Spaceflight control system interface verification device

Abstract

The invention belongs to the technical field of spaceflight control, and particularly relates to an interface verification device for a spaceflight control system. Comprising a simulation computer, an interface adapter, a signal generator, a signal analyzer, a data acquisition module, a data recording module, a monitoring display module, an environment simulation module, a fault injection module, a power management module, an automatic test script generation and execution module and a communication protocol analysis and verification module. A simulation computer and an environment simulation module are arranged to simulate data streams and instructions of a spacecraft in different flight stages, the simulation computer communicates with a data acquisition and recording system, a monitoring display system and other modules, sends and receives test data, and is also matched with a signal generator and a signal analyzer to generate a specific test signal, and the test signal is transmitted to the environment simulation module. The verification comprehensiveness is improved; the automatic test script generation and execution module is arranged in the application, so that the test script can be automatically generated, excessive manual participation is not needed, and the test efficiency is improved.

Description

Technical Field

[0001] The invention relates to the field of aerospace control technology, and in particular to an aerospace control system interface verification device. Background Art

[0002] Space control system interface verification is a device specifically used to detect and verify whether the functions of various interfaces in the spacecraft control system are normal and whether the performance meets the design requirements. This device is crucial to ensure the success of the entire space mission because it can detect and solve potential problems in advance, thereby improving the reliability and safety of the system.

[0003] However, the existing interface verification device still has the following technical problems when used:

[0004] The existing interface verification device still has the following technical problems when used:

[0005] The current interface verification device system has a complex structure and is difficult to operate during the verification process. It is difficult to simulate multiple scenarios to verify the control system interface. The degree of automation is low, and some testing processes still require manual operation, which affects the test efficiency and easily increases the error rate.

[0006] Therefore, an aerospace control system interface verification device is proposed to solve the above-mentioned problems. Summary of the invention

[0007] The purpose of the present invention is to provide an aerospace control system interface verification device to solve the problems raised in the above background technology.

[0008] To achieve the above-mentioned object, the present invention provides the following technical solutions: an aerospace control system interface verification device, comprising a simulation computer, an interface adapter, a signal generator, a signal analyzer, a data acquisition module, a data recording module, a monitoring display module, an environment simulation module, a fault injection module, a power management module, an automated test script generation and execution module, and a communication protocol parsing and verification module;

[0009] The simulation computer is used to generate and control test scenarios, simulate the data flow of the spacecraft at different flight stages and the different instructions received, and provide real-time data processing and analysis capabilities;

[0010] The interface adapter is used to connect different physical interface types, ensure compatibility between the system under test and the test equipment, provide electrical isolation and signal conversion functions, and protect the test equipment and the system under test;

[0011] The signal generator is used to generate various types of electrical signals;

[0012] The signal analyzer is used to analyze and measure the characteristics of the signal and test the data transmission speed, signal integrity and reliability of the interface;

[0013] The data acquisition module is used to collect data during the test in real time;

[0014] The data recording module is used to record the changes of key parameters for subsequent analysis, and can perform high-speed data storage and playback;

[0015] The monitoring and display module is used to display key parameters and status information during the test in real time, provide a graphical interface to facilitate operators to monitor and adjust test conditions, support alarm and fault prompt functions, and detect abnormal situations in a timely manner;

[0016] The environmental simulation module is used to simulate various environmental conditions that a spacecraft may encounter and evaluate the performance and stability of the interface under extreme conditions;

[0017] The fault injection module is used to artificially introduce errors or fault conditions to test the fault tolerance and recovery mechanism of the system;

[0018] The power management module is used to provide a stable and reliable power supply, monitor and adjust the power output, and ensure the stability of the power supply during the test;

[0019] The automated test script generation and execution module is used to automatically generate test scripts, improve test efficiency, automatically execute test processes, reduce manual intervention, and support automatic analysis of test results and report generation;

[0020] The communication protocol parsing and verification module is used to parse and verify the communication protocol, ensure the correctness and consistency of data transmission, check the protocol format and check code, and ensure data integrity.

[0021] Preferably, the physical interface types connected by the interface adapter include RS-422, RS-232, USB, CAN, and Ethernet.

[0022] Preferably, the types of electrical signals generated by the signal generator include analog signals and digital signals.

[0023] Preferably, the signal analyzer analyzes and measures signal characteristics including frequency, amplitude, and phase.

[0024] Preferably, the fault injection module includes software fault injection and hardware fault injection.

