CN116801134B - Rocket-borne space-based telemetry method and device and computing equipment - Google Patents
Rocket-borne space-based telemetry method and device and computing equipment Download PDFInfo
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Abstract
The invention provides an arrow-carried space-based telemetry method, an arrow-carried space-based telemetry device and computing equipment, and relates to the technical field of arrow-carried space-based telemetry, wherein the method comprises the following steps: bit synchronization and frame synchronization processing are carried out on the telemetry data full-frame code stream, and load parameters of a designated subframe are obtained; constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe; processing the space-based telemetry frame to obtain processing data, and transmitting the processing data to a radio frequency front end; the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal; the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit. The invention can provide higher gain and receiving sensitivity, can capture weak signals emitted by the aircraft and ensure high-quality data transmission.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an arrow-carried space-based telemetry method, an arrow-carried space-based telemetry device and computing equipment.
Background
The space-based relay telemetry system realizes relay transmission of space-based telemetry data through an arrow-borne space-based band terminal, a space-based radio frequency front end and an antenna on the air or the orbit and communicates with a ground station of a satellite communication center. Such systems typically consist of three parts, an arrow-mounted device, a relay device and a ground station. However, existing arrow-borne space-based telemetry systems have some technical limitations. Common solutions include the use of dipole antenna systems, directional antenna systems and antenna array systems.
Dipole antenna systems use a pair of dipole antennas for reception and transmission, and data transmission is achieved by adjusting the orientation and position of the antennas. However, dipole antennas have limited coverage and may have some limitations in terms of signal strength and receive sensitivity.
Directional antenna systems use directional antennas to receive and transmit signals. The advantage of such a system is a high gain and reception sensitivity, but the disadvantage is the need to accurately position and track the direction of the aircraft, which can present difficulties for high speed moving rocket-borne aircraft.
The antenna array system is composed of a plurality of antenna units, and beam forming and directional receiving are realized through reasonable phase and amplitude control. Such a system may provide higher gain and directivity, but is more complex and costly, and may require more complex adjustments and controls for dynamic changes in the airborne vehicle.
Therefore, the prior art scheme has the problems of limited coverage range, limited signal strength and receiving sensitivity, difficult positioning and tracking, high complexity and high cost and the like in the space-based relay telemetry system.
Disclosure of Invention
The invention aims to solve the technical problem of providing an arrow-carried space-based telemetry method, an arrow-carried space-based telemetry device and a computing device, which can provide higher gain and receiving sensitivity, capture weak signals emitted by an aircraft and ensure high-quality data transmission.
In order to solve the technical problems, the technical scheme of the invention is as follows:
in a first aspect, an arrow-borne space-based telemetry method, the method comprising:
acquiring a telemetry data full-frame code stream of an on-arrow comprehensive acquisition and coding device;
bit synchronization and frame synchronization processing are carried out on the telemetry data full-frame code stream, and load parameters of a designated subframe are obtained;
constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe;
processing the space-based telemetry frame to obtain processing data, and transmitting the processing data to a radio frequency front end; the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal; the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
Further, performing bit synchronization and frame synchronization processing on the telemetry data full-frame code stream to obtain load parameters of a designated subframe, including:
the baseband terminal receives a telemetry data full-frame code stream from an on-arrow comprehensive editing device;
performing bit synchronization processing on the telemetry data full-frame code stream to determine that each data frame is decoded by a receiving end;
after the bit synchronization processing, the baseband terminal performs frame synchronization processing to determine a start bit and an end bit of the data frame so as to decode each data frame;
after the data frame synchronization is completed, the baseband terminal extracts the load parameters of the designated subframes from each data frame.
Further, constructing the space-based telemetry frame according to the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end and the load parameters of the designated subframe, including:
acquiring telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe;
encoding telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe so as to respectively convert the telemetry parameters, the telemetry parameters and the load parameters into corresponding binary data;
inputting the binary data converted after the encoding into a preset telemetry frame to obtain an original telemetry frame;
And calculating the check code of the original telemetry frame, and adding the check code to the frame tail of the original telemetry frame to obtain the space-based telemetry frame.
Further, processing the space-based telemetry frame to obtain processed data and transmitting the processed data to a radio frequency front end, including:
decoding binary data in the space-based telemetry frame into an original telemetry frame;
analyzing and obtaining actual values of all telemetry parameters according to the original telemetry frame;
packaging or encoding actual values of each telemetry parameter to obtain a data packet adapting to a radio frequency front end transmission protocol, and converting the data packet from a digital form into a first analog signal;
and sending the first analog signal to a radio frequency front end.
