CN111669198B - Aircraft data link terminal and control system of one-station multi-machine dynamic network group - Google Patents
Aircraft data link terminal and control system of one-station multi-machine dynamic network group Download PDFInfo
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Abstract
The invention relates to an aircraft data link terminal and a control system of one-station multi-machine dynamic network group. The digital zero intermediate frequency signal processing unit includes: the analog signal modulation unit is used for receiving the first data signal and converting the first data signal into a second data signal; the first link signal processing unit is used for receiving the second data signal and performing first link signal processing; the second link signal processing unit is used for receiving the third data signal and performing second link signal processing; the direct radio frequency modulation unit is used for receiving the third data signal, converting the third data signal into a fourth data signal and sending the fourth data signal to the antenna control module; the data packet processing unit is used for carrying out TCP packing and unpacking processing on the first data signal, the second data signal, the third data signal and the fourth data signal. The invention realizes the communication function of the autonomous one-station multi-machine dynamic network group according to the design of a specific protocol stack.
Description
Technical Field
The invention belongs to the field of data link communication terminals of aircraft clusters, and particularly relates to an aircraft data link terminal and a control system of a one-station multi-machine dynamic network group.
Background
At present, the combat function of the aircraft is positively expanded in the aspects of cluster combat and the like, particularly unmanned aerial vehicles, and the aircrafts coordinate the whole combat process to form difficulty. The advantages of the system cluster battlefield of the aircrafts, particularly the unmanned aerial vehicles, are converted into real battle effectiveness, and the problem that information between aircraft platforms in the cluster and between an unmanned cluster and a ground control station is reliably exchanged in real time, namely, the key technical problem related to data links in the aircrafts cluster is broken through must be solved. The aircraft cluster data chain is not only to solve the communication problem between the ground control station and the aircraft, but also to solve the data exchange problem between the aircraft in the cluster network.
Disclosure of Invention
The invention provides an aircraft data link terminal and a control system of one-station multi-machine dynamic network group, which aim at the characteristics of autonomous networking and cooperative communication of an aircraft cluster. The aircraft data link terminal is designed to realize that one control station controls one aircraft (a main aircraft) and other auxiliary aircraft, and the communication function of the main one-station multi-aircraft dynamic network group is realized according to the specific protocol stack design.
In order to achieve the above object, according to a first aspect of the present invention, there is provided an aircraft data link terminal for a one-station multi-machine dynamic network group, comprising an antenna control module, a signal processing module and a power supply module, wherein the signal processing module further comprises a digital zero intermediate frequency signal processing unit; wherein, digital zero intermediate frequency signal processing unit includes:
the analog signal modulation unit is used for receiving a current first data signal and converting the current first data signal into a second data signal, wherein the second data signal is a digital zero intermediate frequency signal;
the first link signal processing unit is used for receiving the second data signal, processing the first link signal and then sending the processed first link signal to the data packet processing unit;
the second link signal processing unit is used for receiving the current third data signal, processing the second link signal and then sending the processed second link signal to the direct radio frequency modulation unit;
the direct radio frequency modulation unit is used for receiving the third data signal, converting the third data signal into a fourth data signal and sending the fourth data signal to the antenna control module;
and the data packet processing unit is used for carrying out TCP packing and unpacking processing on the first data signal, the second data signal, the third data signal and the fourth data signal.
Further, the method comprises, among others,
the first data signal is an analog data signal; wherein the first and second data signals each comprise telemetry data and video data; the telemetry data includes flight status information, instrument status information, and geographic location information of the aircraft;
the third data signal is a baseband data signal, and the fourth data signal is a frequency band data signal; wherein the third and fourth data signals each comprise remote control data; the remote control data includes control instruction information.
