CN115903607A - Aircraft control system based on power line carrier communication - Google Patents
Aircraft control system based on power line carrier communication Download PDFInfo
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- CN115903607A CN115903607A CN202211543581.4A CN202211543581A CN115903607A CN 115903607 A CN115903607 A CN 115903607A CN 202211543581 A CN202211543581 A CN 202211543581A CN 115903607 A CN115903607 A CN 115903607A
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Abstract
The invention discloses an aircraft control system based on power carrier communication, which relates to the technical field of spaceflight and comprises a modulation module, a power line coupling module and a modulation-demodulation module, wherein the modulation module is used for modulating information to be transmitted in an aircraft to generate a carrier signal; the power line coupling module is used for coupling the generated carrier signal to a power line between the ground and the aircraft; the modulation and demodulation module is used for decoupling the carrier signal on the power line to obtain information to be transmitted and sending the information to the ground measurement and transmission control system; and the instruction information of the ground test launch control system is modulated to generate a carrier signal, and the carrier signal is coupled to a power line to be sent to the aircraft. The invention realizes self test, self check, data interaction between platforms, power supply connection and the like of the aircraft in a lighter, more universal and more economic form, and expands the selection of the launching platform of the aircraft.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to an aircraft control system based on power line carrier communication.
Background
At present, an aircraft system mainly uses common architectures such as a Controller Area Network (CAN) bus, a 1553B bus (an information transmission bus standard) and the like to support communication in the aircraft system, a power supply system is independent of a communication system, and a matched aircraft ground measurement and control system comprises bus architectures such as an ethernet and a CAN bus.
The common buses are matched with special data wire harnesses, the use price is high, and communication among different bus architectures needs to be converted. Therefore, the existing aircraft and the test, launch and control device thereof have high cost and complex use on a communication bus architecture.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an aircraft control system based on power carrier communication, so that self-test, self-inspection, data interaction between platforms, power supply connection and the like of an aircraft are realized in a lighter, more universal and more economic mode, and the selection of a launching platform of the aircraft is expanded.
In order to achieve the above purpose, the invention adopts the technical scheme that the method comprises the following steps:
the modulation module is used for modulating information to be transmitted in the aircraft to generate a carrier signal;
the power line coupling module is used for coupling the generated carrier signal to a power line between the ground and the aircraft;
the modulation and demodulation module is used for decoupling the carrier signal on the power line to obtain information to be transmitted and sending the information to the ground test and transmission control system;
and the instruction information of the ground test launch control system is modulated to generate a carrier signal, and the carrier signal is coupled to a power line to be sent to the aircraft.
On the basis of the technical scheme, the information to be transmitted is in a bus form in a single aircraft, is processed by a protocol conversion chip and is sent to a modulation module for modulation.
On the basis of the technical scheme, the carrier signal generated by the modulation module is coupled to a power line by the power line coupling module after being processed by the power amplifier circuit.
On the basis of the technical proposal, the device comprises a shell,
the power line coupling module comprises a control circuit based on a single chip microcomputer;
the control circuit is used for disconnecting the signal transmission between the single machine and the power line when the single machine in the aircraft does not need to communicate.
On the basis of the technical scheme, the single machine in the aircraft is also used for receiving, preprocessing and decoupling the carrier signal on the power line and reducing the carrier signal into instruction information.
On the basis of the technical scheme, the preprocessing is filtering processing.
On the basis of the technical proposal, the utility model has the advantages that,
the aircraft comprises a main control unit and a plurality of slave control units;
the master control unit sends a coordination instruction to the slave control unit, so that only the master control unit or one slave control unit uses a power line to transmit information or receive instruction information at the same time.
On the basis of the technical scheme, the main control unit is located in a flight control computer of the aircraft.
On the basis of the technical scheme, the instruction information sent by the ground measurement and control system is transferred to a single aircraft through the flight control computer.
On the basis of the technical proposal, the device comprises a shell,
each subsystem of the aircraft is internally provided with a power supply module;
and the direct current input by the power supply module is processed by the voltage stabilizing chip and the voltage reducing chip to supply power to the chip in the single aircraft.
Compared with the prior art, the invention has the advantages that: the data transmission is carried out through the power line between the ground and the aircraft, and the communication function of the aircraft and the ground test, launch and control platform of the aircraft can be realized only through the power supply cable on the basis of not increasing an independent data transmission cable.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the description below are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an aircraft control system based on power line carrier communication according to an embodiment of the present invention;
fig. 2 is a communication flow diagram of an aircraft.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. It should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only used for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as the case may be. In this application, 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 apparatus 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 apparatus. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of additional like elements in a process, method, article, or apparatus that comprises the element.
