A portable ground test launch control system for a rocket guidance assembly

Abstract

The application discloses a portable rocket guidance assembly ground test launch control system, which comprises a protective box body, a test launch control computer, a power module, an operation panel module and a cable; the protective box body is used for mounting and protecting the internal equipment; the test launch control computer is used for controlling and testing the rocket guidance assembly test; the power module supplies power for the test launch control computer and the rocket guidance assembly; the operation panel module is used for controlling the rocket guidance assembly and providing an electrical communication interface for the test launch control computer and the rocket guidance assembly; the system is provided with built-in fault simulation diagnosis algorithm, navigation algorithm and other related algorithms; the test launch control computer converts instructions into control signals through the electrical communication interface on the operation panel and sends the control signals to the rocket guidance assembly, and receives the feedback state signals of the rocket guidance assembly and sends the feedback state signals to the test launch control computer. The application can load other algorithm software according to actual requirements, and has the advantages of high integration, small size, light weight, comprehensive functions and strong applicability.

Description

Technical Field

[0001] This invention relates to the field of rocket test and launch control system technology, and in particular to a portable ground test and launch control system for rocket guidance components. Background Technology

[0002] With the continuous evolution of modern warfare reconnaissance methods, the survivability of weapon systems is becoming increasingly challenging. Weapons developed in the 1960s and 70s are no longer sufficient to meet the demands of modern warfare, thus placing new demands on weapon systems, including testing systems. Past ground testing systems were large, had limited testing functions, and low accuracy. However, with advancements in testing methods, computer bus technology, storage resources, and data communication speeds, tests that were previously difficult to perform have become relatively easy. Before missile launch, the operational status of each missile component must be checked on the ground. After the checks are completed, launch is carried out according to prescribed procedures. The test results from the ground testing system determine whether the missile is ready for launch, making ground testing extremely important. Therefore, upgrading the technology of weapon system testing equipment can significantly improve the reliability of weapon systems.

[0003] The rocket guidance component ground test and launch control system integrates testing, launch control, and data processing functions. It is used to test and control the performance of rocket guidance components during rocket development. Traditional ground test and launch control systems require customization based on the rocket guidance component model. These systems often have limited and single-function interfaces, require a large number of large and heavy pieces of equipment, and involve complex preparation processes. This prolongs the testing time, wastes resources, and suffers from poor compatibility and inefficient information transmission.

[0004] Ground-based test and control systems, as a crucial component of rocket guidance component testing, typically require significant investment of manpower, resources, and time. Patent CN110411517A discloses a rocket intelligent test and control system, which offers comprehensive functionality but necessitates interaction between multiple computers and servers, resulting in a complex system architecture. The paper "Design of an Integrated Ground-based Test and Control System for Launch Vehicles" (Han Liang, Zhang Hongde, Peng Yue. Design of an Integrated Ground-based Test and Control System for Launch Vehicles [J]. Computer Measurement & Control, 2021, 29(06):5-8,34.) proposes a method that integrates the hardware, software, and information of the launch vehicle ground-based test and control system. This method offers comprehensive functionality and a high degree of integration, but the system architecture remains relatively complex. Patent CN110780599A discloses a mobile test and control system for launch vehicles, which can be configured with different modes depending on the launch environment; however, the system equipment layout and installation process remains complex. Patent CN102042122A discloses a portable rocket engine ground test measurement and control system. While relatively small in size, it still consists of three main parts: a computer, a data acquisition and control card, and a measurement and control box. Its portability could be further improved. Patent CN111997786A discloses a portable rocket engine measurement and control system box, which has a high degree of integration, but relatively limited software functionality. Summary of the Invention

[0005] The purpose of this invention is to provide a portable rocket guidance component ground test and control system that is highly integrated, small in size, lightweight, and fully functional.

[0006] The technical solution for achieving the objective of this invention is: a portable rocket guidance component ground test and control system, the hardware of which includes a protective housing, a test and control computer, a power module, an operation panel module, and cables, and the software includes:

[0007] The protective enclosure is used to install and protect the internal equipment;

[0008] The test launch control computer is used to control and test the rocket guidance components.