Further, the first link signal processing includes: carrier recovery processing, bit synchronization processing, frame synchronization processing, descrambling processing, decoding processing and de-framing processing; and the first link signal processing unit further comprises:
the carrier recovery module is used for receiving the second data signal and carrying out carrier recovery on the digital zero intermediate frequency signal by using a complex phase discrimination algorithm to complete the carrier tracking;
the bit synchronization module is used for carrying out bit synchronization on the data after carrier tracking locking and outputting demodulation result data and loop state data;
the frame synchronization module is used for performing frame header detection on the data after partial bit synchronization; wherein the frame header is a 32-bit sequence based on hexadecimal coding;
the descrambling module is used for descrambling data which are not in frame synchronization; the descrambling mode is exclusive or calculation through a pseudo-random sequence;
the decoding module is used for carrying out RS decoding calculation on all data in the first link signal processing unit;
the de-framing module is used for carrying out frame identification on the decoded data and sending the decoded data to the data packet processing unit; if the data frame is judged to be valid, the valid data packet is extracted and sent to the data interface unit, and if the data frame is judged to be filled, the filled data packet is discarded.
Further, the second link signal processing includes: framing, encoding and synchronous head processing, scrambling and serial-parallel conversion processing; and the second link signal processing unit further comprises:
the framing module is used for receiving the third data signal and converting the third data signal into an effective data frame through data packaging;
the coding and synchronization head module is used for carrying out RS coding calculation on the data after partial framing and adding a synchronization head; wherein the synchronization header is a 32-bit sequence based on hexadecimal coding;
the scrambling module is used for scrambling the data which is not coded and is provided with the synchronous head; the scrambling mode is exclusive or calculation through a pseudo-random sequence;
and the serial-parallel conversion module is used for carrying out IQ modulation on all data in the second link signal processing unit and sending the data to the direct radio frequency modulation unit.
Further, the digital intermediate frequency signal processing unit further includes:
the data interface unit is used for realizing the transmission of the first, second, third and fourth data signals; the data interface unit comprises an Ethernet physical interface and a serial port; wherein,
an ethernet physical interface for transmitting the video data in the fourth data signal;
and the serial port is used for transmitting the telemetering data in the fourth data signal and the remote control data in the first data signal.
Further, the digital intermediate frequency signal processing unit further includes:
the clock generation unit is used for generating current reference clock data required by the digital zero intermediate frequency signal processing unit and sending the current reference clock data to the analog signal modulation unit and the direct radio frequency modulation unit;
and the power supply conversion unit is used for converting the voltage input by the power supply module into the working voltage required by the digital zero intermediate frequency signal processing unit.
Further, the antenna control module includes:
an antenna for transmitting the fourth data signal to free space and receiving the first data signal;
the antenna receiving and transmitting controller is used for finishing the control switching of the transmitting signal and the receiving signal;
and the antenna cover is used for covering the antenna and the shell of the surface of the antenna transceiver controller.
Further, the power supply module includes:
the power supply control unit is used for finishing outputting 5V, 12V and 220V power supplies to the aircraft data chain terminal;
a power supply unit for supplying and transmitting power to the power control unit; the power supply unit comprises a lithium battery and a solar panel.
According to a second aspect of the invention, an aircraft control system of one-station multi-machine dynamic network group is provided, which is characterized by comprising an aircraft platform and a ground control station; the aircraft platform comprises a main aircraft and a plurality of slave aircraft, wherein the main aircraft and the slave aircraft are both provided with the aircraft data chain terminals;
the slave aircraft is used for sending current telemetric data and video data to the master aircraft based on a wireless communication protocol; and receiving remote control data sent by the host aircraft based on a wireless communication protocol;
the main aircraft is used for sending telemetry data and video data to the ground control station based on a wireless communication protocol; and receiving the current remote control data sent by the ground control station based on a wireless communication protocol.
Further, the wireless communication protocol is a TCP/IP protocol stack.
