Test system for multi-mode and multi-system aerospace measurement and control communication platform

Abstract

The present application relates to a test system for a multi-mode and multi-system aerospace measurement and control communication platform, wherein the test system includes: a radio frequency module, a baseband module, a time-frequency module, a power supply module and an industrial computer; the radio frequency module is used to provide a radio frequency channel for the test system, wherein the radio frequency channel includes an uplink channel and a downlink channel; the baseband module is used to process the signal through a preset multi-system and a preset multi-mode; the time-frequency module is used to provide a time-frequency reference for the test system; the industrial computer is used to provide an operating environment for the upper computer software in the test system; the power supply module is used to provide power for the test system; wherein the radio frequency module, the baseband module, the time-frequency module, the industrial computer and the power supply module are connected to each other through a preset standard interface. Through this application, the problem that the test system of the aerospace measurement and control communication platform in the prior art is mainly based on customized requirements and cannot meet the requirements of different systems or modes in different scenarios is solved.

Description

Technical Field

[0001] The present application relates to the field of aerospace measurement and control, and in particular to a test system for a multi-mode and multi-system aerospace measurement and control communication platform. Background Art

[0002] In recent years, with the rapid development of the aerospace industry, the aerospace tracking and control communication platform, as the lifeline of the aerospace industry, also plays a vital role. The aerospace tracking and control communication platform is actually a comprehensive electronic platform, whose main functions are to track and measure orbits, telemetry, remote control, and up / downlink communications for satellites and other aircraft. The satellite tracking and control communication system is the only information channel for the satellite to communicate with the ground after it is launched. Therefore, the stability of the aerospace tracking and control communication platform is the basic guarantee for the normal operation and work of the satellite in orbit.

[0003] At present, the test system of aerospace measurement, control and communication platform has the following shortcomings: it is mainly based on customized needs, with long development cycle and high R&D cost; the degree of modularization and generalization is low, which cannot guarantee the testing needs of various stages of aerospace, resulting in poor effectiveness of test data of spacecraft life cycle. Summary of the invention

[0004] The present application provides a test system for a multi-mode and multi-system aerospace measurement and control communication platform to solve the problem that the test system for aerospace measurement and control communication platform in the prior art is mainly based on customized requirements and cannot meet the requirements of different systems or modes in different scenarios.

[0005] The present application provides a test system for a multi-mode and multi-system aerospace measurement and control communication platform, comprising: a radio frequency module, a baseband module, a time-frequency module, a power supply module and an industrial computer; the radio frequency module is used to provide a radio frequency channel for the test system, wherein the radio frequency channel comprises an uplink channel and a downlink channel; the baseband module is used to process signals through a preset multi-system and a preset multi-mode; the time-frequency module is used to provide a time-frequency reference for the test system; the industrial computer is used to provide an operating environment for the upper computer software in the test system; the power supply module is used to provide power for the test system; wherein the radio frequency module, the baseband module, the time-frequency module, the industrial computer and the power supply module are connected to each other through a preset standard interface.

[0006] Optionally, the RF module is used to receive a 70 MHz intermediate frequency signal sent by a baseband module based on the uplink channel, and to convert, amplify, and filter the 70 MHz intermediate frequency signal to an application frequency band, and to convert, amplify, and filter the received application frequency band signal to the 70 MHz intermediate frequency based on the downlink channel.

[0007] Optionally, the baseband module is used to receive a 70 MHz intermediate frequency signal, and perform signal demodulation, information extraction and modulation on the 70 MHz intermediate frequency signal based on the target system in the preset multi-system, and send the processed 70 MHz intermediate frequency signal to the RF module; the baseband module is also used to perform Doppler dynamic simulation on the processed 70 MHz, and perform coherent measurement or incoherent measurement on the Doppler dynamic simulation result based on the target operating mode in the preset multi-mode.

[0008] Optionally, the time-frequency module is used to automatically switch to the external clock mode when a 10 MHz reference clock input is detected; switch to the internal clock mode when no 10 MHz reference clock input is detected; and send the switching result to the baseband module.

