SoC-Based Test Launch Control Method and System

Abstract

The present invention discloses a test launch control method and system based on SoC. The method pre-stores the target programs for controlling the spacecraft during the test process and the launch process through the SoC processing module, and obtains the device operation status of the spacecraft equipment in real time. The input quantity acquisition module receives the time synchronization pulses of the time synchronization equipment through the time synchronization circuit, acquires the externally input digital quantities and various status signals, and at the same time performs backtesting on various types of switch quantity output signals. The switch quantity output module controls the output of the current signal through the switch quantity output circuit, and outputs the current control signal of the relay module, which can greatly improve the development efficiency of engineers, improve the timekeeping accuracy of the spacecraft system, speed up the reaction performance of the test launch control system, reduce the complexity of the system software, improve the reliability of data transmission, can test the overall performance of the spacecraft, and improve the speed and efficiency of the test launch control based on SoC.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace test launch control, and particularly relates to a test launch control method and system based on SoC. Background Art

[0002] The test launch control system is a system that integrates functions such as comprehensive testing, launch control, data processing, and real-time monitoring, and is used to test and control the overall performance of a spacecraft throughout the entire process of spacecraft development. Generally, through the test launch control system, general assembly tests are carried out in the spacecraft general assembly workshop and technical position, and launch control is carried out during the launch process. The test launch control system is an important part of the spacecraft launch system.

[0003] The control center of the existing test launch control system selects the X86 platform architecture. The X86 platform has high power consumption, high requirements for heat dissipation, poor real-time processing performance, and a high development threshold for driver software. Summary of the Invention

[0004] The main objective of the present invention is to provide a test launch control method and system based on SoC, aiming to solve the technical problems of poor real-time processing performance, high power consumption, high time delay, and high development threshold for driver software in the existing test launch control center.

[0005] In the first aspect, the present invention provides a test launch control method based on SoC. The test launch control method based on SoC includes the following steps:

[0006] The SoC processing module pre-stores the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtains the device operation status of the spacecraft devices.

[0007] The input quantity acquisition module receives the time synchronization pulse of the time synchronization device through the time synchronization circuit, acquires the externally input digital quantities and various status signals, and simultaneously performs backtesting on various switch quantity output signals.

[0008] The switch quantity output module controls the output of the current signal through the switch quantity output circuit, and outputs the current control signal of the relay module.

[0009] Optionally, after the SoC processing module pre-stores the target programs for controlling the spacecraft during the test process and the launch process and real-time obtains the device operation status of the spacecraft devices, the test launch control method based on SoC further includes:

[0010] The power supply module converts the input voltage into the required voltages for each functional module to work.

[0011] The communication module sends control instructions and receives status information between the test launch control system and the spacecraft devices through the CAN bus.

[0012] The SoC processing module integrates a fieldbus protocol and exchanges information with other devices through the fieldbus protocol;

[0013] The relay module realizes the on-off control of current signals and performs the control conversion function of the safety mechanism.

[0014] Optionally, after the relay module realizes the on-off control of current signals and performs the control conversion function of the safety mechanism, the SoC-based test launch control method further includes:

[0015] The AD acquisition module measures multiple analog voltage signals through the relay module;

[0016] The CPCI interconnection module realizes the interconnection and interoperability of each functional module through the CPCI bus standard interface.

[0017] Optionally, after the digital output module controls and outputs the current signal through the digital output circuit and outputs the current control signal of the relay module, the SoC-based test launch control method further includes:

[0018] The network switching module realizes data communication between the test launch control device and the remote control device through the Ethernet bus;

[0019] The display and keyboard / mouse module realizes the function of human-computer interaction.

[0020] Optionally, after the display and keyboard / mouse module realizes the function of human-computer interaction, the SoC-based test launch control method further includes:

[0021] The camera module takes pictures of the spacecraft erection process and transmits the image data to the remote control device;

[0022] The image electro-optical conversion module converts the video signal captured by the camera module into an optical signal for long-distance transmission, and realizes the electro-optical conversion after long-distance image transmission through the optoelectronic conversion device, and converts it into a standard video image signal for display on the device;

[0023] The data recording module records the process data of the spacecraft and the test launch control device;

[0024] The time synchronization equipment control module realizes the time synchronization function of the time synchronization equipment and the test launch control equipment, etc., so that the test launch control equipment can obtain the launch time for the spacecraft to launch on time;

[0025] The AC / DC power supply equipment provides the power required for the operation of the spacecraft and the test launch control equipment.

[0026] Second aspect, to achieve the above object, the present invention further provides a test launch control system based on SoC, and the test launch control system based on SoC includes:

[0027] An SoC processing module, configured to pre-store target programs for controlling a spacecraft during a test process and a launch process, and to acquire in real time the operating states of the spacecraft equipment;

[0028] An input quantity acquisition module, configured to receive time synchronization pulses of a time synchronization device through a time synchronization circuit, acquire externally input digital quantities and various status signals, and simultaneously perform backtesting on various switch quantity output signals;

[0029] A switch quantity output module, configured to perform control output of a current signal through a switch quantity output circuit, and output a current control signal of a relay module.

