control system, characterized in that, include: Variable pitch motor; A variable pitch motor controller, wherein the variable pitch motor controller is connected to the variable pitch motor; An angle sensor, which is connected to the variable pitch motor controller; After the aircraft starts up, the angle sensor collects the pitch angle of the aircraft's propeller blades and transmits it to the variable pitch motor controller, which controls the propeller pitch based on the pitch angle. At least one of the variable pitch motor controller, the variable pitch motor, and the angle sensor is configured with dual redundancy.

2. The system according to claim 1, characterized in that, The system also includes: Transceiver and transmission components; The transceiver and the transmission component are connected by a power cable. The transmission component is also connected to the variable pitch motor controller; The transceiver is used to couple control signals sent to the transmission component to the power line for transmission via power line carrier technology.

3. The system according to claim 2, characterized in that, The transmission component includes multiple sub-components consisting of carbon brushes and slip rings; In each sub-assembly, the slip ring is mounted on the rotor shaft of the power motor, and the carbon brush is mounted on the stator of the power motor.

4. The system according to claim 2, characterized in that, The transmission component includes multiple sets of coils; wherein at least one set of coils is distributed radially along the power motor, and at least two sets of coils are distributed axially along the power motor.

5. The system according to claim 2, characterized in that, The transmission component includes multiple sets of coils; wherein at least one set of coils is distributed along the axial direction of the power motor, and at least two sets of coils are distributed along the radial direction of the power motor.

6. The system according to any one of claims 3 to 5, characterized in that, The angle sensor is located within a first preset range of the propeller blades and is adjacent to the propeller blades.

7. The system according to claim 6, characterized in that, The angle sensor is located at the root of the propeller blades.

8. The system according to any one of claims 3 to 5, characterized in that, The variable pitch motor controller is located within the second preset range of the variable pitch motor and is adjacent to the variable pitch motor.

9. The system according to claim 8, characterized in that, The variable pitch motor controller is located at the shaft end of the variable pitch motor.

10. The system according to any one of claims 3 to 5, characterized in that, The system also includes: Absolute angle sensor; The absolute angle sensor is mounted on the central axis of the variable pitch motor and connected to the variable pitch motor controller to collect the motor angle of the variable pitch motor.

11. The system according to claim 10, characterized in that, The absolute angle sensor includes at least two types, and each type of absolute angle sensor is configured with dual redundancy.

12. An electric motor, characterized in that, include: The propeller pitch control system according to any one of claims 1 to 10.

13. An electric propulsion device, characterized in that, include: The electric motor according to claim 12.

14. An aircraft, characterized in that, include: The aircraft body and the electric propulsion device as described in claim 13.

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