CN113050670B - Control system and control method of manned aircraft and manned aircraft - Google Patents
Control system and control method of manned aircraft and manned aircraft Download PDFInfo
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
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Abstract
The embodiment of the invention provides a control system and a control method of a manned aircraft and the manned aircraft, wherein the control system comprises a flight control module, an electronic speed regulator, a signal line, a single-end-to-differential module, a differential-to-single-end module and an electrical isolation device; the flight control module is used for outputting a single-ended signal to the signal line and transmitting the single-ended signal to the electronic speed regulator through the signal line; and the electric isolating device is used for electrically isolating the single-ended signal provided by the flight control module before the single-ended signal is transmitted to the electronic speed regulator. The embodiment of the invention can block the influence and interference of the electronic speed regulator on the flight control module through the signal line.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a control system of a manned aircraft, a control method of the manned aircraft and the manned aircraft.
Background
The control mode of the existing manned aircraft is that a flight control module controls an electronic speed regulator, and the electronic speed regulator controls a motor. The flight control module transmits the control signal to the electric controller through a signal wire. The electronic speed regulator of the manned aircraft is provided with a strong current module and a weak current module, ripples of the strong current module can possibly generate signal interference on a signal line, and the strong current module can also possibly generate interference on a flight control module through the signal line to influence the operation of the flight control module.
Disclosure of Invention
In view of the above, embodiments of the present invention are proposed in order to provide a control system for a manned aircraft, a control method for a manned aircraft and a manned aircraft that overcome or at least partially solve the above-mentioned problems.
In order to solve the above problems, the embodiment of the present invention discloses a control system for a manned aircraft, which includes a flight control module, an electronic speed regulator, a signal line arranged between the flight control module and the electronic speed regulator, and an electrical isolator element arranged between the flight control module and the electronic speed regulator;
the flight control module is used for outputting a single-ended signal to the signal wire and transmitting the single-ended signal to the electronic speed regulator through the signal wire;
the electrical isolation device is used for electrically isolating the single-ended signal provided by the flight control module before the single-ended signal is transmitted to the electronic speed regulator.
Optionally, the method further comprises: the single-end-to-differential module is arranged between the signal wire and the flight control module, and the differential-to-single-end-to-differential module is arranged between the signal wire and the electronic speed regulator;
the single-ended to differential module is used for converting the single-ended signal output by the flight control module into two paths of differential signals and outputting the two paths of differential signals to the signal line for transmission;
the differential-to-single-ended module is used for converting the two paths of differential signals output by the signal line into single-ended signals and transmitting the single-ended signals to the electronic speed regulator.
Optionally, the electronic speed regulator includes a plurality of electronic speed regulators, and each of the electronic speed regulators and the flight control module has a signal line, a single-end-to-differential module, and a differential-to-single-end-to-differential module in one-to-one correspondence therebetween.
Optionally, the electrical isolation device is a photovoltaic isolation device;
the optoelectronic isolation device is used for converting the single-ended signal provided by the flight control module from an electrical signal form to an optical signal form and converting the single-ended signal from the optical signal form to the electrical signal form before the single-ended signal is transmitted to the electronic governor.
Optionally, the electrical isolator device is disposed between the flight control module and the single-ended to differential module, or between the differential to single-ended module and the electronic governor.
Optionally, the electrical isolator is integrated into the flight control module or the electronic governor.
Optionally, the single-ended to differential module is integrated with the flight control module.
Optionally, the differential-to-single-ended module is integrated with the electronic governor.
The embodiment of the invention also discloses a control method of the manned aircraft, wherein the manned aircraft comprises a flight control module, an electronic speed regulator, a signal line arranged between the flight control module and the electronic speed regulator, and an electrical isolator arranged between the flight control module and the electronic speed regulator; the method comprises the following steps:
the flight control module outputs a single-ended signal to the signal line, and the single-ended signal is transmitted to the electronic speed regulator through the signal line;
the electrical isolation device electrically isolates a single-ended signal provided by the flight control module prior to transmission to the electronic governor.
