CN112393866B - Spacecraft micro-vibration ground test system and test method - Google Patents
Spacecraft micro-vibration ground test system and test method Download PDFInfo
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- CN112393866B CN112393866B CN202011335361.3A CN202011335361A CN112393866B CN 112393866 B CN112393866 B CN 112393866B CN 202011335361 A CN202011335361 A CN 202011335361A CN 112393866 B CN112393866 B CN 112393866B
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- repeater
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- control computer
- sensor network
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
- G01C19/58—Turn-sensitive devices without moving masses
- G01C19/64—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams
- G01C19/72—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams with counter-rotating light beams in a passive ring, e.g. fibre laser gyrometers
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/155—Ground-based stations
- H04B7/15507—Relay station based processing for cell extension or control of coverage area
Abstract
The application provides a spacecraft micro-vibration ground test system and a test method, and the system comprises a sensor network, a repeater and an industrial control computer, wherein the repeater is connected between the sensor network and the industrial control computer, connected with the sensor network through a shielded cable and connected with the industrial control computer through a network cable; the sensor network comprises a plurality of laser gyro sensors, and each laser gyro sensor is connected with the repeater through a shielding cable; the repeater comprises a power supply system, a gyro servo assembly and a controller; the power supply system is used for supplying power to the repeater and the sensor network; and the gyro servo component is used for controlling each laser gyro sensor in the sensor network. The beneficial effect of this application is: the relay is connected between the laser gyro sensor and the industrial personal computer, so that the industrial personal computer is far away from the spacecraft to be tested, the influence of the industrial personal computer on the micro-vibration angular displacement test result is eliminated, and the micro-vibration angular displacement test precision is effectively improved.
Description
Technical Field
The disclosure relates to the technical field of spacecraft micro-vibration ground test, in particular to a spacecraft micro-vibration ground test system and a spacecraft micro-vibration ground test method.
Background
Micro-vibration refers to vibration with a small amplitude, generally less than 10 -2 g magnitude, wide frequency range, low frequency band limit of quasi-steady state, and high frequency band limit of 10 3 In the Hz range. For a spacecraft with high stability and high precision pointing requirements, after the micro-vibration is transmitted into a payload through a spacecraft structure, the vibration response of the payload can be excited, the pointing precision and the position stability are reduced, and even the sensitive load fails to work in severe cases.
In the whole satellite ground test, by measuring the transmission effect of the satellite structure on micro-vibration, the vibration response of the sensitive part under the effect of a disturbance source can be obtained, and a basis is provided for vibration reduction performance evaluation and on-orbit imaging quality prediction. The micro-vibration angular displacement measurement system is mainly used for measuring the angular displacement of a sensitive structure or a load when the disturbance source is in a working state. The existing micro-vibration angular displacement measurement system only comprises a laser gyroscope and an industrial control computer, the laser gyroscope is distributed and installed at different measured positions of a satellite as sensors, the laser gyroscope is connected to the industrial control computer through a shielded cable, the shielding effect is considered, the longest shielded cable is only 9 meters, therefore, in the test process, the industrial control computer is arranged near the measured whole satellite, the noise of a computer body in working is large, and the accuracy of a micro-vibration measurement result is seriously influenced.
Disclosure of Invention
The application aims to solve the problems and provides a spacecraft micro-vibration ground test system and a test method.
In a first aspect, the application provides a spacecraft micro-vibration ground test system, which comprises a sensor network, a repeater and an industrial control computer, wherein the repeater is connected between the sensor network and the industrial control computer, the repeater is connected with the sensor network through a shielded cable, and the repeater is connected with the industrial control computer through a network cable; the sensor network comprises a plurality of laser gyro sensors, and each laser gyro sensor is connected with the repeater through a shielding cable; the repeater comprises a power supply system, a gyro servo assembly and a controller; the power supply system is used for supplying power to the repeater and the sensor network; and the gyro servo component is used for controlling each laser gyro sensor in the sensor network.
According to the technical scheme provided by the embodiment of the application, the power supply system comprises two stages of isolation, wherein the first stage of isolation converts commercial power AC220V into 24V direct current through an AC/DC switching power supply, and the second stage of isolation converts the direct current 24V into the power supply amount required by the gyro servo assembly and the laser gyro sensor through the DC/DC switching power supply.
