CN109975832A - The description method of satellite-borne microwave remote sensing instrument malformation - Google Patents
The description method of satellite-borne microwave remote sensing instrument malformation Download PDFInfo
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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
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/03—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers
- G01S19/07—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing data for correcting measured positioning data, e.g. DGPS [differential GPS] or ionosphere corrections
Abstract
The present invention relates to the description methods of the satellite-borne microwave remote sensing instrument malformation of remote sensing instrument modeling method technical field, comprising the following steps: step 1 defines the connected coordinate system of each stand-alone assembly in instrument.Step 2 defines the rotational deformation parameter and displacement deformation parameter of each reflecting surface and feed.Step 3 calculates the Conversion Matrix of Coordinate between adjacent optical path component from feed according to optical path component rotational deformation parameter and displacement deformation parameter.Conversion Matrix of Coordinate is substituted into optical path model by step 4.The description method of satellite-borne microwave remote sensing instrument malformation of the invention, least deformation parameter can be used, the malformation for describing the satellite-borne microwave remote sensing instrument containing multiple assemblies such as plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflectings surface, facilitating subsequent satellite-borne microwave remote sensing instrument, there are the optical path modelings under structural deformation conditions.
Description
Technical field
The present invention relates to remote sensing instrument modeling method technical fields, and in particular to a kind of satellite-borne microwave remote sensing instrument structure change
The description method of shape.
Background technique
The building of the tight imaging geometry model of satellite is the core of the geometric correction scheme based on remote sensing instrument imaging model.
There are long periods and variation of short period for satellite platform posture, orbital position and thermal environment, mechanical environment, so that instrument sight deviates
Nominal direction causes image pixel and the corresponding relationship in geographical location to generate deviation.
The posture of satellite platform, Orbit revolutionary can accurately measure post-compensation or correction, and thermal environment, mechanical environment etc. because
The in-orbit deformation mechanism of satellite platform caused by element, instrument is complicated, it is difficult to the deformation of each component of direct precise measurement, and different groups
Influence of the part deformation to image is different, therefore remote sensing satellite manufacturer, various countries is directed to the optical path characteristic design of remote sensing instrument
Corresponding framing registration and compensation scheme, it is Russian including the emitted GOES series of satellites for having the U.S. entered the orbit
Electro-L, Japanese Himawari-8, European third generation meteorological satellite MTG, the satellites such as the resource three in China, FY-4.
But geometric correction scheme of the above-mentioned satellite based on remote sensing instrument imaging model is not suitable for for its optical remote sensing instrument
Microwave remote sensing instrument.
The stationary orbit microwave remote sensing satellite for the deployment that takes the lead in is the important composition of global following weather forecast system by China
Part, wherein Microwave sounder is main load.Since stationary orbit microwave sounding frequency range is extended to high frequency, to meet spatial discrimination
Rate requirement, antenna reflective face bore are much larger than conventional aerial bore, are limited to rocket radome fairing size, need to play antenna folds
Come, reinflated deployment after entering the orbit.The angles and positions that expansion movement may cause each reflecting surface deviate nominal value.Secondly, satellite
When in orbit, the flexible vibration of unfolding mechanism causes the angles and positions of reflecting surface to deviate nominal value.With Optical remote satellite
Unlike, microwave remote sensing antenna has plane reflection face and curved-surface reflection side concurrently.It is anti-that the displacement in plane reflection face does not change optical path
Direction is penetrated, therefore optical remote sensing star does not need to model reflecting surface displacement error.And curved-surface reflection side displacement directly results in optical path
Direction change, and then change earth observation visual direction amount and be directed toward, therefore in the modeling of microwave remote sensing satellite optical path, can not ignore reflection
Face displacement error.Finally, microwave remote sensing satellite reflection face is more compared to Optical remote satellite, visual direction amount need by
Just enter imaging system after multipath reflection.
To sum up various factors is it is found that currently consider the geometric correction based on the tight imaging model of remote sensing instrument of instrument deformation
Scheme applicable object is mostly optical remote sensing instrument.And microwave remote sensing instrument is more complicated than the modeling of the optical path of optical remote sensing instrument,
With certain particularity.For the high-precision geometric correction for realizing microwave remote sensing image, the knot for microwave remote sensing instrument is needed first
Structure characteristic establishes instrument, and there are the optical path models under deformation, and the description method of instrument deformation is one of the optical path model
Pith.
