CN107883898A - The real-time high-precision measuring method of satellite structure thermal deformation - Google Patents
The real-time high-precision measuring method of satellite structure thermal deformation Download PDFInfo
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- CN107883898A CN107883898A CN201711096135.2A CN201711096135A CN107883898A CN 107883898 A CN107883898 A CN 107883898A CN 201711096135 A CN201711096135 A CN 201711096135A CN 107883898 A CN107883898 A CN 107883898A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B15/00—Measuring arrangements characterised by the use of electromagnetic waves or particle radiation, e.g. by the use of microwaves, X-rays, gamma rays or electrons
- G01B15/06—Measuring arrangements characterised by the use of electromagnetic waves or particle radiation, e.g. by the use of microwaves, X-rays, gamma rays or electrons for measuring the deformation in a solid
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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
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
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Abstract
The invention discloses a kind of method for real-time measurement of satellite structure thermal deformation, it is included in the radio-frequency antenna that multiple radio-frequency shift labels are uniformly pasted in tested satellite structure plate surface, and install fixation receive radar sensor so that all radio-frequency shift labels in radar within sweep of the eye；Tested satellite structure plate is heated using heating plate, the positional information and displacement information of each label calculated by computer acquisition radar sensor, and the temperature information of temperature sensor is collected, the deflection distribution map for being tested the surface of structural slab and varying with temperature is calculated by least square fitting.The measuring method of the present invention disclosure satisfy that the thermal deformation measurement requirement of a variety of satellite structural materials such as carbon fiber cellular material, aluminium alloy, titanium alloy, and measurement accuracy is better than 0.05mm, and measurement sample frequency is up to 10kHZ.
Description
Technical field
The invention belongs to technical field of industrial measurement, and in particular to a kind of displacement label is defended with what displacement measurement radar was combined
The real-time high-precision measuring method of star structure thermal deformation, this method are mainly used in space precision fields of measurement.
Background technology
The in-orbit dimensional stability of satellite structure be satellite function improve a key factor, the temperature change of in-orbit environment
The deformation of satellite structure can be caused, can not only influence the health status of satellite itself, even can influence satellite when serious effectively carries
The normal work of lotus.Structural deformation monitoring is carried out to satellite, uses obtained measurement data to improve spacecraft structure and sets
Meter, foundation is provided for active control, to ensureing that the in-orbit permanently effective operation tool of spacecraft is of great significance.
Remote sensing satellite to realize high resolution observations over the ground, the determination precision of the attitude of satellite and camera internal position element it is steady
Determine precision, be converted into camera and the quick physical dimension lasting accuracy of star is required in rad level, micron order.Except optical observation system
System, other such as radars, antenna system are in order to reach higher pointing accuracy, it is also desirable to higher dimensional stability.
In view of the importance of the in-orbit physical dimension stability of satellite, external substantial amounts of research institution has all carried out satellite structure
Deformation measurement is studied.U.S. NASA, European ESA, Japanese JAXA etc. have carried out the technical research of spacecraft thermal deformation measurement and reality
Test.U.S. NASA in 2003 carries out deformation survey using Digital-image correlation method technology to the structure and connector of certain spacecraft
Amount.The measuring method precision is high, measurement range is big.But the measuring method is carried out at analysis because needing to substantial amounts of view data
Reason, therefore real-time measurement can not be realized.ESA is early in the nineties just influence of the structural stability to precision of equipment installation point
The requirement as design of satellites is analysed, 2008 using laser speckle interference measuring technology to honeybee in European Space Agency's thermal vacuum simulator
Nest plate antenna carries out deformation measurement, claims measurement accuracy to reach 0.2um.The measuring method is easily by environment such as temperature, humidity, vibrations
Condition influences, and requires high to environmental condition.
Domestic Beijing Satellite Environment Engineering Research Institute in the case where having carried out vacuum low-temperature environment large-scale deployed configuration it is non-contact
Deformation measurement, studied for Φ 660mm bore reflector antenna deformation measurements, the measuring method of use be it is photogrammetric,
Measurement accuracy can reach 30um.Beijing Space aviation university is in thermal vacuum simulator using fiber-optic grating sensor to certain type
Number antenna carried out thermal deformation measurement experiment.However, it can not all meet the purpose of measurement thermal deformation in real time.