[0009] Optionally, the industrial computer is used to run the host computer software based on selecting a system from the preset multiple systems and selecting a mode from the preset multiple modes.

[0010] Optionally, the baseband module also includes an intermediate frequency modulation module, which is used to output a corresponding carrier analog quantity according to a preset dynamic Doppler simulation mode, Doppler frequency range, and Doppler change rate; wherein the dynamic Doppler simulation mode is simulated based on a direct digital frequency DDS method.

[0011] Optionally, the intermediate frequency modulation module is also used to perform scrambling, RS encoding, NRZ code conversion and convolution processing on the input data.

[0012] Optionally, when the input data is instruction information, the instruction information is obtained from a data frame sent by the host software in the industrial computer; when the input data is forwarding information, the forwarding information is forwarded by the host software in the industrial computer; when the input data is transparent information, the forwarding information is obtained by real-time input from an external physical interface.

[0013] Optionally, the baseband module also includes an intermediate frequency demodulation module, and the intermediate frequency demodulation module is used to perform convolution decoding, NRZ code conversion, frame synchronization, RS decoding and descrambling processing on the received demodulated information.

[0014] Optionally, the baseband module, after receiving the downlink ranging link signal, performs despreading, demodulation, and frame synchronization extraction to obtain a downlink measurement frame synchronization signal, and then uses the downlink frame synchronization to sample the uplink signal formed by itself, extracts the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, and ground time, and samples the downlink Doppler value to obtain pseudo-range related information, pseudo-Doppler measurement values, and time sampling values ​​to calculate and complete ranging and speed measurement; wherein, the downlink ranging link signal is obtained by the satellite after receiving the uplink signal and performing despreading, demodulation, and frame synchronization; the baseband module is also used to perform despreading, demodulation, and frame synchronization extraction on the downlink ranging link signal to obtain the downlink ranging signal. The downlink frame synchronization signal is measured, and then the uplink signal formed by itself is sampled by using the downlink frame synchronization, and the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase and ground time are extracted, and the downlink Doppler value is sampled to obtain the uplink pseudo-range information, pseudo-Doppler measurement value, time sampling value and the downlink pseudo-range information, pseudo-Doppler measurement value and time sampling value measured on the ground; wherein, the downlink ranging link signal is despread, demodulated and frame synchronized after the satellite receives the uplink signal, and then the uplink signal is sampled by using the downlink ranging information frame synchronization formed by itself, and the bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase and on-board time are extracted, and the uplink pseudo-Doppler value is sampled.

[0015] The above-mentioned technical scheme provided by the embodiment of the present application has the following advantages compared with the prior art: in the embodiment of the present application, the separate RF modules, baseband modules, time-frequency modules, power modules and industrial computers in the test system are connected through a standard interface; in addition, on the basis of the time-frequency module and the power module providing a reference time-frequency reference and power support for the test system, the RF module in the embodiment of the present application provides the test system with reception and transmission of RF signals through the uplink channel and the downlink channel, and the baseband module can select the corresponding system and / or mode for testing as needed in different application scenarios through the preset multi-system and preset multi-mode, thereby solving the problem that the aerospace measurement and control communication platform test system in the prior art is mainly based on customized requirements and cannot meet the requirements of different systems or modes in different scenarios. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and, together with the description, serve to explain the principles of the invention.

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0018] One or more embodiments are exemplarily described by pictures in the corresponding drawings, and these exemplified descriptions do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings represent similar elements, and unless otherwise stated, the figures in the drawings do not constitute proportional limitations.

[0019] Figure 1 A schematic diagram of the structure of a test system for a multi-mode and multi-system aerospace measurement and control communication platform provided in an embodiment of the present application;

[0020] Figure 2 An optional structural diagram of a test system for a multi-mode and multi-system aerospace measurement and control communication platform provided in an embodiment of the present application;

[0021] Figure 3 A flowchart of processing data input in a test system provided in an embodiment of the present application;

[0022] Figure 4 A flowchart of encoding and decoding information in a test system provided in an embodiment of the present application. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0024] The disclosure below provides many different embodiments or examples to implement different structures of the present invention. In order to simplify the disclosure of the present invention, the parts and settings of specific examples are described below. Of course, they are only examples, and the purpose is not to limit the present invention. In addition, the present invention can repeat reference numbers and / or letters in different examples. This repetition is for the purpose of simplification and clarity, and does not itself indicate the relationship between the various embodiments and / or settings discussed.