[0025] Preferably, the signal generator includes a control processing unit, a microwave generating unit, a modulation unit, a frequency synthesis unit, an amplitude adjustment unit, a phase adjustment unit, an output buffer and isolation unit, a synchronization and triggering unit, and a display unit; the control processing unit is used to control the operation of the entire signal generator and process instructions from a simulation computer or other control device; the microwave generating unit is used to generate different types of waveform signals; the modulation unit is used to modulate the generated baseband signal to generate a modulation signal; the frequency synthesis unit is used to generate an accurate frequency signal; the amplitude adjustment unit is used to adjust the amplitude of the generated signal; the phase adjustment unit is used to adjust the phase of the generated signal; the output buffer and isolation unit is used to provide a stable signal output and realize electrical isolation to protect the signal generator and other devices; the synchronization and triggering unit is used to ensure the synchronization between the signal generator and other devices, and to trigger signal generation at a specific moment; the display unit is used to display signal parameters and waveform diagrams.

[0026] Preferably, the signal analyzer includes a control and processing unit, an input buffer and isolation unit, a front-end amplification and attenuation unit, a filtering unit, an analog-to-digital conversion unit, a spectrum analysis unit, a time domain analysis unit, a modulation analysis unit, a protocol analysis unit, and a synchronization and triggering unit; the control and processing unit is used to control the operation of the entire signal analyzer and process instructions from a simulation computer or other control device; the input buffer and isolation unit is used to provide a stable signal input and achieve electrical isolation; the front-end amplification and attenuation unit is used to adjust the amplitude of the input signal to make it suitable for subsequent processing; the filtering unit is used to filter out unnecessary frequency components and improve signal quality; the analog-to-digital conversion unit is used to convert analog signals into digital signals for digital processing; the spectrum analysis unit is used to perform frequency domain analysis on the signal and generate a spectrum diagram; the time domain analysis unit is used to perform time domain analysis on the signal and generate a waveform diagram; the modulation analysis unit is used to analyze the modulation characteristics of the signal; the synchronization and triggering unit is used to ensure synchronization between the signal analyzer and other devices, and to trigger signal analysis at a specific moment.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1) In this application, a simulation computer and an environmental simulation module are set up to simulate the data flow and instructions of the spacecraft at different flight stages. The simulation computer communicates with modules such as the data acquisition and recording system and the monitoring and display system to send and receive test data. It also cooperates with a signal generator and a signal analyzer to generate specific test signals to increase the comprehensiveness of the verification.

[0029] 2) By setting up an automated test script generation and execution module in the present application, the test script can be automatically generated without excessive manual participation, thereby improving the test efficiency;

[0030] 3) By setting up the communication protocol parsing and verification module, the correctness and consistency of data transmission can be ensured and the error rate can be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a structural diagram of the present invention;

[0032] Figure 2 This is the structural composition diagram of the signal generator;

[0033] Figure 3 This is a structural diagram of the signal analyzer. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0036] Example:

[0037] See also Figure 1-3 , the present invention provides a technical solution:

[0038] An aerospace control system interface verification device, comprising a simulation computer, an interface adapter, a signal generator, a signal analyzer, a data acquisition module, a data recording module, a monitoring display module, an environment simulation module, a fault injection module, a power management module, an automated test script generation and execution module, and a communication protocol analysis and verification module;

[0039] The simulation computer is used to generate and control test scenarios, simulate the data flow of the spacecraft at different flight stages and the different instructions received, and provide real-time data processing and analysis capabilities;

[0040] The interface adapter is used to connect different physical interface types, ensure compatibility between the system under test and the test equipment, provide electrical isolation and signal conversion functions, and protect the test equipment and the system under test;

[0041] The interface adapter converts the signals generated by the simulation computer into a format suitable for the system under test, and converts the response signals of the system under test back into a format that can be processed by the simulation computer;

[0042] The signal generator is used to generate various types of electrical signals; the signal generator generates specific signals according to the instructions of the simulation computer and transmits them to the system under test through the interface adapter.

[0043] The signal analyzer is used to analyze and measure the characteristics of the signal, and test the data transmission speed, signal integrity and reliability of the interface; the signal analyzer receives the response signal from the system under test and feeds it back to the simulation computer for analysis.

[0044] The data acquisition module is used to collect data during the test in real time;

[0045] The data recording module is used to record the changes of key parameters for subsequent analysis, and can perform high-speed data storage and playback;

[0046] The monitoring and display module is used to display key parameters and status information during the test in real time, provide a graphical interface to facilitate operators to monitor and adjust test conditions, support alarm and fault prompt functions, and detect abnormal situations in a timely manner;

[0047] The environmental simulation module is used to simulate various environmental conditions that a spacecraft may encounter and evaluate the performance and stability of the interface under extreme conditions;

[0048] The fault injection module is used to artificially introduce errors or fault conditions to test the fault tolerance and recovery mechanism of the system; the fault injection module injects faults into the system under test at a specific time point according to the instructions of the simulation computer, and the data acquisition and recording system records the response of the system under test and feeds the results back to the simulation computer for analysis.

