CN116946357A - Non-contact type electric pitch-changing system and method for airplane propeller for automatic driving - Google Patents
Non-contact type electric pitch-changing system and method for airplane propeller for automatic driving Download PDFInfo
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- CN116946357A CN116946357A CN202311169926.9A CN202311169926A CN116946357A CN 116946357 A CN116946357 A CN 116946357A CN 202311169926 A CN202311169926 A CN 202311169926A CN 116946357 A CN116946357 A CN 116946357A
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- 238000006243 chemical reaction Methods 0.000 claims description 20
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- 230000007274 generation of a signal involved in cell-cell signaling Effects 0.000 claims description 2
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- 230000005540 biological transmission Effects 0.000 description 11
- 230000008054 signal transmission Effects 0.000 description 8
- 238000004891 communication Methods 0.000 description 7
- 230000009194 climbing Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- 230000000087 stabilizing effect Effects 0.000 description 6
- 230000001360 synchronised effect Effects 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/44—Blade pitch-changing mechanisms electric
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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Abstract
The application discloses a non-contact type electric pitch-changing system and a non-contact type electric pitch-changing method for an automatic steering aircraft propeller, wherein the system comprises a control panel, an automatic steering controller, a coupling coil group, an electric steering engine, an angle sensor, a rechargeable battery, a battery state sensor, a high-frequency signal generating module, a fuselage battery and a high-frequency oscillator; according to the control system and the control method, the electric steering engine is adopted to provide pitch-changing power for the pitch-changing actuating mechanism, information such as the actual rotation angle, speed and temperature of the electric steering engine can be reflected through feedback information of the electric steering engine, and the automatic driving controller can accurately adjust the output control signal according to the feedback information of the electric steering engine, so that the rotation angle of the electric steering engine is adjusted, pitch-changing errors of the propeller are reduced to the greatest extent, and pitch-changing accuracy is improved.
Description
Technical Field
The application discloses the technical field of aviation wireless variable-pitch control, in particular to a non-contact type electric variable-pitch system and method for an airplane propeller for automatic piloting.
Background
The design core principle of the aircraft propulsion system is that the propeller has higher efficiency in the whole sailing state, and mainly a perfect control distribution method is designed, so that the propeller absorbs the energy provided by the engine to the maximum, and the total efficiency value of the whole aircraft is maximized. There are many methods for improving the efficiency of the propeller, and flight tests show that the application of propeller pitch variation greatly improves the adaptability of the aircraft and the power of the aircraft for absorbing the propeller is greatly improved. The use of propeller pitch increases the efficiency of the propulsion system, resulting in substantial improvements and improvements in the maneuverability, long endurance of the aircraft, and overall efficiency of the overall aircraft system.
At present, an electric pitch-changing system of an aircraft propeller is generally connected with an aircraft body and a propeller rotating at a high speed through an electric slip ring, and provides electric energy and transmission signals for a pitch-changing motor. Because the aircraft running environment is complex, the electric slip ring material is required to have high impact toughness, and also has the characteristics of corrosion resistance, wear resistance and inconvenient dragging touch. Compared with the electric energy and signal transmission mode by adopting the electric slip ring, the wireless electric energy and signal transmission technology has the advantages of non-contact, no abrasion, flexibility, convenience and the like. Compared with the existing electric pitch-changing system, the non-contact propeller electric pitch-changing control system has the advantages of small volume, light weight, high control precision and the like. In addition, the non-contact propeller electric variable-pitch control system effectively solves the problems of over-high temperature faults of the conductive slip ring and the electric brush and the like caused by the fact that the surface temperature of the conductive slip ring is too high due to long-time high-speed rotation of the aircraft propeller (rotor wing).
It would be very interesting to provide a non-contact electric pitch-changing system and method for an autopilot aircraft propeller.
Disclosure of Invention
In view of this, the present disclosure provides a non-contact electric pitch-shifting system and method for an autopilot aircraft propeller to improve the efficiency of an aircraft propulsion system.