Generally, compared with the prior art, the above technical solution conceived by the present invention has the following beneficial effects:
according to the aircraft data link terminal of the one-station multi-machine dynamic network group, the aircraft data link terminal of the one-station multi-machine dynamic network group provided by the invention uses the digital intermediate frequency signal processing unit to complete the processing of a forward receiving signal and the processing of a return baseband to a modulation signal. The digital intermediate frequency signal processing unit can realize data processing from the aircraft communication terminal to the main aircraft (forward link), analog data signals from the antenna control module are processed, and the analog data signals are converted into digital zero intermediate frequency signals through the analog signal modulation unit; then completing signal capture, tracking, bit synchronization processing, completing data demodulation, decoding and de-framing the data stream information, synchronizing the frame and outputting the data stream information through a data interface unit. The unit can also realize data processing from the ground communication terminal to the main aircraft (return link), and the return link receives control instruction information through the data interface unit, completes framing, coding, scrambling and serial-parallel conversion, then moves to radio frequency and outputs to the slave aircraft.
Meanwhile, the aircraft control system of the one-station multi-aircraft dynamic network group is designed aiming at the characteristics of autonomous networking and cooperative communication of aircraft cluster, and realizes that one control station controls one aircraft (a main aircraft) and other slave aircraft through an aircraft data link terminal, wherein the communication function of the autonomous one-station multi-aircraft dynamic network group is realized according to the specific protocol stack design, the expansibility of the aircraft control system is ensured, and the operation of several to thousands of aircraft cluster teams is supported.
Drawings
Fig. 1 is a block diagram of a digital zero intermediate frequency signal processing unit in an aircraft data link terminal of a one-station multi-machine dynamic network group implemented according to the present invention;
FIG. 2 is a block diagram of an aircraft data link terminal for a one-station multi-machine dynamic network group implemented in accordance with the present invention;
FIG. 3 is a block diagram of a wireless communication connection of a one-station multi-aircraft dynamic network of an aircraft control system of a one-station multi-aircraft dynamic network implemented in accordance with the present invention;
FIG. 4 is a block diagram of a wireless communication protocol stack for a one-station multi-aircraft dynamic networking of an aircraft control system for one-station multi-aircraft dynamic networking implemented in accordance with the present invention;
the same reference numbers will be used throughout the drawings to refer to the same or like elements or structures, wherein: the device comprises an antenna control module-1, a signal processing module-2, a power supply module-3, a digital zero intermediate frequency signal processing unit-21, an analog signal modulation unit-211, a first link signal processing unit-212, a second link signal processing unit-213, a direct radio frequency modulation unit-214, a data packet processing unit-215, a data interface unit-216, a clock generation unit-217, a power supply conversion unit-218, a carrier recovery module-2121, a bit synchronization module-2122, a frame synchronization module-2123, a descrambling module-2124, a decoding module-2125, a de-framing module-2126, a framing module-2131, an encoding and synchronizing module-2132, a scrambling module-2133 and a serial-parallel conversion module-2134.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
The invention provides an aircraft data link terminal of one-station multi-machine dynamic network group, which can be applied to an aircraft cluster of one-station multi-machine, can be arranged on a main aircraft and can also be arranged on a slave aircraft. The antenna comprises an antenna control module 1, a signal processing module 2 and a power supply module 3, wherein the signal processing module 2 further comprises a digital zero intermediate frequency signal processing unit 21; as shown in fig. 1, the digital zero intermediate frequency signal processing unit 21 includes: an analog signal modulation unit 211, a first link signal processing unit 212, a second link signal processing unit 213, a direct radio frequency modulation unit 214, and a packet processing unit 215.
According to a specific implementation mode, when the aircraft data link terminal is arranged on the main aircraft, the first data signal is an analog data signal, and the second data signal is a digital zero intermediate frequency signal; wherein the first and second data signals each comprise telemetry data and video data; the telemetry data includes flight status information, instrument status information, and geographic location information for the aircraft. The third data signal is a baseband data signal, and the fourth data signal is a frequency band data signal; the third data signal and the fourth data signal comprise remote control data; the remote control data includes control instruction information.