Traditional aircraft control system and survey launch and control system equipment are various, and the communication of the complicated cable network of required design in order to support entire system contains supply cable and data transmission cable in the cable, leads to that the cable is heavy, connects effortlessly and transport the difficulty, can't effective control cost and product weight. And different bus architectures cannot adapt the aircraft to test and launch of multiple platforms. The existing aircraft control system has the requirements of low cost, light weight and generalization, and the traditional data transmission cable obviously cannot meet the requirements. For aircraft, the following requirements apply:
(1) The weight is reduced. Under the condition that a power system is not changed, the flight range of the aircraft is closely related to the self weight, hardware equipment in the aircraft is limited by the weight, cables need to meet the requirements of a platform, the design of integration and lightening is carried out, and the performance of the aircraft is improved;
(2) And (4) generalization. Between the aircraft and a matched ground test launch control system, multiple protocols are used for communication in the test and launch processes, such as a 4M 1553B bus, a 1M 1553B bus, a CAN bus, an RS-422 serial port, a high-speed Ethernet and the like, the traditional communication is adaptive to multiple communication modes, a large number of differential transmission twisted-pair shielded wires exist, connector resources are occupied, different buses are provided with special protocol analysis processors, peripheral modules of the controller are complicated, and cables also need to be designed in a universal mode;
(3) The cost is low. The aircraft is used as a product with high reliability, the internal design is complex and redundant, the development and production cost is extremely high, the redundant cable is simplified, the cost can be reduced, and the economy of the aircraft is improved.
The invention can realize the communication function of the aircraft and the ground test, launch and control platform thereof only through the power supply cable on the basis of not increasing the independent data transmission cable.
The embodiment of the invention provides an aircraft control system based on power line carrier communication, and based on the scheme of the invention, self-test, self-inspection, data interaction between platforms, power supply connection and the like of an aircraft are realized in a lighter, more universal and more economic mode, so that the selection of a launching platform of the aircraft is expanded, the design idea of the aircraft control system is simplified, and the advancement of the aircraft is improved.
Referring to fig. 1, an aircraft control system based on power carrier communication according to an embodiment of the present invention includes a modulation module, a power line coupling module, and a modulation and demodulation module.
The modulation module is used for modulating information to be transmitted in the aircraft to generate a carrier signal; the power line coupling module is used for coupling the generated carrier signal to a power line between the ground and the aircraft; the modulation and demodulation module is used for decoupling the carrier signal on the power line to obtain information to be transmitted and sending the information to the ground measurement and transmission control system; the command information of the ground measurement and launch control system is modulated to generate a carrier signal, and the carrier signal is coupled to the power line to be sent to the aircraft.
The invention modulates the signals of the communication between the aircraft and the ground onto the power line, transmits the signals by using the power line, and demodulates the signals from the power line by using a demodulator at a receiving end to transmit the signals to corresponding terminal equipment when receiving the signals.
In the invention, the information to be transmitted is in a bus form in a single aircraft, and is sent to a modulation module for modulation after being processed by a protocol conversion chip. After being processed by a power amplifier circuit, the carrier signal generated by the modulation module is coupled to a power line by a power line coupling module, namely, the carrier signal is loaded to the power line under 28V or other voltage and transmitted by taking the power line as a medium.
In the invention, the power line coupling module comprises a control circuit based on a single chip microcomputer; the control circuit is used for disconnecting the signal transmission between the single machine and the power line when the single machine in the aircraft does not need to communicate. When a single machine in the aircraft does not need to communicate, the signal transmission between the single machine and the power line is cut off, thereby reducing a large amount of unnecessary power loss, reducing the attenuation of carrier signals and enhancing the reliability of signal transmission.
In the invention, the single machine in the aircraft is also used for receiving, preprocessing and decoupling the carrier signal on the power line and reducing the carrier signal into instruction information. The preprocessing is a filtering process, thereby eliminating noise.
In the invention, the aircraft comprises a main control unit and a plurality of slave control units; the master control unit sends a coordination command to the slave control unit, so that only the master control unit or one slave control unit uses a power line to transmit information or receive command information at the same time. Because the flight control computer is a core single machine of the aircraft, the main control unit is placed in the flight control computer of the aircraft, and the rest of the slave control units are slave nodes.
The ground measurement and control system can supply power to the aircraft, so that the ground measurement and control system can be hung on a power line between the ground and the aircraft as a slave node, and the instruction information of the ground measurement and control system is modulated to generate a carrier signal and is coupled to the power line to be sent to the aircraft.
The power supply of the aircraft is provided by a ground measurement and launch control system or a thermal battery, and a power supply module is arranged in each subsystem of the aircraft; the direct current input by the power module is processed by the voltage stabilizing chip and the voltage reducing chip to supply power to the chip in the single aircraft. For example, the input of the power module is 28V dc, and the voltage of 3.3V, 5V, etc. is output to each chip in the single-chip through the power conversion module, the voltage stabilizing chip, and the voltage dropping chip.
The communication inside the aircraft is realized through the power line coupling module and the modulation and demodulation module, and the power line coupling module is divided into sending and receiving coupling output for preventing the disorder of internal information transmission. The main Control Unit is in communication with an MCU (Micro Control Unit) module through an SPI (Serial Peripheral Interface) Interface circuit, sends Control information to a filter circuit for filtering according to a flight condition or a test state, and finally sends high-quality information to a modulation and demodulation module.