Further, the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal, and the method includes:
the radio frequency front end converts the received first analog signal into a digital signal through an analog-to-digital converter;
channel coding is carried out on the converted digital signals so as to obtain coded digital signals;
data modulation is carried out on the coded digital signal, and the digital signal is converted into a second analog signal;
The second analog signal is amplified and filtered to obtain an amplified signal.
Further, transmitting the amplified signal to a dual-arm helical antenna such that the dual-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit, comprising:
the radio frequency front end transmits the amplified signal to a double-arm spiral antenna through a corresponding transmission line;
the double-arm helical antenna generates a corresponding electromagnetic field according to the amplified signal, and radiates the electromagnetic field into space in the form of electromagnetic waves.
In a second aspect, an arrow-borne space-based telemetry method, the method comprising:
acquiring processing data, wherein the processing data is a telemetry data full-frame code stream of an on-arrow comprehensive acquisition and coding device acquired by a baseband terminal, carrying out bit synchronization and frame synchronization processing on the telemetry data full-frame code stream to obtain load parameters of a designated subframe, constructing a space-base telemetry frame according to the telemetry parameters of the baseband terminal, the telemetry parameters of a radio frequency front end and the load parameters of the designated subframe, and processing the space-base telemetry frame to obtain processing data;
performing channel coding, data modulation and amplification filtering processing on the processed data to obtain an amplified signal;
The amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
In a third aspect, an arrow-carried space-based telemetry device, comprising:
the acquisition module is used for acquiring a telemetry data full-frame code stream of the comprehensive acquisition and coding device on the arrow; bit synchronization and frame synchronization processing are carried out on the telemetry data full-frame code stream, and load parameters of a designated subframe are obtained; constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe;
the processing module is used for processing the space-based telemetry frame to obtain processing data and transmitting the processing data to a radio frequency front end; the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal; the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
In a fourth aspect, a computing device includes:
one or more processors;
and a storage device for storing one or more programs which, when executed by the one or more processors, cause the one or more processors to implement the above-described methods.
In a fifth aspect, a computer readable storage medium stores a program that when executed by a processor implements the above method.
The scheme of the invention at least comprises the following beneficial effects:
according to the scheme, the omnidirectional coverage capacity can be realized by adopting the double-arm spiral antenna, so that telemetry data of the aircraft in different directions and angles can be effectively received and transmitted, the coverage range of a system is expanded, higher gain and receiving sensitivity can be provided, weak signals emitted by the aircraft can be captured, high-quality data transmission is ensured, complicated positioning and tracking operations are not needed, and the system can adapt to dynamic changes of various aircrafts and maintain stable communication connection.
Drawings
Fig. 1 is a schematic flow chart of an arrow-carried space-based telemetry method according to an embodiment of the invention.
Fig. 2 is a schematic diagram of a baseband terminal signal processing flow of an arrow-carried space-based telemetry method according to an embodiment of the present invention.
Fig. 3 is a schematic diagram of an arrow-borne space-based telemetry system provided by an embodiment of the invention.
Fig. 4 is a schematic diagram of a dual-arm helical antenna simulation of an rocket-borne space-based telemetry system provided by an embodiment of the present invention.
FIG. 5 is a flow chart of the design of the upper computer software according to the embodiment of the invention.
Fig. 6 is a schematic diagram of an arrow-carried space-based telemetry device provided by an embodiment of the invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described more closely below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1, an embodiment of the present invention proposes an arrow-carried space-based telemetry method, which includes:
step 11, obtaining a telemetry data full-frame code stream of the comprehensive on-arrow acquisition and coding device;
step 12, carrying out bit synchronization and frame synchronization processing on the telemetry data full-frame code stream to obtain load parameters of a designated subframe;
step 13, constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe;
step 14, processing the space-based telemetry frame to obtain processing data, and transmitting the processing data to a radio frequency front end; the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal; the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
In the embodiment of the invention, the omnidirectional coverage capability can be realized by adopting the double-arm spiral antenna, so that telemetry data of the aircraft in different directions and angles can be effectively received and transmitted, thereby expanding the coverage range of the system, providing higher gain and receiving sensitivity, capturing weak signals transmitted by the aircraft, ensuring high-quality data transmission, adapting to dynamic changes of various aircrafts and maintaining stable communication connection without complex positioning and tracking operation.