The content of the invention
In order to solve the above-mentioned technical problem, it is an object of the invention to provide the method for real-time measurement of satellite structure thermal deformation,
It the method achieve the thermal deformation measurement of a variety of satellite structural materials such as carbon fiber cellular material, aluminium alloy, titanium alloy, it is intended to carry
High measurement accuracy and sample frequency.Wherein, a kind of deformation refers to that successional mechanical structure by a kind of Morphological Transitions is another kind
Form, general direct measurement displacement during deformation measurement, strain, distortion and stress are calculated by displacement.Some measuring method energy
Direct measurement strains or distortion, and stress can also be calculated by strain.
The present invention is achieved through the following technical solutions displacement measurement：
The method for real-time measurement of satellite structure thermal deformation, comprises the following steps：
(1) each radio-frequency shift label mainly comprising sinusoidal signal generator, radio frequency bandpass amplifier, power prosperity device and
Radio-frequency antenna, the radio-frequency antenna of multiple radio-frequency shift labels, affixed points quantity are uniformly pasted in tested satellite structure plate surface
Depending on being tested the size and type face complexity of structural slab；
(2) installation is fixed receives radar sensor, ensures unobstructed object between radar and radio-frequency shift label, all to penetrate
Frequency displacement label in radar within sweep of the eye；
(3) radio-frequency shift label is opened before heating and receives radar sensor, and radar sensor is received from radio frequency
The sine wave signal of label, label are handled the signal received；
(4) required according to the thermograde of Test Cycle, tested satellite structure plate is heated using heating plate；
(5) in heating process, radar sensor receives the mixing echo-signal of all labels, and radar sensor is to returning
Ripple is handled to obtain the displacement of each label；
(6) positional information and displacement information for each label that computer acquisition radar sensor calculates, and gather
To the temperature information of temperature sensor, the deflection for being tested the surface of structural slab and varying with temperature is calculated by least square fitting
Distribution map.
Wherein, in heating process, radar sensor receives the mixing echo-signal of all labels, radar sensor pair
Echo is handled, and the signal by detecting each label comes and goes phase difference to detect displacement of each label in direction of visual lines
Obtain the displacement of each label.
Wherein, radar sensor is separated with label using all phase Fourier transform spectrum or narrow-band bandpass filtering in pole separates
The separation between each label signal is realized, the separation between label signal and background returns.
Wherein, the material for being tested satellite structure plate is carbon fiber cellular material, aluminium alloy or titanium alloy.
Wherein, the radio-frequency antenna of radio-frequency shift label is pasted in tested satellite structure plate front, overleaf sticking heating plates.
Wherein, two radar sensors are fixed in the installation of structural slab front, ensures nothing between radar and radio-frequency shift label
Block object, all radio-frequency shift labels in radar within sweep of the eye.
Wherein, temperature sensor is identical with radio-frequency shift number of labels and is correspondingly arranged near radio-frequency shift label.
The present invention solves the real-time high-precision measuring method technical barrier of satellite structure thermal deformation, can by displacement label
Distribution is pasted onto on satellite structure measured surface, and small volume is in light weight, the structure of existing satellite is influenceed small.The present invention's
Measuring method disclosure satisfy that the thermal deformation measurement of a variety of satellite structural materials such as carbon fiber cellular material, aluminium alloy, titanium alloy will
Ask, measurement accuracy is better than 0.05mm, and measurement sample frequency is up to 10kHZ.
Brief description of the drawings
Fig. 1 is to be tested satellite structure plate surface in the inventive method to paste radio-frequency shift label schematic diagram；
Fig. 2 is the schematic diagram that satellite structure back sticking heating plates are tested in the inventive method；
Fig. 3 is the real-time high-precision measuring method schematic layout pattern of satellite structure thermal deformation.
Wherein, 1 is tested satellite structure plate, and 2 be radio-frequency shift label, 3 temperature sensors, and 4 be radar sensor, 5
For computer.
Embodiment
Below in conjunction with accompanying drawing the present invention is described in further detail, but this is merely exemplary, it is no intended to this
The protection domain of invention carries out any restrictions.