According to the technical scheme provided by the embodiment of the application, the gyro servo assembly comprises: the device comprises a high-voltage current-stabilizing power supply, a frequency-stabilizing drive circuit, a light intensity conditioning circuit, an analog-to-digital converter and a digital-to-analog converter; the high-voltage current-stabilizing power supply is used for providing stable gain for the sensor network and providing 10 -4 A constant current source of magnitude symmetry; the frequency stabilization driving circuit is used for amplifying the output voltage of the digital-to-analog converter to drive a frequency stabilization actuating mechanism in the sensor network; the light intensity conditioning circuit is used for carrying out difference or summation on light intensity signals of the left-handed and right-handed laser gyro sensors output in the sensor network.
According to the technical scheme provided by the embodiment of the application, the controller is used for acquiring data of the sensor network and sending the acquired data to the industrial control computer; the controller comprises an FPGA module and an ARM module, the FPGA module is used for collecting data in real time, and the ARM module is used for calculating and transmitting the collected data.
According to the technical scheme provided by the embodiment of the application, the repeater comprises a shell, the power supply system, the gyro servo assembly and the controller are integrated in the shell, and the shell is respectively provided with a TCP/IP interface, a power supply input port, a manual switch, an SMA synchronous interface and a sensor connecting end; the TCP/IP interface is connected with an industrial personal computer through a network cable; the power input port connects the mains supply AC220V into the power system; the manual switch controls the power supply system to be electrified; the SMA synchronous interface is connected with an external synchronous instrument through a shielded cable; the sensor connecting end is connected with each laser gyro sensor through a shielding cable.
In a second aspect, the present application provides a spacecraft micro-vibration ground test method, including the following steps:
determining the position of the product to be measured for angular displacement, and respectively installing laser gyro sensors at the corresponding positions;
connecting each laser gyro sensor to the repeater through a shielded cable;
connecting the repeater with an industrial control computer through a network cable, wherein the industrial control computer is arranged at a position far away from a product to be tested;
starting up the industrial control computer, and powering on the repeater;
starting angular displacement testing software on the industrial control computer, controlling each laser gyro sensor in the sensor network to start work by the repeater, acquiring testing data of each laser gyro sensor, and sending the acquired data to the industrial control computer;
turning off the angular displacement test software on the industrial control computer, and controlling each laser gyro sensor in the sensor network to stop working by the repeater;
and the industrial personal computer performs test data processing analysis on the received data sent by the repeater.
Compared with the existing micro-vibration angular displacement measurement technology, the technical scheme of the repeater has the following technical characteristics:
1. the repeater for driving the laser gyro sensor to work is designed, servo control of high-resolution work of the gyro is realized, and the repeater has no noise source and reduces interference of a test field;
2. the repeater and the industrial control computer transmit data and control signals by adopting a network cable, and the industrial control computer is far away from the tested star body, so that the noise of the system body is reduced, and the anti-interference capability is high;
3. to accommodate subsequent upgrades, the repeater device may support hardware extensions and software functional extensions.
Drawings
FIG. 1 is a schematic block diagram of the structure of a first embodiment of the present application;
FIG. 2 is a schematic block diagram of a repeater according to a first embodiment of the present invention;
FIG. 3 is a schematic block diagram of a power supply system of a repeater according to a first embodiment of the present application;
FIG. 4 is a schematic block diagram of a gyro servo assembly of a repeater according to a first embodiment of the present disclosure;
FIG. 5 is a schematic block diagram of a controller of a repeater according to a first embodiment of the present invention;
fig. 6 is a flowchart of a second embodiment of the present application.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention, the following detailed description of the present invention is provided in conjunction with the accompanying drawings, and the description of the present section is only exemplary and explanatory, and should not be construed as limiting the scope of the present invention in any way.
As shown in fig. 1 and fig. 2, a schematic diagram of a first embodiment of the present application includes a sensor network, a repeater and an industrial control computer, where the repeater is connected between the sensor network and the industrial control computer, the repeater is connected to the sensor network through a shielded cable, and the repeater is connected to the industrial control computer through a network cable; the sensor network comprises a plurality of laser gyro sensors, and each laser gyro sensor is connected with the repeater through a shielding cable; the repeater comprises a power supply system, a gyro servo assembly and a controller; the power supply system is used for supplying power to the repeater and the sensor network; and the gyro servo component is used for controlling each laser gyro sensor in the sensor network.