In step 11, the telemetry data full-frame code stream is acquired by the comprehensive collecting and editing device on the arrow, the data may include information of the flight state, speed, position, temperature, pressure and the like of the arrow, the full-frame code stream refers to a continuous stream connecting all the data, and the purpose of this step is to collect all necessary data so as to comprehensively monitor the state of the arrow in real time. In step 12, the original telemetry data is decoded and formatted by a bit sync process, which is used to ensure that the data is received at the correct bit rate, and a frame sync process, which is used to organize the data into individual data frames that can be more conveniently processed and parsed, after which the system extracts the payload parameters from the data frames, which may include information about the status of the payload, energy consumption, mode of operation, etc. In step 13, the system constructs a space-based telemetry frame based on the telemetry parameters of the baseband terminal, the telemetry parameters of the rf front end, and the loading parameters of the designated subframes, wherein the telemetry parameters of the baseband terminal may include data transmission rate, power, etc., and the telemetry parameters of the rf front end may include signal frequency, strength, etc., which are included in the space-based telemetry frame, and the purpose of this step is to integrate all telemetry data into a standard data frame for transmission in the space-based network.
In step 14, the space-based telemetry frame is further processed to obtain processed data, and the processed data is then sent to a radio frequency front end to optimize the efficiency of data transmission and reduce errors, where the radio frequency front end receives the processed data, performs channel coding, data modulation, and amplification filtering to enable the data to be sent out in the form of electromagnetic waves, and then sends the processed data to a double-arm helical antenna, which radiates electromagnetic waves to the space around the near-earth orbit, so that ground or other space-based devices can receive the signals, and can send the data from the arrow body to other places to facilitate real-time monitoring of the state and performance of the arrow.
In a preferred embodiment of the present invention, the step 12 may include:
step 121, the baseband terminal receives the telemetry data full-frame code stream from the comprehensive on-arrow editing device;
step 122, performing bit synchronization processing on the telemetry data full-frame code stream to determine that each data frame is decoded by the receiving end;
step 123, after the bit synchronization processing, the baseband terminal performs frame synchronization processing to determine the start bit and the end bit of the data frame, so as to decode each data frame;
In step 124, after the synchronization of the data frames is completed, the baseband terminal extracts the payload parameters of the specified sub-frames from each data frame.
In step 121, the baseband terminal is used as a data receiving device to receive the telemetry data full-frame code stream sent by the comprehensive collecting and editing device on the arrow, where the data is collected in real time and includes various status information of the arrow body, such as speed, position, temperature, pressure, etc. The purpose of the bit synchronization process in step 122 is to ensure accuracy of data reception, and only through bit synchronization, the receiving end can correctly identify the boundary of the data frame and decode, which is an important component of data reception, and if the bit synchronization process is wrong, the decoding of the data may fail. In step 123, frame synchronization ensures the integrity of the data frames, and each data frame can be correctly decoded only if the start bit and the end bit of the data frame are identified, which may result in a missing or erroneous data decoding if the frame synchronization process is incorrect. In step 123, the decoded data frame is further analyzed and processed, and the load parameters of the designated sub-frame are extracted, so that specific state information of the arrow body, such as energy consumption, working mode, etc., of the load can be obtained.
In a preferred embodiment of the present invention, the step 13 may include:
step 131, obtaining telemetry parameters of the baseband terminal, telemetry parameters of the radio frequency front end and load parameters of a designated subframe;
step 132, the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end and the load parameters of the appointed subframe are encoded to be respectively converted into corresponding binary data;
step 133, inputting the binary data converted after encoding into a preset telemetry frame to obtain an original telemetry frame;
step 134, calculating a check code of the original telemetry frame, and adding the check code to a frame tail of the original telemetry frame to obtain the space-based telemetry frame.
In step 131, the necessary telemetry parameters are collected from the various components, which may include data transmission rate, signal frequency, load status, etc. In step 132, the collected telemetry parameters are converted to binary data, which ensures data compatibility and transmission efficiency, and encoding is an important process because it can unify various types of data into one format for processing and transmission. In step 133, the telemetry frame is a data structure for transmitting telemetry data that enables various telemetry parameters to be integrated together to form a complete data packet. In step 134, the check code is one way to check whether an error occurs in the data transmission, and by adding the check code at the end of the data frame, the receiving end can determine the integrity and correctness of the data by calculating the check code, and adding the check code is an important step, because it can guarantee the reliability of the data transmission.
In a preferred embodiment of the present invention, the step 14 may include:
step 141, decoding binary data in the space-based telemetry frame into an original telemetry frame;
step 142, according to the original telemetry frame, analyzing to obtain actual values of each telemetry parameter;
step 143, packaging or encoding the actual values of the telemetry parameters to obtain a data packet adapted to the radio frequency front end transmission protocol, and converting the data packet from digital form to a first analog signal;
step 144, the first analog signal is sent to a radio frequency front end.
