CN106091966A - Thermal deformation measurement method under vacuum low-temperature environment - Google Patents
Thermal deformation measurement method under vacuum low-temperature environment Download PDFInfo
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- CN106091966A CN106091966A CN201610380064.8A CN201610380064A CN106091966A CN 106091966 A CN106091966 A CN 106091966A CN 201610380064 A CN201610380064 A CN 201610380064A CN 106091966 A CN106091966 A CN 106091966A
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- test specimen
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- thermal deformation
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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
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T7/00—Image analysis
- G06T7/0002—Inspection of images, e.g. flaw detection
- G06T7/0004—Industrial image inspection
Abstract
The invention discloses a kind of thermal deformation measurement method under vacuum low-temperature environment, main employing test specimen transfixion, the mode measuring camera rotary taking measures, wherein, test specimen is fixedly installed in vacuum environment simulating chamber, photogrammetric camera is spirally connected in the large-scale low-temperature cantilever design being fixed on rotating mechanism, rotating mechanism is fixed on the supporting mechanism centered by test specimen, during measurement, shooting camera is by the way of low temperature cantilever is rotated shooting, test specimen is carried out circumference measurement, then use image processing system that the digital photo of shooting is resolved, thus obtain shape face and deformation data.Method of the invention, it is possible to solve the deformation measurement demand of the spacecraft of current various big size structure, the measurement reproducibility precision of point position in space reaches 20 microns.
Description
Technical field
The invention belongs to spacecraft Light deformation experiment with measuring field under space environmental simulation, be specifically related to a kind of for vacuum
Method to Large Spacecraft structure thermal deformation measurement under low temperature environment.
Background technology
Spacecraft in orbit time, spatial environments is periodicity acute variation, will bring thermal deformation to spacecraft structure, and add
Under upper spacecraft environment in-orbit, gravity release, also can bring Light deformation to spacecraft.This has higher wanting to self structure stability
For the parts asked, this deformation will have influence on its service behaviour, such as antenna, space telescope, solar array etc..
As a example by antenna, will reach high resolution, the area not requiring nothing more than antenna is big, and the surface accuracy of reflecting surface is high,
And require that the shape of antenna surface is little with the deviation of design shape.For reflector antenna, the shape face, surface that deformation causes with
Preferable paraboloidal random deviation will cause the distortion of antenna pattern, produce antenna beam error in pointing, have influence on antenna and receive
The accuracy of photos and sending messages and transmitting power, reduce the reliability of antenna.The surface accuracy of antenna is to weigh and evaluate antenna quality
Important indicator.Typically require that antenna surface precision is the 1/16～1/32 of its operation wavelength, and negligible former by error
Then, the 1/3～1/5 of certainty of measurement surface accuracy to be reached, operation wavelength is the shortest, operating frequency is the highest, wants measuring proposition
Ask the harshest.Accordingly, it would be desirable to by high-precision thermal deformation measurement ground experiment method under space environmental simulation, will be for the palm
Hold the deformation characteristic of antenna, assess its operation on orbit aberrations in property and there is important function, set simultaneously for the improvement of its structure, optimization
Meter also has directive function, and then the development for high accuracy, long-life, high reliability antenna provides technical support.
Along with the development of industrial measurement technique, spacecraft Light deformation measuring method and means have obtained significant progress, mesh
Before can be used in the technology of spacecraft thermal deformation measurement and have: photogrammetry, transit survey method, moire method, laser with
Track measurement method, electronic speckle or holographic interoferometry etc..But owing to vacuum low-temperature environment uses the limit of requirement or visual field etc.
System, carries out the method that spacecraft thermal deformation measurement used under space environmental simulation and only has holographic interferometry and photogrammetric
Method.
Wherein, interferometry is to utilize two-beam interference principle, measures the deformation on test specimen surface.But it is right
Space environment simulation equipment, the position of optical window, the direction of sunlight irradiation and LASER Light Source have strict requirements, to tested
The size of test specimen has size to limit, and is not suitable for measuring large-sized test specimen, and is mainly used in static measurement, and system of measuring is to vibration isolation
Requiring higher, versatility is poor.Photogrammetry is by obtaining more than 2 width of same object in different positions and direction
Digital picture, processes through computer images match etc. and obtains the accurate three-dimensional coordinate of tested point after relevant mathematical calculation, measures
Mode is relatively flexibly, measurement scope is big, it is little to be affected by the external environment, to space environment simulation equipment, optical window, test specimen heating
Means do not have the requirement of harshness.
