CN116801134A - A rocket-borne space-based telemetry method, device and computing equipment - Google Patents

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

A rocket-borne space-based telemetry method, device and computing equipment

Technical field

The invention relates to the field of aerospace technology, and in particular refers to a rocket-borne space-based telemetry method, device and computing equipment.

Background technique

The space-based relay telemetry system realizes the relay transmission of space-based telemetry data through rocket-borne space-based baseband terminals, space-based radio frequency front-ends and antennas in the air or in orbit, and communicates with the ground station of the satellite communication center. This system usually consists of three parts: rocket-borne equipment, relay equipment and ground station. However, existing rocket-borne space-based telemetry systems have some technical limitations. Common technical solutions include the use of dipole antenna systems, directional antenna systems and antenna array systems.

The dipole antenna system uses a pair of dipole antennas to receive and transmit, and realizes data transmission by adjusting the direction and position of the antennas. However, dipole antennas have limited coverage and may have some limitations in signal strength and reception sensitivity.

Directional antenna systems use directional antennas to receive and transmit signals. The advantage of this system is that it has high gain and receiving sensitivity, but its disadvantage is that it needs to accurately locate and track the direction of the aircraft, which may be difficult for high-speed arrow-borne aircraft.

The antenna array system consists of multiple antenna units, which achieve beam forming and directional reception through reasonable phase and amplitude control. This kind of system can provide higher gain and directivity, but its complexity and cost are higher, and the dynamic changes of the rocket-launched vehicle may require more complex adjustments and controls.

Therefore, existing technical solutions in space-based relay telemetry systems have problems such as limited coverage, limited signal strength and reception sensitivity, difficulty in positioning and tracking, and high complexity and cost.

Contents of the invention

The technical problem to be solved by the present invention is to provide a rocket-borne space-based telemetry method, device and computing equipment that can provide higher gain and receiving sensitivity, capture weak signals emitted by the aircraft, and ensure high-quality data transmission.

In order to solve the above technical problems, the technical solutions of the present invention are as follows:

In the first aspect, a rocket-borne space-based telemetry method, the method includes:

Obtain the full frame code stream of telemetry data from the integrated acquisition and editing device on the arrow;

Perform bit synchronization and frame synchronization processing on the full frame code stream of telemetry data to obtain the payload parameters of the specified subframe;

Construct a space-based telemetry frame based on the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the load parameters of the specified subframe;

Process the space-based telemetry frame to obtain processing data, and send the processing data to the radio frequency front end; causing the radio frequency front end to perform channel coding, data modulation, and amplification filtering processing on the received processing data to obtain amplification signal; sending the amplified signal to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low-Earth orbit.

Further, perform bit synchronization and frame synchronization processing on the full frame code stream of the telemetry data to obtain the load parameters of the specified subframe, including:

The baseband terminal receives the full-frame code stream of telemetry data from the comprehensive acquisition and editing device on the arrow;

Perform bit synchronization processing on the full frame code stream of the telemetry data to determine that the receiving end decodes each data frame;

After bit synchronization processing, the baseband terminal performs frame synchronization processing to determine the start bit and end bit of the data frame to decode each data frame;

When the data frame synchronization is completed, the baseband terminal extracts the payload parameters of the specified subframe from each data frame.

Further, a space-based telemetry frame is constructed based on the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the load parameters of the specified subframe, including:

Obtain the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the payload parameters of the specified subframe;

Encode the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the payload parameters of the specified subframe to convert them into corresponding binary data respectively;

Input the encoded and separately converted binary data into the preset telemetry frame to obtain the original telemetry frame;

Calculate the check code of the original telemetry frame, and add the check code to the end of the original telemetry frame to obtain a space-based telemetry frame.

Further, the space-based telemetry frame is processed to obtain processing data, and the processing data is sent to the radio frequency front end, including:

decoding the binary data in the space-based telemetry frame into a raw telemetry frame;

According to the original telemetry frame, analyze and obtain the actual value of each telemetry parameter;

Encapsulate or encode the actual values of each telemetry parameter to obtain a data packet adapted to the radio frequency front-end transmission protocol, and convert the data packet from digital form to a first analog signal;

Send the first analog signal to a radio frequency front end.