[0009] The power module supplies power to the test launch control computer and rocket guidance components.

[0010] The operation panel module is used to control the rocket guidance components and provides an electrical communication interface for the test launch control computer and the rocket guidance components;

[0011] The cable is used to connect the test launch control system to the rocket guidance components, to charge the power module, and to supply power to the test launch control computer.

[0012] Furthermore, the protective enclosure is injection molded from polymer material and sealed with a flat, elastic foamed rubber strip.

[0013] Furthermore, the test launch control computer includes an industrial control host, a display screen, a keyboard, a speaker, and a heat dissipation system. It pre-stores computer programs and user interface software for controlling the testing of rocket guidance components, and can be configured and updated according to specific needs. The computer programs and user interface software include test launch control software, fault simulation and testing software, and navigation and guidance algorithm software.

[0014] Furthermore, the power module includes two independent power supplies: a test launch control computer power supply and a rocket guidance component power supply.

[0015] Furthermore, the operation panel module includes control buttons and an electrical communication interface, wherein:

[0016] The control button is used to control the rocket guidance assembly;

[0017] The electrical communication interface is used for communication between the test launch control computer and the rocket guidance component. The electrical communication interface converts the instructions issued by the test launch control computer into control signals and sends them to the rocket guidance component, and receives the status signals fed back by the rocket guidance component and sends them to the test launch control computer.

[0018] Furthermore, the test launch control software includes communication settings, system self-test, and ignition / launch functions; the fault simulation and testing software includes fault simulation and fault diagnosis functions; and the navigation and guidance algorithm software includes navigation self-calibration algorithm, GNSS / INS integrated navigation algorithm, factor graph multi-source information fusion algorithm, and intelligent fusion algorithm based on LSTM neural network.

[0019] Furthermore, the control buttons include a power-on button for the test engine control computer; screen brightness and volume adjustment buttons for the test engine control computer; a fuse activation button; a battery activation button; an AC power supply button and a battery power supply button; an ignition button; and a backup ignition button.

[0020] The AC power supply button and the battery power supply button are used to select whether to power the test and control computer with AC power or with the power supply of the test and control computer in the power module, depending on the usage conditions of the test and control system.

[0021] Furthermore, the electrical communication interface includes an Ethernet interface; a USB communication interface; a communication serial port; a voltage input interface; a voltage output interface; a power supply interface and a charging interface for the test and control computer; and a 12-pin connector.

[0022] Furthermore, the test control software, fault simulation and testing software, and navigation and guidance algorithm software are specifically as follows:

[0023] In the test launch control software, the communication setting function is used to set the serial port number and baud rate of the communication serial port. After the communication connection is successful, the parameters of the rocket guidance component will be displayed on the software interface in real time. The system self-test function is used to drive the rocket guidance component to perform system self-test and display the self-test results of components such as GPS and servo motors on the software interface. The ignition and launch function loads the launch parameters, calls the rocket guidance component software, performs simulated flight and displays the results. The corresponding parameters are displayed on the interface in the form of charts.

[0024] The fault simulation and testing software can simulate faults; detect and diagnose rocket faults; and display the corresponding faults as graphical information on the interface.

[0025] The navigation and guidance algorithm software uses GNSS satellite information as a reference and, through the design of a decision latch compensation method, estimates error parameters and automatically calibrates the constant error of inertial navigation components without disassembling the inertial navigation system. The GNSS / INS integrated navigation algorithm uses Kalman filtering technology to fuse GNSS / INS information. The factor graph multi-source information fusion algorithm uses the factor graph method to solve the multi-source information fusion navigation problem. The intelligent fusion algorithm based on LSTM neural network uses the trained neural network to output pseudo-GNSS information for integrated navigation in the case of satellite rejection.

[0026] Furthermore, the USB communication interface includes two USB 3.0 interfaces and one USB 2.0 interface; the communication serial port is an RS232 communication serial port; the voltage input interface includes a 12V input interface and a 28V input interface, and the voltage output interface includes a 12V output interface and a 28V output interface; the power supply interface voltage of the test control computer is AC 220V / 50Hz.