[0025] Figure 1 A structural diagram of a test system for a multi-mode and multi-system aerospace measurement and control communication platform provided in an embodiment of the present application is shown in FIG. Figure 1 As shown, the test system includes: a radio frequency module, a baseband module, a time-frequency module, a power module and an industrial computer;

[0026] The radio frequency module is used to provide a radio frequency channel for the test system, wherein the radio frequency channel includes an uplink channel and a downlink channel;

[0027] In the embodiment of the present application, digitally controlled attenuation is provided for the test system through an uplink channel and a downlink channel.

[0028] A baseband module, used for processing signals through a preset multi-system and a preset multi-mode;

[0029] It should be noted that the multi-system in the embodiment of the present application may include a non-coherent spread spectrum signal system, a coherent spread spectrum system, a unified carrier system, a measurement and control data transmission integrated system, a relay short message system, a ground-based short message system, a low-speed data transmission system, an ad-hoc system, etc. In addition, the multi-mode in the embodiment of the present application may be an intermediate frequency working mode, an S-band radio frequency mode, a QV-band radio frequency mode, a self-closed loop test mode, a remote access mode, etc. In a specific example, the desired system or mode can be selected according to different application scenario requirements.

[0030] The time-frequency module is used to provide a time-frequency reference for the test system;

[0031] In the embodiment of the present application, a high-stability crystal oscillator, a voltage-controlled oscillator, and a digital CPLD are used to provide a highly stable, low-noise time-frequency reference for the system. At the same time, two coherent, highly stable, low-noise frequency signals are provided to provide a stable and reliable working clock for other modules in the device.

[0032] Industrial computer, used to provide operating environment for the host computer software in the test system;

[0033] It should be noted that the host computer software can arbitrarily select a mode and system for operation according to the differences in application scenarios and platforms, and at the same time provide full-platform working status display and interactive interface, as well as process data storage and other functions for the application scenarios.

[0034] A power module, used to provide power to the test system;

[0035] Among them, the radio frequency module, baseband module, time-frequency module, industrial computer and power supply module are connected to each other through a preset standard interface.

[0036] It should be noted that the standard interface in the embodiment of the present application includes a general instrument interface and a signal interface, wherein the general instrument interface can be a 10MHz clock input interface, a 10MHz clock output interface, an IRIG-B interface, a 1PPS input interface, a 1PPS output interface, a network port, etc.; the signal interface can be an up-conversion RF signal output interface, a down-conversion RF signal receiving interface, an up-conversion IF signal input interface, a down-conversion IF signal output interface, an IF signal 70MHz / 140MHz output interface, an IF signal 70MHz / 140MHz receiving interface, etc.

[0037] In an optional implementation manner of an embodiment of the present application, the RF module in the embodiment of the present application is further used to receive a 70 MHz intermediate frequency signal sent by a baseband module based on an uplink channel, and to convert, amplify, and filter the 70 MHz intermediate frequency signal to an application frequency band, and to convert, amplify, and filter the received application frequency band signal to a 70 MHz intermediate frequency based on a downlink channel.

[0038] It can be seen that the RF module in the embodiment of the present application has two channels for transmission and reception, RF input-IF output, and RF output-IF input. That is, the RF module in the embodiment of the present application is a RF channel for measurement and control of the device, which is divided into an uplink transmission channel (uplink channel) and a downlink receiving channel (downlink channel). The uplink transmission channel converts the 70MHz intermediate frequency signal to the application frequency band through frequency conversion, amplification, and filtering; the downlink receiving channel converts the application frequency band signal to a 70MHz intermediate frequency. The RF module converts the baseband transmission intermediate frequency signal to the S-band measurement and control signal, or converts the received application frequency band measurement and control signal to the intermediate frequency signal. Digitally controlled attenuation is provided for the device through the uplink channel and the downlink channel, and a reference clock output interface can also be provided. The RF module also has a self-calibration function.