Through the retrieval to the prior art, and NOAA research report that J.L.Fiorello et al. writes (0989, number N90-
13422) image-guidance positioning concept and principle are described, proposes and fixed star acquisition instrument deformation parameter is observed by optical instrument
Method, but this method is not suitable for microwave remote sensing instrument.
The Ph.D. Dissertation " stationary weather satellite imaging based navigation Study of Registration " (2017) of Lv Wang is with No. four spokes of wind and cloud
Imager is penetrated as research object, has carried out image-guidance Study of Registration.For the remote sensing as caused by the factors such as thermal environment, stress
The in-orbit problem on deformation of instrument proposes dual model modeling method.Influence with physical model detailed description mechanically deform to visual direction amount,
Use equivalent model as backoff algorithm.But this method is only effective to the optical remote sensing instrument with horizontal scanning mirror catoptric imaging.
A kind of patent of invention " tight imaging geometry model construction side of Optical remote satellite of 104764443 A of patent No. CN
Method " describe a kind of tight imaging geometry model using Satellite Camera internal and external orientation building Optical remote satellite image
Method.But this method is not suitable for microwave remote sensing instrument.
Opened, Zhu Yanmin, Fei Wenbo, Li Deren " mapping notification " fifth phase (2009) article " High Resolution SAR-
The tight imaging geometry model of GEC image and its application study " in, propose the building tight imaging geometry of SAR image GEC product
The method of model.But this process simplify the modelings of instrument internal distortion, are unable to fully description scan-type microwave imaging instrument
Deformation.
Therefore, it is necessary to which optical path model can be established by the architectural characteristic to microwave remote sensing instrument, realized by designing one kind
The high-precision geometric correction of microwave remote sensing image, facilitating subsequent satellite-borne microwave remote sensing instrument, there are under structural deformation conditions
The description method of the satellite-borne microwave remote sensing instrument malformation of optical path modeling.
Summary of the invention
In view of the drawbacks of the prior art, the object of the present invention is to provide the description sides of satellite-borne microwave remote sensing instrument malformation
Method, the present invention can be established optical path model by the architectural characteristic to microwave remote sensing instrument, realize the high-precision of microwave remote sensing image
Spend geometric correction, and facilitate subsequent satellite-borne microwave remote sensing instrument there are under structural deformation conditions optical path modeling.
The present invention relates to the description methods of satellite-borne microwave remote sensing instrument malformation, by the stand-alone assembly of microwave remote sensing instrument
It is divided into plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflecting surface and feed totally four class stand-alone assembly, using rotation
Transformation shape parameter and displacement deformation parameter describe component strain, are become according to rotational deformation parameter and displacement deformation parameter building component
Coordinate conversion matrix after shape realizes that sight state vector is connected between coordinate system in neighboring reflection face by coordinate conversion matrix
Conversion.
Further, plane reflection face is described using rotational deformation parameter and displacement deformation parameter, the paraboloid of revolution reflects
The deformation of the components such as face, hyperboloid of revolution reflecting surface.
Further, the plane reflection face rotational deformation parameter and displacement deformation parameter, including and only include that plane is anti-
Penetrate face around plane reflection face be connected coordinate system X-axis rotation angle, around the rotation angle of Y-axis, and along the displacement of Z axis.
Further, the rotational deformation parameter and displacement deformation parameter of the paraboloid of revolution reflecting surface, including and only wrap
Include paraboloid of revolution reflecting surface around paraboloid of revolution reflecting surface be connected coordinate system X-axis rotation angle, around the rotation angle of Y-axis, and along X
The displacement of axis, the displacement along Y-axis, the displacement along Z axis.
Further, the rotational deformation parameter and displacement deformation parameter of the hyperboloid of revolution reflecting surface, including and only wrap
Include hyperboloid of revolution reflecting surface around hyperboloid of revolution reflecting surface be connected coordinate system X-axis rotation angle, around the rotation angle of Y-axis, and along X
The displacement of axis, the displacement along Y-axis, the displacement along Z axis.