The controller in the repeater is a control center of the repeater and is responsible for monitoring the working state of the repeater, controlling the electrification of each laser gyro sensor in the sensor network, controlling the acquisition of each laser gyro sensor signal, controlling the uploading of a signal, receiving/sending of a synchronous signal and the like.
In a preferred embodiment, as shown in fig. 3, the power supply system includes two-stage isolation, which can effectively reduce interference of the mains supply, the first stage of isolation converts the mains supply AC220V into 24V direct current through the AC/DC switching power supply, and the second stage of isolation converts the direct current 24V into the power supply required by the gyro servo assembly and the laser gyro sensor through the DC/DC switching power supply.
In this embodiment, a power switch of the power supply system adopts a structure in which a hardware switch and a software switch are connected in series, after the hardware switch on the panel of the repeater is turned on, a controller inside the repeater is powered on, and then the software switch can be controlled to be turned on or off through test software.
In a preferred embodiment, as shown in fig. 4, the gyro servo assembly includes a hardware portion and a software portion, the hardware portion mainly completes signal conditioning and power amplification of each circuit, the software portion mainly completes a closed-loop algorithm of each feedback control loop, and a DSP digital processor chip is used as a hardware basis.
The hardware part comprises: the device comprises a high-voltage current-stabilizing power supply, a frequency-stabilizing drive circuit, a light intensity conditioning circuit, an analog-to-digital converter and a digital-to-analog converter.
The high-voltage current-stabilizing power supply is used for providing stable gain for the sensor network and providing 10 -4 And the constant current source with the magnitude symmetry is used for inhibiting zero offset caused by the Langmuir effect term.
The frequency stabilization driving circuit is used for amplifying the output voltage of the digital-to-analog converter to drive a frequency stabilization actuating mechanism on the laser gyro sensor so as to realize the functions of mode scanning, path length control and the like.
The light intensity conditioning circuit is used for performing difference or summation on light intensity signals of the left-handed and right-handed laser gyro sensors output by the preamplifier in the sensor network, wherein the light intensity difference output is used for frequency stabilization control, and the light intensity and the output are used for power monitoring and light power stabilization control of the laser gyro sensors.
In a preferred embodiment, as shown in fig. 5, the controller is used to collect data of the sensor network, control the working state of the repeater, and communicate with a high-speed industrial computer through an ethernet interface. In the preferred embodiment, the controller adopts a basic framework of an FPGA module and an ARM module, the FPGA module is used for collecting data in real time, and the ARM module is used for calculating and transmitting the collected data.
In this embodiment, the repeater includes a housing, the power supply system, the gyro servo assembly and the controller are integrated in the housing, and the housing is provided with a TCP/IP interface, a power input port, a manual switch, an SMA synchronization interface, and a sensor connection end, respectively.
The TCP/IP interface is connected with an industrial personal computer through a network cable; the power input port connects commercial power AC220V into a power system in the shell; the manual switch controls the power-on and power-off of the power supply system; the SMA synchronous interface is connected with an external instrument needing synchronization through a shielded cable; the sensor connecting end is connected with each laser gyro sensor through a shielding cable.
Fig. 6 is a flowchart of a second embodiment of the present application, and the present embodiment is a testing method using the testing system of the first embodiment, and the method includes the following steps:
s1, determining the position of the angular displacement to be measured on a product to be measured, and respectively installing a laser gyro sensor at each corresponding position.
And S2, connecting each laser gyro sensor to the repeater through a shielded cable.
In this embodiment, if the measurement data needs to be synchronized with other measurement data, the SMA synchronization interface of the repeater is connected to the acquisition system of other data by using the shielded cable.
And S3, connecting the repeater with an industrial control computer through a network cable, wherein the industrial control computer is arranged at a position far away from the product to be tested.
And S4, starting the industrial control computer, and electrifying the repeater.
