CN-116294836-B - Portable rocket guidance assembly ground test launch control system

CN116294836BCN 116294836 BCN116294836 BCN 116294836BCN-116294836-B

Abstract

The invention discloses a ground test launch control system of a portable rocket guidance assembly, which comprises a protective box body, a test launch control computer, a power module, an operation panel module and a cable, wherein the protective box body is used for installing and protecting internal equipment, the test launch control computer is used for controlling and testing the test of the rocket guidance assembly, the power module is used for supplying power to 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 internally provided with related algorithms such as a fault simulation diagnosis algorithm, a navigation algorithm and the like, and the test launch control computer converts an instruction into a control signal through the electrical communication interface on the operation panel and sends the control signal to the rocket guidance assembly and receives a feedback state signal to the test launch control computer. The invention can load other algorithm software according to actual demands and has the advantages of high integration level, small volume, light weight, comprehensive functions and strong applicability.

Inventors

BAI HONGYANG
CAO YU
Zou Guanyu
Jin Kerui
Deng tianyu

Assignees

南京理工大学

Dates

Publication Date: 20260512
Application Date: 20230327

Claims (9)

1. The utility model provides a portable rocket guidance subassembly ground test initiating and controlling system which characterized in that, the hardware includes protection box, test initiating and controlling computer, power module, operating panel module and cable, wherein: The protective box body is used for installing and protecting 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 electric appliance communication interface for the test launch control computer and the rocket guidance assembly; the cable is used for connecting the test launch control system and the rocket guidance assembly, charging the power module and supplying power to the test launch control computer; The software comprises test initiation control software, fault simulation and test software and navigation guidance algorithm software: In the test launch control software, the communication setting function is used for setting the serial number and the communication baud rate of the communication serial port, and after the communication connection is successful, parameters of the rocket guidance assembly are displayed on a software interface in real time; the system self-checking function is used for driving the rocket guidance assembly to carry out system self-checking, and displaying self-checking results of the GPS and steering engine on a software interface; The fault simulation and test software can simulate and simulate faults, detect and diagnose rocket faults, and display corresponding faults on an interface in a graphical information manner; The navigation guidance algorithm software takes GNSS satellite information as a reference, completes estimation of error parameters and automatic calibration of constant errors of inertial navigation components on the premise of not disassembling inertial navigation through a design decision latch compensation method, utilizes a Kalman filtering technology to fuse the GNSS/INS information by a GNSS/INS combined navigation algorithm, utilizes a factor graph multi-source information fusion algorithm to solve a multi-source information fusion navigation problem by a factor graph method, and utilizes a trained neural network to output pseudo GNSS information for combined navigation under the condition of satellite rejection by an intelligent fusion algorithm based on an LSTM neural network.
2. The ground test launch control system of a portable rocket guidance assembly of claim 1 wherein said protective housing is injection molded of polymeric material and is sealed with a flat resilient foam sealing rubber strip.
3. The ground test launch control system of a portable rocket guidance assembly according to claim 1, wherein the test launch control computer comprises an industrial control host, a display screen, a keyboard, a loudspeaker and a heat dissipation system, pre-stores computer programs and operation interface software for controlling the rocket guidance assembly test, and configures and updates the computer programs and the operation interface software according to specific requirements, wherein the computer programs and the operation interface software comprise test launch control software, fault simulation and test software and navigation guidance algorithm software.
4. A portable rocket guidance assembly ground test launch control system according to claim 1 wherein said power module comprises two independent sets of power supplies, a test launch control computer power supply and a rocket guidance assembly power supply, respectively.
5. The portable rocket guidance assembly ground test launch control system of claim 1 wherein said operator panel module comprises a control button and electrical communication interface wherein: The control button is used for controlling the rocket guidance assembly; The electrical communication interface is used for communicating the test initiation control computer with the rocket guidance assembly, and the electrical communication interface converts an instruction sent by the test initiation control computer into a control signal and sends the control signal to the rocket guidance assembly, receives a state signal fed back by the rocket guidance assembly and sends the state signal to the test initiation control computer.
6. A portable rocket guidance assembly ground test launch control system according to claim 3 wherein the functions of said test launch control software include communication setup, system self-test and firing launch functions, said fault simulation and test software includes fault simulation functions and fault diagnosis functions, said navigation guidance algorithm software includes navigation self-calibration algorithm, GNSS/INS integrated navigation algorithm, factor graph multisource information fusion algorithm, LSTM neural network based intelligent fusion algorithm.
7. The ground test launch control system of claim 5 wherein said control buttons comprise a power-on button of a test launch control computer, a screen brightness adjustment button and a volume adjustment button of the test launch control computer, an active safety button, a battery activation button, an ac power button and a battery power button, an ignition button, a standby ignition button; The alternating current power supply button and the battery power supply button are used for selecting to supply power for the test control computer through alternating current or supplying power for the test control computer through a test control computer power supply in the power supply module according to the using condition of the test control system.
8. The ground test launch control system of a portable rocket guidance assembly of claim 5, wherein said electrical communication interface comprises 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 of a test launch control computer, and a 12-core connector.
9. The ground test launch control system of a portable rocket guidance assembly according to claim 8, wherein the USB communication interface comprises two USB3.0 interfaces and one USB2.0 interface, the communication serial port is an RS232 communication serial port, the voltage input interface comprises a 12V input interface and a 28V input interface, the voltage output interface comprises a 12V output interface and a 28V output interface, and the power supply interface voltage of the test launch control computer is 220V/50Hz.