[0030] Optionally, the test launch control system based on SoC further includes:

[0031] A power supply module, configured to convert an input voltage into voltages required for each functional module to operate;

[0032] A communication module, configured to send control instructions and receive status information between the test launch control system and the spacecraft equipment through a CAN bus;

[0033] The SoC processing module is further configured to integrate a fieldbus protocol and perform information interaction with other devices through the fieldbus protocol;

[0034] A relay module, configured to implement on-off control of a current signal and perform a safety mechanism control conversion function.

[0035] Optionally, the test launch control system based on SoC further includes:

[0036] An AD acquisition module, configured to measure multiple-channel analog voltage signals through the relay module;

[0037] A CPCI interconnection module, configured to achieve interconnection and interoperability of each functional module through a CPCI bus standard interface.

[0038] Optionally, the test launch control system based on SoC further includes:

[0039] A network switching module, configured to implement data communication between the test launch control device and a remote control device through an Ethernet bus;

[0040] A display and keyboard mouse module, configured to implement the function of human-computer interaction.

[0041] Optionally, the test launch control system based on SoC further includes:

[0042] The camera module is used to take pictures during the erection process of the spacecraft and transmit the image data to the remote control device;

[0043] The image electro-optical conversion module is used to convert the video signal captured by the camera module into an optical signal for long-distance transmission, and realize the photoelectric conversion after long-distance image transmission through a photoelectric conversion device, and convert it into a standard video image signal for display on the device;

[0044] The data recording module is used to record the process data of the spacecraft and the test launch control equipment;

[0045] The time synchronization equipment control module is used to realize the time synchronization function between the time synchronization equipment and the test launch control equipment, etc., so that the test launch control equipment can obtain the launch time for the spacecraft to launch on time;

[0046] The AC / DC power supply module is used to provide the power required for the operation of the spacecraft and the test launch control equipment.

[0047] The test launch control method based on SoC proposed by the present invention pre-stores the target program for controlling the spacecraft during the test process and the launch process through the SoC processing module, and obtains the equipment operation status of the spacecraft equipment in real time; the input quantity acquisition module receives the time synchronization pulse of the time synchronization equipment through the time synchronization circuit, collects the externally input digital quantity and various status signals, and at the same time performs backtesting on various switch quantity output signals; the switch quantity output module controls the output of the current signal through the switch quantity output circuit, and outputs the current control signal of the relay module, which can realize the time synchronization function between the time synchronization equipment and the test launch control equipment, etc., reduces power consumption and delay, analogizes and batch-processes the test data as needed, realizes system fault self-diagnosis, can greatly improve the development efficiency of engineers, improves the timekeeping accuracy of the spacecraft system, speeds up the response performance of the test launch control system, reduces the complexity of the system software, improves the reliability of data transmission, can test the overall performance of the spacecraft, and improves the speed and efficiency of the test launch control based on SoC. Brief Description of the Drawings

[0048] Figure 1 It is a schematic flowchart of the first embodiment of the test launch control method based on SoC of the present invention;

[0049] Figure 2 It is a schematic flowchart of the second embodiment of the test launch control method based on SoC of the present invention;

[0050] Figure 3 It is a schematic flowchart of the third embodiment of the test launch control method based on SoC of the present invention;

[0051] Figure 4Schematic flowchart of the fourth embodiment of the test launch control method based on SoC of the present invention;

[0052] Figure 5 Schematic flowchart of the fifth embodiment of the test launch control method based on SoC of the present invention;

[0053] Figure 6 Functional module diagram of the first embodiment of the test launch control system based on SoC of the present invention;

[0054] Figure 7 Functional module diagram of the second embodiment of the test launch control system based on SoC of the present invention;

[0055] Figure 8 Functional module diagram of the third embodiment of the test launch control system based on SoC of the present invention;

[0056] Figure 9 Functional module diagram of the fourth embodiment of the test launch control system based on SoC of the present invention;

[0057] Figure 10 Functional module diagram of the fifth embodiment of the test launch control system based on SoC of the present invention.

[0058] The realization, functional characteristics and advantages of the object of the present invention will be further described with reference to the embodiments and the accompanying drawings. Detailed implementation manners

[0059] It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0060] The solution of the embodiment of the present invention is mainly as follows: the SoC processing module pre-stores the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtains the device operation status of the spacecraft equipment; the input quantity acquisition module receives the time synchronization pulse of the time synchronization equipment through the time synchronization circuit, collects the externally input digital quantities and various status signals, and at the same time performs backtesting on various switch quantity output signals; the switch quantity output module controls the output of the current signal through the switch quantity output circuit, and outputs the current control signal of the relay module, which can realize the time synchronization function of the time synchronization equipment and the test launch control equipment, etc., reduces the power consumption and time delay, analogizes and batch processes the test data as needed, realizes the system fault self-diagnosis, can greatly improve the development efficiency of engineers, improves the timekeeping accuracy of the spacecraft system, speeds up the response performance of the test launch control system, reduces the complexity of the system software, improves the reliability of data transmission, can test the overall performance of the spacecraft, improves the speed and efficiency of the test launch control based on SoC, and solves the technical problems of poor real-time processing performance, high power consumption, high time delay and high development threshold of the driving software in the prior art.