Further, the radio frequency front end performs channel coding, data modulation and amplification filtering on the received processed data to obtain an amplified signal, including:

The radio frequency front end converts the received first analog signal into a digital signal through an analog-to-digital converter;

Perform channel coding on the converted digital signal to obtain a coded digital signal;

Perform data modulation on the encoded digital signal and convert it into a second analog signal;

The second analog signal is amplified and filtered to obtain an amplified signal.

Further, sending the amplified signal to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low-Earth orbit, including:

The radio frequency front end sends the amplified signal to the double-arm helical antenna through the corresponding transmission line;

The two-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 the second aspect, a rocket-borne space-based telemetry method, the method includes:

Acquire processing data, which is the full-frame code stream of telemetry data of the comprehensive acquisition and editing device on the arrow obtained by the baseband terminal. Perform bit synchronization and frame synchronization processing on the full-frame code stream of the telemetry data to obtain the load parameters of the specified subframe. According to The telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end and the load parameters of the specified subframe construct a space-based telemetry frame, and process the space-based telemetry frame to obtain the processing data;

Perform channel coding, data modulation and amplification filtering on the processed data to obtain an amplified signal;

The amplified signal is sent to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low earth orbit.

In the third aspect, a rocket-borne space-based telemetry device includes:

The acquisition module is used to obtain the full-frame code stream of the telemetry data of the comprehensive acquisition and editing device on the arrow; perform bit synchronization and frame synchronization processing on the full-frame code stream of the telemetry data to obtain the load parameters of the specified subframe; according to the telemetry parameters and radio frequency of the baseband terminal The front-end telemetry parameters and the payload parameters of the specified subframe construct a space-based telemetry frame;

A processing module for processing the space-based telemetry frame to obtain processing data, and sending the processing data to a radio frequency front end; causing the radio frequency front end to perform channel coding, data modulation, and amplification filtering on the received processing data. Processing to obtain an amplified signal; sending the amplified signal to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low-Earth orbit.

In a fourth aspect, a computing device includes:

one or more processors;

A storage device is used to store one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the above method.

In a fifth aspect, a computer-readable storage medium stores a program, and when the program is executed by a processor, the above method is implemented.

The above solution of the present invention at least includes the following beneficial effects:

According to the above solution of the present invention, the present invention can achieve omnidirectional coverage by using a double-arm helical antenna, so that the telemetry data of the aircraft in different directions and angles can be effectively received and transmitted, thereby expanding the coverage of the system and enabling Provides high gain and receiving sensitivity, can capture weak signals emitted by aircraft, and ensure high-quality data transmission. This invention does not require complex positioning and tracking operations, can adapt to dynamic changes of various aircraft, and maintain stable communication connections. .

Description of the drawings

Figure 1 is a schematic flowchart of a rocket-borne space-based telemetry method provided by an embodiment of the present invention.

Figure 2 is a schematic diagram of the baseband terminal signal processing flow of the rocket-borne space-based telemetry method provided by an embodiment of the present invention.

Figure 3 is a schematic diagram of a rocket-borne space-based telemetry system provided by an embodiment of the present invention.

Figure 4 is a schematic diagram of a two-arm helical antenna simulation of a rocket-borne space-based telemetry system provided by an embodiment of the present invention.

Figure 5 is a flow chart of the software design of the host computer provided by the embodiment of the present invention.

Figure 6 is a schematic diagram of a rocket-borne space-based telemetry device provided by an embodiment of the present invention.

Detailed ways

Exemplary embodiments of the present disclosure will be described in detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to provide a thorough understanding of the disclosure, and to fully convey the scope of the disclosure to those skilled in the art.

As shown in Figure 1, an embodiment of the present invention proposes a rocket-borne space-based telemetry method. The method includes:

Step 11: Obtain the full frame code stream of telemetry data from the comprehensive acquisition and editing device on the arrow;

Step 12: Perform bit synchronization and frame synchronization processing on the full frame code stream of the telemetry data to obtain the payload parameters of the specified subframe;

Step 13: Construct a space-based telemetry frame based on the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the load parameters of the specified subframe;

Step 14: Process the space-based telemetry frame to obtain processing data, and send the processing data to the radio frequency front end; causing the radio frequency front end to perform channel coding, data modulation, and amplification filtering processing on the received processing data, To obtain an amplified signal; send the amplified signal to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low-Earth orbit.

In the embodiment of the present invention, the present invention can achieve omnidirectional coverage by using a double-arm helical antenna, so that the telemetry data of the aircraft in different directions and angles can be effectively received and transmitted, thereby expanding the coverage of the system. It can provide high gain and receiving sensitivity, capture weak signals emitted by aircraft, and ensure high-quality data transmission. This invention does not require complex positioning and tracking operations, can adapt to dynamic changes of various aircraft, and maintain stable communication. connect.