[0027] Compared with the prior art, the significant advantages of this invention are: (1) High integration, small size, and light weight. The total weight of this invention is less than 13 kg, and the size of the protective box is less than 500×400×200 mm. It does not require other auxiliary equipment and can charge the built-in power module to achieve field application, effectively solving the portability problem of the ground test and launch control system; (2) Diverse built-in algorithms and powerful functions. The built-in computer program and operation interface software of this invention include test and launch control software, fault simulation and diagnosis software, and navigation algorithm software, which can simulate the rocket launch process; (3) Simple architecture and strong applicability. This invention can use or replace various test and launch control or simulation software according to actual needs, which improves the compatibility of the rocket ground test and launch control system, reduces the structural complexity of the traditional rocket ground test and launch control system, and improves the applicability of the rocket ground test and launch control system. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the ground test launch control system for the rocket guidance component of the present invention.

[0029] Figure 2 This is a schematic diagram of the operation panel module structure of the ground test launch control system for the rocket guidance component in the embodiment.

[0030] Figure 3 This is a schematic diagram of the test launch control software interface of the ground test launch control system for the rocket guidance component in the embodiment.

[0031] Figure 4 This is a schematic diagram of the software and hardware architecture of the ground test launch control system for the rocket guidance component in the embodiment. Detailed Implementation

[0032] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0033] Combination Figure 1 This invention discloses a portable ground test and control system for rocket guidance components. The hardware includes a protective enclosure, a test and control computer, a power module, an operation panel module, and cables. The software includes the following components:

[0034] The protective enclosure is used to install and protect the internal equipment;

[0035] The test launch control computer is used to control and test the rocket guidance components.

[0036] The power module supplies power to the test launch control computer and rocket guidance components.

[0037] The operation panel module is used to control the rocket guidance components and provides an electrical communication interface for the test launch control computer and the rocket guidance components;

[0038] The cable is used to connect the test launch control system to the rocket guidance components, to charge the power module, and to supply power to the test launch control computer.

[0039] Furthermore, the protective enclosure is injection molded from polymer material and sealed with a flat, elastic foamed rubber strip.

[0040] Furthermore, the test launch control computer includes an industrial control host, a display screen, a keyboard, a speaker, and a heat dissipation system. It pre-stores computer programs and user interface software for controlling the testing of rocket guidance components, and can be configured and updated according to specific needs. The computer programs and user interface software include test launch control software, fault simulation and testing software, and navigation and guidance algorithm software.

[0041] Furthermore, the power module includes two independent power supplies: a test launch control computer power supply and a rocket guidance component power supply.

[0042] Furthermore, the operation panel module includes control buttons and an electrical communication interface, wherein:

[0043] The control button is used to control the rocket guidance assembly;

[0044] The electrical communication interface is used for communication between the test launch control computer and the rocket guidance component. The electrical communication interface converts the instructions issued by the test launch control computer into control signals and sends them to the rocket guidance component, and receives the status signals fed back by the rocket guidance component and sends them to the test launch control computer.

[0045] Furthermore, the test launch control software includes communication settings, system self-test, and ignition / launch functions; the fault simulation and testing software includes fault simulation and fault diagnosis functions; and the navigation and guidance algorithm software includes navigation self-calibration algorithm, GNSS / INS integrated navigation algorithm, factor graph multi-source information fusion algorithm, and intelligent fusion algorithm based on LSTM neural network.

[0046] Furthermore, the control buttons include a power-on button for the test engine control computer; screen brightness and volume adjustment buttons for the test engine control computer; a fuse activation button; a battery activation button; an AC power supply button and a battery power supply button; an ignition button; and a backup ignition button.

[0047] The AC power supply button and the battery power supply button are used to select whether to power the test and control computer with AC power or with the power supply of the test and control computer in the power module, depending on the usage conditions of the test and control system.