[0049] The power management module is used to provide a stable and reliable power supply, monitor and adjust the power output, ensure the stability of power supply during the test, and if an abnormality is detected, it can take timely measures to prevent equipment damage.

[0050] The automated test script generation and execution module is used to automatically generate test scripts, improve test efficiency, automatically execute test processes, reduce manual intervention, and support automatic analysis of test results and report generation;

[0051] The communication protocol parsing and verification module is used to parse and verify the communication protocol, ensure the correctness and consistency of data transmission, check the protocol format and check code, and ensure data integrity.

[0052] The physical interface types connected by the interface adapter include RS-422, RS-232, USB, CAN, and Ethernet.

[0053] The types of electrical signals generated by the signal generator include analog signals and digital signals.

[0054] The signal analyzer analyzes and measures signal characteristics including frequency, amplitude, and phase.

[0055] The fault injection module includes software fault injection and hardware fault injection.

[0056] The signal generator includes a control processing unit, a microwave generating unit, a modulation unit, a frequency synthesis unit, an amplitude adjustment unit, a phase adjustment unit, an output buffer and isolation unit, a synchronization and triggering unit, and a display unit; the control processing unit is used to control the operation of the entire signal generator and process instructions from a simulation computer or other control devices; the microwave generating unit is used to generate different types of waveform signals; the modulation unit is used to modulate the generated baseband signal to generate a modulation signal; the frequency synthesis unit is used to generate an accurate frequency signal; the amplitude adjustment unit is used to adjust the amplitude of the generated signal; the phase adjustment unit is used to adjust the phase of the generated signal; the output buffer and isolation unit is used to provide a stable signal output and realize electrical isolation to protect the signal generator and other devices; the synchronization and triggering unit is used to ensure the synchronization between the signal generator and other devices, and trigger signal generation at a specific time; the display unit is used to display signal parameters and waveform diagrams.

[0057] The signal analyzer includes a control and processing unit, an input buffer and isolation unit, a front-end amplification and attenuation unit, a filtering unit, an analog-to-digital conversion unit, a spectrum analysis unit, a time domain analysis unit, a modulation analysis unit, a protocol analysis unit, and a synchronization and triggering unit; the control and processing unit is used to control the operation of the entire signal analyzer and process instructions from a simulation computer or other control devices; the input buffer and isolation unit is used to provide a stable signal input and achieve electrical isolation; the front-end amplification and attenuation unit is used to adjust the amplitude of the input signal to make it suitable for subsequent processing; the filtering unit is used to filter out unnecessary frequency components and improve signal quality; the analog-to-digital conversion unit is used to convert analog signals into digital signals for digital processing; the spectrum analysis unit is used to perform frequency domain analysis on the signal and generate a spectrum diagram; the time domain analysis unit is used to perform time domain analysis on the signal and generate a waveform diagram; the modulation analysis unit is used to analyze the modulation characteristics of the signal; the synchronization and triggering unit is used to ensure synchronization between the signal analyzer and other devices and to trigger signal analysis at a specific moment.

[0058] The operator sets the test parameters and scenarios through the monitoring and display module; the simulation computer generates test signals and sends them to the spacecraft through the signal generator; the interface adapter converts the signals into a format suitable for the system under test; the environmental simulation module generates specific environmental conditions and applies them to the spacecraft; the data acquisition module and the data recording module collect test data in real time and record key parameters; the monitoring and display module displays real-time data, and the operator adjusts the test parameters as needed; the fault injection module injects faults into the spacecraft at a specific time point; the data acquisition module and the data recording module feed back the test results to the simulation computer for analysis and report generation; the monitoring and display module displays the test results, and the operator evaluates the test effect and completes the verification of the aerospace control system interface.

[0059] The above shows and describes the basic principles and main features of the present invention and the advantages of the present invention. For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention; therefore, no matter from which point of view, the embodiments should be regarded as exemplary and non-restrictive. The scope of the present invention is limited by the attached claims rather than the above description. Therefore, it is intended to include all changes within the meaning and scope of the equivalent elements of the claims in the present invention, and any figure marks in the claims should not be regarded as limiting the claims involved.