In step 11, the full-frame code stream of telemetry data is obtained through the comprehensive acquisition and editing device on the arrow. This data may include information such as the flight status, speed, position, temperature, pressure, etc. of the arrow. The full-frame code stream refers to the connection of all Continuous streaming of this data, the purpose of this step is to collect all necessary data to allow for comprehensive real-time monitoring of the arrow's status. In step 12, the raw telemetry data is decoded and formatted through bit synchronization, which ensures the data is received at the correct bit rate, and frame synchronization, which organizes the data into separate data frames, which can be processed and parsed more conveniently. Later, the system will extract load parameters from these data frames. These parameters may include information such as load status, energy consumption, and working mode. In step 13, the system will construct a space-based telemetry frame based on the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the load parameters of the specified subframe. The telemetry parameters of the baseband terminal may include data transmission rate, power, etc., and the radio frequency front end The telemetry parameters may include signal frequency, strength, etc., which will be included in the space-based telemetry frame. The purpose of this step is to integrate all telemetry data and convert it into a standard data frame to facilitate transmission in the space-based network. .

In step 14, the space-based telemetry frame will be further processed to obtain processed data, and then the processed data will be sent to the radio frequency front end to optimize the efficiency of data transmission and reduce errors. The radio frequency front end will receive these processed data and perform channel coding. , data modulation and amplification filtering processing, so that the data can be sent out in the form of electromagnetic waves. Next, the processed data will be sent to the double-arm helical antenna, which will radiate electromagnetic waves to the space around low-Earth orbit. , so that ground or other space-based equipment can receive these signals and send data from the rocket body to other places to monitor the status and performance of the rocket in real time.

In a preferred embodiment of the present invention, the above step 12 may include:

Step 121: The baseband terminal receives the full frame code stream of telemetry data from the comprehensive acquisition and editing device on the arrow;

Step 122: Perform bit synchronization processing on the entire frame code stream of the telemetry data to determine that the receiving end decodes each data frame;

Step 123: After bit synchronization processing, the baseband terminal performs frame synchronization processing to determine the start bit and end bit of the data frame to decode each data frame;

Step 124: After completing the data frame synchronization, the baseband terminal extracts the payload parameters of the specified subframe from each data frame.

In step 121, the baseband terminal functions as a data receiving device to receive the full frame code stream of telemetry data sent by the comprehensive acquisition and editing device on the rocket. These data are collected in real time and include various status information of the rocket body, such as speed, location, temperature, pressure, etc. In step 122, the purpose of bit synchronization processing is to ensure the accuracy of data reception. Only through bit synchronization can the receiving end correctly identify the boundaries of the data frame and decode it. This step is an important part of data reception. If the bit synchronization is Synchronization processing errors may cause data decoding to fail. In step 123, frame synchronization can ensure the integrity of the data frame. Only by identifying the start bit and end bit of the data frame can each data frame be correctly decoded. If the frame synchronization is processed incorrectly, it may result in missing data decoding. or error. In step 123, the decoded data frame is further analyzed and processed. By extracting the load parameters of the specified subframe, specific status information of the rocket body, such as the energy consumption of the load, working mode, etc., can be obtained.

In a preferred embodiment of the present invention, the above step 13 may include:

Step 131: Obtain the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the load parameters of the specified subframe;

Step 132: Encode the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the load parameters of the specified subframe to convert them into corresponding binary data respectively;

Step 133: Input the encoded and respectively converted binary data into the preset telemetry frame to obtain the original telemetry frame;

Step 134: Calculate the check code of the original telemetry frame, and add the check code to the end of the original telemetry frame to obtain a space-based telemetry frame.

In step 131, necessary telemetry parameters are collected from various parts, which may include data transmission rate, signal frequency, load status, etc. In step 132, the collected telemetry parameters are converted into binary data, which ensures data compatibility and transmission efficiency. Encoding is an important process because it can unify various types of data into one format. , easy to process and transmit. In step 133, the telemetry frame is a data structure used to transmit telemetry data, which can integrate various telemetry parameters to form a complete data package. In step 134, the check code is a way to check whether errors occur during data transmission. By adding a 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. performance, adding a check code is an important step because it can ensure the reliability of data transmission.