In the invention, the digital intermediate frequency signal processing unit completes the first link signal processing, namely the processing of a forward received signal, and the second link signal processing, namely the processing of a return baseband to a modulation signal. The digital intermediate frequency signal processing unit can realize data processing from the aircraft communication terminal to the main aircraft (forward link), and can process the analog data signal from the antenna control module 1, and convert the analog data signal into a digital zero intermediate frequency signal through the analog signal modulation unit 211; the first link signal processing unit 212 completes signal capture, tracking, bit synchronization processing, data demodulation, decoding, de-framing, frame synchronization, and data interface unit output. The unit can also realize data processing from a ground communication terminal to a main aircraft (return link), the second link signal processing unit 213 receives control instruction information through the data interface unit, completes framing, coding, scrambling and serial-parallel conversion, and then completes moving to radio frequency by the direct radio frequency modulation unit 214 and outputs the radio frequency to the antenna control module 1, and then transmits the frequency band data after spreading to the receiving direction of the auxiliary aircraft by the antenna control module 1.
Further, the analog signal modulation unit 211 is configured to receive the current first data signal and convert the current first data signal into a second data signal, where the second data signal is a digital zero intermediate frequency signal, and uses the digital zero intermediate frequency signal output by the a/D conversion circuit; the analog data signals of the telemetering data and the video data are digitally converted, so that the circuit is miniaturized.
Further, the first link signal processing unit 212 is configured to receive the second data signal, perform first link signal processing, and send the second data signal to the data packet processing unit 215; the first link signal processing includes: carrier recovery processing, bit synchronization processing, frame synchronization processing, descrambling processing, decoding processing and de-framing processing; and the first link signal processing unit 212 further includes the following modules, and the specific functions are as follows:
the carrier recovery module 2121 is configured to receive the second data signal, perform carrier recovery on the digital zero intermediate frequency signal by using a complex phase discrimination algorithm, and complete carrier tracking;
a bit synchronization module 2122, configured to perform bit synchronization on the data after carrier tracking locking, and output demodulation result data and loop state data;
a frame synchronization module 2123, configured to perform frame header detection on the data after partial bit synchronization; the frame header is a 32-bit sequence based on hexadecimal coding, and the hexadecimal representation is as follows: 1ACFFC 1D;
a descrambling module 2124, configured to descramble data that is not frame-synchronized; the descrambling mode is exclusive-or calculation through a pseudo-random sequence, and a generator polynomial of the pseudo-random code generator is as follows: h (x) x8+ x7+ x5+ x3+ 1;
a decoding module 2125, configured to perform RS decoding calculation on all data in the first link signal processing unit 212;
a de-framing module 2126, configured to perform frame identification on the decoded data and send the decoded data to the data packet processing unit 215; if the valid data frame is determined to be a valid data frame, the valid data frame is extracted and sent to the data interface unit 216, and if the padding data frame is determined to be a padding data frame, the padding data frame is discarded.
Further, the second link signal processing unit 213 is configured to receive the current third data signal, perform second link signal processing, and send the processed second link signal to the direct radio frequency modulation unit 214; the second link signal processing includes: framing, encoding and synchronous head processing, scrambling and serial-parallel conversion processing; and the second link signal processing unit 213 further includes the following modules, and the specific functions are as follows:
a framing module 2131, configured to receive the third data signal, and convert the third data signal into an effective data frame with a fixed frame length of 1024 bytes through data packing, and when no data packet is sent, send a padding data frame;
the coding and synchronization head module 2132 is used for performing RS coding calculation on the data after partial framing and adding a synchronization head; the synchronization header is a 32-bit sequence based on hexadecimal coding, is specified as 32 bits by adopting a CCSDS standard, and is represented as follows in hexadecimal: 1ACFFC 1D;
a scrambling module 2133, configured to scramble uncoded data with a synchronization header; the scrambling mode is exclusive-or calculation through a pseudo-random sequence, a generator polynomial of a pseudo-random code generator is h (x) ═ x8+ x7+ x5+ x3+1, and the polynomial is repeatedly used once every 255 bits;
the serial-to-parallel conversion module 2134 is configured to perform IQ modulation on all data in the second link signal processing unit 213 and send the data to the direct radio frequency modulation unit 214, and further convert one path of serial baseband data into IQ two paths of baseband data. The IQ data serves as input data for the direct rf modulation unit 214.