In step 141, binary data in the received space-based telemetry frame is converted back to the original telemetry frame. This process is necessary because binary data itself is difficult for humans to understand, and requires decoding into the original telemetry frame for further processing and analysis. In step 142, the system parses the original telemetry frame to obtain actual values of each telemetry parameter, where the values may reflect information such as the operation state of the baseband terminal, the operation state of the rf front end, and the state of the load. In step 143, the system encapsulates or encodes the parsed actual values of the telemetry parameters to generate a packet that conforms to the RF front-end transmission protocol, and then the system needs to convert the packet in digital form to an analog signal, since the RF front-end typically processes only analog signals. In step 144, the system sends the data packet converted into an analog signal to the rf front end, which, after receiving the analog signal, converts it back into a digital signal, and then performs a corresponding operation based on the received data. In general, the invention realizes the whole process from receiving the space-based telemetry frame to analyzing out telemetry parameters and then converting the parameters into analog signals suitable for radio frequency front-end processing, and is a complete data processing and transmission flow.
In a preferred embodiment of the present invention, the step 14 may include:
step 145, the radio frequency front end converts the received first analog signal into a digital signal through an analog-to-digital converter;
step 146, performing channel coding on the converted digital signal to obtain a coded digital signal;
step 147, performing data modulation on the encoded digital signal, and converting the digital signal into a second analog signal;
in step 148, the second analog signal is amplified and filtered to obtain an amplified signal.
In step 145, the rf front end converts the received first analog signal into a digital signal through an analog-to-digital converter, which is used to convert the analog signal into a digital signal, so as to facilitate subsequent processing and transmission. In step 146, the converted digital signal is subjected to channel coding to obtain a coded digital signal, where the channel coding is used to ensure reliability of the signal in the transmission process, and redundant information is added to the original information, so that the original information can be recovered by error detection and correction technology even if errors occur in the signal transmission process. In step 147, the encoded digital signal is subjected to data modulation, which is an important element in the communication system, to convert the information signal to be transmitted into a form suitable for transmission over a specific transmission medium, and to convert the encoded digital signal into an analog signal, so as to adapt to the wireless communication environment. In step 148, the second analog signal is amplified and filtered to obtain an amplified signal, the amplification being to enhance the strength of the signal so that it can be successfully transmitted to the destination; the filtering is to remove noise in the signal and improve the quality of the signal. The invention carries out a series of processing on the received analog signal, including analog-to-digital conversion, channel coding, data modulation, amplification and filtering, finally obtains the amplified signal which can be transmitted, ensures that the signal can keep the original information in the transmission process and can be successfully transmitted to the destination.
In a preferred embodiment of the present invention, the step 14 may include:
step 149, the rf front-end transmits the amplified signal to a dual-arm helical antenna through a corresponding transmission line; the double-arm helical antenna generates a corresponding electromagnetic field according to the amplified signal, and radiates the electromagnetic field into space in the form of electromagnetic waves.
In step 149, the rf front-end transmits the amplified signal to the dual-arm helical antenna, which is a primary hardware device for transmitting and receiving radio signals, the transmission line is a medium, typically a coaxial cable or other type of transmission line, connecting the rf front-end and the dual-arm helical antenna, and the dual-arm helical antenna then generates a corresponding electromagnetic field based on the amplified signal and radiates the electromagnetic field into space in the form of electromagnetic waves, which are fundamental principles of wireless communication, the generation and radiation of the electromagnetic field being driven by the amplified signal, the amplified signal determining the nature of the electromagnetic field, such as frequency, phase, etc., the electromagnetic wave being generated by electromagnetic field variations, which can traverse air and vacuum, carrying information for remote transmission.
An arrow-borne space-based telemetry method, the method comprising:
Acquiring processing data, wherein the processing data is a telemetry data full-frame code stream of an on-arrow comprehensive acquisition and coding device acquired by a baseband terminal, carrying out bit synchronization and frame synchronization processing on the telemetry data full-frame code stream to obtain load parameters of a designated subframe, constructing a space-base telemetry frame according to the telemetry parameters of the baseband terminal, the telemetry parameters of a radio frequency front end and the load parameters of the designated subframe, and processing the space-base telemetry frame to obtain processing data;
performing channel coding, data modulation and amplification filtering processing on the processed data to obtain an amplified signal;
the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
In the embodiment of the invention, the baseband terminal acquires the telemetry data full-emperor code stream of the comprehensive on-arrow acquisition and coding device. Then, bit synchronization and frame synchronization processing are carried out on the telemetry data full-frame code stream so as to ensure the integrity and accuracy of data in the transmission process. Load parameters for the specified sub-frames are then obtained, which are descriptive of the load conditions, including but not limited to temperature, pressure, location, etc. And then, constructing a space-base telemetry frame according to the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end and the load parameters of the designated subframes, wherein the step is to integrate all acquired data to form a complete space-base telemetry frame. And finally, processing the space-based telemetry frame to acquire the processing data to be transmitted. And performing channel coding, data modulation and amplification filtering processing on the processed data. The channel coding is to ensure stability and reliability of information in a transmission process, and by adding redundant information to original information, the original information can be recovered by error detection and correction techniques even if errors occur in the transmission process. Data modulation is the conversion of digital signals into analog signals for transmission over radio waves. The amplifying and filtering processing is to amplify and filter noise from the signal to ensure the quality and strength of the signal, so that the signal can be successfully transmitted to a destination. The amplified signal is sent to the double-arm helical antenna so that the double-arm helical antenna radiates the signal to the space around the near-earth track. This is the basic principle of wireless communication, and the transmission of telemetry information is achieved by transmitting signals to spatial devices in the form of electromagnetic waves through antennas.