From the point of view of the successful case of external spacecraft thermal deformation measurement, photogrammetry is space industry application nearly ten years
The method the most extensive, technology is the most ripe, the IABG mechanism in particularly U.S. NASA and Europe utilizes under vacuum low-temperature environment to be taken the photograph
Shadow measurement technology carries out spacecraft thermal deformation measurement and has widely applied.
But domestic being also not set up under reliable vacuum low-temperature environment uses photogrammetric technology to carry out spacecraft large scale
The Light deformation measuring method of structure and pilot system.However as domestic high capacity communications satellite and heavy caliber space telescope etc.
Developing, the bore of antenna reflector and the size of space telescope high stable supporting construction constantly increase, and deformation accuracy requires also
More and more higher, therefore in the urgent need to using antenna deformation under space environmental simulation to measure technology, meet high-precision heavy-caliber antenna
Testing requirement with spacecraft high stable structure.
Summary of the invention
For current various models shape face under vacuum low-temperature environment and deformation measurement demand, the present invention proposes one
Thermal deformation measurement method under vacuum low-temperature environment, i.e. uses binocular stereo vision method based on close-range photogrammetry, passes through
The layout that shooting camera rotates, test specimen is static measures.
Thermal deformation measurement method under vacuum low-temperature environment, the main test specimen transfixion that uses, measurement camera rotary taking
Mode measure, wherein, test specimen is fixedly installed in vacuum environment simulating chamber, and photogrammetric camera is spirally connected and is fixed on rotation
In the large-scale low-temperature cantilever design of mechanism, rotating mechanism is fixed on the supporting mechanism centered by test specimen, during measurement, claps
Camera, by the way of low temperature cantilever is rotated shooting, carries out circumference measurement, then uses image processing system test specimen
The digital photo of shooting is resolved, thus obtains shape face and deformation data.
Wherein, binocular stereo vision method based on close-range photogrammetry, test specimen is carried out circumference shooting.
Wherein, during measurement, photogrammetric camera rotating 360 degrees, every 10 °～20 ° of degree carry out one group of shooting, when often group is measured
Measure camera along optical axis 90-degree rotation, uniform intervals shooting 2～3 sheet photos.
Further, use image processing system based on light-stream adjustment, all of digital photo is carried out at image
Understand calculate, then obtain all measure point D coordinates value (x, y, z), by the space three-dimensional by index points all on test specimen
Coordinate figure and specimen Design model carry out optimization matching, obtain all index points and the deviation designed a model on test specimen, thus
Obtain the thermal deformation result of surface of test piece.
Further, test specimen is provided with some index points for measurement.
Further, test specimen is Large Spacecraft antenna, Large Spacecraft.
Further, photogrammetric camera for be contained in protection cabin in photogrammetric camera.
Method of the invention, it is possible to solve the deformation measurement demand of the spacecraft of current various big size structure, space
The measurement reproducibility precision of some position reaches 20 microns.The design may be used for the large-scale antenna thermal-induced deformation feelings at vacuum low-temperature environment
The measurement of condition, thus obtain the deformation result in shape face, test specimen surface.This measuring method can expand to for various large-scale
Structure position in particular circumstances and deformation measurement, have broad application prospects.
Accompanying drawing explanation
Fig. 1 be the embodiment of the invention vacuum environment under measuring system for thermal deformation schematic diagram.
In figure: 1 vacuum environment simulating chamber, 2 supporting mechanisms, 3 low temperature cantilever mechanisms, 4 photogrammetric CCD camera
And protection cabin, 5 test specimens, 6 test specimen supporting mechanisms, 7 low temperature station meters.
Fig. 2 be the embodiment of the invention vacuum environment under the signal of style of shooting in thermal deformation measurement method
Figure.
Detailed description of the invention
Below in conjunction with the accompanying drawings thermal deformation measurement method under the vacuum environment of the present invention is further described.