Further, the direct rf modulation unit 214 is configured to receive the third data signal, convert the third data signal into a fourth data signal, and send the fourth data signal to the antenna control module 1, so as to implement shifting the baseband data signal to the set L, S rf signal, thereby forming a frequency band data signal.
Further, the data packet processing unit 215 is configured to perform TCP packetizing and depacketizing on the first, second, third, and fourth data signals. The data packet from the first link after signal processing is subjected to TCP packaging and then sent out through the data interface unit 216; the TCP data packets from the data interface unit 216 are extracted and sent to the first link signal processing unit 212 for signal processing.
In the present invention, the digital if signal processing unit further includes a data interface unit 216.
Further, a data interface unit 216, configured to implement transmission of the first, second, third, and fourth data signals; the data interface unit 216 includes an ethernet physical interface and a serial port, and has the following specific functions:
the Ethernet physical interface is used for transmitting the video data in the fourth data signal; furthermore, the main aircraft sends video data to the antenna control module 1 through the Ethernet physical interface and then sends the video data to the ground control station;
the serial port is used for transmitting the telemetering data in the fourth data signal and the remote control data in the first data signal; furthermore, the flight state of the aircraft is controlled by receiving a remote control command of the ground control station through the serial port, and the telemetering data of the aircraft is sent through the serial port.
In the present invention, the digital intermediate frequency signal processing unit further includes a clock generating unit 217 and a power converting unit 218, and the specific functions are as follows:
the clock generating unit 217 is configured to generate current reference clock data required by the digital zero intermediate frequency signal processing unit 21, and send the current reference clock data to the analog signal modulating unit 211 and the direct radio frequency modulating unit 214; the 25MHz clock input by the temperature compensation crystal oscillator is taken as a reference to generate a 60MHz working clock of the digital zero intermediate frequency signal processing unit 21 and a working clock of the direct radio frequency modulation unit 214, and simultaneously, the working clocks required by all functional modules in the digital zero intermediate frequency signal processing unit 21 are generated by using the working clocks;
and the power conversion unit 218 is configured to convert the voltage input by the power supply module 3 into an operating voltage required by the digital zero intermediate frequency signal processing unit 21. The +5V secondary voltage input from the power supply module 3 is converted into an operating voltage required by each main device in the circuit.
In the present invention, the analog signal modulation unit 211, the first link signal processing unit 212, the second link signal processing unit 213, the direct radio frequency modulation unit 214, the data packet processing unit 215, the data interface unit 216, the clock generation unit 217, and the power conversion unit 218 in the digital zero intermediate frequency signal processing unit 21 are integrated on the same Field Programmable Gate Array (FPGA).
In the present invention, the antenna control module 1 includes an antenna, an antenna transceiver controller, and an antenna cover, and has the following specific functions:
an antenna 11 for transmitting a fourth data signal to free space and receiving the first data signal; further, the antenna is a device made of a metal material and capable of radiating communication of the fourth data signal working frequency to free space;
an antenna transceiver controller 12 for completing control switching between signal transmission and signal reception; further, the antenna transceiving controller is configured to complete the switching between transmitting the communication signal and receiving the communication signal, while ensuring that the antenna beam direction of the fourth data signal operating frequency is aligned with the direction of the communication antenna of the slave aircraft.
An antenna cover 13 for covering the antenna and the housing of the antenna transceiver controller surface; further, the radome is made of a material capable of transmitting radio signals of operating frequency, and is used for protecting the communication antenna or the communication equipment from water and other faults.