Further, the connected coordinate origin in plane reflection face is taken as reflecting surface geometric center, and z-axis is plane positive normal, x
Axis is planar directed toward a characteristic direction, and y-axis is determined by the right-hand rule；
The connected coordinate origin of paraboloid of revolution reflecting surface is the inflection point of paraboloid of revolution reflecting surface, z-axis and rotary parabolic
Reflecting surface symmetrical overlapping of axles in face are directed toward paraboloid of revolution inflection point positive normal direction, and the vertical z-axis of x-axis is directed toward paraboloid of revolution reflecting surface
One characteristic direction, y-axis are determined by the right-hand rule；
The connected coordinate origin of hyperboloid of revolution reflecting surface is the inflection point of hyperboloid of revolution reflecting surface, z-axis and rotation hyperbolic
The symmetrical overlapping of axles of face reflecting surface are directed toward hyperboloid of revolution reflecting surface inflection point positive normal direction, and the vertical z-axis of x-axis is directed toward rotation hyperbolic
Face reflecting surface characteristic direction, y-axis are determined by the right-hand rule；
The connected coordinate origin of feed is taken as feed entrance geometric center, and the vertical feed plane of inlet of z-axis is directed toward outside feed
Side, the vertical z-axis of x-axis are directed toward one characteristic direction of feed plane of inlet, and y-axis is determined by the right-hand rule.
Further, sight state vector X is 7 dimensional vectors, by sight reflecting surface landing point coordinates [x, y, z]T, sight
Direction unit vector [u, v, w]TIt is constituted with 1:
X=[x y z u v w 1]T。
Further, according to the path order of sight transmission and reflection, sight state vector is realized by coordinate conversion matrix
Conversion between the connected coordinate system in neighboring reflection face:
Xb=TbaXa, XaProjection for premultiplication sight state vector X in a coordinate system, XbIt is sat for sight state vector X in b
Mark the projection of system, TbaCoordinate conversion matrix of the coordinate system to b coordinate system.
Further, the coordinate conversion matrix after component strain has following form:
It is describedIt indicates under nominal state, direction cosine matrix of a coordinate system to b coordinate system, RaIndicate the rotation of a component
Direction cosine matrix, the R of deformationbIndicate the direction cosine matrix of b component rotational deformation,It indicates under no deformation, a system is former
Point A is in the projection of b system, and △ A respectively indicates a coordinate system displacement deformation parameter, △ B indicates the displacement deformation parameter of b coordinate system.
The description method of satellite-borne microwave remote sensing instrument malformation of the invention, comprising the following steps:
Step 1, the independent optical paths component in satellite-borne microwave remote sensing instrument is divided into plane reflection face, the paraboloid of revolution reflects
Face, hyperboloid of revolution reflecting surface and feed totally four seed type；According to the type of stand-alone assembly, definition is connected flat with stand-alone assembly
Face reflecting surface be connected coordinate system, paraboloid of revolution reflecting surface be connected coordinate system, hyperboloid of revolution reflecting surface be connected coordinate system, rotation
The connected coordinate system of shafting and the connected coordinate system of feed；
Step 2, the rotational deformation parameter in plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflecting surface is defined
With displacement deformation parameter；
Step 3, from feed, adjacent optical path portion is calculated according to light path part rotational deformation parameter and displacement deformation parameter
Conversion Matrix of Coordinate between part；
Step 4, coordinate conversion matrix is substituted into optical path model.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the description method of satellite-borne microwave remote sensing instrument malformation of the invention can use least deformation parameter, retouch
State the satellite-borne microwave remote sensing instrument containing multiple assemblies such as plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflectings surface
The deformation of the structure of device, facilitating subsequent satellite-borne microwave remote sensing instrument, there are the optical path modelings under structural deformation conditions；
2, the description method of satellite-borne microwave remote sensing instrument malformation of the invention, can be by microwave remote sensing instrument
The high-precision geometric correction that architectural characteristic establishes optical path model, realizes microwave remote sensing image；
3, the description method of satellite-borne microwave remote sensing instrument malformation of the invention, is conducive to remote sensing instrument imaging model
Geometric correction facilitates the building of the tight imaging geometry model of satellite, even if satellite platform posture, orbital position and thermal environment,
There are long periods and variation of short period for mechanical environment, and instrument sight will not be made to deviate nominal direction, not will lead to image slices
Element and the corresponding relationship in geographical location generate deviation.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon.