[0048] Furthermore, the electrical communication interface includes an Ethernet interface; a USB communication interface; a communication serial port; a voltage input interface; a voltage output interface; a power supply interface and a charging interface for the test and control computer; and a 12-pin connector.

[0049] Furthermore, the test control software, fault simulation and testing software, and navigation and guidance algorithm software are specifically as follows:

[0050] In the test launch control software, the communication setting function is used to set the serial port number and baud rate of the communication serial port. After the communication connection is successful, the parameters of the rocket guidance component will be displayed on the software interface in real time. The system self-test function is used to drive the rocket guidance component to perform system self-test and display the self-test results of components such as GPS and servo motors on the software interface. The ignition and launch function loads the launch parameters, calls the rocket guidance component software, performs simulated flight and displays the results. The corresponding parameters are displayed on the interface in the form of charts.

[0051] The fault simulation and testing software can simulate faults; detect and diagnose rocket faults; and display the corresponding faults as graphical information on the interface.

[0052] The navigation and guidance algorithm software uses GNSS satellite information as a reference and, through the design of a decision latch compensation method, estimates error parameters and automatically calibrates the constant error of inertial navigation components without disassembling the inertial navigation system. The GNSS / INS integrated navigation algorithm uses Kalman filtering technology to fuse GNSS / INS information. The factor graph multi-source information fusion algorithm uses the factor graph method to solve the multi-source information fusion navigation problem. The intelligent fusion algorithm based on LSTM neural network uses the trained neural network to output pseudo-GNSS information for integrated navigation in the case of satellite rejection.

[0053] Furthermore, the USB communication interface includes two USB 3.0 ports and one USB 2.0 port; the communication serial port is an RS232 communication serial port; the voltage input interface includes a 12V input port and a 28V input port, and the voltage output interface includes a 12V output port and a 28V output port; the power supply interface voltage of the test control computer is AC 220V / 50Hz. The 12V output port has a current of 5A, and the 28V output port has 4 pins, with a maximum current of 10A per pin, of which 2 pins are positive and 2 pins are negative.

[0054] Furthermore, the protective enclosure is injection molded from polymer material and sealed with a flat, elastic foamed rubber strip.

[0055] Furthermore, the activation safety button is equipped with a protective cover to prevent accidental activation.

[0056] Example 1

[0057] Combination Figure 1 , Figure 2 The ground test and control system for rocket guidance components provided in this embodiment requires opening the protective enclosure first. The upper part integrates the test and control computer screen, while the lower part is the main control panel. The test and control computer communicates with the corresponding electrical communication interface on the control panel via a communication bus, and also interacts with the rocket guidance component through this interface. The electrical communication interface converts the command signals issued by the test and control computer into control signals and sends them to the rocket guidance component. It also receives status signals from the rocket guidance component and sends them back to the test and control computer. The test and control computer processes and analyzes the feedback signals to obtain the operating status of the rocket guidance component. Figure 2This is a schematic diagram of the operation panel module of the ground test launch control system for the rocket guidance assembly provided in this embodiment. In addition to the electrical communication interface and operation buttons, the operation module is also equipped with an LED screen that displays the power module's battery level / voltage in real time. The operation panel also integrates the speaker module, cooling system, and keyboard of the test launch control computer. The keyboard includes a touchpad and mouse buttons for operator use.

[0058] Figure 3 This diagram illustrates the test launch control software for the ground test launch control system of the rocket guidance component provided by this invention. The test launch control software is developed using an integrated development environment (IDE), facilitating the calling and communication of other related software, as well as the verification of the hardware and software systems. The software is practical, reliable, and has a simple and aesthetically pleasing interface. The software functions include communication settings, system self-test, and ignition / launch functions. The communication settings section allows setting the serial port number and baud rate of the communication serial port. After successful communication, the parameters of the rocket guidance component are displayed in real-time on the software interface. The system self-test function drives the rocket guidance component to perform a system self-test and displays the self-test results of components such as GPS and servo motors on the software interface. The ignition / launch function can load launch parameters, call the rocket guidance component software, perform simulated flight, and display the relevant results. After setting the launch conditions, clicking the "Ignition" button initiates a closed-loop simulation. The ground test launch control system sends the corresponding ballistic parameters to the rocket guidance component, which then sends the parsed rudder deflection commands to the servo motors, driving them to deflect accordingly until the simulation ends. During software operation, the corresponding ballistic parameters will be displayed on the interface in the form of charts.