In the invention, the power supply module 3 comprises a power supply control unit and a power supply unit, and the specific functions are as follows:
the power supply control unit is used for outputting 5V, 12V and 220V power supplies to the aircraft data chain terminal;
a power supply unit for supplying and transmitting power to the power control unit; the power supply unit comprises a lithium battery and a solar panel; furthermore, the design of a solar power supply board is adopted, and solar power can be used for supplying power.
The invention provides an aircraft control system of one-station multi-machine dynamic network group, which comprises an aircraft platform and a ground control station, as shown in figure 3.
The aircraft platform comprises a main aircraft and a plurality of auxiliary aircraft, and the main aircraft is provided with the aircraft data chain terminal.
Further, the host aircraft is configured to accept the transmission of the first data signal from the aircraft and to transmit the fourth data signal to the ground control station based on the wireless communication protocol.
As shown in fig. 3, according to a specific embodiment, the ground control station and the aircraft platform (for example, the aircraft platform includes a master aircraft, a slave aircraft a, and a slave aircraft B), wherein the master aircraft, the slave aircraft a, and the slave aircraft B are each installed with an aircraft data link terminal, constitute a dynamic networking and cooperative communication system of the aircraft cluster, complete that the ground control station operates one master aircraft, and the master aircraft performs autonomous dynamic networking with the other two slave aircraft a and the slave aircraft B according to a set routing protocol, including communication between the master aircraft and the ground control station, and communication between the master aircraft and the two slave aircraft.
Further, the basic workflow: after the aircraft data chain terminal is initialized; the slave aircraft A and the slave aircraft B send current telemetering data and video data to the master aircraft based on a wireless communication protocol, and the master aircraft receives the front telemetering data and the video data based on the wireless communication protocol, carries out first link signal processing and then sends the processed data to the ground control station; meanwhile, the ground control station sends current remote control data, the main aircraft receives the remote control data, carries out first link signal processing and then sends the processed remote control data to the auxiliary aircraft A and the auxiliary aircraft B based on a wireless communication protocol, and therefore the three aircrafts are controlled to execute different flight tasks.
In the invention, the wireless communication protocol is a TCP/IP protocol stack. The aircraft control system is actually a dynamic wireless network system, communication is often performed in a multi-task mode, and the method is realized by improving the utilization rate of channels and needing a reasonable channel allocation method. The wireless communication protocol and the control algorithm of the aircraft control system are key factors for solving the problem, and in the network communication of the shared radio medium, the wireless communication protocol design of one-station multi-machine dynamic network group can utilize the wireless channel to the maximum extent and solve the problem of information conflict.
Further, the design of the dynamic network group protocol in the aircraft cluster considers the problems of the coexistence of hollow ground measurement and control and high-speed data transmission, the design of a three-dimensional random access and routing strategy, the tight constraint between a physical layer and a network layer and an omnidirectional or directional antenna, the shielding influence of an antenna installation mode and a fuselage and the like in the aircraft cluster communication from the system perspective. Therefore, the design of a one-station multi-machine dynamic networking communication protocol stack mainly adopts a TDD-TDMA system to realize the relay communication among multiple aircraft, and the data transmission rate is 2Mbps-10 Mbps.
As shown in fig. 4, the structure of one-station multi-machine dynamic networking protocol stack of the aircraft control system is as follows:
further, the physical layer mainly comprises an antenna control module 1. The antenna controller analyzes the remote control information of the communication connection transmitted by each aircraft on the Mac layer of the data chain, and the antenna control module 1 is controlled. And data transmitted from the Mac layer and received by the antenna control module 1 is directly transmitted. The antenna control module 1 corresponds to a protocol stack in the digital zero intermediate frequency signal processing unit 21 of the aircraft to complete the processing and generation of the frequency band data signal. The antenna control module 1 corresponds to an antenna of an aircraft protocol stack, and the directional communication between aircrafts often needs an omnidirectional antenna to maintain a link to complete the coordination task between networking aircrafts. The omnidirectional antenna is mainly installed on most aircrafts for communication in the line of sight, the directional antenna is mainly used for expanding the working distance or improving the transmission rate, and the aircrafts requiring over-line-of-sight communication generally adopt the self-tracking satellite-borne communication antenna.