Optionally, the manned vehicle further comprises: the single-end-to-differential module is arranged between the signal line and the flight control module, and the differential-to-single-end-to-differential module is arranged between the signal line and the electronic speed regulator; the method further comprises the following steps:
the single-ended to differential module converts the single-ended signal output by the flight control module into two paths of differential signals, and outputs the two paths of differential signals to the signal line for transmission;
and the differential-to-single-ended module converts the two paths of differential signals output by the signal line into single-ended signals and transmits the single-ended signals to the electronic speed regulator.
Optionally, the electrical isolation device is a photoelectric isolation device;
the electrical isolation device electrically isolates a single-ended signal provided by the flight control module prior to transmission to the electronic governor, comprising:
the optoelectronic isolation device converts the single-ended signal provided by the flight control module from an electrical signal form to an optical signal form and vice versa before the single-ended signal is transmitted to the electronic governor.
The embodiment of the invention also discloses a manned aircraft which comprises the control system.
The embodiment of the invention has the following advantages:
in the embodiment of the invention, the aircraft comprises a flight control module, an electronic speed regulator and a signal wire arranged between the flight control module and the electronic speed regulator, wherein a single-ended signal can be transmitted to the electronic speed regulator through the signal wire, and the electrical isolation device can electrically isolate the single-ended signal before the single-ended signal provided by the flight control module is transmitted to the electronic speed regulator, so that the influence and the interference of the electronic speed regulator on the flight control module through the signal wire can be blocked.
Drawings
FIG. 1 is a schematic diagram of normal control signals;
FIGS. 2A and 2B are schematic diagrams of control signals after being interfered;
FIG. 3 is a block diagram of a control system for a manned aircraft according to an embodiment of the present invention;
FIG. 4 is a block diagram of an alternative exemplary embodiment of a control system for a manned aircraft;
FIG. 5 is a block diagram of an alternative exemplary embodiment of a control system for a manned aircraft;
FIG. 6 is a block diagram of an alternative exemplary embodiment of a control system for a manned aircraft;
FIG. 7 is a flowchart illustrating steps of a method for controlling a manned vehicle, according to an embodiment of the present invention.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
In the manned aircraft, the flight control module can acquire attitude data acquired by various sensors and generate control signals according to the attitude data. Fig. 1 is a schematic diagram of a normal control signal, which is a PWM (Pulse width modulation) signal. As shown in fig. 2A and 2B, the disturbed control signal may change in waveform, which may cause the aircraft to be in a dangerous state.
For a manned aircraft, the flight control module may be positioned between the forward and copilot pilots, the electronic governor may be positioned below the propeller of the aircraft, and the flight control module may transmit control signals to the electronic governor via a signal line (e.g., a cable).
Because the manned aircraft has large bearing weight, the electronic speed regulator of the manned aircraft can be provided with a strong current module and a weak current module, and the weak current module can control the strong current module. The strong current module and the weak current module have ripples, and the fluctuation value of the weak current module voltage can be smaller, for example: the voltage fluctuation range of 5V direct current can be 4.99V-5.01V. The voltage fluctuation of the strong electric module is relatively large, and may be between 98V and 103V, taking 100V as an example. On one hand, the ripples of the strong current module can generate signal interference on the signal line, and on the other hand, the strong current module can be arranged on the same circuit board in the electronic speed regulator due to the weak current module, and the strong current module can also cause signal interference through other connecting circuits such as a ground wire of the circuit board.
In some cases, the strong power module of the electronic governor may also cause some interference or influence on the flight control module through the signal. For example: when the electronic governor is broken or the electronic governor 32 may be damaged by any electric regulation such as lightning strike, electromagnetic waves generated by strong electricity or lightning strike in the electric regulation may adversely interfere or affect the flight control module through the signal line.
Aiming at the problem that a strong current module of the electronic speed regulator can interfere with a flight control module through a signal wire, the invention provides an embodiment which can avoid the strong current module of the electronic speed regulator from interfering the flight control module through the signal wire through electric isolation.