[0059] In addition to the test launch control software, the ground test launch control system provided in this embodiment also integrates fault simulation and diagnosis software and navigation algorithm software.

[0060] In the fault simulation and diagnosis software, the fault simulation software can simulate faults, and the fault diagnosis software can detect and diagnose rocket faults and display the corresponding faults as graphical information on the interface.

[0061] The navigation algorithm software can simulate the onboard computer for navigation and guidance calculations. Built-in algorithms include a navigation self-calibration algorithm, a GNSS / INS integrated navigation algorithm, a factor graph multi-source information fusion algorithm, and an intelligent fusion algorithm based on an LSTM (Long Short Term Memory) neural network. The navigation self-calibration algorithm uses GNSS satellite information as a reference and, through a designed decision latch compensation method, can estimate error parameters and automatically calibrate the constant errors of inertial navigation components without disassembling the inertial navigation system. The GNSS / INS integrated navigation algorithm uses an improved Kalman filter technique to fuse GNSS / INS information, effectively improving navigation accuracy. The factor graph multi-source information fusion algorithm uses a factor graph method to solve the multi-source information fusion navigation problem. The intelligent fusion algorithm based on an LSTM (Long Short Term Memory) neural network can use a trained neural network to output pseudo-GNSS information for integrated navigation methods in the event of satellite rejection. The software can simulate navigation and guidance calculations under various operating conditions, and all algorithms can be modified or expanded according to specific usage requirements.

[0062] Figure 4 This is a schematic diagram of the software and hardware architecture of the portable rocket guidance component ground test and launch control system provided in this embodiment. The hardware of the portable rocket guidance component ground test and launch control system includes a protective housing, a test and launch control computer, a power module, an operation panel module, and cables. The test and launch control computer pre-stores computer programs and operating interface software for controlling the testing of the rocket guidance component. The computer programs and operating interface software include test and launch control software, fault simulation and diagnosis software, and navigation algorithm software. The test and launch control software functions include communication settings, system self-test, and ignition and launch functions; the fault simulation and diagnosis software includes fault simulation and fault diagnosis functions; the navigation algorithm software includes a navigation self-calibration algorithm, a GNSS / INS integrated navigation algorithm, a factor graph multi-source information fusion algorithm, and an intelligent fusion algorithm based on LSTM (Long Short-Term Memory) neural networks.

[0063] The computer program and user interface software enable simulation testing of various test items and execution of real rocket launch missions. The computer program pre-stored in this test and launch control system can be set according to the computer programs used in various test devices in traditional schemes, or it can be integrated by those skilled in the art.

[0064] The above-mentioned solution provided in this embodiment proposes an architecture mode for a portable rocket guidance component ground test and control system, which realizes the integration and lightweighting of the test and control system, with a total weight of less than 13 kg and a protective box size of less than 500×400×200 mm, effectively reducing the volume and weight of the ground test and control system and improving its portability.

[0065] The above description is merely an embodiment of the present invention and an explanation of the technical principles and solutions employed. Furthermore, the scope of the invention is not limited to specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the inventive concept.