[0039] In an optional implementation manner of the embodiment of the present application, the baseband module in the embodiment of the present application is used to receive a 70 MHz intermediate frequency signal, and perform signal demodulation, information extraction and modulation on the 70 MHz intermediate frequency signal based on a target system in a preset multi-system, and send the processed 70 MHz intermediate frequency signal to the radio frequency module;

[0040] The baseband module is also used to perform Doppler dynamic simulation on the processed 70 MHz, and perform coherent measurement or incoherent measurement on the Doppler dynamic simulation result based on the target working mode in the preset multi-mode.

[0041] It should be noted that the baseband module in the embodiment of the present application uses a large-scale programmable device FPGA as the core, and includes an integrated baseband signal processing including the digital-to-analog and analog-to-digital conversion parts to complete multi-system signal processing and multi-mode control processing. The baseband module is used to receive a 70MHz intermediate frequency signal, and complete signal demodulation and information extraction according to the required signal system; modulate according to the required signal system requirements, and send a 70MHz intermediate frequency signal; complete Doppler dynamic simulation; process relevant information according to the required working mode, and complete coherent measurement or incoherent measurement and other tasks.

[0042] In an optional implementation manner of an embodiment of the present application, the time and frequency module in the embodiment of the present application is used to automatically switch to the external clock mode when a 10MHz reference clock input is detected; switch to the internal clock mode when no 10MHz reference clock input is detected; and send the switching result to the baseband module.

[0043] It can be seen that the time-frequency module in the embodiment of the present application has the ability to automatically switch between internal and external clocks. When a 10MHz reference clock input is detected, it automatically switches to the external clock module, otherwise it is the internal clock module. And the current mode indication of the internal and external clocks is output to the baseband module. The working mode of 1PPS is consistent with the working mode of 10MHz. The time-frequency module determines whether there is an external input, automatically switches the module selection, and gives the working status to the baseband module. At the same time, the time-frequency module has the reference output capability of 10MHz and 1PPS. The module has an interface for data communication with an external control module, and establishes a safe and reliable data protocol to complete the module's reception and response of control instructions to the external control module.

[0044] In an optional implementation manner of the embodiment of the present application, the industrial computer in the embodiment of the present application is used to run the host computer software based on selecting a system from a preset multiple system and selecting a mode from a preset multiple modes.

[0045] It can be seen that the industrial computer in the embodiment of the present application can provide a multi-mode and multi-system aerospace measurement and control communication platform test system architecture and the operating environment of the application host computer software of the equipment. The host computer software can select the corresponding mode and system for operation and use as needed according to the differences in application scenarios and platforms, and at the same time provide the application scenarios with the working status display and interactive interface of the whole platform, as well as the storage of process data and other functions.

[0046] like Figure 2 As shown, the baseband module in the embodiment of the present application also includes an intermediate frequency modulation module, which is used to output the corresponding carrier analog quantity according to a preset dynamic Doppler simulation mode, a Doppler frequency range, and a Doppler change rate; wherein the dynamic Doppler simulation mode is simulated based on a DDS (Direct Digital frequency Synthesis) method.

[0047] In a specific example, the present application embodiment involves four dynamic Doppler modes, namely, orbit simulation mode, sine sweep mode, triangle sweep mode, and over-the-air sweep mode. Dopp , Doppler change rate Rate Dopp The following will explain the four Doppler modes accordingly.

[0048] 1) Orbital simulation mode: From orbital parameters to Doppler simulation, multiple levels of multiplication and division operations are required. In order to save resources and simplify FPGA engineering implementation, the host computer software in the industrial computer calculates the third-order derivation parameters instead, and the baseband module completes the Doppler simulation according to the settings of the host computer.