[0061] Refer to Figure 1 , Figure 1 which is a schematic flowchart of the first embodiment of the test launch control method based on SoC of the present invention.

[0062] In the first embodiment, the test launch control method based on SoC includes the following steps:

[0063] Step S10: The SoC processing module pre-stores the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtains the operating status of the spacecraft equipment.

[0064] It should be noted that the SoC processing module pre-stores the programs for controlling the spacecraft during the test process and the launch process; and is also used to real-time obtain and display the operating status of the spacecraft equipment captured by the camera device.

[0065] Step S20: The input quantity acquisition module receives the time synchronization pulse of the time synchronization device through the time synchronization circuit, acquires the externally input digital quantity and various status signals, and simultaneously performs backtesting on various switch quantity output signals.

[0066] It can be understood that the input quantity acquisition module can receive the time synchronization pulse of the time synchronization device through a high-precision high-speed time synchronization circuit; and acquire the externally input digital quantity and various status signals, and simultaneously perform backtesting on various switch quantity output signals.

[0067] In specific implementation, the input quantity acquisition module includes receiving the time synchronization pulse of the time synchronization device through a high-precision high-speed time synchronization interface circuit, using a filtering algorithm to remove interference signals such as glitches from the acquired pulse signals; and can also acquire the externally input digital quantity and various status signals of the spacecraft after the external input quantity input opto-isolation circuit, and then perform backtesting on various switch quantity signals output by the switch quantity output module.

[0068] Step S30: The switch quantity output module performs control output of current signals through the switch quantity output circuit, and outputs the current control signal of the relay module.

[0069] It should be understood that the switch quantity output module can achieve the control output of some small current signals through the switch quantity output circuit, and output the large current control signal of the relay module.

[0070] In specific implementation, the switch quantity output module can achieve the output of some weak current signals through the switch quantity output circuit; and can also send weak control signals to the relay module in the way of weak electricity controlling strong electricity to achieve the purpose of strong current output of the relay module.

[0071] In this embodiment, through the above solution, the SoC processing module prestores the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtains the operating status of the spacecraft equipment; the input quantity acquisition module receives the time synchronization pulse of the time synchronization equipment through the time synchronization circuit, acquires the externally input digital quantity and various status signals, and at the same time performs backtesting on various switch quantity output signals; the switch quantity output module performs the control output of the current signal through the switch quantity output circuit, and outputs the current control signal of the relay module, which can realize the time synchronization function between the time synchronization equipment and the test, launch and control equipment, etc., reduce the power consumption and delay, analogize and batch process the test data as needed, realize the self-diagnosis of system faults, can greatly improve the development efficiency of engineers, improve the timekeeping accuracy of the spacecraft system, speed up the response performance of the test, launch and control system, reduce the complexity of the system software, improve the reliability of data transmission, can test the overall performance of the spacecraft, and improve the speed and efficiency of the test and launch control based on SoC.

[0072] Further, Figure 2 is a schematic flowchart of the second embodiment of the test and launch control method based on SoC of the present invention. As Figure 2 shown, based on the first embodiment, the second embodiment of the test and launch control method based on SoC of the present invention is proposed. In this embodiment, after the step S10, the test and launch control method based on SoC further includes the following steps:

[0073] Step S11: The power supply module converts the input voltage into the required voltages for each functional module during operation.

[0074] It should be noted that the power supply module can convert the input voltage into the required voltages for each functional module. In actual operation, a 6U standard module structure form can be used to convert the DC 28V voltage into 5V and 12V to supply power to each functional module in the device, and generally can supply power to the SoC processing module, communication module, AD acquisition module, etc.

[0075] Step S12: The communication module sends control instructions and receives status information between the test, launch and control system and the spacecraft equipment through the CAN bus.

[0076] It can be understood that the communication module can realize networking between the test, launch and control equipment and the equipment and power supply equipment on the spacecraft through the CAN bus, and send relevant control instructions and receive response commands and feedback status information according to the needs of the test process and the launch process.

[0077] Step S13: The SoC processing module integrates the fieldbus protocol and performs information interaction with other devices through the fieldbus protocol.

[0078] In a specific implementation, the SoC processing module can implement tests for multiple test items, and at the same time has the capabilities of one-key testing, automatic testing, and remote testing, as well as executing spacecraft launch missions. The SoC processing module can be designed with a unique heterogeneous multi-core SoC processor of ARM + floating-point DSP as the core architecture, integrating field bus protocols such as high-definition video input, HDMI, CAN, UART, USB, PCIe, Ethernet, and SATA hard disk; the unique combination of two different types of computing cores allows developers to maximize benefits. Each computing core is used to execute different tasks. With the help of ARM, developers can separate control functions, advanced graphical user interfaces from other real-time algorithms programmed on the DSP processor, thereby reducing the complexity of the system software; it can also interact with other functional modules through the CPCI bus; and it also pre-stores programs for controlling the spacecraft testing process and launch process.

[0079] Step S14: The relay module realizes the on-off control of the current signal and performs the safety mechanism control conversion function.

[0080] It should be understood that the relay module can use a solid-state relay to realize the on-off control of strong current signals, driving related devices to be in working and stopped states; it can also control the conversion of high-power safety mechanisms through relays to realize the safety control function of the equipment.