Fig. 1 is the flow chart of the description method of satellite-borne microwave remote sensing instrument malformation of the invention；
Fig. 2 is feed of the invention and outgoing beam schematic diagram；
Fig. 3 is that plane reflection face optical path of the invention models schematic diagram；
Fig. 4 is that hyperboloid of revolution reflecting surface optical path of the invention models schematic diagram；
Fig. 5 is that paraboloid of revolution reflecting surface optical path of the invention models schematic diagram；
Fig. 6 is light path schematic diagram inside certain satellite-borne microwave remote sensing instrument.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
Embodiment
In the present embodiment, the description method of satellite-borne microwave remote sensing instrument malformation of the invention, by microwave remote sensing instrument
Stand-alone assembly be divided into plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflecting surface and feed totally four class independence group
Part describes component strain using rotational deformation parameter and displacement deformation parameter, according to rotational deformation parameter and displacement deformation parameter
Coordinate conversion matrix after constructing component strain realizes that sight state vector is connected in neighboring reflection face by coordinate conversion matrix
Conversion between coordinate system.
Next the present invention is described in detail.
The object of the present invention is to provide the description method of satellite-borne microwave remote sensing instrument malformation, the present invention can be by right
The architectural characteristic of microwave remote sensing instrument establishes optical path model, realizes the high-precision geometric correction of microwave remote sensing image, and helps
In subsequent satellite-borne microwave remote sensing instrument, there are the optical path modelings under structural deformation conditions.
As shown in Figures 1 to 6, the description side of the satellite-borne microwave remote sensing instrument malformation of a preferred embodiment of the present invention
Method, comprising the following steps:
It step 1, is plane reflection face, rotary parabolic by the independent optical paths component clustering in stationary orbit microwave remote sensing instrument
Face reflecting surface, hyperboloid of revolution reflecting surface, rotary axis and feed totally five seed type；According to the type of stand-alone assembly, definition with
The connected coordinate system in the connected plane reflection face of stand-alone assembly, paraboloid of revolution reflecting surface are connected coordinate system, the hyperboloid of revolution reflect
Face be connected coordinate system and the feed of coordinate system, rotary axis that be connected is connected coordinate system.
The connected coordinate system for defining each component is as follows:
Feed entrance is connected coordinate system (subscript a, coordinate origin are denoted as A): origin A is taken as feed entrance geometric center, Za
Axis is taken as the outer normal direction of feed entrance, and Xa axis vertical Z a is directed toward feed characteristic direction, and Ya is determined by the right-hand rule；
Mirror is swept fastly first is that plane reflection face, sweep mirror one fastly and be connected coordinate system (subscript b, coordinate origin are denoted as B): origin B takes
To sweep mirror geometric center fastly, Zb axis is taken as sweeping mirror positive normal fastly, and Xb axis vertical Z b axis is directed toward certain characteristic direction, and Yb axis is by the right hand
Rule determines；
Mirror is swept fastly but plane reflection face, sweep mirror two fastly and be connected coordinate system (subscript c, coordinate origin are denoted as C): origin C takes
To sweep mirror geometric center fastly, Zc axis is taken as sweeping two positive normal of mirror fastly, and Xc axis vertical Z c-axis is directed toward certain characteristic direction, and Yc axis is by the right side
Hand rule determines；；
Counter second pair is plane reflection face, and second secondary anti-connected coordinate system (subscript d, coordinate origin are denoted as D): origin D takes
For the second secondary anti-geometric center, Zd axis is taken as the second secondary normal direction anyway, and Xd axis vertical Z d axis is directed toward certain characteristic direction, Yd axis by
The right-hand rule determines；
Counter first pair is hyperboloid of revolution reflecting surface, first secondary anti-connected coordinate system (subscript e, coordinate origin are denoted as E): former
Point E is taken as the first secondary anti-inflection point, and Ze axis is taken as and the first secondary antisymmetry overlapping of axles, the outer normal orientation of direction, Xe axis vertical Z d axis
It is directed toward certain characteristic direction, Ye axis is determined by the right-hand rule；；
Anti- master is that paraboloid of revolution reflecting surface master is instead connected coordinate system (subscript f, coordinate origin are denoted as F): origin F is taken as leading
Anti- inflection point, Zf axis are taken as being directed toward certain characteristic direction, Yf with main antisymmetry overlapping of axles, direction main anti-outer normal direction, Xf axis vertical Z f axis
Axis is determined by the right-hand rule；
Step 2, define plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflecting surface rotational deformation parameter and
Displacement deformation parameter.