In a preferred embodiment of the present invention, the above step 14 may include:

Step 141, decode the binary data in the space-based telemetry frame into the original telemetry frame;

Step 142: Analyze and obtain the actual values of each telemetry parameter according to the original telemetry frame;

Step 143: Encapsulate or encode the actual values of each telemetry parameter to obtain a data packet adapted to the radio frequency front-end transmission protocol, and convert the data packet from digital form to a first analog signal;

Step 144: Send the first analog signal to the radio frequency front end.

In step 141, the binary data in the received space-based telemetry frame is converted back to the original telemetry frame. This process is necessary because the binary data itself is incomprehensible to humans and needs to be decoded into raw telemetry frames before it can be further processed and analyzed. In step 142, the system parses the original telemetry frame to obtain the actual values of each telemetry parameter. These values can reflect information such as the operating status of the baseband terminal, the operating status of the radio frequency front-end, and the status of the load. In step 143, the system will encapsulate or encode the actual values of the parsed telemetry parameters to generate a data packet that conforms to the radio frequency front-end transmission protocol. Then, the system needs to convert this digital data packet into an analog signal, because the radio frequency Front-ends can usually only handle analog signals. In step 144, the system sends the data packet converted into an analog signal to the radio frequency front end. After receiving the analog signal, the radio frequency front end converts it back to a digital signal, and then performs corresponding operations based on the received data. In general, the present invention realizes the entire process from receiving space-based telemetry frames, to parsing out telemetry parameters, to converting parameters into analog signals suitable for radio frequency front-end processing. It is a complete data processing and transmission process.

In a preferred embodiment of the present invention, the above 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: Perform channel coding on the converted digital signal to obtain a coded digital signal;

Step 147, perform data modulation on the encoded digital signal and convert it into a second analog signal;

Step 148: Amplify and filter the second analog signal to obtain an amplified signal.

In step 145, the radio frequency front end converts the received first analog signal into a digital signal through an analog-to-digital converter. This process is to convert the analog signal into a digital signal to facilitate subsequent processing and transmission. The analog-to-digital converter Its function is to convert analog signals into digital signals. In step 146, channel coding is performed on the converted digital signal to obtain a coded digital signal. Channel coding is to ensure the reliability of the signal during transmission. By adding redundant information to the original information, the signal is Even if errors occur during transmission, the original information can be restored through error detection and correction technology. In step 147, the encoded digital signal is data modulated and converted into a second analog signal. Data modulation is an important link in the communication system, and its purpose is to convert the information signal that needs to be transmitted into a signal suitable for transmission on a specific transmission medium. form, this step converts the encoded digital signal into an analog signal to adapt to the wireless communication environment. In step 148, the second analog signal is amplified and filtered to obtain an amplified signal. Amplification is to enhance the strength of the signal so that it can be successfully transmitted to the destination; filtering is to remove noise in the signal and improve signal quality. quality. The present invention performs a series of processing on the received analog signal, including analog-to-digital conversion, channel coding, data modulation, amplification and filtering, and finally obtains an amplified signal that can be transmitted, ensuring that the signal can maintain its integrity during the transmission process. original information and can be successfully transmitted to the destination.

In a preferred embodiment of the present invention, the above step 14 may include:

Step 149: The radio frequency front end sends the amplified signal to the double-arm helical antenna through the corresponding transmission line; the double-arm helical antenna generates a corresponding electromagnetic field according to the amplified signal, and converts the electromagnetic field into the form of electromagnetic waves. Radiate into space.

In step 149, the RF front-end sends the amplified signal to the double-arm helical antenna, which is a main hardware device used to send and receive radio signals. The transmission line is the medium connecting the RF front-end and the double-arm helical antenna. Usually It is a coaxial cable or other type of transmission line. The next process is that the double-arm helical antenna generates the corresponding electromagnetic field according to the amplified signal, and radiates the electromagnetic field into the space in the form of electromagnetic waves, which is the basis of wireless communication. The basic principle is that the generation and radiation of electromagnetic fields are driven by amplified signals. The amplified signals determine the properties of the electromagnetic field, such as frequency, phase, etc. Electromagnetic waves are generated by changes in the electromagnetic field. They can travel through air and vacuum, carrying information for long-distance transmission.