See Fig. 1, Fig. 1 and show measuring system for thermal deformation signal under the vacuum environment of the embodiment of the invention
Figure.Wherein, the present invention, to measuring system for thermal deformation under vacuum environment, is fixedly installed tested in being included in vacuum environment simulating chamber 1
Test specimen 5, vacuum simulating chamber e.g. internal diameter is the bedroom container of Φ 10m, can be Large Spacecraft structure under vacuum low-temperature environment
Thering is provided vacuum is 6 × 10-3Pa, ambient temperature is about the deformation measurement environment of-180 DEG C；Gantry supporting mechanism 2 is led by double
Rail is fixed on the testing experiment position of Dewar vessel, and low temperature cantilever mechanism 3 hangs on gantry supporting mechanism 2 across beam by bolt
Center, can realize under vacuum low-temperature environment radius of turn be 3m ± 360 ° of round rotary motions；Photogrammetric CCD camera and
Protection cabin 4 symmetry hangs on low temperature cantilever mechanism 3 two ends, and angles and positions are measured in the shooting being in optimum.Photogrammetric CCD
Camera and protection cabin 4 use electric heater temperature control mode and vacuum seal structure, make photogrammetric CCD camera at vacuum and low temperature ring
Being in room temperature, normal pressure duty under border, the turntable in protection cabin realizes photogrammetric CCD camera and carries out ± 90 ° along primary optical axis
Round rotation.Test specimen 5 is placed in test specimen supporting mechanism 6 and is in low temperature cantilever mechanism center of rotation position, and surface is uniformly glued
Patch vacuum and low temperature retro-reflective target point, as target measurement point；Low temperature station meter 7 uses the devitrified glass of low thermal coefficient of expansion
Processing, have retro-reflective target point at surface mount, the distance between index point carries out Accurate Calibration before the test, as survey
Datum length in amount data solution process, and use the mode of electric heater to carry out temperature control, it is ensured that datum length was being tested
Journey keep constant, it is ensured that photogrammetric CCD camera is in the steady-working state of room temperature, normal pressure during testing experiment.
During measuring, first being provided vacuum low-temperature environment by vacuum environment simulating chamber, test can be at horizontal vessel
Inside carry out.By test specimen fixed placement in container, low temperature retro-reflective target point need to be pasted in test specimen surface.Index point
Uniformly paste in surface of test piece.The orthogonal devitrified glass station meter of fixed placement two in test specimen ambient water plane.
Then will be used for photogrammetric industrial CCD camera to be placed in temperature control protection cabin.Protection cabin is placed on low temperature and hangs
On arm mechanism.After protection cabin has been placed, the shooting angle to CCD camera is needed to carry out preconditioning.Pre-according to test specimen
Shooting image, regulation CCD camera is from vertical height, horizontal range and the shooting angle of test specimen.During regulation, ensure as far as possible
CCD camera when rotary motion to the intersection angle of same measured point in the range of 60 °～120 °, and ensure CCD camera pair as far as possible
The angle of incidence of single index point is less than 60 °.
In test process, low temperature cantilever mechanism drives CCD camera to carry out circumference rotation and interval angles carries out shooting and surveys
Amount.Interval angles about 10 °～20 °, when each interval shooting, CCD camera rotates 0 °～90 ° along camera light direction of principal axis, rotates
During, CCD camera carries out interval shooting 2～3 sheet photo.After low temperature cantilever mechanism drives CCD camera to carry out 360 ° of rotations,
Complete a shot to measure, see thermal deformation measurement method under the vacuum environment that Fig. 2, Fig. 2 are the embodiment of the invention
The schematic diagram of middle style of shooting.
The digital picture real-time Transmission of all shootings is in the image processing software outside vacuum environment simulating chamber, at image
Reason software uses light-stream adjustment to resolve.This calculation method is by by the image coordinates of index point, 3 d space coordinate
With the elements of interior orientation of video camera, elements of exterior orientation as observation, the one of the optimum value of all observations of integrated solution
Resolve settlement method.Firstly, since picture point, image center and impact point three point on a straight line during camera imaging, it is possible to form bag
Collinearity equation containing various observations.Then, camera must in space to the imaging beam of same object point under the difference survey station of space
Intersect at this point, it is possible to connected by same point collinearity condition equation in different survey stations.Finally, all marks are combined
Will point collinearity condition equation in all survey stations, form equation group, using index point in each survey station in space rough position as
Known initial value, application bundle adjustment technology just can solve the accurate three-dimensional coordinate figure of surface of test piece all retro-reflective target point
(x, y, z).
Finally, by the 3 d space coordinate value of index points all on test specimen and specimen Design model are carried out optimization plan
Close, obtain all index points and the deviation value designed a model on test specimen, thus obtain the thermal deformation result of surface of test piece.