Referring to fig. 3, there is shown a block diagram of a control system of a manned vehicle according to an embodiment of the present invention, the control system of the manned vehicle includes a flight control module 31 and an electronic speed governor 32, a signal line 33 disposed between the flight control module 31 and the electronic speed governor 32, and an electrical isolator 34 disposed between the flight control module and the electronic speed governor; the flight control module 31 is configured to output a single-ended signal to the signal line 33, and transmit the single-ended signal to the electronic governor 32 through the signal line 33; the electrical isolation device 34 is configured to electrically isolate the single-ended signal provided by the flight control module 31 before the single-ended signal is transmitted to the electronic governor 32.
In the embodiment of the present invention, the control signal output by the output terminal of the flight control module 31 is a single-ended signal, and the single-ended signal can be transmitted to the electronic governor 32 through the signal line 33. The electrical isolation device 34 has a good isolation effect on input and output electrical signals, and the electrical isolation device 34 can electrically isolate a single-ended signal provided by the flight control module before the single-ended signal is transmitted to the electronic speed regulator, so that the influence and interference of the electronic speed regulator on the flight control module through the signal line can be blocked. In one embodiment, the electrical isolation device 34 may be a photovoltaic isolation device; the optoelectronic isolation device is used for converting the single-ended signal provided by the flight control module from an electrical signal form to an optical signal form and converting the single-ended signal from the optical signal form to the electrical signal form before the single-ended signal is transmitted to the electronic governor. Of course, the electrical isolation device 34 may also be a magnetic induction isolator, a capacitive isolator, or other types of electrical isolation devices, which is not limited in the embodiment of the present invention.
In one example, the optoelectronic isolation device may be an optocoupler, which may include a light emitting diode and a photodiode. The electrical signal at the input end drives the light emitting diode to emit light with a certain wavelength, the light signal is received by the photosensitive diode to generate photocurrent, and the photocurrent is amplified to become the electrical signal, so that the conversion of the electrical signal to the optical signal is realized, the electrical isolation of communication is realized, and the influence and the interference of the electronic speed regulator 32 on the flight control module 31 through the signal wire 33 are blocked.
As shown in fig. 3, an electrical isolation device 34 is provided between the signal line 33 and the electronic governor 32. The electrical isolation device 34 may be an external component connected to the electronic governor 32, or may be a component integrated with the electronic governor 32. If the electrical isolator device is an optical coupler, the single-ended signal output by the output terminal of the signal line 33 may be transmitted to the input terminal of the optical coupler, the optical coupler may convert the single-ended signal into an optical signal, and then convert the optical signal into the single-ended signal, and the output terminal of the optical coupler may output the single-ended signal to the input terminal of the electronic governor.
Referring to FIG. 4, a block diagram of another embodiment of a control system for a manned aircraft is shown. Wherein an electrical isolator device 34 may be provided between the flight control module 31 and the signal line 33. The electrical isolator device 34 may be an external component connected to the flight control module 31 or a component integrated with the flight control module 31. If the electrical isolation device is an optical coupler, the single-ended signal output by the output terminal of the flight control module 31 may be transmitted to the input terminal of the optical coupler, the optical coupler may convert the single-ended signal into an optical signal, and then convert the optical signal into the single-ended signal, and the output terminal of the optical coupler may output the single-ended signal to the input terminal of the signal line 33.
In practice, the longer the length of the signal line 33, the more interference may occur, and the signal line 33 may be mainly interfered by external environment or by electromagnetic waves on a human body. Referring to FIG. 5, a block diagram of another embodiment of a control system for a manned aircraft is shown. In the embodiment of the present invention, the control system may further include a single-end-to-differential module 35 disposed between the signal line 33 and the flight control module 31, a differential-to-single-end-to-differential module 36 disposed between the signal line 33 and the electronic governor 32; the single-ended to differential module 35 is configured to convert the single-ended signal output by the flight control module 31 into two differential signals, and output the two differential signals to the signal line 33 for transmission; the differential-to-single-ended module 36 is configured to convert the two paths of differential signals output by the signal line 33 into single-ended signals, and transmit the single-ended signals to the electronic speed governor 32.