Mirror is swept fastly first is that plane reflection face, is nominally swept the coordinate system that is connected of mirror one fastly and according to XY is turned sequence rotation Eulerian angles
Then z is translated along postrotational connected coordinate system Zb axisb, obtain reality and sweep mirror one fastly being connected coordinate system.Then mirror is swept fastly before deformation
Mirror one is swept after one connected coordinate system to deformation fastly to be connected the direction cosine matrix of coordinate system
Mirror is swept fastly second is that plane reflection face, is nominally swept the coordinate system that is connected of mirror two fastly and according to XY is turned sequence rotation Eulerian angles
Then z is translated along postrotational connected coordinate system Zc axisc, obtain reality and sweep mirror two fastly being connected coordinate system.Then mirror is swept fastly before deformation
Mirror two is swept after two connected coordinate systems to deformation fastly to be connected the direction cosine matrix of coordinate system
Counter second pair is plane reflection face, and the nominal second secondary anti-connected coordinate system turns sequence rotation Eulerian angles according to XY
Then z is translated along postrotational connected coordinate system Zdd, obtain the practical second secondary anti-connected coordinate system.It is secondary anti-then to deform preceding second
Penetrate the direction cosine matrix of the connected coordinate system in face connected coordinate system of the second subreflector to after deforming
Counter first pair is hyperboloid of revolution reflecting surface, and the nominal first secondary anti-connected coordinate system turns sequence rotation Eulerian angles according to XYThen x is translated along postrotational connected coordinate systeme,ye,ze, obtain the practical first secondary anti-connected coordinate system.Before then deforming
The direction cosine matrix of the connected coordinate system of first subreflector after the connected coordinate system to deformation of first subreflector
Primary reflection surface is paraboloid of revolution reflecting surface, and nominal main anti-connected coordinate system turns sequence rotation Eulerian angles according to XYThen x is translated along postrotational connected coordinate systemf,yf,zf, obtain the practical first secondary anti-connected coordinate system.Before then deforming
The direction cosine matrix of the connected coordinate system of primary reflection surface after the connected coordinate system to deformation of primary reflection surface
Step 3, from feed, consider light path part rotational deformation parameter and displacement deformation parameter, calculate adjacent optical path
Conversion Matrix of Coordinate between component.
It is connected the coordinate conversion matrix of coordinate system b from the feed coordinate system a that is connected to sweeping mirror one fastly:
It is connected the coordinate conversion matrix of coordinate system from the coordinate system that is connected of mirror one is swept fastly to sweeping mirror two fastly:
From sweep fastly mirror two be connected coordinate system to the second subreflector be connected coordinate system coordinate conversion matrix:
From the second secondary anti-connected coordinate system to the coordinate conversion matrix to the connected coordinate system of the first subreflector:
Be connected the coordinate conversion matrix of coordinate system from the first secondary anti-connected coordinate system to primary reflection surface:
Step 4, finally above-mentioned coordinate is converted and lifts matrix substitution optical path model.
In conclusion the description method of satellite-borne microwave remote sensing instrument malformation of the invention, can use least deformation
Parameter describes the satellite-borne microwave containing multiple assemblies such as plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflectings surface
The deformation of the structure of remote sensing instrument, facilitating subsequent satellite-borne microwave remote sensing instrument, there are the optical paths under structural deformation conditions to build
Mould；The high-precision geometry that optical path model can be established by the architectural characteristic to microwave remote sensing instrument, realize microwave remote sensing image
Correction；The geometric correction for being conducive to remote sensing instrument imaging model facilitates the building of the tight imaging geometry model of satellite, even if defending
There are long periods and variation of short period for star platform stance, orbital position and thermal environment, mechanical environment, will not make instrument sight
Deviate nominal direction, the corresponding relationship that not will lead to image pixel and geographical location generates deviation.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of description method of satellite-borne microwave remote sensing instrument malformation, which is characterized in that by the independence of microwave remote sensing instrument
Component is divided into plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflecting surface and feed totally four class stand-alone assembly, adopts
Component strain is described with rotational deformation parameter and displacement deformation parameter, according to rotational deformation parameter and displacement deformation parameter building group
The deformed coordinate conversion matrix of part realizes sight state vector in the connected coordinate system in neighboring reflection face by coordinate conversion matrix
Between conversion.
2. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 1, which is characterized in that using rotation
Transformation shape parameter and displacement deformation parameter describe plane reflection face, paraboloid of revolution reflecting surface, hyperboloid of revolution reflecting surface component
Deformation.
3. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 2, which is characterized in that described flat
Face reflecting surface rotational deformation parameter and displacement deformation parameter, including and only include plane reflection face around the connected coordinate in plane reflection face
Rotation angle, the rotation angle around Y-axis for being X-axis, and the displacement along Z axis.
4. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 3, which is characterized in that the rotation
Turn the rotational deformation parameter and displacement deformation parameter of parabolic reflector, including and only includes paraboloid of revolution reflecting surface around rotation
Parabolic reflector be connected coordinate system X-axis rotation angle, the rotation angle around Y-axis, and the displacement along X-axis, the displacement along Y-axis, along Z
The displacement of axis.
5. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 2, which is characterized in that the rotation
Turn the rotational deformation parameter and displacement deformation parameter of hyperboloid reflecting surface, including and only includes hyperboloid of revolution reflecting surface around rotation
Hyperboloid reflecting surface be connected coordinate system X-axis rotation angle, the rotation angle around Y-axis, and the displacement along X-axis, the displacement along Y-axis, along Z
The displacement of axis.
6. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 5, which is characterized in that plane is anti-
It penetrates the connected coordinate origin in face and is taken as reflecting surface geometric center, z-axis is plane positive normal, and x-axis is planar directed toward a feature side
To y-axis is determined by the right-hand rule；The connected coordinate origin of paraboloid of revolution reflecting surface is the inflection point of paraboloid of revolution reflecting surface, z
Axis and the symmetrical overlapping of axles of paraboloid of revolution reflecting surface are directed toward paraboloid of revolution inflection point positive normal direction, and the vertical z-axis of x-axis is directed toward rotation
One characteristic direction of parabolic reflector, y-axis are determined by the right-hand rule；
The connected coordinate origin of hyperboloid of revolution reflecting surface is the inflection point of hyperboloid of revolution reflecting surface, and z-axis is anti-with the hyperboloid of revolution
The symmetrical overlapping of axles for penetrating face are directed toward hyperboloid of revolution reflecting surface inflection point positive normal direction, and it is anti-that the vertical z-axis of x-axis is directed toward the hyperboloid of revolution
Face characteristic direction is penetrated, y-axis is determined by the right-hand rule；
The connected coordinate origin of feed is taken as feed entrance geometric center, and the vertical feed plane of inlet of z-axis is directed toward on the outside of feed, x
The vertical z-axis of axis is directed toward one characteristic direction of feed plane of inlet, and y-axis is determined by the right-hand rule.
7. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 2, which is characterized in that sight shape
State vector X is 7 dimensional vectors, by sight reflecting surface landing point coordinates [x, y, z]T, direction of visual lines unit vector [u, v, w]TWith 1
It constitutes:
X=[x y z u v w 1]T, wherein X is sight state vector.
8. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 7, which is characterized in that according to view
Line reflection transmission path order, by coordinate conversion matrix realize sight state vector neighboring reflection face be connected coordinate system it
Between conversion:
Xb=TbaXa。
9. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 2, which is characterized in that component becomes
Coordinate conversion matrix after shape has following form:
It indicates under nominal state, direction cosine matrix of a coordinate system to b coordinate system, RaIndicate the direction of a component rotational deformation
Cosine matrix, RbIndicate the direction cosine matrix of b component rotational deformation,It indicates under no deformation, a system origin A is in b system
Projection, Δ A respectively indicates a coordinate system displacement deformation parameter, Δ B indicates the displacement deformation parameter of b coordinate system.