Further, the MAC layer mainly includes a TDMA executor and a packet processing unit 215, and first performs buffering processing on the service data in the link, and the TDMA executor generates and controls the packet transmitted from the link according to the time slot table in the clock generating unit 217.
Further, the network layer mainly includes a topology information base, a data packet processing unit 215, and a network control module, and mainly realizes that the signal processing module 2 realizes intermediate-level forwarding of information reporting packets and information issuing packets; the network control unit realizes the functions of network initialization algorithm, network access and exit control, time slot allocation, time slot table generation and the like according to the networking control algorithm, and can realize the network control function of the aircraft; meanwhile, the topology information base realizes the routing control function of the aircraft multiple machines.
Further, the application layer mainly comprises a remote control service source, a remote measurement service source and a video service source, remote control and remote measurement functions are carried out on the aircraft through an aircraft data chain, and meanwhile obtained videos, videos and the like are used for judging situations such as hostility and surrounding environment.
The invention provides an aircraft data link terminal of one-station multi-machine dynamic network group and a control system thereof, which comprise the readable storage medium.
It should be understood that any process or method descriptions of methods, flow diagrams, or otherwise described herein, may be understood as representing modules, segments, or portions of code which include one or more executable instructions for implementing specific logical functions or steps of the process, and that the scope of the preferred embodiments of the present invention includes additional implementations in which functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art of the embodiments of the present invention.
It should be understood that portions of the present invention may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, the various steps or methods may be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are known in the art, may be used: discrete logic circuits with logic gates for implementing logic functions on data signals, Field Programmable Gate Arrays (FPGAs) with appropriate combinational logic gates.
It will be understood by those skilled in the art that all or part of the steps carried by the method for implementing the above embodiments may be implemented by hardware related to instructions of a program, which may be stored in a computer readable storage medium, and when the program is executed, the program includes one or a combination of the steps of the method embodiments.
In addition, functional units in the embodiments of the present invention may be integrated into one processing module, or each unit may exist alone physically, or two or more units are integrated into one module. The integrated module can be realized in a hardware mode, and can also be realized in a software functional module mode. The integrated module, if implemented in the form of a software functional module and sold or used as a stand-alone product, may also be stored in a computer readable storage medium.
The storage medium mentioned above may be a read-only memory, a magnetic or optical disk, etc.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. The aircraft data link terminal of the one-station multi-machine dynamic network group is characterized by comprising an antenna control module, a signal processing module and a power supply module, wherein the signal processing module further comprises a digital zero intermediate frequency signal processing unit; wherein, digital zero intermediate frequency signal processing unit includes:
the analog signal modulation unit is used for receiving a current first data signal and converting the current first data signal into a second data signal, wherein the second data signal is a digital zero intermediate frequency signal;
the first link signal processing unit is used for receiving the second data signal, processing the first link signal and then sending the processed first link signal to the data packet processing unit;
the second link signal processing unit is used for receiving the current third data signal, processing the second link signal and then sending the processed second link signal to the direct radio frequency modulation unit;
the direct radio frequency modulation unit is used for receiving the third data signal, converting the third data signal into a fourth data signal and sending the fourth data signal to the antenna control module;
the data packet processing unit is used for carrying out TCP packing and unpacking processing on the second data signal and the third data signal;
the first link signal processing includes: carrier recovery processing, bit synchronization processing, frame synchronization processing, descrambling processing, decoding processing and de-framing processing; and the first link signal processing unit further comprises:
the carrier recovery module is used for receiving the second data signal and carrying out carrier recovery on the digital zero intermediate frequency signal by using a complex phase discrimination algorithm to complete carrier tracking;
the bit synchronization module is used for carrying out bit synchronization on the data after carrier tracking locking and outputting demodulation result data and loop state data;
the frame synchronization module is used for performing frame header detection on the data after partial bit synchronization; wherein the frame header is a 32-bit sequence based on hexadecimal coding;
the descrambling module is used for descrambling data which are not in frame synchronization; the descrambling mode is exclusive or calculation through a pseudo-random sequence;
the decoding module is used for carrying out RS decoding calculation on all data in the first link signal processing unit;
the de-framing module is used for carrying out frame identification on the decoded data and sending the decoded data to the data packet processing unit; if the data frame is judged to be valid, the valid data packet is extracted and sent to the data interface unit, and if the data frame is judged to be filled, the filled data packet is discarded.