[0081] In this embodiment, through the above solution, the power supply module converts the input voltage into the required voltage for each functional module to work; the communication module sends control instructions and receives status information through the CAN bus between the test launch control system and the spacecraft equipment; the SoC processing module integrates the field bus protocol and interacts with other devices through the field bus protocol; the relay module realizes the on-off control of the current signal and performs the safety mechanism control conversion function, and can realize the time synchronization function between the timekeeping device and the test launch control device, etc., reducing power consumption and delay, and improving the speed and efficiency of test launch control based on SoC.

[0082] Further, Figure 3 This is a flowchart of the third embodiment of the test launch control method based on SoC of the present invention. As Figure 3 shown, based on the second embodiment, the third embodiment of the test launch control method based on SoC of the present invention is proposed. In this embodiment, after the step S14, the test launch control method based on SoC further includes the following steps:

[0083] Step S15: The AD acquisition module measures multiple analog voltage signals through the relay module.

[0084] It should be noted that the AD acquisition module can select several channels of analog voltage signals through a relay for conversion measurement. The analog voltage signals first enter the switch circuit of the relay multiplexer to select several channels for gating, then are processed by the signal conditioning circuit, then are denoised by the isolation amplifier circuit, and finally are sent to the ADC converter circuit for acquisition, and the acquired digital voltage signals are filtered.

[0085] Step S16: The CPCI interconnection module realizes the interconnection and interoperability of each functional module through the CPCI bus standard interface.

[0086] It should be understood that the CPCI interconnection module can realize the interconnection and interoperability of the signals of each functional module in the device through the CPCI bus standard interface.

[0087] In this embodiment, through the above solution, the AD acquisition module measures multiple channels of analog voltage signals through the relay module; the CPCI interconnection module realizes the interconnection and interoperability of each functional module through the CPCI bus standard interface, and can realize the interconnection and interoperability between the test launch control system and devices such as spacecraft, improving the speed and efficiency of test launch control based on SoC.

[0088] Further, Figure 4 This is a flowchart of the fourth embodiment of the test launch control method based on SoC of the present invention. As Figure 4 shown, the fourth embodiment of the test launch control method based on SoC of the present invention is proposed based on the first embodiment. In this embodiment, the step S30 specifically includes the following steps:

[0089] Step S40: The network switching module realizes data communication between the test launch control device and the remote control device through the Ethernet bus.

[0090] It should be noted that the network switching device can realize data communication between the test launch control device and the remote control device through the Ethernet bus.

[0091] In specific implementation, the network switching device can have multiple 10 / 100 / 1000 Mbps adaptive Ethernet switch ports. The ports support flow control and support full-duplex / half-duplex adaptive transmission modes, and are used to realize data transmission between the test launch control device and the remote control device through the Ethernet bus frame format; it also adopts an acknowledgment mechanism to avoid misframes and lost frames caused by network link failures, and adopts a retransmission strategy to improve the reliability of data transmission.

[0092] Step S50: The display and keyboard mouse module realizes the function of human-computer interaction.

[0093] It should be understood that the display and keyboard-mouse module can realize the real-time display of test results such as the operating state of the spacecraft, feedback data, and the motion curve of the servo mechanism. It can also enable the operator to input control instructions or control parameters through the keyboard and mouse to realize the function of human-computer interaction.

[0094] Through the above solution, in this embodiment, the network switching module realizes data communication between the test launch control device and the remote control device through the Ethernet bus; the display and keyboard-mouse module realizes the function of human-computer interaction, can realize the time synchronization function between the time synchronization device and the test launch control device, etc., which can greatly improve the development efficiency of engineers and improve the timekeeping accuracy of the spacecraft system.

[0095] Furthermore, Figure 5 This is a schematic flowchart of the fifth embodiment of the test launch control method based on SoC of the present invention. As Figure 5 shown, the fifth embodiment of the test launch control method based on SoC of the present invention is proposed based on the fourth embodiment. In this embodiment, after the step S50, the test launch control method based on SoC further includes the following steps:

[0096] Step S60: The camera module takes pictures of the spacecraft erection process and transmits the image data to the remote control device.

[0097] It should be noted that the camera device can take pictures of the spacecraft erection process and transmit the image data to the remote control device, and then the operating state of devices such as the spacecraft can be monitored in real time according to the image data.

[0098] Step S70: The image electro-optical conversion module converts the video signal captured by the camera module into an optical signal for long-distance transmission, and realizes the photoelectric conversion after the long-distance transmission of the image through the optoelectronic conversion device, and converts it into a standard video image signal for display on the device.

[0099] It can be understood that the image electro-optical conversion device can convert the video signal captured by the camera device into an optical signal for long-distance transmission, that is, convert the video signal captured by the camera device into an optical signal through the electro-optical conversion device for long-distance, lossless and low-latency transmission.

[0100] Step S80: The data recording module records the process data of the spacecraft and the test launch control device.

[0101] It should be understood that the data recording device can record the process data of the spacecraft and the test launch control device, and then perform fault analysis according to the process data.