Fig. 1 is to be tested satellite structure plate surface in the inventive method to paste the signal of radio-frequency shift label, radio-frequency shift label
Radio-frequency shift label point is represented with black circles in point diagram, white circle represents temperature sensor.Using size as 500mm*300mm
Tested structural slab exemplified by, in the front of plate, be uniformly pasted with the radio-frequency antenna of 15 radio-frequency shift labels, and glued beside it
Temperature sensor is pasted to monitor the temperature of the point.A radio-frequency shift label point, the point are pasted on the fixed support of structural slab
It is as a reference point, to eliminate influence of the ambient vibration to deformation measurement.
Fig. 2 is tested satellite structure back sticking heating plates schematic diagram, represents the heating of stickup in figure with white box
Piece.The position of heating plate and radio-frequency shift label point are pasted with 15 heating plates to corresponding altogether.Heating plate controller, which is set, to be added
Heat thermograde, range of temperature from 20 DEG C to 60 DEG C, temperature be 20 DEG C, 25 DEG C, 30 DEG C, 35 DEG C, 40 DEG C, 45 DEG C,
50 DEG C, 55 DEG C and 60 DEG C carry out deflection measurement respectively.
Fig. 3 is the real-time high-precision measuring method schematic layout pattern of satellite structure thermal deformation, and satellite structure plate is placed vertically
And it is fixed, radio-frequency shift label is pasted in tested satellite structure plate front, overleaf sticking heating plates.Installed in structural slab front
The distance of fixed radar sensor, radar sensor and Board Under Test is 2m and contour with the center of Board Under Test.Ensure radar with
Unobstructed object between the radio-frequency antenna of radio-frequency shift label, all radio-frequency antennas in radar within sweep of the eye.Before heating
Radar sensor is opened, radar sensor radiation signal irradiates these RF tags, and label is handled the signal received,
It is then forwarded to radar sensor.Required according to the thermograde of Test Cycle, tested satellite structure plate is entered using heating plate
Row heating.
In heating process, radar sensor receives the mixing echo-signal of all labels, and radar sensor is to echo
Handled, the signal by detecting each label comes and goes phase difference and obtained to detect each label in the displacement of direction of visual lines
The displacement of each label.Dynamic measures while to realize multi-tag displacement, and label modulation system selection suppressed carrier is double
Sideband amplitude modulated technique, radar use all phase Fourier transformation spectral analysis technology or pole narrow band filter technology with label
Separation algorithm realizes the separation between each label signal, the separation between label signal and background returns.It is distant by microwave
The relative theory of survey technology, the position of reference point radio-frequency antenna immobilize, by measuring other radio-frequency antennas and referring to radio frequency
Relative phase change situation between antenna, calculate the displacement Δ d of its radio-frequency antenna：
Wherein, ΔΦ is phase place change, and λ is wavelength.
The positional information and displacement information for each label that computer acquisition radar sensor calculates, and collect temperature
The temperature information of sensor is spent, the change for being tested the surface of each measuring point of structural slab and varying with temperature is calculated by least square fitting
Shape spirogram.Its approximating method uses least square method polynomial curve fitting.The tag displacements amount obtained by radar sensor
With the temperature value binding analysis near the label point of temperature sensor measurement, the deformation of thermal deformation can be studied,
And analyze corresponding satellite temperature control and indemnifying measure.
Although giving detailed description and explanation to the embodiment of patent of the present invention above, it should be noted that
It is that we can carry out various equivalent changes and modification according to the conception of patent of the present invention to above-mentioned embodiment, produced by it
Function still covered without departing from specification and accompanying drawing spirit when, all should be within the protection domain of patent of the present invention.
Claims (7)
1. the method for real-time measurement of satellite structure thermal deformation, comprises the following steps：
(1) each radio-frequency shift label mainly includes sinusoidal signal generator, radio frequency bandpass amplifier, power prosperity device and radio frequency
Antenna, uniformly pastes the radio-frequency antenna of multiple radio-frequency shift labels in tested satellite structure plate surface, and affixed points quantity depends on
In the size and type face complexity of tested structural slab；
(2) installation is fixed receives radar sensor, ensures unobstructed object between radar and radio-frequency shift label, all radio frequency positions
Transfer label in radar within sweep of the eye；
(3) radio-frequency shift label is opened before heating and receives radar sensor, and radar sensor is received from RF tag
Sine wave signal, label handled the signal received；
(4) required according to the thermograde of Test Cycle, tested satellite structure plate is heated using heating plate；
(5) in heating process, radar sensor receives the mixing echo-signal of all labels, and radar sensor enters to echo
Row processing obtains the displacement of each label；
(6) positional information and displacement information for each label that computer acquisition radar sensor calculates, and collect temperature
The temperature information of sensor is spent, is calculated by least square fitting and is tested the deflection distribution that the surface of structural slab varies with temperature
Figure.