The single-ended-to-differential module 35 may be disposed between the output end of the flight control module 31 and the input end of the signal line 33, and convert the single-ended signal output by the flight control module 31 into two differential signals, and then output the two differential signals to the signal line 33 for transmission. Differential-to-single-ended module 36 may be disposed between the output of signal line 33 and the input of electronic governor 32, convert the two differential signals output from signal line 33 into a single-ended signal, and transmit the single-ended signal to electronic governor 32. In the signal line 33, the control signal is transmitted in the form of two differential signals, the two differential signals are subtracted to obtain the original single-ended signal, and even if external interference is received, the result of the subtraction of the two differential signals does not change because the two differential signals receive the interference at the same time, so that the interference can be offset. As shown in fig. 5, an electrical isolation device 34 can be disposed between the differential to single ended module 36 and the electronic governor 32. Referring to FIG. 6, a block diagram of another embodiment of a control system for a manned aircraft is shown. Wherein an electrical isolator device 34 may be provided between the flight control module 31 and the single-ended to differential module 35.
In an embodiment of the present invention, the manned vehicle may include a plurality of rotors, a plurality of motors that drive the rotation of the rotors, and a plurality of electronic governors 32 that control the operating state of the motors. The flight control module 31 may send control signals to each electronic governor 32, and each electronic governor 32 and the flight control module 31 may have a signal line 33, a single-end-to-differential module 35, and a differential-to-single-end module 36 that correspond to one another, that is, the control signal corresponding to each electronic governor 32 is transmitted through the corresponding signal line 33, the single-end-to-differential module 35, and the differential-to-single-end module 36.
In an embodiment, the single-ended to differential conversion module 35 may be a single-ended to differential chip, and the single-ended to differential conversion module 35 may be an external component connected to the flight control module 31 or a component integrated in the flight control module 31. In one embodiment, the differential-to-single-ended module 36 can be a differential-to-single-ended chip, and the differential-to-single-ended module 36 can be an external component connected to the electronic governor 32 or a component integrated with the electronic governor 32.
Referring to fig. 7, a flowchart illustrating steps of a control method of a manned vehicle according to an embodiment of the present invention is shown, wherein the manned vehicle may include a flight control module, an electronic governor, a signal line disposed between the flight control module and the electronic governor, and an electrical isolator disposed between the flight control module and the electronic governor; the method may specifically include:
and 701, outputting a single-ended signal to the signal wire by the flight control module, and transmitting the single-ended signal to the electronic speed regulator through the signal wire.
In the embodiment of the invention, the control signal output by the flight control module is a single-ended signal, and the single-ended signal can be transmitted to the electronic speed regulator through a signal wire. The electrical isolation device can electrically isolate the single-ended signal provided by the flight control module before the single-ended signal is transmitted to the electronic speed regulator, so that the influence and interference of the electronic speed regulator on the flight control module through the signal wire can be blocked.
In an embodiment of the present invention, the manned vehicle may further include: the single-end-to-differential module is arranged between the signal wire and the flight control module, and the differential-to-single-end-to-differential module is arranged between the signal wire and the electronic speed regulator; the method further comprises the following steps:
the single-ended to differential module converts the single-ended signal output by the flight control module into two paths of differential signals, and outputs the two paths of differential signals to the signal line for transmission;
and the differential-to-single-ended module converts the two paths of differential signals output by the signal line into single-ended signals and transmits the single-ended signals to the electronic speed regulator.
In an embodiment of the present invention, the manned vehicle may include a plurality of rotors, a plurality of motors that drive the rotors to rotate, and a plurality of electronic governors that control the operating state of the motors. The flight control module can send control signals to each electronic speed regulator respectively, and a signal line, a single-end-to-differential module and a differential-to-single-end module which are in one-to-one correspondence can be arranged between each electronic speed regulator and the flight control module, namely, the control signals corresponding to each electronic speed regulator are transmitted through the corresponding signal line, the single-end-to-differential module and the differential-to-single-end module.