A rocket-borne space-based telemetry method, the method includes:

Acquire processing data, which is the full-frame code stream of telemetry data of the comprehensive acquisition and editing device on the arrow obtained by the baseband terminal. Perform bit synchronization and frame synchronization processing on the full-frame code stream of the telemetry data to obtain the load parameters of the specified subframe. According to The telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end and the load parameters of the specified subframe construct a space-based telemetry frame, and process the space-based telemetry frame to obtain the processing data;

Perform channel coding, data modulation and amplification filtering on the processed data to obtain an amplified signal;

The amplified signal is sent to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low earth orbit.

In the embodiment of the present invention, the baseband terminal obtains the entire code stream of the telemetry data of the onboard comprehensive acquisition and editing device. Then, bit synchronization and frame synchronization processing are performed on the full frame code stream of the telemetry data to ensure the integrity and accuracy of the data during the transmission process. Then, obtain the load parameters of the specified subframe. These parameters describe the load status, including but not limited to temperature, pressure, position, etc. Then, a space-based telemetry frame is constructed based on the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front-end, and the load parameters of the specified subframe. This step is to integrate all the acquired data to form a complete space-based telemetry frame. Finally, the space-based telemetry frames are processed to obtain the processed data that needs to be transmitted. Perform channel coding, data modulation and amplification filtering on the processed data. Channel coding is to ensure the stability and reliability of information during transmission. By adding redundant information to the original information, even if an error occurs during the transmission process, the original information can be restored through error detection and correction technology. Data modulation is the conversion of digital signals into analog signals for transmission over radio waves. Amplification and filtering process is to amplify the signal and filter out the noise to ensure the quality and strength of the signal so that the signal can be successfully transmitted to the destination. The amplified signal is sent to the double-arm helical antenna, so that the double-arm helical antenna radiates the signal into the space around low Earth orbit. This is the basic principle of wireless communication. The signal is transmitted to the space equipment in the form of electromagnetic waves through the antenna to realize the transmission of telemetry information.

As shown in Figures 1 to 5, in the embodiment of the present invention, the double-arm helical antenna is the key medium connecting the rocket-borne space-based telemetry system and the ground space-based detection station. The selection, simulation and design of the space-based antenna are important for the rocket. The performance of the space-based telemetry system plays a decisive role. When the space-based single-arm helical antenna resonates in the axial mode, its impedance is well below 50 ohms, and when a helix shorted to the ground is added, the antenna can be used as a folded antenna, and the low impedance can be adjusted to close to The reference impedance of the coaxial cable is 50 ohms. This invention innovatively applies the two-arm helical antenna to the rocket-borne space-based telemetry system, with a gain 2dB higher than that of the single-arm helical antenna; and with sector directional antennas and oscillator linear polarization Compared with the antenna, the feed network is simplified. Of course, the selection of the double-arm helical antenna also puts forward more stringent requirements on the electromagnetic compatibility of the rocket body. In order to more realistically simulate the working environment and working status of the antenna in low-Earth orbit, the present invention selects the electromagnetic wave, frequency domain and gravity field interface modules in the advanced numerical simulation software COMSOL to perform multi-physics coupling of the rocket-borne space-based antenna. simulation.

In the embodiment of the present invention, the space-based double-arm spiral antenna multi-physics coupling simulation model consists of an double-arm spiral radiator, a circular ground plate, a tuning stub, a coaxial cable and a perfect matching layer surrounding the air area. . One end of the two-arm helix radiator is connected to the inner conductor pin of the RF cable and the other end is shorted to the ground plate. The two-arm spiral radiator structure is wound along the z-axis and connected at the top, with the tuning stub located in the center of the ground plate. All metal parts in this coupling simulation are simulated as ideal electrical conductors, and their internal domains are not included in the analysis scope; the space between the internal conductor and the external conductor of the coaxial cable is filled with polytetrafluoroethylene material, and the coaxial type The lumped port is used to excite the antenna. All domains except the perfectly matched layer are meshed by tetrahedrons.

In the embodiment of the present invention, after completing the preliminary preparation work such as the construction of the geometric model of the double-arm helical antenna, setting the material parameters, and confirming the port boundaries, the electromagnetic wave, frequency domain and gravity field interfaces are added to the simulation model. First, the center frequency is set is 385MHz. During the process of setting up the physical field and viewing the grid, "physical field hiding" is set for the specified domain and boundary in the simulation model, so that the electric field intensity and axial mode around the low-Earth orbit space can be more clearly observed during the operation of the antenna. The lower double-arm helix antenna radiates the energy obtained from the feeder evenly to the surrounding space, and the maximum radiation direction is on the horizontal plane, indicating that the system antenna under multi-physics coupling conditions can control the maximum signal gain in the horizontal direction, verifying the antenna design omnidirectionality.