[0102] In a specific implementation, the data recording device can record the test process data of the spacecraft and the launch measurement, control and command equipment in real time and store it; manage the stored test data by classification based on database technology, and can analogize and batch process the test data as needed to achieve system fault self-diagnosis; relevant professionals can read the data according to the fault phenomenon for in-depth analysis.

[0103] Step S90: The time synchronization equipment control module realizes the time synchronization function between the time synchronization equipment and the launch measurement, control and command equipment, etc., so that the launch measurement, control and command equipment can obtain the launch time for the spacecraft to launch on time.

[0104] It can be understood that the time synchronization equipment control module can realize the time synchronization function between the time synchronization equipment (such as rubidium clocks, etc.) and the launch measurement, control and command equipment, etc., and the launch measurement, control and command equipment obtains the time for the spacecraft to launch on time.

[0105] Step S100: The AC / DC power supply equipment provides the power required for the operation of the spacecraft and the launch measurement, control and command equipment.

[0106] In a specific implementation, the AC / DC power supply equipment can convert the AC / DC voltage into voltages such as 28V after passing through an electromagnetic interference (EMI) circuit, a rectification and filtering circuit, a high-frequency conversion circuit, an output filtering circuit and a monitoring and display circuit, and provide the voltage and current required for the operation of the spacecraft, the launch measurement, control and command equipment, etc.

[0107] In this embodiment, through the above solution, the camera module takes pictures of the spacecraft erection process and transmits the image data to the remote control device; the image electro-optical conversion module converts the video signal captured by the camera module into an optical signal for long-distance transmission, and realizes the electro-optical conversion after long-distance image transmission through an optoelectronic conversion device, and converts it into a standard video image signal for display on the device; the data recording module records the process data of the spacecraft and the launch measurement, control and command equipment; the time synchronization equipment control module realizes the time synchronization function between the time synchronization equipment and the launch measurement, control and command equipment, etc., so that the launch measurement, control and command equipment can obtain the launch time for the spacecraft to launch on time; the AC / DC power supply equipment provides the power required for the operation of the spacecraft and the launch measurement, control and command equipment, can realize the time synchronization function between the time synchronization equipment and the launch measurement, control and command equipment, etc., reduces power consumption and delay, analogizes and batch processes the test data as needed, realizes system fault self-diagnosis, can greatly improve the development efficiency of engineers, improves the timekeeping accuracy of the spacecraft system, speeds up the response performance of the launch measurement, control and command system, reduces the complexity of the system software, improves the reliability of data transmission, and improves the speed and efficiency of the test launch control based on SoC.

[0108] Correspondingly, the present invention further provides a test launch control system based on SoC.

[0109] Refer to Figure 6 ,Figure 6 This is the functional block diagram of the first embodiment of the test launch control system based on SoC of the present invention.

[0110] In the first embodiment of the test launch control system based on SoC of the present invention, the test launch control system based on SoC includes:

[0111] The SoC processing module 10 is used to pre-store the target program for controlling the spacecraft during the test process and the launch process, and to obtain the device operation status of the spacecraft equipment in real time.

[0112] It should be noted that the SoC processing module pre-stores the program for controlling the spacecraft test process and the launch process; and is also used to obtain and display the operation status of the spacecraft equipment captured by the camera device in real time.

[0113] The input quantity acquisition module 20 is used to receive the time synchronization pulse of the time synchronization device through the time synchronization circuit, collect the externally input digital quantity and various status signals, and at the same time perform backtesting on various switch quantity output signals.

[0114] It can be understood that the input quantity acquisition module can receive the time synchronization pulse of the time synchronization device through the high-precision high-speed time synchronization circuit; and collect the externally input digital quantity and various status signals, and at the same time perform backtesting on various switch quantity output signals.

[0115] In specific implementation, the input quantity acquisition module includes receiving the time synchronization pulse of the time synchronization device through the high-precision high-speed time synchronization interface circuit, using the filtering algorithm to eliminate interference signals such as burrs from the collected pulse signals; and after the external input quantity input opto-isolation circuit, collecting the externally input digital quantity and various status signals of the spacecraft through the acquisition circuit; and then performing backtesting on various switch quantity signals output by the switch quantity output module.

[0116] The switch quantity output module 30 is used to control the output of the current signal through the switch quantity output circuit, and output the current control signal of the relay module.

[0117] It should be understood that the switch quantity output module can realize the control output of some small current signals through the switch quantity output circuit, and output the large current control signal of the relay module.

[0118] In specific implementation, the switch quantity output module can realize the output of some weak current signals through the switch quantity output circuit; and can also send weak control signals to the relay module in the way of weak electricity controlling strong electricity to achieve the purpose of strong current output of the relay module.

[0119] In this embodiment, through the above solution, the SoC processing module prestores the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtains the operating status of the spacecraft equipment; the input quantity acquisition module receives the timing pulses of the timekeeping equipment through the timing circuit, acquires the externally input digital quantities and various status signals, and simultaneously performs backtesting on various switch quantity output signals; the switch quantity output module controls the output of the current signal through the switch quantity output circuit, and outputs the current control signal of the relay module, which can realize the timing function of the timekeeping equipment and the test launch control equipment, etc., reduce power consumption and delay, analogize and batch process the test data as needed, realize system fault self-diagnosis, greatly improve the development efficiency of engineers, improve the timekeeping accuracy of the spacecraft system, speed up the response performance of the test launch control system, reduce the complexity of the system software, improve the reliability of data transmission, and improve the speed and efficiency of the test launch control based on SoC.

