CN-122017893-A - Rotation characteristic test system of missile-borne GPS receiver

CN122017893ACN 122017893 ACN122017893 ACN 122017893ACN-122017893-A

Abstract

The invention relates to the technical field of missile-borne navigation equipment testing, and discloses a missile-borne GPS receiver rotation characteristic testing system which comprises a rotation simulation module, a GPS signal simulation module, a data acquisition and processing module, a gesture measurement module, a power supply module, an environment simulation module, a calibration module and a system control module, wherein the system control module is used as a core control center. The invention can realize complex rotation modes such as speed change, angle change and the like through the rotation simulation module, the high-precision turntable ensures centering precision through the laser aligner, the locking mechanism is stable and reliable, the rotation state of ammunition in flight can be accurately reproduced, the GPS signal simulation module supports multi-satellite constellation, variable frequency and power signal generation, the array antenna accurately controls beam pointing, GPS signals in different electromagnetic environments can be simulated, the environment simulation module integrates temperature and humidity and vibration control, the collaborative simulation of rotation and environmental factors can be realized, and the actual working scene of the receiver is comprehensively covered.

Inventors

XU LIYUAN
JIANG HONGTAO
YIN YOUGUI
SHI LI
XIONG LINA
CHEN JIANSHE

Assignees

江苏翔凯岩土工程有限公司

Dates

Publication Date: 20260512
Application Date: 20260122

Claims (8)