Although the detailed description of the invention to the present invention gives detailed description and illustrates above, but it should be noted that
We can carry out various equivalence according to the conception of the present invention to above-mentioned embodiment and change and amendment, and function produced by it is made
With still without departing from description and accompanying drawing contained spiritual time, all should be within protection scope of the present invention.
Claims (7)
1. the thermal deformation measurement method under vacuum low-temperature environment, wherein, the main test specimen transfixion that uses, measurement camera rotates to be clapped
The mode taken the photograph measures；Wherein, test specimen is fixedly installed in vacuum environment simulating chamber, and photogrammetric camera is spirally connected and is fixed on rotation
In the large-scale low-temperature cantilever design of rotation mechanism, rotating mechanism is fixed on the supporting mechanism centered by test specimen, during measurement,
Shooting camera, by the way of low temperature cantilever is rotated shooting, carries out circumference measurement, then uses image procossing system test specimen
The digital photo to shooting of uniting resolves, thus obtains shape face and deformation data.
The most the method for claim 1, wherein binocular stereo vision method based on close-range photogrammetry, enters test specimen
Row circumference shoots.
When the most the method for claim 1, wherein measuring, photogrammetric camera rotating 360 degrees, every 10 °～20 ° spend into
Row one group shooting, often group measures camera along optical axis 90-degree rotation, uniform intervals shooting 2～3 sheet photos when measuring.
The most the method for claim 1, wherein image processing system based on light-stream adjustment is used, to all of number
Word photograph carries out image procossing resolving, then obtain all measure point D coordinates value (x, y, z), by will on test specimen all
The 3 d space coordinate value of index point and specimen Design model carry out optimization matching, obtain all index points and design on test specimen
The deviation of model, thus obtain the thermal deformation result of surface of test piece.
5. the method as described in any one of claim 1-4, wherein, test specimen is provided with some index points for measurement.
6. the method as described in any one of claim 1-4, wherein, test specimen is Large Spacecraft antenna, Large Spacecraft.
7. the method as described in any one of claim 1-4, wherein, photogrammetric camera be contained in protection cabin in photogrammetric
Camera.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106969743A (en) * | 2017-04-17 | 2017-07-21 | 南京工程学院 | Nut-welding deflection infrared detection and method of dissolving |
| CN107153428A (en) * | 2017-06-26 | 2017-09-12 | 西安汾阳钢结构有限公司 | A kind of spacecraft testing tester equipped system |
| CN109883345A (en) * | 2019-03-07 | 2019-06-14 | 北京卫星环境工程研究所 | The space net form strength determining method of parabola antenna vacuum and low temperature deformation measurement |
| CN110595374A (en) * | 2019-09-17 | 2019-12-20 | 中国人民解放军火箭军工程大学 | Large structural part real-time deformation monitoring method based on image transmission machine |
| CN112097667A (en) * | 2020-10-12 | 2020-12-18 | 北京卫星环境工程研究所 | Nanoscale interferometry method for differential pressure deformation measurement |
| CN112945125A (en) * | 2021-03-26 | 2021-06-11 | 中国人民解放军火箭军工程大学 | Non-contact type tire rolling deformation characteristic testing method |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106969743A (en) * | 2017-04-17 | 2017-07-21 | 南京工程学院 | Nut-welding deflection infrared detection and method of dissolving |
| CN107153428A (en) * | 2017-06-26 | 2017-09-12 | 西安汾阳钢结构有限公司 | A kind of spacecraft testing tester equipped system |
| CN109883345A (en) * | 2019-03-07 | 2019-06-14 | 北京卫星环境工程研究所 | The space net form strength determining method of parabola antenna vacuum and low temperature deformation measurement |
| CN110595374A (en) * | 2019-09-17 | 2019-12-20 | 中国人民解放军火箭军工程大学 | Large structural part real-time deformation monitoring method based on image transmission machine |
| CN110595374B (en) * | 2019-09-17 | 2020-05-05 | 中国人民解放军火箭军工程大学 | Large structural part real-time deformation monitoring method based on image transmission machine |
| CN112097667A (en) * | 2020-10-12 | 2020-12-18 | 北京卫星环境工程研究所 | Nanoscale interferometry method for differential pressure deformation measurement |
| CN112945125A (en) * | 2021-03-26 | 2021-06-11 | 中国人民解放军火箭军工程大学 | Non-contact type tire rolling deformation characteristic testing method |
| CN112945125B (en) * | 2021-03-26 | 2023-08-11 | 中国人民解放军火箭军工程大学 | Non-contact tire rolling deformation characteristic test method |
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