2. method for real-time measurement as claimed in claim 1, wherein, in heating process, radar sensor receives all marks
The mixing echo-signal of label, radar sensor are handled echo, by detect each label signal come and go phase difference come
Detect each label and obtain the displacement of each label in the displacement of direction of visual lines.
3. method for real-time measurement as claimed in claim 1, wherein, radar sensor uses all phase Fourier transformation with label
Separation between each label signal is realized in spectrum separation or the filtering separation of pole narrow-band bandpass, label signal and background returns it
Between separation.
4. method for real-time measurement as claimed in claim 1, wherein, the material for being tested satellite structure plate is carbon fiber honeycomb material
Material, aluminium alloy or titanium alloy.
5. method for real-time measurement as claimed in claim 1, wherein, paste radio-frequency shift label in tested satellite structure plate front
Radio-frequency antenna, overleaf sticking heating plates.
6. method for real-time measurement as claimed in claim 1, wherein, two radar sensors are fixed in the installation of structural slab front,
Ensure unobstructed object between radar and radio-frequency shift label, all radio-frequency shift labels in radar within sweep of the eye.
7. method for real-time measurement as claimed in claim 1 is wherein, temperature sensor is identical and right with radio-frequency shift number of labels
It should be arranged near radio-frequency shift label.
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Cited By (7)
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|---|---|---|---|---|
| CN109828248A (en) * | 2019-01-08 | 2019-05-31 | 上海卫星工程研究所 | The analysis method that the angular distortion of satellite-borne microwave remote sensing instrument influences visual direction amount |
| CN111380567A (en) * | 2020-03-24 | 2020-07-07 | 上海卫星工程研究所 | Satellite star sensor pointing in-orbit thermal deformation correction system |
| CN112014135A (en) * | 2020-08-24 | 2020-12-01 | 中国科学院微小卫星创新研究院 | Optical load optical axis thermal deformation detection system and method |
| CN112082496A (en) * | 2020-09-08 | 2020-12-15 | 西安建筑科技大学 | Concrete internal deformation measurement method and system based on improved digital volume image correlation method |
| CN112527029A (en) * | 2020-12-07 | 2021-03-19 | 上海卫星工程研究所 | Wireless passive temperature control system applied to satellite thermal control system |
| CN112629429A (en) * | 2020-12-04 | 2021-04-09 | 哈尔滨工业大学 | Whole-satellite thermal deformation measuring device, system and method in vacuum and variable temperature environment |
| US20220229175A1 (en) * | 2019-05-09 | 2022-07-21 | Robert Bosch Gmbh | Coherent, Multi-Static Radar System, In Particular For Use In A Vehicle |
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| CN109828248A (en) * | 2019-01-08 | 2019-05-31 | 上海卫星工程研究所 | The analysis method that the angular distortion of satellite-borne microwave remote sensing instrument influences visual direction amount |
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| CN111380567A (en) * | 2020-03-24 | 2020-07-07 | 上海卫星工程研究所 | Satellite star sensor pointing in-orbit thermal deformation correction system |
| CN112014135A (en) * | 2020-08-24 | 2020-12-01 | 中国科学院微小卫星创新研究院 | Optical load optical axis thermal deformation detection system and method |
| CN112082496A (en) * | 2020-09-08 | 2020-12-15 | 西安建筑科技大学 | Concrete internal deformation measurement method and system based on improved digital volume image correlation method |
| CN112629429A (en) * | 2020-12-04 | 2021-04-09 | 哈尔滨工业大学 | Whole-satellite thermal deformation measuring device, system and method in vacuum and variable temperature environment |
| CN112629429B (en) * | 2020-12-04 | 2023-02-07 | 哈尔滨工业大学 | Whole-satellite thermal deformation measuring device, system and method in vacuum and variable temperature environment |
| CN112527029A (en) * | 2020-12-07 | 2021-03-19 | 上海卫星工程研究所 | Wireless passive temperature control system applied to satellite thermal control system |
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Application publication date: 20180406 |