In the embodiment of the present invention, the host computer software mainly implements the configuration of the space-based baseband and space-based frequency conversion board and the collection, display, storage, and analysis functions of telemetry data. The system software data communication method adopts a standard Gigabit Ethernet interface. The host computer software sends control instructions to the space-based detection station through the switch through the UDP/IP protocol, and uses multicast to receive telemetry data sent by the space-based detection station. The data After the acceptance is stable, the four status indicators on the upper right side of the software interface turn green, and the received data is refreshed and displayed in the "Data Acceptance" area in the middle area of the interface. The refresh time interval is 50ms. The real-time data is stored and recorded in .DAT files. At the same time, the upper The space-based data frame count change curve is drawn in real time below the machine interface.

The invention has been verified through a series of experiments, simulations and actual use to prove its feasibility and effectiveness.

First, we conducted a series of experiments, built a rocket-borne space-based telemetry system based on a double-arm helical antenna in a laboratory environment, and tested its system performance. Through experiments, we verified the omnidirectional coverage capability, high gain and receiving sensitivity, as well as the anti-interference capability and stability of the double-arm helical antenna.

Secondly, we conducted extensive simulation and simulation work to evaluate the performance of the system through computer models and simulation software. Through simulations, we verified the theoretical performance of the double-arm helical antenna structure, including key indicators such as coverage, gain, and receiving sensitivity. The simulation results are consistent with the experimental data, further proving the feasibility and effectiveness of the system design of the present invention.

Finally, we verified the system of the present invention in actual usage scenarios. We applied the rocket-borne space-based telemetry system based on the dual-arm helical antenna to a real rocket-borne vehicle and conducted actual data transmission and reception tests. Through actual use, we verified the performance of the system in the actual flight environment. Actual use results show that the system of the present invention can stably receive and transmit the space-based telemetry data of the aircraft, and has reliable communication connections under different flight conditions.

As shown in Figure 2, an embodiment of the present invention also provides a rocket-borne space-based telemetry device 20, which includes:

The acquisition module 21 is used to obtain the full-frame code stream of the telemetry data of the comprehensive acquisition and editing device on the arrow; perform bit synchronization and frame synchronization processing on the full-frame code stream of the telemetry data to obtain the load parameters of the specified subframe; according to the telemetry parameters of the baseband terminal, The telemetry parameters of the radio frequency front end and the payload parameters of the specified subframe construct a space-based telemetry frame;

The processing module 22 is used to process the space-based telemetry frame to obtain processing data, and send the processing data to the radio frequency front end; causing the radio frequency front end to perform channel coding, data modulation and amplification on the received processing data. Filtering is performed to obtain an amplified signal; and the amplified signal is sent to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low-Earth orbit.

Optionally, perform bit synchronization and frame synchronization processing on the full frame code stream of the telemetry data to obtain the payload parameters of the specified subframe, including:

The baseband terminal receives the full-frame code stream of telemetry data from the comprehensive acquisition and editing device on the arrow;

Perform bit synchronization processing on the full frame code stream of the telemetry data to determine that the receiving end decodes each data frame;

After bit synchronization processing, the baseband terminal performs frame synchronization processing to determine the start bit and end bit of the data frame to decode each data frame;

When the data frame synchronization is completed, the baseband terminal extracts the payload parameters of the specified subframe from each data frame.

Optionally, construct a space-based telemetry frame based on the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the load parameters of the specified subframe, including:

Obtain the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the payload parameters of the specified subframe;

Encode the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the payload parameters of the specified subframe to convert them into corresponding binary data respectively;

Input the encoded and separately converted binary data into the preset telemetry frame to obtain the original telemetry frame;

Calculate the check code of the original telemetry frame, and add the check code to the end of the original telemetry frame to obtain a space-based telemetry frame.

Optionally, process the space-based telemetry frame to obtain processing data, and send the processing data to the radio frequency front end, including:

decoding the binary data in the space-based telemetry frame into a raw telemetry frame;

According to the original telemetry frame, analyze and obtain the actual value of each telemetry parameter;

Encapsulate or encode the actual values of each telemetry parameter to obtain a data packet adapted to the radio frequency front-end transmission protocol, and convert the data packet from digital form to a first analog signal;

Send the first analog signal to a radio frequency front end.