Description

Portable rocket guidance assembly ground test launch control system Technical Field The invention relates to the technical field of rocket test launch control systems, in particular to a portable rocket guidance assembly ground test launch control system. Background With the continuous evolution of modern war investigation means, the survival difficulty of weapon systems is increasing, and weapons developed in the sixth seventies of the last century are difficult to meet the requirements of modern war, so new requirements are put on weapon systems, including test systems. The ground test system developed in the past has the advantages of large volume, single test function and low test precision. With the improvement of testing means, the development of computer bus technology, the increase of memory resources and the improvement of data communication rate, the test which is difficult to be completed in the past is easier. Before the missile is launched, the working states of all the equipment of the missile are required to be checked one by one on the ground, the missile is launched according to a specified flow after the checking is completed, and the test result of the ground test system determines whether the missile has launching conditions or not, so that the ground test is very important. Therefore, the technical upgrading of the weapon system testing equipment can greatly improve the reliability of the weapon system. The ground test launch control system (Ground test and launch control system) of the rocket guidance assembly integrates the functions of test, launch control, data processing and the like and is used for testing and controlling the performance of the rocket guidance assembly in the process of rocket development. The traditional ground test launch control system needs to be customized according to the model of the rocket guidance assembly, the number of interfaces and functions in the test equipment are less, the functions are single, the number of the test equipment is more, the size is large, the weight is large, the preparation process is complex, the test time of rocket test launch control is prolonged, and the problems of resource waste, poor compatibility, low information transmission and the like also exist. The ground test launch control system is used as an important component of the rocket guidance assembly test, and a great deal of manpower, material resources and time are generally required to be input. Patent CN110411517a discloses a rocket intelligent testing, launching and controlling system, which has comprehensive functions but requires interaction of multiple computers and servers, and has a complex system architecture. The method proposed by the paper (Han Liang, zhang Hongde, peng Yue. Design of ground integrated launch control system of carrier rocket [ J ]. Computer measurement and control 2021,29 (06): 5-8,34 ]) carries out integrated design on hardware, software and information of ground launch control system of carrier rocket, and the system has comprehensive functions and high integration degree, but the system architecture is still complex. Patent CN110780599a discloses a launch vehicle maneuvering testing and controlling system, which can set different modes according to the launching environment, but the system equipment arrangement and installation process is still complex. Patent CN102042122a discloses a portable rocket engine ground test measurement and control system, which has a small volume structure but is divided into three parts of a computer, a data acquisition and control card and a measurement and control box, and portability can be further improved. Patent CN111997786a discloses a rocket engine portable measurement and control system box, which has higher integration degree, but relatively fewer software functions. Disclosure of Invention The invention aims to provide a ground test launch control system of a portable rocket guidance assembly, which has the advantages of high integration level, small volume, light weight and complete functions. The technical scheme for realizing the purpose of the invention is that the ground test launch control system of the portable rocket guidance assembly comprises a protective box body, a test launch control computer, a power module, an operation panel module and a cable, wherein software comprises the following components: The protective box body is used for installing and protecting 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 electric appliance communication interface for the test launch control computer and the rocket guidance assembly; The cable is used for connecting the test launch control system and the rocket guidance assembly