Claims

1. A portable rocket guidance component ground test and launch control system, characterized in that, The hardware includes a protective enclosure, a test and control computer, a power module, an operation panel module, and cables, among which: The protective enclosure is used to install and protect the internal equipment; The test launch control computer is used to control and test the rocket guidance components. The power module supplies power to the test launch control computer and rocket guidance components. The operation panel module is used to control the rocket guidance components and provides an electrical communication interface for the test launch control computer and the rocket guidance components; The cable is used to connect the test launch control system to the rocket guidance components, to charge the power module, and to supply power to the test launch control computer. The software includes test and control software, fault simulation and testing software, and navigation and guidance algorithm software: In the test launch control software, the communication setting function is used to set the serial port number and baud rate of the communication serial port. After the communication connection is successful, the parameters of the rocket guidance component will be displayed on the software interface in real time. The system self-test function is used to drive the rocket guidance component to perform system self-test and display the self-test results of components such as GPS and servo motors on the software interface. The ignition and launch function loads the launch parameters, calls the rocket guidance component software, performs simulated flight and displays the results. The corresponding parameters are displayed on the interface in the form of charts. The fault simulation and testing software can simulate faults; detect and diagnose rocket faults; and display the corresponding faults as graphical information on the interface. The navigation and guidance algorithm software uses GNSS satellite information as a reference and, through the design of a decision latch compensation method, estimates error parameters and automatically calibrates the constant error of inertial navigation components without disassembling the inertial navigation system. The GNSS / INS integrated navigation algorithm uses Kalman filtering technology to fuse GNSS / INS information. The factor graph multi-source information fusion algorithm uses the factor graph method to solve the multi-source information fusion navigation problem. The intelligent fusion algorithm based on LSTM neural network uses the trained neural network to output pseudo-GNSS information for integrated navigation in the case of satellite rejection.

2. The portable rocket guidance component ground test and launch control system according to claim 1, characterized in that, The protective enclosure is injection molded from polymer material and sealed with a flat, elastic foamed rubber strip.

3. The portable rocket guidance component ground test and launch control system according to claim 1, characterized in that, The test launch control computer includes an industrial control host, a display screen, a keyboard, a speaker, and a cooling system. It is pre-stored with computer programs and user interface software for controlling the testing of rocket guidance components, and can be configured and updated according to specific needs. The computer programs and user interface software include test launch control software, fault simulation and testing software, and navigation and guidance algorithm software.

4. The portable rocket guidance component ground test and launch control system according to claim 1, characterized in that, The power module includes two independent power supplies: a test launch control computer power supply and a rocket guidance component power supply.

5. The portable rocket guidance component ground test and launch control system according to claim 1, characterized in that, The operation panel module includes control buttons and an electrical communication interface, wherein: The control button is used to control the rocket guidance assembly; The electrical communication interface is used for communication between the test launch control computer and the rocket guidance component. The electrical communication interface converts the instructions issued by the test launch control computer into control signals and sends them to the rocket guidance component, and receives the status signals fed back by the rocket guidance component and sends them to the test launch control computer.

6. The portable rocket guidance component ground test and launch control system according to claim 3, characterized in that, The test launch control software includes communication settings, system self-test, and ignition and launch functions; the fault simulation and testing software includes fault simulation and fault diagnosis functions; the navigation and guidance algorithm software includes navigation self-calibration algorithm, GNSS / INS integrated navigation algorithm, factor graph multi-source information fusion algorithm, and intelligent fusion algorithm based on LSTM neural network.

7. The portable rocket guidance component ground test and launch control system according to claim 5, characterized in that, The control buttons include a power button for the test control computer; a screen brightness adjustment button and a volume adjustment button for the test control computer; Activate insurance button; Battery activation button; AC power button and battery power button; ignition button; backup ignition button; The AC power supply button and the battery power supply button are used to select whether to power the test and control computer with AC power or with the power supply of the test and control computer in the power module, depending on the usage conditions of the test and control system.

8. The portable rocket guidance component ground test and launch control system according to claim 5, characterized in that, The electrical communication interfaces include an Ethernet interface; a USB communication interface; a communication serial port; a voltage input interface; a voltage output interface; a power supply interface and a charging interface for the test and control computer; and a 12-pin connector.

9. The portable rocket guidance component ground test and launch control system according to claim 8, characterized in that, The USB communication interface includes two USB 3.0 interfaces and one USB 2.0 interface; the communication serial port is an RS232 communication serial port; the voltage input interface includes a 12V input interface and a 28V input interface, and the voltage output interface includes a 12V output interface and a 28V output interface; the power supply interface voltage of the test control computer is AC 220V / 50Hz.

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