[0049] Assuming Δf″(t) is the second-order derivative of the Doppler frequency, the Doppler first-order derivative Δf′(t) and the Doppler frequency Δf(t) can be derived as:

[0050] Δf′(t)=Δf′(t0)+∫0 t Δf″(a)da

[0051] Δf(t)=Δf(t0)+∫0 t Δf′(a)da

[0052] 2) In the sine sweep mode, the third-order derivatives are derived as follows:

[0053]

[0054]

[0055]

[0056] (2)3) In triangular sweep mode, set α·MAX Dopp ~MAX Dopp , where α∈(0,1) is the vertex buffer, the buffer time is T, and the Doppler acceleration in this interval is: The third-order derivatives are derived as follows:

[0057]

[0058]

[0059]

[0060]

[0061] 4) Passing the sweep mode

[0062]

[0063] Among them, λ=0.13m, v=10000m / s, h=200000m, and t0 is 500s, 100s, 30s, 10s, 5s, 0s, -5s, -10s, -30s, and -100s respectively.

[0064] The derivation process is as follows:

[0065]

[0066]

[0067]

[0068] In an optional implementation manner of the embodiment of the present application, the intermediate frequency modulation module in the embodiment of the present application is also used to perform scrambling, RS encoding, non-return-to-zero NRZ code conversion and convolution processing on the input data.

[0069] The order of scrambling and RS encoding can be adjusted accordingly according to the requirements, and the output data can be directly modulated; in the specific example, the input can be instruction information, forwarding information and transparent transmission information, and the processing flow of the three types of input data is as follows: Figure 3 shown.

[0070] 1) When the input data is command information, the command information is obtained from the data frame sent by the upper computer software in the industrial computer. Furthermore, the command information in the embodiment of the present application supports two sending modes: "send by time" and "send in a loop"; "send by time", that is, according to the working mode selection, the same command is sent by time, and after the sending is completed, it is restored to the state before sending; "send in a loop", that is, the same command is sent in a loop in sequence until the working mode is switched.

[0071] 2) When the input data is forwarding information, the forwarding information is forwarded by the host computer software in the industrial computer. Based on the working mode provided by the test system, the remote control data or digital transmission data from the remote control front end is received, and the data transmission simulation of the satellite in orbit is completed by cache forwarding.

[0072] 3) When the input data is transparent information, the forwarding information is obtained by real-time input from the external physical interface. The external physical interface can be a standard SPI (Serial Peripheral Interface), CAN or other bus interface, which can complete real-time data sampling and status, and can simulate intersatellite data communication and other scenarios.

[0073] In an optional implementation manner of the embodiment of the present application, if Figure 2 As shown, the baseband module in the embodiment of the present application also includes an intermediate frequency demodulation module, which is used to perform convolution decoding, NRZ code conversion, frame synchronization, RS decoding and descrambling processing on the received demodulated information. Among them, the order of RS decoding and descrambling can be adjusted accordingly according to actual needs.

[0074] In a specific example, the intermediate frequency demodulation module performs convolution decoding, NRZ code conversion, frame synchronization, RS decoding and descrambling processing on the received demodulated information, such as Figure 4 shown.

[0075] In an optional implementation manner of an embodiment of the present application, the baseband module in the embodiment of the present application, after receiving the downlink ranging link signal, performs despreading, demodulation, and frame synchronization extraction to obtain a downlink measurement frame synchronization signal, and then uses the downlink frame synchronization to sample the uplink signal formed by itself, extracts the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, ground time, and samples the downlink Doppler value to obtain pseudo-range related information, pseudo-Doppler measurement values, and time sampling values ​​to calculate and complete ranging and speed measurement; wherein, the downlink ranging link signal is obtained by the satellite after receiving the uplink signal and performing despreading, demodulation, and frame synchronization.

[0076] It can be seen that taking the spread spectrum system as an example: after the ground station measurement frame is framed and spread, it is sent to the satellite using the uplink; after the satellite receives the uplink signal, it performs despreading, demodulation, frame synchronization, and synchronously forwards the carrier and pseudo code to the ground; after the ground receives the downlink ranging link signal, it performs despreading, demodulation, frame synchronization to extract the downlink measurement frame synchronization signal, and then uses the downlink frame synchronization to sample the uplink signal formed by itself, extract the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, ground time, and sample the downlink Doppler value and other measurement information. The downlink pseudo-range related information, pseudo-Doppler measurement value, and time sampling value measured on the ground are calculated to complete the ranging and speed measurement.