As shown in fig. 1 to 5, in the embodiment of the present invention, the dual-arm helical antenna is a key medium for connecting the rocket-borne space-based telemetry system and the ground space-based detection station, and the selection, simulation and design of the space-based antenna play a decisive role in the performance of the rocket-borne space-based telemetry system. When the antenna-based single-arm spiral antenna resonates in an axial mode, the impedance of the antenna-based single-arm spiral antenna is far lower than 50 ohms, and when a spiral line which is short-circuited to the ground is added, the antenna can be used as a folding antenna, the low impedance can be adjusted to be close to the reference impedance of a coaxial cable by 50 ohms, and the antenna-based single-arm spiral antenna is creatively applied to an rocket-based space-based telemetry system and has a gain higher than that of the single-arm spiral antenna by 2 dB; compared with a sector directional antenna and a vibrator linear polarization antenna, the antenna simplifies the feed network, and the selection of the double-arm spiral antenna also puts more severe requirements on the electromagnetic compatibility of an arrow body. In order to simulate the working environment and working state of the antenna at the near-earth orbit more truly, the invention selects the electromagnetic wave, frequency domain and gravitational field interface module in the advanced digital simulation software COMSOL to perform multi-physical field coupling simulation of the rocket-borne antenna.
In the embodiment of the invention, the space-based double-arm helical antenna multi-physical field coupling simulation model consists of a double-arm helical radiator, a circular grounding plate, a tuning stub, a coaxial cable and a perfect matching layer surrounding an air area. One end of the double-arm spiral radiator is connected to the inner conductor pin of the radio frequency cable, and the other end is short-circuited to the ground plate. The dual-arm spiral radiator structure is wound along the z-axis and connected at the top end with the tuning stub centered on the ground plate. All metal parts in the coupling simulation are simulated into ideal electric conductors, and the inner domain of the metal parts is not included in the analysis range; the space between the inner conductor and the outer conductor of the coaxial cable is filled with a polytetrafluoroethylene material and the coaxial lumped port is used to excite the antenna. All domains except the perfect matching layer are partitioned by a tetrahedral mesh.
In the embodiment of the invention, on the basis of completing the preliminary preparation work of the geometric model construction, material parameter setting, port boundary confirmation and the like of the double-arm helical antenna, electromagnetic wave, frequency domain and gravitational field interfaces are added to the simulation model, and the center frequency is firstly set to 385MHz. In the process of setting physical fields and checking grids, a physical field hiding mode is set for designated domains and boundaries in a simulation model so as to more clearly observe the electric field intensity around a near-earth orbit space in the working process of an antenna, the double-arm spiral antenna uniformly radiates energy acquired from a feeder line to the surrounding space in an axial mode, and the maximum radiation direction is on a horizontal plane, so that the system antenna under the condition of multi-physical field coupling can control the maximum signal gain in the horizontal direction, and the omnidirectionality of the antenna design is verified.
In the embodiment of the invention, the upper computer software mainly realizes the functions of configuration of a space-based baseband and a space-based variable frequency board card and collection, display, storage and analysis of telemetry data. The system software data communication mode adopts a standard gigabit Ethernet interface, the upper computer software sends a control instruction to the space-based detection station through a UDP/IP protocol by a switch, and receives telemetry data sent by the space-based detection station in a multicast mode, after the data is received stably, a status indicator lamp at the upper right part of the software interface turns green, the received data is refreshed and displayed in a data receiving area in the middle area of the interface, the refreshing time interval is 50ms, real-time data is stored and recorded in a DAT file, and meanwhile, the lower part of the upper computer interface draws a space-based data frame counting change curve in real time.
The feasibility and the effectiveness of the invention are proved through a series of experiments, simulation and practical use verification.
