CN106679695A - Method for testing thermal deformation of focal plane based on star sensor - Google Patents
Method for testing thermal deformation of focal plane based on star sensor Download PDFInfo
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- CN106679695A CN106679695A CN201710018555.2A CN201710018555A CN106679695A CN 106679695 A CN106679695 A CN 106679695A CN 201710018555 A CN201710018555 A CN 201710018555A CN 106679695 A CN106679695 A CN 106679695A
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- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C25/00—Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
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Abstract
The invention discloses a method for testing the thermal deformation of a focal plane based on a star sensor. The method comprises the following steps: S1, installing a static light star simulator on a star sensor, and putting the static light star simulator and the star sensor in a vacuum tank; and S2, applying temperature change excitation to the focal plane of the star sensor, and collecting posture measurement curves output by the star sensor to obtain the error of thermal deformation of the focal plane for posture output.
Description
Technical field
The present invention be more particularly directed to a kind of method of testing of the focal plane thermal deformation based on star sensor.
Background technology
With the fast development of China's aerospace industry, the development demand of high-resolution earth observation satellite is increasingly urgent, its
The accurate measurement of attitude uses star sensor, and thus star sensor is the vitals of current spacecraft attitude measurement.Will
Realize that high-precision attitude is measured it is necessary to carry out control to its links.Star sensor generally by optics and precision structure system,
The part of photodetector and signal processing circuit and software etc. three constitutes.During in orbit, spatial environmentss are severe, can run into each
Plant complicated temperature case, therefore the especially heat stability of test Photodetection system.Based on star sensor technology, photodetection
Device shoots the image that the optical axis points to starry sky, and image extracts the position of punctate opacity of the cornea and monochrome information, passes through through signal processing circuit
Star Pattern Recognition Algorithm finds the Corresponding matching of observation star in navigation star database, using the direction vector information meter of these matching stars pair
Star sensor three-axis attitude information is calculated, so that it is determined that the spatial attitude of spacecraft.
Accurate three-axis attitude information be unable to do without the basic guarantee of photodetector obtained by star sensor.Photodetector
Be placed in the position of focal plane of optical system, for shoot the optical axis sensing starry sky image, be able to determine punctate opacity of the cornea accurate location (including
X-direction coordinate, Y-direction coordinate, punctate opacity of the cornea half-tone information etc.), it is mainly used in being accurately positioned for star place.From in-orbit flying quality
Visible with ground thermal vacuum test, the attitude angle precision that the change of ambient temperature is exported to star sensor is fixing with one
Ring, it can thus be appreciated that there is deformation during temperature change in photodetector, so that the two-dimensional plane coordinate of punctate opacity of the cornea becomes
It is dynamic, error is introduced in punctate opacity of the cornea barycenter solution process, the attitude transfer matrix for being solved and the attitude accuracy that finally exported are also
Bring deviation into.It is therefore desirable to impact of the analysis focal plane cause of deformation to Attitude Calculation precision, is to obtain high-precision attitude
Basic foundation is provided.
At present, the field tests based on focal plane thermal deformation also belong to blank, not yet refer to the test and research of this aspect.This
Invention gives a kind of method of testing of star sensor focal plane thermal deformation, for focal plane thermal deformation to star sensor attitude essence
The impact of degree carries out succinct effectively test.
The content of the invention
It is an object of the invention to provide a kind of method of testing of the focal plane thermal deformation based on star sensor, measurement star sensitivity
The variable quantity of the attitude measurement accuracy curve that device is exported under cycle change excitation warm in nature, and then be to correct due to detector deformation band
The measurement error come provides theoretical foundation and actual reference.
In order to realize object above, the present invention is achieved by the following technical solutions：
A kind of method of testing of the focal plane thermal deformation based on star sensor, is characterized in, comprises the steps of：
S1, static light star simulator is arranged on star sensor, and by static light star simulator and star sensor together
In being placed in vacuum tank；
S2, to the focal plane of star sensor temperature change excitation is applied, and gathers the attitude measurement song that star sensor is exported
Line, draws focal plane thermal deformation to attitude output error.
Star sensor fixes static light star simulator by adaptation ring in described step S1, when the temperature is changed, described
Deformation of the deformation of the focal plane of star sensor higher than adaptation ring and static light star simulator.
Described static light star simulator simulation generates width static state star chart in day area, and star sensor is clapped quasistatic star chart
Take the photograph, data handling system can calculate right ascension, the declination in the static star chart place day area.
Needed to deduct due to environment temperature before drawing focal plane thermal deformation to attitude output error in described step S2
Star sensor optical axis point to variation tendency item caused by degree change.
Described show that focal plane thermal deformation is specifically included to attitude output error：
Take the temperature fluctuation in period of waves, right ascension to fluctuate and declination fluctuation data；
Right ascension angle maximum period of waves and declination angle maximum period of waves are calculated, and draws focal plane thermal deformation to appearance
State output error.