[0077] In addition, the baseband module is also used to despread, demodulate, and frame synchronize the downlink ranging link signal to obtain the downlink measurement frame synchronization signal, and then use the downlink frame synchronization to sample the uplink signal formed by itself, extract the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase and ground time, and sample the downlink Doppler value to obtain the uplink pseudo-range information, pseudo-Doppler measurement value, time sampling value and the downlink pseudo-range information, pseudo-Doppler measurement value, and time sampling value measured on the ground; wherein, the downlink ranging link signal is despread, demodulated, and frame synchronized after the satellite receives the uplink signal, and then uses the downlink ranging information frame synchronization formed by itself to sample the uplink signal, extract the bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, on-board time, and sample the uplink pseudo-Doppler value.

[0078] It can be seen that, taking the spread spectrum system as an example: after the ground station measurement frame is framed and spread, it is sent to the satellite using the uplink; after receiving the uplink signal, the satellite performs despreading, demodulation, and frame synchronization, and then uses the downlink ranging information frame synchronization formed by itself to sample the uplink signal, extract the bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, on-board time, and sample the uplink pseudo Doppler value and other measurement information, and put these sampled information into the downlink measurement frame in real time and send it to the ground;

[0079] After receiving the downlink ranging link signal, the ground performs despreading, demodulation, and frame synchronization extraction to obtain the downlink measurement frame synchronization signal, and then uses the downlink frame synchronization to sample the uplink signal formed by itself, extract the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, ground time, and sample the downlink Doppler value and other measurement information. The ground calculates the uplink pseudo-range related information, pseudo-Doppler measurement value, time sampling value transmitted by the satellite and the downlink pseudo-range related information, pseudo-Doppler measurement value, and time sampling value measured on the ground to complete the ranging, speed measurement, and time difference measurement.

[0080] The device embodiments described above are merely illustrative, wherein 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 distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0081] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a general hardware platform, and of course, by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the relevant technology can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0082] It should be understood that the terms used herein are only for the purpose of describing specific example embodiments and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "one", "an" and "said" as used herein may also be meant to include plural forms. The terms "include", "comprise", "contain", and "have" are inclusive, and therefore specify the existence of stated features, steps, operations, elements and / or parts, but do not exclude the existence or addition of one or more other features, steps, operations, elements, parts, and / or combinations thereof. The method steps, processes, and operations described herein are not interpreted as necessarily requiring them to be performed in the specific order described or illustrated, unless the execution order is clearly indicated. It should also be understood that additional or alternative steps may be used.