The technical scheme provided by the application is that in a first aspect, the application provides a non-contact type electric pitch-changing system of an airplane propeller for automatic driving, which comprises a control panel, an automatic driving controller, a coupling coil set, an electric steering engine, an angle sensor, a rechargeable battery, a battery state sensor, a high-frequency signal generating module, a fuselage battery and a high-frequency oscillator;
the control panel is in signal connection with the automatic driving controller and is used for switching the control mode of the automatic driving controller; the automatic driving controller is in signal connection with the electric steering engine and the rechargeable battery through the coupling coil group and is used for sending driving control signals to the electric steering engine and the rechargeable battery;
the angle sensor and the battery state sensor are in signal connection with the automatic driving controller through the coupling coil group and are used for sending feedback signals to the automatic driving controller; the feedback signal is a rotation angle feedback signal and a battery state feedback signal;
the aircraft body battery is connected with the high-frequency oscillator, the high-frequency oscillator is used for generating alternating current electric energy signals, the high-frequency signal generating module and the high-frequency oscillator are respectively connected with the power amplifier, and the automatic driving controller is connected with the high-frequency signal generating module;
the display screen is connected with the autopilot controller and is used for displaying the flight state.
Further, the auxiliary power supply conversion circuit comprises a 15V voltage stabilizing chip, a 5V conversion chip and a 3.3V conversion chip, wherein the input end of the 15V voltage stabilizing chip is connected with a 15V power supply, the input end of the 5V conversion chip is connected with the output end of the 15V voltage stabilizing chip, and the input end of the 3.3V conversion chip is connected with the output end of the 5V conversion chip.
The control panel 1 comprises an automatic/manual control rocker S1, a lifting switch S2, a climbing switch S3, a cruise switch S4, a holding switch S5 and a feathering switch S6, wherein a fixed contact of the automatic/manual control rocker S1 is connected with a PA0 pin of an automatic driving controller, a movable contact of the automatic/manual control rocker S1 is connected with ground or resistance switching, the other end of the resistance is connected with a 3.3V power supply, the lifting switch S2 is connected with a 22.0 pin of the automatic driving controller, the climbing switch S3 is connected with a PC13 pin of the automatic driving controller, the cruise switch S4 is connected with a PE3 pin of the automatic driving controller, the holding switch S5 is connected with a PA0 pin of the automatic driving controller U4, and the feathering switch S6 is connected with a PB11 pin of the automatic driving controller U4; the system is grounded through a manipulation switch, and the manipulation switch is connected with a PG15 pin of the automatic driving controller through a manipulation panel of the manipulation switch.
In another aspect, the application provides a method for controlling non-contact electric pitch variation of an aircraft propeller by using the system, comprising the following steps:
step 1: the high-frequency oscillator generates an alternating current electric energy signal and a control signal generated by the signal generating module jointly pass through the power amplifier;
step 2: the power amplifier transmits the generated high-frequency energy signal to the coupling coil and the transmitting coil, the receiving coil is coupled in the magnetic field to obtain an energy signal, and the energy signal is converted into the charging current of a battery used by a direct current load and the driving signal of the steering engine through the extraction rectifying device;
s3: the control signal output by the automatic driving controller is changed through the control panel, the control signal is transmitted to the steering engine through the coupling coil group, further the driving signal of the steering engine is changed, and the steering engine starts to rotate by a corresponding angle so as to realize the switching of the flight state;
s4: the sensor on the steering engine generates a rotating angle feedback signal, and the battery state feedback signal generated by the battery state sensor in the battery module is transmitted to the automatic driving controller through the coupling coil group;
s5: and the automatic driving controller further accurately adjusts the output control signal according to the feedback signal and displays the control signal through a display screen.
And the steering engine driving signal adopts RS485 communication.
According to the non-contact type electric pitch-changing system and method for the airplane propeller for automatic driving, provided by the application, the electric steering engine is adopted to provide pitch-changing power for the pitch-changing actuating mechanism, the feedback information of the electric steering engine can reflect the information of the actual rotation angle, speed, temperature and the like of the electric steering engine, and the automatic driving controller can accurately adjust the output control signal according to the feedback information of the electric steering engine, so that the rotation angle of the electric steering engine is adjusted, the pitch-changing error of the propeller is reduced to the greatest extent, and the pitch-changing precision is improved.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure of the application as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the application and together with the description, serve to explain the principles of the application.
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required to be used in the description of the embodiments or the prior art will be briefly described below, and it will be obvious to those skilled in the art that other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a structural diagram of an aircraft propeller wireless pitch control system provided by the application;
FIG. 2 is a schematic diagram of the steering engine of the present application;
FIG. 3 is a schematic diagram of the pin STM32F103ZET6 of the autopilot controller chip of the present application;
fig. 4 is a schematic diagram of a 485 communication chip used in the present application.