10. the description method of satellite-borne microwave remote sensing instrument malformation according to claim 1, which is characterized in that including
Following steps:
Step 1, by the independent optical paths component in satellite-borne microwave remote sensing instrument be divided into plane reflection face, paraboloid of revolution reflecting surface,
Hyperboloid of revolution reflecting surface and feed totally four seed type；The plane being connected according to the type of stand-alone assembly, definition with stand-alone assembly
Reflecting surface be connected coordinate system, paraboloid of revolution reflecting surface be connected coordinate system, hyperboloid of revolution reflecting surface be connected coordinate system, rotary shaft
It is be connected coordinate system and the connected coordinate system of feed；
Step 2, plane reflection face, paraboloid of revolution reflecting surface, the rotational deformation parameter of hyperboloid of revolution reflecting surface and position are defined
Move deformation parameter；
Step 3, from feed, according to light path part rotational deformation parameter and displacement deformation parameter calculate adjacent optical path component it
Between Conversion Matrix of Coordinate；
Step 4, coordinate conversion matrix is substituted into optical path model.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000151971A (en) * | 1998-11-10 | 2000-05-30 | Hitachi Ltd | Picture processor |
| CN104537184A (en) * | 2015-01-07 | 2015-04-22 | 西安电子科技大学 | Thermal deformation real-time forecast method for axial symmetry reflector antenna |
| CN104764443A (en) * | 2015-04-24 | 2015-07-08 | 国家测绘地理信息局卫星测绘应用中心 | Optical remote sensing satellite rigorous imaging geometrical model building method |
| CN105930570A (en) * | 2016-04-15 | 2016-09-07 | 西安电子科技大学 | Calculation method for parameter of optimally-fit shaped surface of shaped dual-reflector antenna |
| CN106025550A (en) * | 2016-05-27 | 2016-10-12 | 中国科学院新疆天文台 | Subreflector position adjustment method of dual-reflector antenna employing electrical property as target |
| CN108872942A (en) * | 2018-06-15 | 2018-11-23 | 西安电子科技大学 | The real-time keeping method in active primary reflection surface antenna ideal shape face based on datum mark |
| CN108879106A (en) * | 2018-06-15 | 2018-11-23 | 西安电子科技大学 | Dual reflector antenna shape face method of real-time adjustment based on best fit |
| CN109004362A (en) * | 2018-06-20 | 2018-12-14 | 上海卫星工程研究所 | It is a kind of based on multi-point displacement adjust satellite antenna in rail type face active control device |
| CN109066058A (en) * | 2018-06-19 | 2018-12-21 | 上海卫星工程研究所 | A kind of inclined formula feedback Cassegrain deployable antenna of heavy caliber |
-
2019
- 2019-01-30 CN CN201910092179.0A patent/CN109975832B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000151971A (en) * | 1998-11-10 | 2000-05-30 | Hitachi Ltd | Picture processor |
| CN104537184A (en) * | 2015-01-07 | 2015-04-22 | 西安电子科技大学 | Thermal deformation real-time forecast method for axial symmetry reflector antenna |
| CN104764443A (en) * | 2015-04-24 | 2015-07-08 | 国家测绘地理信息局卫星测绘应用中心 | Optical remote sensing satellite rigorous imaging geometrical model building method |
| CN105930570A (en) * | 2016-04-15 | 2016-09-07 | 西安电子科技大学 | Calculation method for parameter of optimally-fit shaped surface of shaped dual-reflector antenna |
| CN106025550A (en) * | 2016-05-27 | 2016-10-12 | 中国科学院新疆天文台 | Subreflector position adjustment method of dual-reflector antenna employing electrical property as target |
| CN108872942A (en) * | 2018-06-15 | 2018-11-23 | 西安电子科技大学 | The real-time keeping method in active primary reflection surface antenna ideal shape face based on datum mark |
| CN108879106A (en) * | 2018-06-15 | 2018-11-23 | 西安电子科技大学 | Dual reflector antenna shape face method of real-time adjustment based on best fit |
| CN109066058A (en) * | 2018-06-19 | 2018-12-21 | 上海卫星工程研究所 | A kind of inclined formula feedback Cassegrain deployable antenna of heavy caliber |
| CN109004362A (en) * | 2018-06-20 | 2018-12-14 | 上海卫星工程研究所 | It is a kind of based on multi-point displacement adjust satellite antenna in rail type face active control device |
Non-Patent Citations (3)
| Title |
|---|
| T. TOUTIN: "Review article: Geometric processing of remote sensing images: models, algorithms and methods", 《REMOTE SENSING》 * |
| 刘佳等: "星载太赫兹辐射计天线系统设计与分析", 《电波科学学报》 * |
| 虞梦月: "110米口径超大型全可动天线轴系误差对指向精度的影响", 《中国优秀硕士学位论文全文数据库 信息科技辑》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111103001A (en) * | 2020-01-21 | 2020-05-05 | 上海航天测控通信研究所 | Motion scanning device and method for stationary track microwave radiometer |
| CN111103001B (en) * | 2020-01-21 | 2021-06-22 | 上海航天测控通信研究所 | Motion scanning device and method for stationary track microwave radiometer |
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