Firstly, a series of experiments are carried out, an arrow-carried space-based telemetry system based on a double-arm helical antenna is built in a laboratory environment, and system performance tests are carried out on the arrow-carried space-based telemetry system. Through experiments, the omnidirectional coverage capability, high gain and receiving sensitivity, and anti-interference capability and stability of the double-arm spiral antenna are verified.
Secondly, a great deal of simulation and emulation work is carried out, and the performance of the system is evaluated through a computer model and emulation software. Through simulation, the theoretical performance of the double-arm helical antenna structure is verified, wherein the theoretical performance comprises key indexes such as coverage, gain, receiving sensitivity and the like. The simulation results are consistent with experimental data, and the feasibility and effectiveness of the system design of the invention are further demonstrated.
Finally, we have verified the system of the invention in an actual usage scenario. The arrow-borne space-based telemetry system based on the double-arm helical antenna is applied to a real arrow-borne aircraft, and actual data transmission and receiving tests are carried out. Through practical use, we verify the performance of the system in an actual flight environment. The practical use result shows that the system can stably receive and transmit the space-based telemetry data of the aircraft, and has reliable communication connection under different flight states.
As shown in fig. 2, an embodiment of the present invention further provides an arrow-carried space-based telemetry device 20, comprising:
an acquisition module 21, configured to acquire a telemetry data full-frame code stream of the on-arrow comprehensive acquisition and encoding device; bit synchronization and frame synchronization processing are carried out on the telemetry data full-frame code stream, and load parameters of a designated subframe are obtained; constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe;
a processing module 22, configured to process the space-based telemetry frame to obtain processing data, and send the processing data to a radio frequency front end; the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal; the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
Optionally, performing bit synchronization and frame synchronization processing on the telemetry data full-frame code stream to obtain load parameters of a specified subframe, including:
the baseband terminal receives a telemetry data full-frame code stream from an on-arrow comprehensive editing device;
performing bit synchronization processing on the telemetry data full-frame code stream to determine that each data frame is decoded by a receiving end;
After the bit synchronization processing, the baseband terminal performs frame synchronization processing to determine a start bit and an end bit of the data frame so as to decode each data frame;
after the data frame synchronization is completed, the baseband terminal extracts the load parameters of the designated subframes from each data frame.
Optionally, constructing the space-based telemetry frame according to the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end and the load parameters of the designated subframe includes:
acquiring telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe;
encoding telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe so as to respectively convert the telemetry parameters, the telemetry parameters and the load parameters into corresponding binary data;
inputting the binary data converted after the encoding into a preset telemetry frame to obtain an original telemetry frame;
and calculating the check code of the original telemetry frame, and adding the check code to the frame tail of the original telemetry frame to obtain the space-based telemetry frame.
Optionally, processing the space-based telemetry frame to obtain processed data and transmitting the processed data to a radio frequency front end includes:
decoding binary data in the space-based telemetry frame into an original telemetry frame;
Analyzing and obtaining actual values of all telemetry parameters according to the original telemetry frame;
packaging or encoding actual values of each telemetry parameter to obtain a data packet adapting to a radio frequency front end transmission protocol, and converting the data packet from a digital form into a first analog signal;
and sending the first analog signal to a radio frequency front end.
Optionally, the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal, and includes:
the radio frequency front end converts the received first analog signal into a digital signal through an analog-to-digital converter;
channel coding is carried out on the converted digital signals so as to obtain coded digital signals;
data modulation is carried out on the coded digital signal, and the digital signal is converted into a second analog signal;
the second analog signal is amplified and filtered to obtain an amplified signal.
Optionally, transmitting the amplified signal to a dual-arm helical antenna, such that the dual-arm helical antenna radiates the amplified signal to a space around a near-earth orbit, comprising:
the radio frequency front end transmits the amplified signal to a double-arm spiral antenna through a corresponding transmission line;
The double-arm helical antenna generates a corresponding electromagnetic field according to the amplified signal, and radiates the electromagnetic field into space in the form of electromagnetic waves.
It should be noted that the apparatus is an apparatus corresponding to the above method, and all implementation manners in the above method embodiment are applicable to this embodiment, so that the same technical effects can be achieved.
Embodiments of the present invention also provide a computing device comprising: a processor, a memory storing a computer program which, when executed by the processor, performs the method as described above. All the implementation manners in the method embodiment are applicable to the embodiment, and the same technical effect can be achieved.
Embodiments of the present invention also provide a computer-readable storage medium storing instructions that, when executed on a computer, cause the computer to perform a method as described above. All the implementation manners in the method embodiment are applicable to the embodiment, and the same technical effect can be achieved.