[0120] Further, Figure 7 is the functional module diagram of the second embodiment of the test launch control system based on SoC of the present invention. As Figure 7 shown, based on the first embodiment, the second embodiment of the test launch control system based on SoC of the present invention is proposed. In this embodiment, the test launch control system based on SoC further includes:

[0121] A power supply module 40, which is used to convert the input voltage into the required voltages for each functional module to work.

[0122] It should be noted that the power supply module can convert the input voltage into the required voltages for each functional module to work. In actual operation, a 6U standard module structure form can be adopted to convert the DC 28V voltage into 5V and 12V to supply power to each functional module in the device, and generally can supply power to the SoC processing module, communication module, AD acquisition module, etc.

[0123] A communication module 50, which is used to send control instructions and receive status information between the test launch control system and the spacecraft equipment through the CAN bus.

[0124] It can be understood that the communication module can realize networking between the test launch control equipment and the equipment and power supply equipment on the spacecraft through the CAN bus, and send relevant control instructions and receive response commands and feedback status information according to the needs of the test process and the launch process.

[0125] The SoC processing module 10 is further used to integrate the fieldbus protocol and interact information with other devices through the fieldbus protocol.

[0126] In a specific implementation, the SoC processing module can implement tests for multiple test items, and at the same time has the capabilities of one-key testing, automatic testing, and remote testing, as well as executing spacecraft launch missions. The SoC processing module can be designed with a unique heterogeneous multi-core SoC processor of ARM + floating-point DSP as the core architecture, integrating field bus protocols such as high-definition video input, HDMI, CAN, UART, USB, PCIe, Ethernet, and SATA hard disk; the unique combination of two different types of computing cores allows developers to maximize benefits. Each computing core is used to execute different tasks. With the help of ARM, developers can separate control functions, advanced graphical user interfaces from other real-time algorithms programmed on the DSP processor, thereby reducing the complexity of the system software; it can also interact with other functional modules through the CPCI bus; and it also pre-stores programs for controlling the spacecraft testing process and launch process.

[0127] The relay module 60 is used to implement the on-off control of current signals and perform the control conversion function of the safety mechanism.

[0128] It should be understood that the relay module can use a solid-state relay to implement the on-off control of strong current signals, driving related devices to be in working and stopping states; it can also control the conversion of high-power safety mechanisms through relays to achieve the safety control function of the device.

[0129] In this embodiment, through the above solution, the power supply module converts the input voltage into the required voltage for each functional module to work; the communication module sends control instructions and receives status information through the CAN bus between the test launch control system and spacecraft equipment; the SoC processing module integrates the field bus protocol and exchanges information with other devices through the field bus protocol; the relay module implements the on-off control of current signals and performs the control conversion function of the safety mechanism, and can achieve the time synchronization function between the timekeeping device and the test launch control device, etc., reducing power consumption and delay, and improving the speed and efficiency of test launch control based on SoC.

[0130] Furthermore, Figure 8 This is the functional module diagram of the third embodiment of the test launch control system based on SoC of the present invention. As Figure 8 shown, based on the second embodiment, the third embodiment of the test launch control system based on SoC of the present invention is proposed. In this embodiment, the test launch control system based on SoC further includes:

[0131] The AD acquisition module 70 is used to measure multiple-channel analog voltage signals through the relay module.

[0132] It should be noted that the AD acquisition module can use a relay to select several of multiple analog voltage signals for conversion measurement. The analog voltage signals first enter the switch circuit of the relay multiplexer for selection, then are processed by the signal conditioning circuit, then pass through the isolation amplifier circuit for noise reduction, and finally are sent to the ADC converter circuit for acquisition. The acquired digital voltage signals are filtered.

[0133] The CPCI interconnection module 80 is used to achieve the interconnection and interoperability of each functional module through the CPCI bus standard interface.

[0134] It should be understood that the CPCI interconnection module can achieve the interconnection and interoperability of the signals of each functional module within the device through the CPCI bus standard interface.

[0135] In this embodiment, through the above solution, the AD acquisition module measures multiple analog voltage signals through the relay module; the CPCI interconnection module realizes the interconnection and interoperability of each functional module through the CPCI bus standard interface, and can achieve the interconnection and interoperability between the test launch control system and devices such as spacecraft, improving the speed and efficiency of the test launch control based on SoC.

[0136] Furthermore, Figure 9 This is the functional block diagram of the fourth embodiment of the test launch control system based on SoC of the present invention. As Figure 9 shown, the fourth embodiment of the test launch control system based on SoC of the present invention is proposed based on the third embodiment. In this embodiment, the test launch control system based on SoC further includes:

[0137] The network switching module 90 is used to achieve data communication between the test launch control device and the remote control device through the Ethernet bus.

[0138] It should be noted that the network switching device can achieve data communication between the test launch control device and the remote control device through the Ethernet bus.