The present invention compared with prior art, with advantages below：
The present invention is by measurement star sensor in the cycle change for becoming the attitude measurement accuracy curve exported under excitation warm in nature
Amount, and then for amendment because the measurement error that detector deformation band comes provides theoretical foundation and actual reference.
Description of the drawings
Fig. 1 is a kind of structure chart of the test system of the focal plane thermal deformation based on star sensor of the present invention；
Fig. 2 is a kind of method of testing flow chart of the focal plane thermal deformation based on star sensor of the present invention；
Optical axis is pointed to and temperature variation curve when Fig. 3 is star sensor thermal vacuum test；
Optical axis is pointed to and temperature variation curve (deduction trend term) when Fig. 4 is star sensor thermal vacuum test.
Specific embodiment
Below in conjunction with accompanying drawing, by describing a preferably specific embodiment in detail, the present invention is further elaborated.
Apply temperature change to star sensor in vacuum tank to encourage, detector image planes produce deformation, punctate opacity of the cornea positional information
Change, so as to the attitude curve for being exported produces change.Specifically being calculated as follows for the variable quantity is described.
It is to describe punctate opacity of the cornea in the position in space, by detector if the position coordinateses that detector makes real survey punctate opacity of the cornea are (x, y)
Photo coordinate system conversion imaging space coordinates, light of the zero in the photocentre position of star sensor, z-axis and star sensor
The sides aligned parallel of overlapping of axles, x, y and detector face, position of the punctate opacity of the cornea under star sensor body coordinate system is [x y z] t.Star
Point is intersection point of the focal length on detector target surface, and (x ', y ') is the punctate opacity of the cornea barycenter after distortion correction, is understood by calibration result.
Therefore coordinate of the starlight direction vector under star sensor body coordinate system such as formula (1)：
F is star sensor focal length in formula.Based on coordinate such as formula of the J2000.0 coordinate systems correspondence under celestial coordinate system
(2), then coordinate of the starlight direction vector under celestial coordinate system is：
W=T (3)
T is attitude transfer matrix.By Quest algorithms, you can obtain the Attitude Calculation result that star sensor claps star chart.
If punctate opacity of the cornea positional information becomes and turns to caused by now photodetector deformation (Δ x, Δ y), then actual observation star vector with it is preferable
Star vector there is deviation, as shown from the above formula, the Attitude Calculation result for being exported also changes therewith, thus focal plane heat become
The measurement attitude that shape is exported to star sensor introduces error.
Intercepting -50 DEG C of low temperature keeps data segment to enter the change excitation of row detector temperature.The control during -50 DEG C of low temperature keep is caused
Cooler observes the change that star sensor exports attitude curve to uniform temperature.Open the data graphs after refrigerator, then with its it
It is that focal plane produces shadow of the deformation to punctate opacity of the cornea change in location because cycle temperature becomes excitation that the data and curves of front preservation carry out contrasting
Ring.The data taken in the period of waves are estimated, so as to obtain the measurement error that focal plane component thermal deformation is caused.
For this purpose, as shown in Figure 1, 2, the invention provides a kind of test side of the focal plane thermal deformation based on star sensor
Method, comprises the steps of：
S1, static light star simulator 1 is arranged on star sensor 2, and by static light star simulator 1 and star sensor 2
In being together placed in vacuum tank 3；Wherein star sensor is connected with data handling system 4.It is quick star to be enclosed within using light-weighted adaptation ring
On sensor shade, the static photostar mould simulator for matching is laid thereon.In the present embodiment, the star sensor of employing and quiet
Impact of the state photostar mould simulator using the method treatment temperature of athermalisation to the image quality of product, i.e., by certain
Compensation technique, makes optical system keep focal length constant under a larger temperature changing environment or changes small.Avoid due to the temperature difference
The tremendous influence that the precision of Space Optical System is brought into.
Start evacuation in S2, vacuum tank, be allowed to vacuum and be maintained at 1.3 × 103Pa, then starts heating and cooling to ± 50
DEG C circulation, refrigerator applies temperature change excitation to the focal plane of star sensor, gathers the attitude measurement that star sensor is exported
Curve, draws focal plane thermal deformation to attitude output error.
Above-mentioned static light star simulator simulation generates width static state star chart in day area, and star sensor is clapped quasistatic star chart
Taking the photograph data handling system can calculate right ascension, the declination in the star chart place day area.
Star sensor fixes static light star simulator by adaptation ring in above-mentioned step S1, when the temperature is changed, described
Deformation of the deformation of the focal plane of star sensor higher than adaptation ring and static light star simulator.
Needed to deduct due to environment temperature before drawing focal plane thermal deformation to attitude output error in above-mentioned step S2
Star sensor optical axis point to variation tendency item caused by degree change, and the trend term is obtained by the fitting of 7 rank multinomials, such as Fig. 3.Button
Except rear right ascension, declination fluctuation only to refrigerator apply temperature become excitation it is related, it is possible thereby to examine focal plane temperature deformation to draw
The measurement error for entering.