Detailed Description
Reference will now be made in detail to exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, the same numbers in different drawings refer to the same or similar elements, unless otherwise indicated. The implementations described in the following exemplary examples do not represent all implementations consistent with the application. Rather, they are merely examples of systems consistent with aspects of the application as detailed in the accompanying claims.
In order to solve the problems of over-temperature faults of a conductive slip ring and an electric brush and the like in the existing electric variable-pitch control system, as shown in fig. 1, the embodiment provides a non-contact type electric variable-pitch system for an airplane propeller for automatic driving, which comprises a control panel 1, an automatic driving controller 2, a coupling coil group 3, an electric steering engine 41, an angle sensor 42, a rechargeable battery 51, a battery state sensor 52, a high-frequency signal generation module 7, a fuselage battery 8 and a high-frequency oscillator 9;
the control panel 1 is in signal connection with the automatic driving controller 2 and is used for switching the control mode of the automatic driving controller 2; the automatic driving controller 2 is in signal connection with the electric steering engine 41 and the rechargeable battery 51 through the coupling coil group 3 and is used for sending driving control signals to the electric steering engine 41 and the rechargeable battery 51;
the angle sensor 42 and the battery state sensor 52 are in signal connection with the automatic driving controller 2 through the coupling coil set 3 and are used for sending feedback signals to the automatic driving controller 2; the feedback signal is a rotation angle feedback signal and a battery state feedback signal;
the aircraft body battery 8 is connected with the high-frequency oscillator 9, the high-frequency oscillator 9 is used for generating alternating current electric energy signals, the high-frequency signal generating module 7 and the high-frequency oscillator 9 are respectively connected with the power amplifier 10, and the automatic driving controller 2 is connected with the high-frequency signal generating module 7;
the display screen 6 is connected to the autopilot controller 2 for displaying the flight status.
The system further comprises an auxiliary power supply conversion circuit, wherein the auxiliary power supply conversion circuit comprises a 15V voltage stabilizing chip, a 5V conversion chip and a 3.3V conversion chip, wherein the input end of the 15V voltage stabilizing chip is connected with a 15V power supply, the input end of the 5V conversion chip is connected with the output end of the 15V voltage stabilizing chip, and the input end of the 3.3V conversion chip is connected with the output end of the 5V conversion chip.
As shown in fig. 3, the control panel 1 includes an automatic/manual control rocker S1, a lifting switch S2, a climbing switch S3, a cruise switch S4, a holding switch S5, and a feathering switch S6, where a fixed contact of the automatic/manual control rocker S1 is connected to a PA0 pin of the automatic driving controller, a movable contact of the automatic/manual control rocker S1 is connected to ground or a resistor, the other end of the resistor is connected to a 3.3V power supply, the lifting switch S2 is connected to a 22.0 pin of the automatic driving controller, the climbing switch S3 is connected to a PC13 pin of the automatic driving controller, the cruise switch S4 is connected to a PE3 pin of the automatic driving controller, the holding switch S5 is connected to a PA0 pin of the automatic driving controller U4, and the feathering switch S6 is connected to a PB11 pin of the automatic driving controller U4; the system is grounded through a control switch, and the control switch is connected with a PG15 pin of the automatic driving controller through a control panel of the control switch.
Through the control circuit, the wireless pitch control system of the airplane propeller can realize two control modes, namely manual control and automatic control, the corresponding control mode can be selected through a switch, and when the manual mode is selected, the propeller pitch can be changed in real time through operating a rocker; when an automatic mode is selected, setting up and down, climbing, cruising, maintaining and feathering five-state gear switches respectively, wherein the three gear switches of the up and down, climbing and feathering correspond to fixed variable pitch angles, and the propeller pitch can be adjusted until the corresponding variable pitch angles are pressed down by the corresponding switches; when the cruise switch is pressed down, the automatic steering controller calculates the optimal pitch angle of the propeller at the moment according to the flying speed information acquired by the airspeed meter and sends an adjustment control signal to the electric steering engine, meanwhile, the electric steering engine is provided with a feedback signal output interface, the interface can output information such as the rotating angle, the speed, the temperature and the like of the steering engine, the data fed back by the interface are fed to the automatic steering controller, the automatic steering controller processes the received feedback information and then displays the feedback information on a display screen in real time, and meanwhile, the electric steering engine is adjusted according to the feedback information, namely, the judgment such as increasing the rotating angle of the electric steering engine or reducing the rotating angle is selected, and the pitch-changing precision of the propeller can be improved maximally; when the hold switch is pressed, the current state of the propeller pitch of the aircraft can be kept unchanged.