In an embodiment, the single-ended to differential conversion module may be a single-ended to differential chip, and the single-ended to differential conversion module may be an external component connected to the flight control module or a component integrated in the flight control module. In one embodiment, the differential-to-single-ended module may be a differential-to-single-ended chip, and the differential-to-single-ended module is an external component connected to the electronic speed regulator, or a component integrated with the electronic speed regulator.
In one embodiment, the electrical isolation device may be an opto-electrical isolation device; the step of electrically isolating the single-ended signal provided by the flight control module by the electrical isolation device prior to transmission to the electronic governor may include:
the optoelectronic isolation device converts the single-ended signal provided by the flight control module from an electrical signal form to an optical signal form and vice versa before the single-ended signal is transmitted to the electronic governor.
Of course, the electrical isolator device may also be a magnetic induction isolator, a capacitive isolator, or other types of electrical isolator devices, which is not limited in the embodiment of the present invention. In one example, the optoelectronic isolation device can be an optical coupler, and the optical coupler can realize conversion of an electric-optical-electric signal and electric isolation of communication, so that influence and interference of the electronic speed regulator on the flight control module through a signal line are blocked.
In one embodiment, an electrical isolation device may be disposed between the flight control module and the signal line. If the electrical isolator device is an optical coupler, the optical coupler can receive the single-ended signal output by the flight control module, convert the single-ended signal into an optical signal, convert the optical signal into the single-ended signal, and output the single-ended signal to the signal line.
In another embodiment, an electrical isolation device can be disposed between the signal line and the electronic governor. If the electrical isolator is an optical coupler, the optical coupler can receive the single-ended signal output by the signal line, convert the single-ended signal into an optical signal, convert the optical signal into the single-ended signal and output the single-ended signal to the electronic speed regulator.
The embodiment of the invention also provides a manned aircraft which comprises the control system, the rotor wing and the motor. The rotor can be by motor drive, and flight control module can send control signal to electronic governor through the signal line, and electronic governor rotates according to control signal control motor to the drive rotor rotates. The manned vehicle may also include a nacelle on top of which the rotor may be positioned and a shock mount on the bottom of which the nacelle may be used to carry an aircraft operator and passengers for manned functions.
The embodiments in the present specification are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
As will be appreciated by one of skill in the art, embodiments of the present invention may be provided as a method, apparatus, or computer program product. Accordingly, embodiments of the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, embodiments of the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
Embodiments of the present invention are described with reference to flowchart illustrations and/or block diagrams of methods, terminal devices (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing terminal to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing terminal, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing terminal to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing terminal to cause a series of operational steps to be performed on the computer or other programmable terminal to produce a computer implemented process such that the instructions which execute on the computer or other programmable terminal provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While preferred embodiments of the present invention have been described, additional variations and modifications of these embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including the preferred embodiment and all changes and modifications that fall within the true scope of the embodiments of the present invention.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or terminal. Without further limitation, an element defined by the phrases "comprising one of 8230; \8230;" 8230; "does not exclude the presence of additional like elements in a process, method, article, or terminal device that comprises the element.