1. The system is characterized in that the system control module is used as a core control center and is respectively connected with a rotation control sub-module of the rotation simulation module, a signal parameter configuration sub-module of the GPS signal simulation module, a data analysis sub-module of the data acquisition and processing module and a gesture resolving sub-module of the gesture measurement module through an Ethernet bus; the system control module transmits control instructions such as a rotation mode, a rotation speed, a rotation angle and the like to the rotation control sub-module and receives real-time rotation state feedback of the turntable; The system control module transmits parameter configuration instructions such as GPS signal frequency, power, satellite constellation and the like to the signal parameter configuration sub-module, and receives signal generation state and signal quality data; the system control module transmits instructions such as data acquisition frequency, analysis algorithm selection and the like to the data analysis sub-module, and receives a data processing result and an error analysis report; The system control module transmits instructions such as gesture resolving frequency, filtering parameters and the like to the gesture resolving operator module and receives real-time gesture angle data; The system control module establishes bidirectional data and instruction connection with the man-machine interaction interface through a USB/RS232 interface, outputs test parameters, module running states, data processing results and alarm information to the man-machine interaction interface, and receives user operation instructions and test scheme configuration data uploaded by the man-machine interaction interface; The high-speed acquisition card establishes unidirectional data connection with an angular position sensor of the rotation simulation module, a signal quality analysis unit of the GPS signal simulation module, an inertia measurement unit of the gesture measurement module and an inclination sensor respectively through special data lines, synchronously acquires multi-source test data, and establishes bidirectional data connection with the data storage unit and the data analysis submodule through an internal bus to realize data storage and processing; The power supply module is respectively connected with all power utilization modules through distribution lines, an alternating current voltage-stabilizing power supply and a direct current switching power supply provide stable power for a driving motor of the rotation simulation module, a signal source host of the GPS signal simulation module, a high-speed acquisition card of the data acquisition and processing module, an inertial measurement unit of the gesture measurement module, an industrial computer of the system control module and a man-machine interaction interface, and the standby power supply unit is connected with the main power supply lines in parallel and connected with the system control module through a change-over switch to receive a power supply switching instruction.
2. The system for testing the rotation characteristics of the missile-borne GPS receiver is characterized in that a rotation control sub-module of the rotation simulation module is connected with a driving motor in a bidirectional control mode through a control cable, a rotation speed control signal is sent to the driving motor, state feedback such as motor running current and temperature is received, the driving motor is connected with a speed reduction transmission mechanism through a mechanical transmission structure, the speed reduction transmission mechanism is fixedly connected with a table top of a high-precision turntable to achieve power transmission, a laser aligner of a table top centering positioning device of the turntable is connected with a system control module through a signal cable to upload alignment deviation data, an air pressure control system of a locking mechanism is connected with the system control module through the control cable to receive clamping/loosening control instructions, a pressure sensor of the locking mechanism is connected with the system control module through the signal cable to upload clamping force data, an angular position sensor of the turntable is connected with a high-speed acquisition card of a data acquisition and processing module through a special data line to upload angular position and angular speed measurement data.
3. The rotation characteristic test system of the missile-borne GPS receiver is characterized in that a signal source host of the GPS signal simulation module is connected with an antenna radiation unit through a radio frequency cable to output GPS radio frequency signals, the signal source host is connected with a signal parameter configuration sub-module and a signal quality analysis unit through an internal data bus to establish bidirectional data connection, receive parameter configuration data and output signal quality monitoring data, the signal parameter configuration sub-module is connected with a system control module through an Ethernet bus to establish bidirectional communication connection, receive scene configuration instructions and feed back signal configuration states, the multi-satellite system simulation unit is connected with the signal source host through an internal bus to achieve cooperative generation of multi-system signals, an array antenna of the antenna radiation unit is connected with the signal source host through a phase control circuit to receive beam pointing control signals, and accurate coverage of the signal on the missile-borne GPS receiver is ensured.
4. The rotation characteristic test system of the missile-borne GPS receiver is characterized in that a data analysis submodule of the data acquisition and processing module is connected with a data synchronization calibration unit and an error tracing submodule through an internal bus to establish bidirectional data connection, receive synchronous calibration data and error analysis data and output processed test results, a data storage unit is connected with an industrial solid state disk through a SATA interface to establish bidirectional data connection to achieve read-write storage of test data, a visualization unit of the data analysis submodule is connected with a man-machine interaction interface through a video interface to establish unidirectional data connection to output a test data chart, and the data synchronization calibration unit is connected with a system control module through a time synchronization circuit to receive unified time reference signals to ensure time consistency of multi-source data.
5. The rotation characteristic test system of the missile-borne GPS receiver is characterized in that an inertia measurement unit of the gesture measurement module is connected with a temperature compensation submodule through a signal cable to establish bidirectional data connection, temperature measurement data are received and compensated inertia measurement data are output, the inertia measurement unit and an inclination angle sensor are connected with a gesture resolving operator module through special data lines to establish unidirectional data connection, original measurement data are uploaded, the gesture resolving operator module is connected with an expansion Kalman filtering unit through an internal bus to establish bidirectional data connection, data fusion resolving is achieved, the gesture resolving operator module is connected with a system control module through an Ethernet bus to establish bidirectional communication connection, gesture angle resolving results are uploaded and resolving parameter configuration instructions are received, a GPS data fusion interface is connected with a GPS receiver data interface through a communication line to receive GPS positioning speed measurement data for fusion resolving.
6. The system for testing the rotation characteristics of the missile-borne GPS receiver according to claim 1, wherein control software of the system control module is connected with a test flow automation unit and a fault diagnosis sub-module through an internal bus in a bidirectional data mode, receives an automation test scheme and fault diagnosis data and outputs a control command, a remote control interface is connected with an external remote control terminal through an Ethernet interface in a bidirectional communication mode to achieve remote command transmission and data feedback, and the fault diagnosis sub-module is connected with state monitoring sensors (voltage, current and temperature sensors) of all modules through signal monitoring lines in a unidirectional data mode to acquire module operation state data for fault identification.
7. The rotation characteristic test system of the missile-borne GPS receiver is characterized in that a temperature control unit, a humidity control unit and a vibration simulation unit of the environment simulation module are connected with a system control module in a two-way communication mode through control cables, environment parameter configuration instructions are received and environment state data are fed back, the temperature control unit and the humidity control unit are integrated in the same test box structure, environmental parameters are collected and controlled through an internal pipeline and a sensor, the vibration simulation unit is connected with a high-precision turntable of the rotation simulation module through a mechanical installation structure to achieve synergistic effect of vibration and rotation, and the environment simulation module is connected with a power supply module in a power supply mode through a distribution circuit to receive stable working power supplies and ensure accurate control of the environment parameters.
8. The rotation characteristic test system of the missile-borne GPS receiver is characterized in that a turntable calibration unit of the calibration module is connected with a high-precision turntable of the rotation simulation module through an optical interface, is connected with a system control module through a data bus in a two-way communication mode, uploads calibration data and receives calibration instructions, a signal source calibration unit is connected with a signal source host of the GPS signal simulation module through a radio frequency interface, is connected with the system control module through the data bus and feeds back a signal calibration result, an attitude measurement calibration unit is connected with an inertia measurement unit and an inclination sensor of the attitude measurement module through a mechanical interface and is connected with the system control module through a data bus, the attitude calibration data is uploaded, the system control module is connected with a calibration result analysis unit through an internal bus in a two-way data mode, receives the calibration data and generates a calibration report, and the working parameters of each module are automatically adjusted according to the calibration result.