Above-mentioned show that focal plane thermal deformation is specifically included to attitude output error：
Temperature fluctuation curve, attitude (the right ascension, declination) curve of cyclical fluctuations can be drawn by data handling system, period of waves is taken
Interior temperature fluctuation, right ascension fluctuation and declination fluctuation data；
By data handling system deduct trend term after gained attitude curve such as Fig. 4, take right ascension angle maximum period of waves and
Declination angle maximum period of waves, can draw focal plane thermal deformation to attitude output error, if right ascension angle maximum period of waves
For a, declination angle maximum period of waves is b, and optical axis drift value can be estimated as caused by the temperature change of focal planeTemperature variation is N DEG C, then the measurement error that focal plane thermal deformation is caused is about M/N (arcsec/
℃)。
In sum, a kind of method of testing of the focal plane thermal deformation based on star sensor of the present invention, measures star sensor
In the cycle variable quantity for becoming the attitude measurement accuracy curve exported under excitation warm in nature, and then for amendment because detector deformation band comes
Measurement error theoretical foundation and actual reference are provided.
Although present disclosure has been made to be discussed in detail by above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read the above, for the present invention's
Various modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (5)
1. a kind of method of testing of the focal plane thermal deformation based on star sensor, it is characterised in that comprise the steps of：
S1, static light star simulator is arranged on star sensor, and static light star simulator and star sensor are together placed in
In vacuum tank；
S2, to the focal plane of star sensor temperature change excitation is applied, and gathers the attitude measurement curve that star sensor is exported, and is obtained
Go out focal plane thermal deformation to attitude output error.
2. the method for testing of the focal plane thermal deformation of star sensor is based on as claimed in claim 1, it is characterised in that described
Star sensor fixes static light star simulator by adaptation ring in step S1, and when the temperature is changed, Jiao of the star sensor puts down
Deformation of the deformation in face higher than adaptation ring and static light star simulator.
3. the method for testing of the focal plane thermal deformation of star sensor, described static photostar mould are based on as claimed in claim 1
Intend device simulation and generate width static state star chart in day area, star sensor shoots to quasistatic star chart, and data handling system can be calculated
Right ascension, the declination in the static star chart place day area.
4. the method for testing of the focal plane thermal deformation of star sensor is based on as claimed in claim 1, it is characterised in that described
Star caused by needing to deduct due to variation of ambient temperature before drawing focal plane thermal deformation to attitude output error in step S2
Sensor optical axis points to variation tendency item.
5. the method for testing of the focal plane thermal deformation of star sensor is based on as claimed in claim 4, it is characterised in that described
Show that focal plane thermal deformation is specifically included to attitude output error：
Take the temperature fluctuation in period of waves, right ascension to fluctuate and declination fluctuation data；
Right ascension angle maximum period of waves and declination angle maximum period of waves are calculated, and show that focal plane thermal deformation is defeated to attitude
Go out error.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108663137A (en) * | 2018-05-15 | 2018-10-16 | 北京控制工程研究所 | A kind of star sensor temperature field measurement and it is directed toward temperature drift compensation method |
| CN108759868A (en) * | 2018-06-20 | 2018-11-06 | 上海卫星工程研究所 | The antenna of the quick integral type mounting structure of satellite load star is directed toward thermal deformation measurement method |
| CN109141472A (en) * | 2018-08-13 | 2019-01-04 | 上海航天控制技术研究所 | For assessing the sight star test device and method of star sensor thermal stability |
| CN111323210A (en) * | 2020-03-17 | 2020-06-23 | 北京控制工程研究所 | Device and method for testing optical axis thermal stability of optical lens |
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| CN102354123A (en) * | 2011-07-18 | 2012-02-15 | 北京航空航天大学 | Cross-platform extendible satellite dynamic simulation test system |
| CN102564458A (en) * | 2011-12-29 | 2012-07-11 | 北京控制工程研究所 | Low-frequency error measuring method for star sensor |
| CN204514279U (en) * | 2015-03-24 | 2015-07-29 | 中国科学院上海技术物理研究所 | A kind of device measuring infrared focus plane module low temperature deformation |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108663137A (en) * | 2018-05-15 | 2018-10-16 | 北京控制工程研究所 | A kind of star sensor temperature field measurement and it is directed toward temperature drift compensation method |
| CN108663137B (en) * | 2018-05-15 | 2019-12-20 | 北京控制工程研究所 | Star sensor temperature field measurement and pointing temperature drift compensation method |
| CN108759868A (en) * | 2018-06-20 | 2018-11-06 | 上海卫星工程研究所 | The antenna of the quick integral type mounting structure of satellite load star is directed toward thermal deformation measurement method |
| CN109141472A (en) * | 2018-08-13 | 2019-01-04 | 上海航天控制技术研究所 | For assessing the sight star test device and method of star sensor thermal stability |
| CN109141472B (en) * | 2018-08-13 | 2020-08-28 | 上海航天控制技术研究所 | Star observation testing device and method for evaluating thermal stability of star sensor |
| CN111323210A (en) * | 2020-03-17 | 2020-06-23 | 北京控制工程研究所 | Device and method for testing optical axis thermal stability of optical lens |
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