And S5, starting the angular displacement testing software on the industrial control computer, controlling each laser gyro sensor in the sensor network to start to work by the repeater, acquiring the testing data of each laser gyro sensor, and sending the acquired data to the industrial control computer.
And S6, turning off the angular displacement testing software on the industrial control computer, and controlling each laser gyro sensor in the sensor network to stop working by the repeater.
And S7, the industrial personal computer processes and analyzes the received data sent by the repeater.
The principles and embodiments of the present application are described herein using specific examples, which are set forth only to help understand the methods and their core ideas of the present application. The foregoing is only a preferred embodiment of the present application, and it should be noted that there are objectively infinite specific structures due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes may be made without departing from the principle of the present application, and the technical features described above may be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention using its spirit and scope, as defined by the claims, may be directed to other uses and embodiments, or may be learned by practice of the invention.
Claims (4)
1. The spacecraft micro-vibration ground test system is characterized by comprising a sensor network, a repeater and an industrial control computer, wherein the repeater is connected between the sensor network and the industrial control computer, is connected with the sensor network through a shielded cable and is connected with the industrial control computer through a network cable;
the sensor network comprises a plurality of laser gyro sensors, and each laser gyro sensor is connected with the repeater through a shielding cable;
the repeater comprises a power supply system, a gyro servo assembly and a controller; the power supply system is used for supplying power to the repeater and the sensor network; the gyro servo component is used for controlling each laser gyro sensor in the sensor network;
the power switch of the power system adopts a structure that a hardware switch is connected with a software switch in series, the power system comprises two stages of isolation, the first stage of isolation converts commercial power AC220V into 24V direct current through an AC/DC switch power supply, and the second stage of isolation converts the direct current 24V into power supply required by a gyro servo assembly and a laser gyro sensor through a DC/DC switch power supply;
the gyro servo assembly includes: the device comprises a high-voltage current-stabilizing power supply, a frequency-stabilizing drive circuit, a light intensity conditioning circuit, an analog-to-digital converter and a digital-to-analog converter;
the high voltage regulated power supply is used for providing stable gain for the sensor network and provides 10 -4 A constant current source of magnitude symmetry;
the frequency stabilization driving circuit is used for amplifying the output voltage of the digital-to-analog converter to drive a frequency stabilization actuating mechanism in the sensor network;
the light intensity conditioning circuit is used for performing difference calculation or summation on light intensity signals of the left-handed and right-handed laser gyro sensors output in the sensor network.
2. A spacecraft microvibration ground test system according to claim 1, wherein the controller is configured to collect data of the sensor network and send the collected data to an industrial control computer; the controller comprises an FPGA module and an ARM module, the FPGA module is used for collecting data in real time, and the ARM module is used for calculating and transmitting the collected data.
3. A spacecraft micro-vibration ground test system according to claim 2, wherein the repeater comprises a shell, the power supply system, the gyro servo assembly and the controller are integrated in the shell, and the shell is respectively provided with a TCP/IP interface, a power input port, a manual switch, an SMA synchronous interface and a sensor connecting end;
the TCP/IP interface is connected with an industrial control computer through a network cable; the power input port connects commercial power AC220V into the power system; the manual switch controls the power supply system to be electrified; the SMA synchronous interface is connected with an external synchronous instrument through a shielded cable; the sensor connecting end is connected with each laser gyro sensor through a shielding cable.
4. A test method using the spacecraft micro-vibration ground test system according to any one of claims 1 to 3, characterized by comprising the following steps:
determining the position of the product to be measured for angular displacement, and respectively installing a laser gyro sensor at each corresponding position;
connecting each laser gyro sensor to the repeater through a shielded cable;
connecting the repeater with an industrial control computer through a network cable, wherein the industrial control computer is arranged at a position far away from a product to be tested;
starting up the industrial control computer, and powering on the repeater;
starting angular displacement testing software on the industrial control computer, controlling each laser gyro sensor in the sensor network to start work by the repeater, acquiring testing data of each laser gyro sensor, and sending the acquired data to the industrial control computer;
turning off the angular displacement test software on the industrial control computer, and controlling each laser gyro sensor in the sensor network to stop working by the repeater;
and the industrial personal computer performs test data processing analysis on the received data sent by the repeater.
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