Description

Rotation characteristic test system of missile-borne GPS receiver Technical Field The invention relates to the technical field of missile-borne navigation equipment testing, in particular to a system for testing rotation characteristics of a missile-borne GPS receiver. Background The missile-borne GPS receiver is subjected to severe working conditions such as high-speed rotation, complex electromagnetic environment, extreme temperature and humidity, vibration and the like in the ammunition flight process, and the rotation characteristic of the missile-borne GPS receiver directly influences the navigation positioning precision and reliability. The traditional missile-borne GPS receiver testing system has a plurality of defects: firstly, rotation simulation is single, only constant-speed rotation at a fixed rotating speed can be realized, variable speed and turning rotation modes in the ammunition flight process cannot be simulated, and the fitting degree of a test scene is low; Secondly, GPS signal simulation is simplified, the capability of collaborative simulation and signal quality dynamic adjustment of a multi-satellite system is lacked, and scenes such as signal attenuation, interference and the like in a complex electromagnetic environment cannot be reproduced; thirdly, data acquisition is asynchronous, multi-source test data (rotation state, GPS signals, receiver output and gesture data) lack of a unified time reference, and data correlation is poor, so that analysis of test results is affected; fourth, the environment is not suitable enough, the environment simulation modules such as temperature and humidity and vibration are not integrated, and the performance of the receiver under the synergistic effect of rotation and environmental stress cannot be tested; Fifthly, the intelligent degree is low, the test flow needs manual intervention, fault diagnosis and calibration depend on professional staff, the test efficiency is low, and the error is large. At present, the industry lacks a comprehensive test system integrating multimode rotation simulation, complex GPS signal generation, multi-source data synchronous acquisition, environment stress cooperation and intelligent calibration, and is difficult to meet the test requirements of high precision and multiple scenes of an missile-borne GPS receiver, and a full-flow and integrated rotation characteristic test system is needed. Disclosure of Invention The invention aims to provide a rotation characteristic testing system of an missile-borne GPS receiver, which aims to solve the problems in the background technology. The invention provides a technical scheme that the rotation characteristic test system of the missile-borne GPS receiver comprises a rotation simulation module, a GPS signal simulation module, a data acquisition and processing module, an attitude measurement module, a power supply module, an environment simulation module, a calibration module and a system control module, wherein the system control module is used as a core control center and is respectively connected with a rotation control sub-module of the rotation simulation module, a signal parameter configuration sub-module of the GPS signal simulation module, a data analysis sub-module of the data acquisition and processing module and an attitude solution sub-module of the attitude measurement module through Ethernet buses; the system control module transmits control instructions such as a rotation mode, a rotation speed, a rotation angle and the like to the rotation control sub-module and receives real-time rotation state feedback of the turntable; The system control module transmits parameter configuration instructions such as GPS signal frequency, power, satellite constellation and the like to the signal parameter configuration sub-module, and receives signal generation state and signal quality data; the system control module transmits instructions such as data acquisition frequency, analysis algorithm selection and the like to the data analysis sub-module, and receives a data processing result and an error analysis report; The system control module transmits instructions such as gesture resolving frequency, filtering parameters and the like to the gesture resolving operator module and receives real-time gesture angle data; The system control module establishes bidirectional data and instruction connection with the man-machine interaction interface through a USB/RS232 interface, outputs test parameters, module running states, data processing results and alarm information to the man-machine interaction interface, and receives user operation instructions and test scheme configuration data uploaded by the man-machine interaction interface; The high-speed acquisition card establishes unidirectional data connection with an angular position sensor of the rotation simulation module, a signal quality analysis unit of the GPS signal simulation module, an inertia measurement unit of the gestur