Those of ordinary skill in the art will appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, or combinations of computer software and electronic hardware. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the solution. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
It will be clear to those skilled in the art that, for convenience and brevity of description, specific working procedures of the above-described systems, apparatuses and units may refer to corresponding procedures in the foregoing method embodiments, and are not repeated herein.
In the embodiments provided in the present invention, it should be understood that the disclosed apparatus and method may be implemented in other manners. For example, the apparatus embodiments described above are merely illustrative, e.g., the division of the units is merely a logical function division, and there may be additional divisions when actually implemented, e.g., multiple units or components may be combined or integrated into another system, or some features may be omitted or not performed. Alternatively, the coupling or direct coupling or communication connection shown or discussed with each other may be an indirect coupling or communication connection via some interfaces, devices or units, which may be in electrical, mechanical or other form.
The units described as separate units may or may not be physically separate, and units shown as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.
In addition, each functional unit in the embodiments of the present invention may be integrated in one processing unit, or each unit may exist alone physically, or two or more units may be integrated in one unit.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution, in the form of a software product stored in a storage medium, comprising several instructions for causing a computer device (which may be a personal computer, a server, a network device, etc.) to perform all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a usb disk, a removable hard disk, a ROM, a RAM, a magnetic disk, or an optical disk, etc.
Furthermore, it should be noted that in the apparatus and method of the present invention, it is apparent that the components or steps may be disassembled and/or assembled. Such decomposition and/or recombination should be considered as equivalent aspects of the present invention. Also, the steps of performing the series of processes described above may naturally be performed in chronological order in the order of description, but are not necessarily performed in chronological order, and some steps may be performed in parallel or independently of each other. It will be appreciated by those of ordinary skill in the art that all or any of the steps or components of the methods and apparatus of the present invention may be implemented in hardware, firmware, software, or a combination thereof in any computing device (including processors, storage media, etc.) or network of computing devices, as would be apparent to one of ordinary skill in the art after reading this description of the invention.
The object of the invention can thus also be achieved by running a program or a set of programs on any computing device. The computing device may be a well-known general purpose device. The object of the invention can thus also be achieved by merely providing a program product containing program code for implementing said method or apparatus. That is, such a program product also constitutes the present invention, and a storage medium storing such a program product also constitutes the present invention. It is apparent that the storage medium may be any known storage medium or any storage medium developed in the future. It should also be noted that in the apparatus and method of the present invention, it is apparent that the components or steps may be disassembled and/or assembled. Such decomposition and/or recombination should be considered as equivalent aspects of the present invention. The steps of executing the series of processes may naturally be executed in chronological order in the order described, but are not necessarily executed in chronological order. Some steps may be performed in parallel or independently of each other.
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the present invention.
Claims (9)
1. An arrow-borne space-based telemetry method, the method comprising:
acquiring a telemetry data full-frame code stream of an on-arrow comprehensive acquisition and coding device;
bit synchronization and frame synchronization processing are carried out on the telemetry data full-frame code stream, and load parameters of a designated subframe are obtained;
constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe; the method specifically comprises the following steps: acquiring telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe, and constructing a space-based telemetry frame; the telemetry parameters of the baseband terminal comprise data transmission rate, signal frequency and load state; the telemetry parameters of the radio frequency front end comprise signal frequency and intensity; integrating telemetry parameters and converting the telemetry parameters into standard data frames; encoding telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe so as to respectively convert the telemetry parameters, the telemetry parameters and the load parameters into corresponding binary data; inputting the binary data converted after the encoding into a preset telemetry frame to obtain an original telemetry frame; calculating a check code of the original telemetry frame, and adding the check code to the frame tail of the original telemetry frame to obtain a space-based telemetry frame; the original telemetry frame is a data structure for transmitting telemetry data, and various telemetry parameters are integrated together to form a complete data packet;
Processing the space-based telemetry frame to obtain processing data, and transmitting the processing data to a radio frequency front end; the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal; the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
2. The method of claim 1, wherein performing bit synchronization and frame synchronization processing on the telemetry data full-frame code stream to obtain load parameters of a specified subframe comprises:
the baseband terminal receives a telemetry data full-frame code stream from an on-arrow comprehensive editing device;
performing bit synchronization processing on the telemetry data full-frame code stream to determine that each data frame is decoded by a receiving end;
after the bit synchronization processing, the baseband terminal performs frame synchronization processing to determine a start bit and an end bit of the data frame so as to decode each data frame;
after the data frame synchronization is completed, the baseband terminal extracts the load parameters of the designated subframes from each data frame.