[0139] In specific implementation, the network switching device can have multiple 10 / 100 / 1000 Mbps adaptive Ethernet switch ports. The ports support flow control and support full-duplex / half-duplex adaptive transmission modes, and are used to achieve data transmission between the test launch control device and the remote control device through the Ethernet bus frame format; it also adopts an acknowledgment mechanism to avoid misframes and lost frames caused by network link failures, and adopts a retransmission strategy to improve the reliability of data transmission.

[0140] The display and keyboard / mouse module 100 is used to achieve the function of human-computer interaction.

[0141] It should be understood that the display and keyboard - mouse module can realize the real - time display of test results such as the operating state of the spacecraft, feedback data, and the motion curve of the servo mechanism. It can also enable the operator to input control commands or control parameters through the keyboard and mouse, thus realizing the function of human - machine interaction.

[0142] In this embodiment, through the above - mentioned solution, the data communication between the test - launch - control equipment and the remote - control equipment is realized through the Ethernet bus by the network - switching module; the display and keyboard - mouse module realizes the function of human - machine interaction, can realize the time - synchronization function between the time - synchronization equipment and the test - launch - control equipment, etc., which can greatly improve the development efficiency of engineers and improve the time - keeping accuracy of the spacecraft system.

[0143] Furthermore, Figure 10 This is the functional - module diagram of the fifth embodiment of the test - launch control system based on SoC of the present invention. As Figure 10 shown, based on the fourth embodiment, the fifth embodiment of the test - launch control system based on SoC of the present invention is proposed. In this embodiment, the test - launch control system based on SoC further includes:

[0144] The camera module 110 is used to photograph the erection process of the spacecraft and transmit the image data to the remote - control equipment.

[0145] It should be noted that the camera device can photograph the erection process of the spacecraft, transmit the image data to the remote - control equipment, and then the operating state of equipment such as the spacecraft can be monitored in real time according to the image data.

[0146] The image electro - optical conversion module 120 is used to convert the video signal captured by the camera module into an optical signal for long - distance transmission, and realizes the photoelectric conversion after the long - distance transmission of the image through the optoelectronic conversion device, and converts it into a standard video - image signal for display on the device.

[0147] It can be understood that the image electro - optical conversion device can convert the video signal captured by the camera device into an optical signal for long - distance transmission, that is, convert the video signal captured by the camera device into an optical signal through the electro - optical conversion device for long - distance, lossless and low - delay transmission, and can also display the converted standard video - image signal on the display device.

[0148] The data - recording module 130 is used to record the process data of the spacecraft and the test - launch - control equipment.

[0149] It should be understood that the data - recording device can record the process data of the spacecraft and the test - launch - control equipment, and then conduct fault analysis according to the process data.

[0150] In a specific implementation, the data recording device can record the test process data of the spacecraft and the test launch control equipment in real time and store it; manage the stored test data in a classified manner based on database technology, and can perform analogy and batch processing on the test data as needed to achieve system fault self-diagnosis; relevant professionals can read the data according to the fault phenomenon for in-depth analysis.

[0151] The time synchronization equipment control module 140 is used to implement the time synchronization function between the time synchronization equipment and the test launch control equipment, etc., so that the test launch control equipment can obtain the launch time for the spacecraft to launch on time.

[0152] It can be understood that the time synchronization equipment control module can implement the time synchronization function between the time synchronization equipment (such as rubidium clocks, etc.) and the test launch control equipment, etc., and the test launch control equipment obtains the time for the spacecraft to launch on time.

[0153] The AC / DC power supply module 150 is used to provide the power required for the operation of the spacecraft and the test launch control equipment.

[0154] In a specific implementation, the AC / DC power supply device can convert the AC / DC voltage into voltages such as 28V after passing through an electromagnetic interference (EMI) circuit, a rectifier filter circuit, a high-frequency conversion circuit, an output filter circuit, and a monitoring and display circuit, and provide the voltage and current required for the operation of the spacecraft, the test launch control equipment, etc.

[0155] Through the above solutions in this embodiment, the camera module takes pictures of the spacecraft erection process and transmits the image data to the remote control device; the image electro-optical conversion module converts the video signal captured by the camera module into an optical signal for long-distance transmission, and realizes the electro-optical conversion after long-distance image transmission through an optoelectronic conversion device, and converts it into a standard video image signal for display on the device; the data recording module records the process data of the spacecraft and the test launch control equipment; the time synchronization equipment control module implements the time synchronization function between the time synchronization equipment and the test launch control equipment, etc., so that the test launch control equipment can obtain the launch time for the spacecraft to launch on time; the AC / DC power supply device provides the power required for the operation of the spacecraft and the test launch control equipment, can implement the time synchronization function between the time synchronization equipment and the test launch control equipment, etc., reduces power consumption and latency, performs analogy and batch processing on the test data as needed to achieve system fault self-diagnosis, can greatly improve the development efficiency of engineers, improve the timekeeping accuracy of the spacecraft system, speed up the response performance of the test launch control system, reduce the complexity of the system software, improve the reliability of data transmission, and improve the speed and efficiency of the test launch control based on SoC.

[0156] It should be noted that in this text, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or system including a series of elements not only includes those elements, but also includes other elements not explicitly listed, or elements inherent to such a process, method, article or system. Without further limitation, an element defined by the statement "including one..." does not exclude the existence of another identical element in the process, method, article or system including that element.