2. The aircraft data link terminal of claim 1, wherein the second link signal processing comprises: framing, encoding and synchronous head processing, scrambling and serial-parallel conversion processing; and the second link signal processing unit further comprises:
the framing module is used for receiving the third data signal and converting the third data signal into an effective data frame through data packaging;
the coding and synchronization head module is used for carrying out RS coding calculation on the data after partial framing and adding a synchronization head; wherein the synchronization header is a 32-bit sequence based on hexadecimal coding;
the scrambling module is used for scrambling the data which is not coded and is provided with the synchronous head; the scrambling mode is exclusive or calculation through a pseudo-random sequence;
and the serial-parallel conversion module is used for carrying out IQ modulation on all data in the second link signal processing unit and sending the data to the direct radio frequency modulation unit.
3. The aircraft data link terminal of claim 1, wherein the digital intermediate frequency signal processing unit further comprises:
the data interface unit is used for realizing the transmission of the second and third data signals; the data interface unit comprises an Ethernet physical interface and a serial port; wherein,
the Ethernet physical interface is used for transmitting video data;
and the serial port is used for transmitting the telemetering data and the remote control data.
4. The aircraft data link terminal of claim 1, wherein the digital intermediate frequency signal processing unit further comprises:
the clock generation unit is used for generating current reference clock data required by the digital zero intermediate frequency signal processing unit and sending the current reference clock data to the analog signal modulation unit and the direct radio frequency modulation unit;
and the power supply conversion unit is used for converting the voltage input by the power supply module into the working voltage required by the digital zero intermediate frequency signal processing unit.
5. The aircraft data link terminal of claim 1, wherein the antenna control module comprises:
an antenna for transmitting the fourth data signal to free space and receiving the first data signal;
the antenna receiving and transmitting controller is used for finishing the control switching of the transmitting signal and the receiving signal;
and the antenna cover is used for covering the antenna and the shell of the surface of the antenna transceiver controller.
6. The aircraft data link terminal of claim 1, wherein the power module comprises:
the power supply control unit is used for finishing outputting 5V, 12V and 220V power supplies to the aircraft data chain terminal;
a power supply unit for supplying and transmitting power to the power control unit; the power supply unit comprises a lithium battery and a solar panel.
7. The aircraft control system of the one-station multi-machine dynamic network group is characterized by comprising an aircraft platform and a ground control station; the aircraft platform comprises a main aircraft and a plurality of auxiliary aircraft, wherein the main aircraft and the auxiliary aircraft are provided with the aircraft data chain terminal according to any one of claims 1-6;
the slave aircraft is used for sending current telemetric data and video data to the master aircraft based on a wireless communication protocol; and receiving remote control data sent by the host aircraft based on a wireless communication protocol;
the main aircraft is used for sending telemetry data and video data to the ground control station based on a wireless communication protocol; and receiving the current remote control data sent by the ground control station based on a wireless communication protocol.
8. The aircraft control system of claim 7 wherein said wireless communication protocol is a TCP/IP protocol stack.
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| CN109756244B (en) * | 2019-03-28 | 2021-03-16 | 河南九乾电子科技有限公司 | Unmanned aerial vehicle data link system architecture device aiming at data transmission asymmetry |
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