Preferably, the model of the automatic driving controller is STM32F103ZET6, the model of the battery is JUHAI35C, the model of the electric steering engine is SM60CL, and the model of the battery state sensor is 5-15V. The model of the display screen is ILI9341.
The automatic driving controller is connected with a 5V power supply, the battery charging voltage is 4.2V, the input voltage of the electric steering engine is 12V, the power supply voltage of the angular velocity sensor is 3-5V, and the input voltage of the battery state sensor 52 is 2.2-5V.
The coupling coil set adopted in the embodiment adopts a frequency division multiplexing type radio energy and signal synchronous transmission system structure, and comprises a frequency division multiplexing type radio energy and signal forward synchronous transmission system structure and a frequency division multiplexing type radio energy and signal reverse synchronous transmission system structure. The power frequency defaults to a frequency that enables the system to reach a resonance state, and the power transmission process is as follows: the alternating power source generates low-frequency electric energy, and the low-frequency electric energy is wirelessly transmitted to the secondary side resonant circuit inductance coil in a coupling mode through the primary side resonant circuit inductance coil and is transmitted through the secondary side resonant circuit to supply power to the power load. The signal transmission process is as follows: the signal source outputs a modulation signal, the modulation signal is transmitted to the primary side resonance coil in a coupling mode through the transmitting loop inductance coil in a wireless mode, and the signal acquisition module acquires the signal from the primary side resonance circuit.
Further preferably, the steering engine control signal adopts RS485 communication, which has the characteristics of supporting multiple nodes (32 nodes), having long transmission distance (1219 m at maximum), high receiving sensitivity (200 mV voltage), simple connection (only needing a pair of twisted pair wires as a transmission line when forming a communication network), being capable of inhibiting common mode interference (differential transmission), having low cost and the like, and is widely applied to multiple industrial control environments such as multi-station and long-distance communication and the like.
In an RS485 communication network, a 485 transceiver is typically used to convert the TTL level into a differential signal for RS 485. The serial port automatic driving controller TxD of the MCU sends data, and the data is converted into differential signals through a 485 transceiver and transmitted to a bus. When receiving data, the 485 transceiver converts the differential signal on the bus into a TTL signal from the RxD to the serial port automatic driving controller. In the whole communication network, there is usually only one master, and all the remaining slaves. In the RS485 bus, a terminal matching resistor of about 120Q is usually added to the start and stop ends of the bus, so as to ensure the stability of the RS485 bus. The USART2_RX pin of the automatic driving controller is connected with RO and DI of a 485 chip, as shown in a schematic diagram of an RS485 part of a development board, and U16 is a 3.3V low-power-consumption half-duplex transceiver which meets the RS-485 standard. RX and TX of USART are converted by U16 and become A, B port of RS 485. The 2-pin RE of U16 is receive enable, and the upper dashed line indicates active low, i.e., when the 2-pin of U16 is low, U16 receives data. The 3-pin DE of U16 is output enabled, active high, i.e., when the 3-pin of U16 is high, the U16 sends data.
The USART2_RX and USART2_RX pins of the automatic driving controller are connected with RO and DI of the 485 chip, as shown in fig. 4, which is a schematic diagram of the RS485 part of the development board, and U16 is a 3.3V low-power-consumption half-duplex transceiver, which meets the RS-485 standard. RX and TX of USART are converted by U16 to A, B of RS 485. The 2-pin RE of U16 is the receive enable, the upper dash indicates active low, i.e., when the 2-pin of U16 is low, U16 receives data; the 3-pin DE of U16 is output enabled, active high, i.e., when the 3-pin of U16 is high, U16 sends data.
Further preferably, the electric steering engine is SM-60CL, is a 12V serial bus intelligent steering engine, adopts an all-aluminum alloy shell, a brushless motor, a steel gear box, an RS485 control board, a 12-bit high-precision magnetic coding sensor and an external stainless steel main steering wheel. The locked rotor torque is 60kg.cm, the working modes of 360-degree arbitrary angle controllability, multi-turn continuous rotation and the like can be realized, the one-key setting of the middle position function can be realized, the acceleration is slowly started and slowly stopped, and the position, speed, current, voltage, temperature and load parameters can be fed back, so that overload and overcurrent protection can be realized.