Each single machine in the aircraft adopts a unified application layer communication protocol, the protocol comprises the contents of signal content, ID, length, check code and the like, and the protocol is defined according to different model requirements.
In the invention, the modulation module outputs signals through the modulation circuit, and the modulation module is realized through the demodulation circuit when receiving the signals. The frequency hopping and spread spectrum are realized by inputting a modulated digital signal into a multiplier of a frequency modulation system and another radio frequency which is provided by a controlled PN code frequency synthesizer and randomly changes the frequency value of the digital signal, the modulated digital signal and the other radio frequency are used as carrier waves to be mixed with the carrier waves, a band-pass filter outputs a transmitting signal, and the whole process forms a transmitting module of the frequency hopping and spread spectrum modulation system. The spread spectrum demodulation process is similar to the modulation process, and the signal after spread spectrum modulation is subjected to amplitude demodulation operation through a multiplier chip to obtain a demodulated signal. The spread spectrum demodulation signal is input to the demodulation module, the control signal is demodulated out, and then the control signal is sent to the control unit through the receiving filter circuit.
According to the bus communication requirement of the aircraft, the communication flow of the aircraft is shown in fig. 2 by combining each single-machine module in the aircraft. And under the action of the control unit, sending the information to be transmitted in the aircraft to a modulation module for modulation.
According to the aircraft control system based on power line carrier communication, data transmission is carried out through the power line between the ground and the aircraft, the communication function of the aircraft and the ground test, launch and control platform of the aircraft can be realized only through the power supply cable on the basis of not increasing an independent data transmission cable, and based on the scheme of the invention, self test, self inspection, data interaction between platforms, power supply connection and the like of the aircraft are realized in a lighter, more universal and more economic mode, the launch platform selection of the aircraft is expanded, the design idea of the aircraft control system is simplified, and the advancement of the aircraft is improved.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are merely for convenience of describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be configured and operated in a specific orientation, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
It is noted that, in the present application, relational terms such as "first" and "second", and the like, are 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 apparatus 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 apparatus. 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 apparatus that comprises the element.
The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. An aircraft control system based on power carrier communication, comprising:
the modulation module is used for modulating information to be transmitted in the aircraft to generate a carrier signal;
the power line coupling module is used for coupling the generated carrier signal to a power line between the ground and the aircraft;
the modulation and demodulation module is used for decoupling the carrier signal on the power line to obtain information to be transmitted and sending the information to the ground measurement and transmission control system;
and the instruction information of the ground test launch control system is modulated to generate a carrier signal, and the carrier signal is coupled to a power line to be sent to the aircraft.
2. An aircraft control system based on power carrier communication according to claim 1, wherein: the information to be transmitted is in a bus form in a single aircraft, is processed by a protocol conversion chip and is sent to a modulation module for modulation.
3. An aircraft control system based on power carrier communication according to claim 1, wherein: and the carrier signal generated by the modulation module is coupled to a power line by the power line coupling module after being processed by the power amplifier circuit.
4. An aircraft control system based on power carrier communication according to claim 1, wherein:
the power line coupling module comprises a control circuit based on a single chip microcomputer;
the control circuit is used for disconnecting the signal transmission between the single machine and the power line when the single machine in the aircraft does not need to communicate.
5. An aircraft control system based on power carrier communication according to claim 4, wherein: and the single machine in the aircraft is also used for receiving, preprocessing and decoupling the carrier signal on the power line and reducing the carrier signal into instruction information.
6. An aircraft control system based on power carrier communication according to claim 5, wherein: the preprocessing is filtering processing.
7. An aircraft control system based on power carrier communication according to claim 1, wherein:
the aircraft comprises a main control unit and a plurality of slave control units;
the master control unit sends a coordination command to the slave control unit, so that only the master control unit or one slave control unit uses a power line at the same time to transmit information or receive command information.
8. An aircraft control system based on power carrier communication according to claim 7, wherein: the main control unit is located in a flight control computer of the aircraft.
9. An aircraft control system based on power carrier communication according to claim 8, wherein: and the instruction information sent by the ground measurement and control system is transferred to a single aircraft through the flight control computer.
10. An aircraft control system based on power carrier communication according to claim 1, wherein:
each subsystem of the aircraft is internally provided with a power supply module;
and the direct current input by the power supply module is processed by the voltage stabilizing chip and the voltage reducing chip to supply power to the chip in the single aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211543581.4A CN115903607A (en) | 2022-12-03 | 2022-12-03 | Aircraft control system based on power line carrier communication |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211543581.4A CN115903607A (en) | 2022-12-03 | 2022-12-03 | Aircraft control system based on power line carrier communication |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115903607A true CN115903607A (en) | 2023-04-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211543581.4A Pending CN115903607A (en) | 2022-12-03 | 2022-12-03 | Aircraft control system based on power line carrier communication |
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| CN (1) | CN115903607A (en) |
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- 2022-12-03 CN CN202211543581.4A patent/CN115903607A/en active Pending
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