[0060] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aerospace control system interface verification device, characterized in that: It includes simulation computer, interface adapter, signal generator, signal analyzer, data acquisition module, data recording module, monitoring display module, environment simulation module, fault injection module, power management module, automated test script generation and execution module, communication protocol analysis and verification module; The simulation computer is used to generate and control test scenarios, simulate the data flow of the spacecraft at different flight stages and the different instructions received, and provide real-time data processing and analysis capabilities; The interface adapter is used to connect different physical interface types, ensure compatibility between the system under test and the test equipment, provide electrical isolation and signal conversion functions, and protect the test equipment and the system under test; The signal generator is used to generate various types of electrical signals; The signal analyzer is used to analyze and measure the characteristics of the signal and test the data transmission speed, signal integrity and reliability of the interface; The data acquisition module is used to collect data during the test in real time; The data recording module is used to record the changes of key parameters for subsequent analysis, and can perform high-speed data storage and playback; The monitoring and display module is used to display key parameters and status information during the test in real time, provide a graphical interface to facilitate operators to monitor and adjust test conditions, support alarm and fault prompt functions, and detect abnormal situations in a timely manner; The environmental simulation module is used to simulate various environmental conditions that a spacecraft may encounter and evaluate the performance and stability of the interface under extreme conditions; The fault injection module is used to artificially introduce errors or fault conditions to test the fault tolerance and recovery mechanism of the system; The power management module is used to provide a stable and reliable power supply, monitor and adjust the power output, and ensure the stability of the power supply during the test; The automated test script generation and execution module is used to automatically generate test scripts, improve test efficiency, automatically execute test processes, reduce manual intervention, and support automatic analysis of test results and report generation; The communication protocol parsing and verification module is used to parse and verify the communication protocol, ensure the correctness and consistency of data transmission, check the protocol format and check code, and ensure data integrity.

2. The aerospace control system interface verification device according to claim 1, characterized in that: The physical interface types connected by the interface adapter include RS-422, RS-232, USB, CAN, and Ethernet.

3. The aerospace control system interface verification device according to claim 1, characterized in that: The types of electrical signals generated by the signal generator include analog signals and digital signals.

4. The aerospace control system interface verification device according to claim 1, characterized in that: The signal analyzer analyzes and measures signal characteristics including frequency, amplitude, and phase.

5. The aerospace control system interface verification device according to claim 1, characterized in that: The fault injection module includes software fault injection and hardware fault injection.

6. The aerospace control system interface verification device according to claim 1, characterized in that: The signal generator includes a control processing unit, a microwave generating unit, a modulation unit, a frequency synthesis unit, an amplitude adjustment unit, a phase adjustment unit, an output buffer and isolation unit, a synchronization and triggering unit, and a display unit; the control processing unit is used to control the operation of the entire signal generator and process instructions from a simulation computer or other control devices; the microwave generating unit is used to generate different types of waveform signals; The modulation unit is used to modulate the generated baseband signal to generate a modulation signal; the frequency synthesis unit is used to generate an accurate frequency signal; the amplitude adjustment unit is used to adjust the amplitude of the generated signal; the phase adjustment unit is used to adjust the phase of the generated signal; the output buffer and isolation unit is used to provide a stable signal output and realize electrical isolation to protect the signal generator and other equipment; the synchronization and triggering unit is used to ensure the synchronization between the signal generator and other equipment, and to trigger signal generation at a specific time; the display unit is used to display signal parameters and waveform diagrams.

7. The aerospace control system interface verification device according to claim 1, characterized in that: The signal analyzer includes a control and processing unit, an input buffer and isolation unit, a front-end amplification and attenuation unit, a filtering unit, an analog-to-digital conversion unit, a spectrum analysis unit, a time domain analysis unit, a modulation analysis unit, a protocol analysis unit, and a synchronization and triggering unit; the control and processing unit is used to control the operation of the entire signal analyzer and process instructions from a simulation computer or other control devices; the input buffer and isolation unit is used to provide a stable signal input and achieve electrical isolation; the front-end amplification and attenuation unit is used to adjust the amplitude of the input signal to make it suitable for subsequent processing; the filtering unit is used to filter out unnecessary frequency components and improve signal quality; the analog-to-digital conversion unit is used to convert analog signals into digital signals for digital processing; the spectrum analysis unit is used to perform frequency domain analysis on the signal and generate a spectrum diagram; the time domain analysis unit is used to perform time domain analysis on the signal and generate a waveform diagram; The modulation analysis unit is used to analyze the modulation characteristics of the signal; the synchronization and triggering unit is used to ensure the synchronization between the signal analyzer and other equipment, and to trigger the signal analysis at a specific time.

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