The non-contact electric variable-pitch control system of the aircraft propeller also carries out parameter design on the electric energy and the signal transmission loop according to different circuit impedance characteristics under different frequencies, so that the electric energy and the signal transmission loop can be in high impedance characteristics under the opposite transmission frequency. And moreover, a signal acquisition processing module is constructed by using the coupling coil, so that the interference of low-frequency electric energy to the acquisition module can be effectively filtered, and the signal-to-noise ratio of signal transmission is improved. Therefore, the low-interference synchronous transmission of the electric energy and the signals can be realized by simply changing the topology of the wireless electric energy transmission circuit. Second, to increase the signal transmission rate, the frequency of the signal carrier must be made as high as possible. According to the LC loop resonant frequency calculation formula, since the capacitor C has an adjustable lower limit, to increase the carrier frequency, the coil inductance L must be reduced, which can be achieved by flexibly selecting the size of a part of the coils.
The method for controlling the non-contact electric variable pitch of the aircraft propeller by using the system comprises the following steps of:
step 1: the high-frequency oscillator 9 generates an alternating current power signal and the control signal generated by the signal generating module passes through the power amplifier 10 together;
step 2: the power amplifier 10 transmits the generated high-frequency energy signal to the coupling coil and the transmitting coil, the receiving coil is coupled in the magnetic field to obtain the energy signal, and the energy signal is converted into the charging current of the battery 51 used by the direct current load and the driving signal of the steering engine 41 through the extraction rectifying device;
step 3: the control signal output by the automatic driving controller 2 is changed through the control panel 1, the control signal is transmitted to the steering engine through the coupling coil group 3, further the driving signal of the steering engine is changed, and the steering engine starts to rotate by a corresponding angle so as to realize the switching of the flight state;
step 4: the sensor 42 on the steering engine generates a rotation angle feedback signal, and the battery state sensor 52 in the battery module generates a battery state feedback signal which is transmitted to the automatic driving controller through the coupling coil group 3;
step 5: the automatic driving controller 2 further precisely adjusts the output control signal according to the feedback signal and displays the control signal through a display screen.
The non-contact electric variable-pitch control system of the airplane propeller adopts wireless electric energy and signal transmission to provide electric energy for the variable-pitch steering engine and transmit and receive control instructions, and compared with the adoption of the conductive slip ring, the non-contact electric variable-pitch control system has the advantages of non-contact, no abrasion, flexibility, convenience and the like. Compared with the existing electric pitch-changing system, the wireless propeller electric pitch-changing control system has the advantages of small volume, light weight, high control precision and the like. In addition, the wireless variable-pitch control system effectively solves the problems of over-temperature faults of the conductive slip ring and the electric brush and the like caused by over-high surface temperature of the conductive slip ring due to long-time high-speed rotation of the propeller of the airplane.
The non-contact electric variable pitch propeller control system of the embodiment adopts a singlechip as a core chip of the control system, so that the response speed and the control efficiency of an automatic driving controller are remarkably improved, and the purposes of real-time control and real-time response are achieved; the wireless electric energy and the signal are transmitted through the coupling coil, the control signal output by the automatic driving controller can be transmitted to the electric steering engine, and meanwhile, the feedback signal of the electric steering engine is transmitted to the automatic driving controller, and the automatic driving controller can display the control signal in real time through the display screen after processing.
Other embodiments of the application will be apparent to those skilled in the art from consideration of the specification and practice of the application disclosed herein. This application is intended to cover any variations, uses, or adaptations of the application following, in general, the principles of the application and including such departures from the present disclosure as come within known or customary practice within the art to which the application pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the application being indicated by the following claims.