[0083] The foregoing is merely a specific embodiment of the present invention, which enables those skilled in the art to understand or implement the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A test system for a multi-mode and multi-system aerospace measurement and control communication platform, characterized in that: include: RF module, baseband module, time-frequency module, power module and industrial computer; The radio frequency module is used to provide a radio frequency channel for the test system, wherein the radio frequency channel includes an uplink channel and a downlink channel; The baseband module is used to process the signal through a preset multi-system and a preset multi-mode; The time-frequency module is used to provide a time-frequency reference for the test system; The industrial computer is used to provide an operating environment for the host computer software in the test system; The power supply module is used to provide power to the test system; Wherein, the radio frequency module, the baseband module, the time-frequency module, the industrial computer and the power supply module are connected to each other via a preset standard interface; The RF module is used to receive the 70 MHz intermediate frequency signal sent by the baseband module based on the uplink channel, and convert, amplify and filter the 70 MHz intermediate frequency signal to the application frequency band, and convert, amplify and filter the received application frequency band signal to the 70 MHz intermediate frequency based on the downlink channel; The baseband module is used to receive a 70 MHz intermediate frequency signal, and perform signal demodulation, information extraction and modulation on the 70 MHz intermediate frequency signal based on a target system in the preset multi-system, and send the processed 70 MHz intermediate frequency signal to the radio frequency module; wherein the preset multi-system includes an incoherent spread spectrum signal system, a coherent spread spectrum system, a unified carrier system, a measurement and control data transmission integrated system, a relay short message system, a ground-based short message system, a low-speed data transmission system, and an ad hoc system; The baseband module is further used to perform Doppler dynamic simulation on the processed 70MHz, and perform coherent measurement or incoherent measurement on the Doppler dynamic simulation result based on the target working mode in the preset multi-mode, wherein the preset multi-mode includes: intermediate frequency working mode, S-band radio frequency mode, QV-band radio frequency mode, self-closed loop test mode, and remote access mode; The industrial computer is used to run the host computer software based on selecting a system from the preset multiple systems and selecting a mode from the preset multiple modes; The baseband module also includes an intermediate frequency modulation module, which is used to output a corresponding carrier analog quantity according to a preset dynamic Doppler simulation mode, a Doppler frequency range, and a Doppler change rate; wherein the dynamic Doppler simulation mode is simulated based on a direct digital frequency DDS method; The intermediate frequency modulation module is also used to perform scrambling, RS encoding, NRZ code conversion and convolution processing on the input data; Wherein, in the case where the input data is instruction information, the instruction information is obtained from a data frame sent by the upper computer software in the industrial computer; wherein, the instruction information supports two sending modes: sending in sequence and cyclic sending; sending in sequence means sending the same instruction in sequence according to the working mode selection, and restoring to the state before sending after sending; cyclic sending means sending the same instruction in sequence in a cyclic manner until the working mode is switched; In the case where the input data is forwarding information, the forwarding information is forwarded by the upper computer software in the industrial computer; wherein, based on the working mode provided by the test system, the remote control data or digital transmission data is received from the remote control front end, and the data transmission simulation of the satellite in the orbit operation state is completed by cache forwarding; In the case where the input data is transparent transmission information, the forwarding information is obtained by real-time input of an external physical interface; wherein the external physical interface is a standard serial peripheral interface SPI and a controller area network CAN bus interface; the external physical interface can complete real-time sampling and status of data, and simulate inter-satellite data communication; After the ground station measurement frame is framed and spread, it is sent to the satellite using the uplink; after receiving the uplink signal, the satellite performs despreading, demodulation, frame synchronization, and synchronously forwards the carrier and pseudo code to the ground; after the ground receives the downlink ranging link signal, the baseband module is used to despread, demodulate, and frame synchronize the downlink ranging link signal to extract the downlink measurement frame synchronization signal, and then use the downlink frame synchronization to sample the uplink signal formed by itself, extract the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, ground time, and sample the downlink Doppler value; the downlink pseudo range related information, pseudo Doppler measurement value, and time sampling value measured on the ground are calculated to complete the ranging and speed measurement; After the ground station measurement frame is framed and spread, it is sent to the satellite using the uplink; after receiving the uplink signal, the satellite performs despreading, demodulation, and frame synchronization, and then uses the downlink ranging information frame synchronization formed by itself to sample the uplink signal, extract the bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, and satellite time, and sample the uplink pseudo Doppler value, and put the sampling information into the downlink measurement frame in real time and send it to the ground; after the ground receives the downlink ranging link signal, the baseband module is used to despread, demodulate, and frame synchronize the downlink ranging link signal to extract the downlink measurement frame synchronization signal, and then use the downlink frame synchronization to sample the uplink signal formed by itself, extract the frame count, bit count, spread spectrum pseudo code count, code phase, carrier count, carrier phase, ground time, and sample the downlink Doppler value; the ground calculates the uplink pseudo range related information, pseudo Doppler measurement value, time sampling value on the satellite transmitted by the satellite and the downlink pseudo range related information, pseudo Doppler measurement value, and time sampling value measured on the ground to complete ranging, speed measurement, and time difference measurement; The time-frequency module is used to automatically switch to the external clock mode when a 10 MHz reference clock input is detected; switch to the internal clock mode when no 10 MHz reference clock input is detected; and send the switching result to the baseband module; The baseband module also includes an intermediate frequency demodulation module, which is used to perform convolution decoding, NRZ code conversion, frame synchronization, RS decoding and descrambling processing on the received demodulation information.

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