The present invention provides a manned vehicle control system, a manned vehicle control method and a manned vehicle, detailed description has been made above, the present invention has been described in the specific embodiments, the present invention has been described in the principle and implementation, the above embodiments are only used to help understanding the method and its core ideas; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (10)
1. A control system of a manned aircraft comprises a flight control module, an electronic speed regulator, a signal line arranged between the flight control module and the electronic speed regulator, and an electrical isolation device arranged between the flight control module and the electronic speed regulator;
the flight control module is used for outputting a single-ended signal to the signal wire and transmitting the single-ended signal to the electronic speed regulator through the signal wire;
the electrical isolation device is used for electrically isolating the single-ended signal provided by the flight control module before the single-ended signal is transmitted to the electronic speed regulator;
the system further comprises: the single-end-to-differential module is arranged between the signal wire and the flight control module, and the differential-to-single-end-to-differential module is arranged between the signal wire and the electronic speed regulator; the single-ended signal is transmitted in the signal line in the form of two paths of differential signals;
the electronic speed regulators comprise a plurality of electronic speed regulators, and a signal line, a single-end-to-differential module and a differential-to-single-end module which are in one-to-one correspondence are arranged between each electronic speed regulator and the flight control module;
the electrical isolator is arranged between the flight control module and the single-end-to-differential module or between the differential-to-single-end module and the electronic speed regulator.
2. The control system according to claim 1, wherein the single-ended-to-differential module is configured to convert the single-ended signal output by the flight control module into two differential signals, and output the two differential signals to the signal line for transmission;
the differential-to-single-ended module is used for converting the two paths of differential signals output by the signal line into single-ended signals and transmitting the single-ended signals to the electronic speed regulator.
3. The control system of claim 1, wherein the electrical isolation device is a photovoltaic isolation device;
the photoelectric isolation device is used for converting the single-ended signal provided by the flight control module from an electrical signal form into an optical signal form and converting the single-ended signal from the optical signal form into the electrical signal form before the single-ended signal is transmitted to the electronic speed regulator.
4. The control system of claim 1, the electrical isolation device being integrated into the flight control module or the electronic governor.
5. The control system of claim 2, the single-ended to differential module integrated with the flight control module.
6. The control system of claim 2, the differential to single ended module integrated with the electronic governor.
7. A control method of a manned vehicle is characterized in that the manned vehicle comprises a flight control module, an electronic speed regulator, a signal wire arranged between the flight control module and the electronic speed regulator, and an electric isolation device arranged between the flight control module and the electronic speed regulator; the method comprises the following steps:
the flight control module outputs a single-ended signal to the signal line, and the single-ended signal is transmitted to the electronic speed regulator through the signal line;
the electrical isolation device electrically isolates the single-ended signal provided by the flight control module before the single-ended signal is transmitted to the electronic governor;
the manned vehicle further includes: the single-end-to-differential module is arranged between the signal line and the flight control module, and the differential-to-single-end-to-differential module is arranged between the signal line and the electronic speed regulator; the single-ended signal is transmitted in the signal line in the form of two paths of differential signals;
the electronic speed regulators comprise a plurality of electronic speed regulators, and a signal line, a single-end-to-differential module and a differential-to-single-end module which are in one-to-one correspondence are arranged between each electronic speed regulator and the flight control module;
the electrical isolator is arranged between the flight control module and the single-end-to-differential module or between the differential-to-single-end module and the electronic speed regulator.
8. The method of claim 7, further comprising:
the single-ended to differential conversion module converts the single-ended signal output by the flight control module into two differential signals, and outputs the two differential signals to the signal line for transmission;
and the differential-to-single-ended module converts the two paths of differential signals output by the signal wire into single-ended signals and transmits the single-ended signals to the electronic speed regulator.
9. The method of claim 7, wherein the electrical isolation device is a photovoltaic isolation device;
the electrical isolation device electrically isolates the single-ended signal provided by the flight control module prior to transmission to the electronic governor, comprising:
the optoelectronic isolation device converts the single-ended signal provided by the flight control module from an electrical signal form to an optical signal form and vice versa before the single-ended signal is transmitted to the electronic governor.
10. A manned vehicle comprising a control system according to any one of claims 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110240132.1A CN113050670B (en) | 2021-03-04 | 2021-03-04 | Control system and control method of manned aircraft and manned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110240132.1A CN113050670B (en) | 2021-03-04 | 2021-03-04 | Control system and control method of manned aircraft and manned aircraft |
Publications (2)
| Publication Number | Publication Date |
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| CN113050670A CN113050670A (en) | 2021-06-29 |
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