Claims (5)
1. The non-contact type electric pitch-changing system for the automatic steering propeller of the airplane is characterized by comprising a control panel (1), an automatic steering controller (2), a coupling coil group (3), an electric steering engine (41), an angle sensor (42), a rechargeable battery (51), a battery state sensor (52), a high-frequency signal generating module (7), a fuselage battery (8) and a high-frequency oscillator (9);
the control panel (1) is in signal connection with the automatic driving controller (2) and is used for switching the control mode of the automatic driving controller (2); the automatic driving controller (2) is in signal connection with the electric steering engine (41) and the rechargeable battery (51) through the coupling coil group (3) and is used for sending driving control signals to the electric steering engine (41) and the rechargeable battery (51);
the angle sensor (42) and the battery state sensor (52) are in signal connection with the automatic driving controller (2) through the coupling coil group (3) and are used for sending feedback signals to the automatic driving controller (2); the feedback signal is a rotation angle feedback signal and a battery state feedback signal;
the aircraft body battery (8) is connected with the high-frequency oscillator (9), the high-frequency oscillator (9) is used for generating alternating current electric energy signals, the high-frequency signal generating module (7) and the high-frequency oscillator (9) are respectively connected with the power amplifier (10), and the automatic driving controller (2) is connected with the high-frequency signal generating module (7);
the display screen (6) is connected with the autopilot controller (2) and is used for displaying the flight state.
2. The non-contact electric pitch system for an autopilot aircraft propeller of claim 1 further comprising an auxiliary power conversion circuit, wherein the auxiliary power conversion circuit comprises a 15V voltage regulator chip, a 5V conversion chip, and a 3.3V conversion chip, wherein an input of the 15V voltage regulator chip is connected to a 15V power supply, an input of the 5V conversion chip is connected to an output of the 15V voltage regulator chip, and an input of the 3.3V conversion chip is connected to an output of the 5V conversion chip.
3. An aircraft propeller non-contact electric pitch system for autopilot as claimed in claim 1, characterized in that the control panel (1) comprises an automatic/manual control rocker S1, a take-off and landing switch S2, a climb switch S3, a cruise switch S4, a hold switch S5 and a feathering switch S6, the stationary contact of the automatic/manual control rocker S1 being connected to the PA0 pin of the autopilot, the movable contact of the automatic/manual control rocker S1 being connected to ground or resistance switching, the other end of the resistance terminating a 3.3V power supply, the take-off and landing switch S2 being connected to the 22.0 pin of the autopilot, the climb switch S3 being connected to the PC13 pin of the autopilot, the cruise switch S4 being connected to the PE3 pin of the autopilot, the hold switch S5 being connected to the PA0 pin of the autopilot U4, the feathering switch S6 being connected to the PB11 pin of the autopilot U4; the system is grounded through a manipulation switch, and the manipulation switch is connected with a PG15 pin of the automatic driving controller through a manipulation panel of the manipulation switch.
4. A non-contact electric pitch-shifting method for an aircraft propeller for autopilot using the system according to claims 1-3, characterized in that it comprises the steps of:
step 1: the high-frequency oscillator (9) generates an alternating current power signal and a control signal generated by the signal generation module jointly pass through the power amplifier (10);
step 2: the power amplifier (10) transmits the generated high-frequency energy signal to the coupling coil and the transmitting coil, the receiving coil is coupled in a magnetic field to obtain an energy signal, and the energy signal is converted into a charging current of a battery (51) used by a direct current load and a driving signal of the steering engine (41) through the extraction rectifying device;
s3: the control signal output by the automatic driving controller (2) is changed through the control panel (1), the control signal is transmitted to the steering engine through the coupling coil group (3), further a steering engine driving signal is changed, and the steering engine starts to rotate by a corresponding angle so as to realize the switching of the flight state;
s4: a sensor (42) on the steering engine generates a rotating angle feedback signal, and a battery state sensor (52) in the battery module generates a battery state feedback signal which is transmitted to the automatic driving controller through the coupling coil group (3);
s5: and the automatic driving controller (2) further accurately adjusts the output control signal according to the feedback signal and displays the control signal through a display screen.
5. The method of claim 4, wherein the steering engine drive signal is communicated using RS 485.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311169926.9A CN116946357A (en) | 2023-09-12 | 2023-09-12 | Non-contact type electric pitch-changing system and method for airplane propeller for automatic driving |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311169926.9A CN116946357A (en) | 2023-09-12 | 2023-09-12 | Non-contact type electric pitch-changing system and method for airplane propeller for automatic driving |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116946357A true CN116946357A (en) | 2023-10-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311169926.9A Pending CN116946357A (en) | 2023-09-12 | 2023-09-12 | Non-contact type electric pitch-changing system and method for airplane propeller for automatic driving |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116946357A (en) |
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2023
- 2023-09-12 CN CN202311169926.9A patent/CN116946357A/en active Pending
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