Optionally, the radio frequency front end performs channel coding, data modulation and amplification filtering on the received processed data to obtain an amplified signal, including:

The radio frequency front end converts the received first analog signal into a digital signal through an analog-to-digital converter;

Perform channel coding on the converted digital signal to obtain a coded digital signal;

Perform data modulation on the encoded digital signal and convert it into a second analog signal;

The second analog signal is amplified and filtered to obtain an amplified signal.

Optionally, the amplified signal is sent to the double-arm helical antenna, so that the double-arm helical antenna radiates the amplified signal to the space around the low-Earth orbit, including:

The radio frequency front end sends the amplified signal to the double-arm helical antenna through the corresponding transmission line;

The two-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 this device is a device corresponding to the above method. All implementation methods in the above method embodiment are applicable to this embodiment and can achieve the same technical effect.

An embodiment of the present invention also provides a computing device, including: a processor and a memory storing a computer program. When the computer program is run by the processor, the method as described above is executed. All implementations in the above method embodiment are applicable to this embodiment and can achieve the same technical effect.

Embodiments of the present invention also provide a computer-readable storage medium that stores instructions that, when executed on a computer, cause the computer to perform the method described above. All implementations in the above method embodiment are applicable to this embodiment and can achieve the same technical effect.

Those of ordinary skill in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented with electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Skilled artisans may implement the described functionality using different methods for each specific application, but such implementations should not be considered to be beyond the scope of the present invention.

Those skilled in the art can clearly understand that for the convenience and simplicity of description, the specific working processes of the systems, devices and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be described again here.

In the embodiments provided by the present invention, it should be understood that the disclosed devices and methods can be implemented in other ways. For example, the device embodiments described above are only illustrative. For example, the division of the units is only a logical function division. In actual implementation, there may be other division methods. For example, multiple units or components may be combined or can be integrated into another system, or some features can be ignored, or not implemented. On the other hand, the coupling or direct coupling or communication connection between each other shown or discussed may be through some interfaces, and the indirect coupling or communication connection of the devices or units may be in electrical, mechanical or other forms.

The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place, or they may be distributed to multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

In addition, each functional unit in various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit.

If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention essentially or the part that contributes to the existing technology or the part of the technical solution can be embodied in the form of a software product. The computer software product is stored in a storage medium, including Several instructions are used to cause a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The aforementioned storage media include: U disk, mobile hard disk, ROM, RAM, magnetic disk or optical disk and other media that can store program codes.

In addition, it should be pointed out that in the device and method of the present invention, obviously, each component or each step can be decomposed and/or recombined. These decompositions and/or recombinations should be regarded as equivalent solutions of the present invention. Furthermore, the steps for executing the above series of processes can naturally be executed in chronological order in the order described, but they do not necessarily need to be executed in chronological order, and some steps may be executed in parallel or independently of each other. For those of ordinary skill in the art, it can be understood that all or any steps or components of the method and device of the present invention can be implemented in any computing device (including processor, storage medium, etc.) or a network of computing devices in the form of hardware or firmware. , software or their combination, this can be achieved by those of ordinary skill in the art using their basic programming skills after reading the description of the present invention.

Therefore, the objects of the invention can 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. Therefore, the object of the present invention can also be achieved only by providing a program product containing a program code for implementing the 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. Obviously, the storage medium may be any known storage medium or any storage medium developed in the future. It should also be pointed out that in the device and method of the present invention, obviously, each component or each step can be decomposed and/or recombined. These decompositions and/or recombinations should be regarded as equivalent solutions of the present invention. Furthermore, the steps for executing the above series of processes can naturally be executed in chronological order in the order described, but do not necessarily need to be executed in chronological order. Certain steps can be performed in parallel or independently of each other.

The above is the preferred embodiment of the present invention. It should be pointed out that for those of ordinary skill in the art, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications can also be made. should be regarded as the protection scope of the present invention.

Claims (10)

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;

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 according to claim 2, wherein constructing the space-based telemetry frame based on the telemetry parameters of the baseband terminal, the telemetry parameters of the radio frequency front end, and the loading parameters of the designated subframes, comprises:

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.

4. The method of claim 3, 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.

5. The method of claim 4, 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.

6. The method of claim 5, 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.

7. 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.

8. 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.

9. 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 1-7.

10. 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 1-7.