[0157] The serial numbers of the embodiments of the present invention above are only for description and do not represent the superiority or inferiority of the embodiments.

[0158] The above are only the preferred embodiments of the present invention and do not limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made by using the content of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, is equally included in the patent protection scope of the present invention.

Claims

1. A test launch control method based on SoC, characterized in that The described SoC-based test launch control method includes: The SoC processing module pre-stores the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtains the operating status of the spacecraft equipment; The input quantity acquisition module receives the time synchronization pulses of the timekeeping equipment through the time synchronization circuit, acquires the externally input digital quantities and various status signals, and at the same time performs backtesting on various switch quantity output signals; The switch quantity output module controls the output of the current signal through the switch quantity output circuit, and outputs the current control signal of the relay module; Among them, after the SoC processing module pre-stores the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtains the operating status of the spacecraft equipment, the SoC-based test launch control method further includes: The power supply module converts the input voltage into the required voltages for the operation of each functional module; The communication module sends control instructions and receives status information between the test launch control system and the spacecraft equipment through the CAN bus; The SoC processing module integrates the field bus protocol and performs information interaction with other devices through the field bus protocol; The relay module realizes the on-off control of the current signal and performs the safety mechanism control conversion function.

2. The test launch control method based on SoC according to claim 1, characterized in that, After the relay module realizes the on-off control of the current signal and performs the safety mechanism control conversion function, the SoC-based test launch control method further includes: The AD acquisition module measures multiple analog voltage signals through the relay module; The CPCI interconnection module realizes the interconnection and interoperability of each functional module through the CPCI bus standard interface.

3. The test launch control method based on SoC according to claim 1, characterized in that After the switch quantity output module controls the output of the current signal through the switch quantity output circuit and outputs the current control signal of the relay module, the SoC-based test launch control method further includes: The network switching module realizes data communication between the test launch control equipment and the remote control equipment through the Ethernet bus; The display and keyboard mouse module realizes the function of human-computer interaction.

4. The test launch control method based on SoC according to claim 3, characterized in that, After the display and keyboard mouse module realizes the function of human-computer interaction, the SoC-based test launch control method further includes: The camera module takes pictures during the erection process of the spacecraft and transmits the image data to the remote control equipment; The image electro-optical conversion module converts the video signal captured by the camera module into an optical signal for long-distance transmission, and realizes the electro-optical conversion after the long-distance transmission of the image through the optoelectronic conversion device, and converts it into a standard video image signal for display on the equipment; The data recording module records the process data of the spacecraft and the test launch control equipment; The timekeeping equipment control module realizes the time synchronization function between the timekeeping equipment and the test launch control equipment, etc., so that the test launch control equipment can obtain the launch time for the spacecraft to launch on time; The AC / DC power supply equipment provides the power required for the operation of the spacecraft and the test launch control equipment.

5. A test launch control system based on SoC, characterized in that, The described SoC-based test launch control system includes: The SoC processing module is used to pre-store the target programs for controlling the spacecraft during the test process and the launch process, and real-time obtain the operating status of the spacecraft equipment; The input acquisition module is used to receive the time synchronization pulse of the time synchronization device through the time synchronization circuit, acquire the externally input digital quantities and various status signals, and at the same time perform backtesting on various switch quantity output signals; The switch quantity output module is used to control the output of the current signal through the switch quantity output circuit and output the current control signal of the relay module; The power supply module is used to convert the input voltage into the required voltage for each functional module during operation; The communication module is used to send control instructions and receive status information between the test launch control system and the spacecraft equipment through the CAN bus; The SoC processing module is also used to integrate the fieldbus protocol and interact with other devices through the fieldbus protocol; The relay module is used to realize the on-off control of the current signal and perform the safety mechanism control conversion function.

6. The test launch control system based on SoC according to claim 5, characterized in that, The SoC-based test launch control system further includes: The AD acquisition module is used to measure multiple analog voltage signals through the relay module; The CPCI interconnection module is used to achieve the interconnection and interoperability of each functional module through the CPCI bus standard interface.

7. The test launch control system based on SoC according to claim 5, characterized in that, The SoC-based test launch control system further includes: The network switching module is used to realize data communication between the test launch control equipment and the remote control equipment through the Ethernet bus; The display and keyboard mouse module is used to realize the function of human-computer interaction.

8. The test launch control system based on SoC according to claim 7, characterized in that, The SoC-based test launch control system further includes: The camera module is used to take pictures during the spacecraft erection process and transmit the image data to the remote control equipment; The image electro-optical conversion module is used to convert the video signal captured by the camera module into an optical signal for long-distance transmission, and realize the electro-optical conversion after long-distance transmission of the image through the optoelectronic conversion device, and convert it into a standard video image signal for display on the equipment; The data recording module is used to record the process data of the spacecraft and the test launch control equipment; The time synchronization equipment control module is used to realize the time synchronization function between the time synchronization equipment and the test launch control equipment, etc., so that the test launch control equipment can obtain the launch time for the spacecraft to launch on time; The AC / DC power supply module is used to provide the power required for the operation of the spacecraft and the test launch control equipment.

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