3. The method of claim 1, wherein processing the space-based telemetry frame to obtain processed data and transmitting the processed data to a radio frequency front end comprises:
Decoding binary data in the space-based telemetry frame into an original telemetry frame;
analyzing and obtaining actual values of all telemetry parameters according to the original telemetry frame;
packaging or encoding actual values of each telemetry parameter to obtain a data packet adapting to a radio frequency front end transmission protocol, and converting the data packet from a digital form into a first analog signal;
and sending the first analog signal to a radio frequency front end.
4. The method of claim 3, wherein the radio frequency front end performs channel coding, data modulation, and amplification filtering on the received processed data to obtain an amplified signal, and comprising:
the radio frequency front end converts the received first analog signal into a digital signal through an analog-to-digital converter;
channel coding is carried out on the converted digital signals so as to obtain coded digital signals;
data modulation is carried out on the coded digital signal, and the digital signal is converted into a second analog signal;
the second analog signal is amplified and filtered to obtain an amplified signal.
5. The method of claim 4, wherein transmitting the amplified signal to a dual-arm helical antenna such that the dual-arm helical antenna radiates the amplified signal into a space surrounding a near-earth orbit comprises:
The radio frequency front end transmits the amplified signal to a double-arm spiral antenna through a corresponding transmission line;
the double-arm helical antenna generates a corresponding electromagnetic field according to the amplified signal, and radiates the electromagnetic field into space in the form of electromagnetic waves.
6. An arrow-borne space-based telemetry method, the method comprising:
acquiring processing data, wherein the processing data is a telemetry data full-frame code stream of an on-arrow comprehensive acquisition and coding device acquired by a baseband terminal, carrying out bit synchronization and frame synchronization processing on the telemetry data full-frame code stream to obtain load parameters of a designated subframe, constructing a space-base telemetry frame according to the telemetry parameters of the baseband terminal, the telemetry parameters of a radio frequency front end and the load parameters of the designated subframe, and processing the space-base telemetry frame to obtain processing data;
performing channel coding, data modulation and amplification filtering processing on the processed data to obtain an amplified signal;
transmitting the amplified signal to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space around a near-earth orbit;
constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe; the method specifically comprises the following steps: acquiring telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe, and constructing a space-based telemetry frame; the telemetry parameters of the baseband terminal comprise data transmission rate, signal frequency and load state; the telemetry parameters of the radio frequency front end comprise signal frequency and intensity; integrating telemetry parameters and converting the telemetry parameters into standard data frames; encoding telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe so as to respectively convert the telemetry parameters, the telemetry parameters and the load parameters into corresponding binary data; inputting the binary data converted after the encoding into a preset telemetry frame to obtain an original telemetry frame; calculating a check code of the original telemetry frame, and adding the check code to the frame tail of the original telemetry frame to obtain a space-based telemetry frame; the original telemetry frame is a data structure for transmitting telemetry data, integrating various telemetry parameters together to form a complete data packet.
7. An arrow-carried space-based telemetry device, comprising:
the acquisition module is used for acquiring a telemetry data full-frame code stream of the comprehensive acquisition and coding device on the arrow; bit synchronization and frame synchronization processing are carried out on the telemetry data full-frame code stream, and load parameters of a designated subframe are obtained; constructing a space-based telemetry frame according to telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe;
acquiring telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe, and constructing a space-based telemetry frame; the telemetry parameters of the baseband terminal comprise data transmission rate and power; the telemetry parameters of the radio frequency front end comprise signal frequency and intensity; integrating telemetry parameters and converting the telemetry parameters into standard data frames;
encoding telemetry parameters of a baseband terminal, telemetry parameters of a radio frequency front end and load parameters of a designated subframe so as to respectively convert the telemetry parameters, the telemetry parameters and the load parameters into corresponding binary data;
inputting the binary data converted after the encoding into a preset telemetry frame to obtain an original telemetry frame;
calculating a check code of the original telemetry frame, and adding the check code to the frame tail of the original telemetry frame to obtain a space-based telemetry frame;
The processing module is used for processing the space-based telemetry frame to obtain processing data and transmitting the processing data to a radio frequency front end; the radio frequency front end performs channel coding, data modulation and amplification filtering processing on the received processed data to obtain an amplified signal; the amplified signal is transmitted to a double-arm helical antenna such that the double-arm helical antenna radiates the amplified signal to a space surrounding a near-earth orbit.
8. A computing device, comprising:
one or more processors;
one or more processors;
storage means for storing one or more programs which when executed by the one or more processors cause the one or more processors to implement the method of any of claims 1 to 6.
9. A computer readable storage medium, characterized in that the computer readable storage medium has stored therein a program which, when executed by a processor, implements the method according to any of claims 1 to 6.
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