CN105403888A - Geosynchronous orbit circular track SAR imaging method using beam pointing control - Google Patents

Geosynchronous orbit circular track SAR imaging method using beam pointing control Download PDF

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CN105403888A
CN105403888A CN201511022581.XA CN201511022581A CN105403888A CN 105403888 A CN105403888 A CN 105403888A CN 201511022581 A CN201511022581 A CN 201511022581A CN 105403888 A CN105403888 A CN 105403888A
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胡文龙
江冕
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Institute of Electronics of CAS
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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
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
    • G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
    • 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
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
    • G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
    • G01S13/904—SAR modes
    • G01S13/9058—Bistatic or multistatic SAR

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • General Physics & Mathematics (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

The invention belongs to the technical field of synthetic aperture radar and particularly relates to a geosynchronous orbit circular track SAR imaging method using beam pointing control. By using such a method, a circular track geosynchronous satellite having a 8-shaped sub satellite point locus is taken as a radar platform, 12 hours corresponding to the half 8 shape where an object to be observed is arranged are regarded as an imaging period, the two-dimension antenna wave beam directional control is carried out in the imaging period by means of a stepping technique, so that the satellite can be in the corresponding movement process of the half 8-shaped sub satellite point locus, the antenna wave beam can always point to the imaged ground object to be observed, the 360-degree relative movement of radar relative to the object is formed, and the circular track SAR imaging based on the geosynchronous orbit satellite platform is realized.

Description

Adopt the geostationary orbit circle mark SAR formation method of beam point steering
Technical field
The invention belongs to Synthetic Aperture Radar Technique field, particularly a kind of geostationary orbit circle mark SAR formation method adopting beam point steering.
Background technology
Synthetic-aperture radar (SyntheticApertureRadar, SAR) be the important means that a kind of Imaging remote sensing is over the ground observed, the feature of " round-the-clock, round-the-clock " is not so by meteorological condition and the impact at night because having, thus is widely used.Circle mark SAR utilizes the relative motion between Texas tower and target being observed, can realize 360 ° of omnibearing observations to target, has the multiple advantages such as resolution height and three-dimensional imaging.At present, circle mark SAR often adopts aircraft or near space dirigible as Texas tower, realizes the imaging of circle mark by aircraft or dirigible circular motion on a surface target.In satellite-borne SAR, the track of common imaging satellite is lower, cannot form 360 ° of relative motions between radar and target, there is no spaceborne round mark SAR system in orbit at present.It is the spaceborne round mark SAR imaging technique of platform that the patent that patent of invention name is called " geostationary orbit circle mark synthetic aperture radar three-dimensional microwave imaging method (patent No. ZL200710176924.7) " proposes with geo-synchronous orbit satellite, utilize geostationary orbits high and the feature identical with earth rotation period that revolve round the sun, by by circular for Orbit Design sub-satellite track, achieve the image forming job pattern of spaceborne round mark SAR.
But there is following main shortcoming in the spaceborne round mark SAR imaging technique of above-mentioned geostationary orbit:
The first, there is the geostationary satellite of circular sub-satellite track, earth while one week also from target overhead around target relative movement circumference.Now, the imaging of SAR circle mark mainly make use of the orbital motion of satellite, and requires that the inclination angle radian of satellite orbit numerically remains 2 times of excentricity.This requirement keeps proposing particular/special requirement to the track of satellite, and these requirements are difficult to realize usually, or needs the cost paying very high track maintenance.
The second, for forming the circular sub-satellite track in ground, satellite orbit needs larger eccentricity parameter.Although satellite is circular at the substar projected footprint on ground, the track that satellite spatially runs around the earth is oval.Excentricity is larger, and the shape of the space orbit of satellite more departs from circle, and closer to ellipse.When satellite runs along elliptical orbit, all can there is acute variation relative to the movement velocity of target in the height of satellite orbit and satellite, each of which increases imaging processing difficulty.
Three, in order to realize spaceborne round mark SAR to the imaging of target, need satellite to run complete cycle around the earth, this makes the cycle of circle mark SAR imaging reach 24 hours, thus reduces the ageing of acquisition of information.
Summary of the invention
(1) technical matters that will solve
In order to solve the problem, the present invention proposes a kind of geostationary orbit circle mark SAR formation method of employing beam point steering newly, reduce satellite along rail move hourly velocity and height acute variation degree, reduce the intractability of imaging, shorten imaging cycle, the requirement proposing singularity is not kept to the track of satellite simultaneously.
(2) technical scheme
In order to realize object of the present invention, the geostationary orbit circle mark SAR formation method of employing beam point steering provided by the invention, comprises the following steps:
The first step, according to the position of terrain object being observed imaging, selectedly has zero excentricity, sub-satellite track be that the geostationary satellite of " 8-shaped " is as the Texas tower justifying mark SAR;
Second step, designed path parameter, makes sub-satellite track certain half " 8-shaped " cover the target area that ground makes a reservation for be observed imaging;
3rd step, with the angle in SAR antenna beam center line and substar direction for distance points to angle, with the angle in antenna beam center line and satellite orbit motion direction for bearing sense angle, assuming that SAR antenna beam points to target all the time, and represent beam position with wave beam distance sensing angle and beam positional sensing angle, calculate distance and point to angle and bearing sense angle rule over time;
4th step, points to angle and bearing sense angle rule over time according to the described distance calculated, within the observation cycle of circle mark SAR imaging, take step-by-step method to carry out two-dimensional antenna beam point steering.
(3) beneficial effect
The present invention by adopt orbital eccentricity be the geostationary satellite of zero as Texas tower, propose a kind of geostationary orbit circle mark SAR formation method of employing beam point steering newly.Compared with existing spaceborne round mark SAR formation method, the beneficial effect acquired by the present invention is:
1, the track that the geostationary satellite being zero due to excentricity aloft runs around the earth is circular orbit, so satellite is little apart from the height change on ground, the speed run along circular orbit of satellite is equal simultaneously, is more conducive to the process of SAR imaging.
2, the present invention's mode of adopting wave beam to control, thus the imaging in whole round mark cycle in the period, can be completed in half " 8-shaped " of circular orbit geostationary satellite sub-satellite track, circle mark imaging time is reduced to 12 hours.
3, the present invention adopts two dimensional beam control realization spaceborne round mark SAR imaging, no longer requiring that the radian of inclination of satellite orbit is numerically 2 times of excentricity, thus without the need to proposing particular/special requirement to the maintenance of satellite orbit, reducing the difficulty that satellite orbit keeps.
Accompanying drawing explanation
Fig. 1 is the observation schematic diagram of the geostationary orbit circle mark SAR imaging of the employing beam point steering of one embodiment of the invention;
Fig. 2 is the schematic diagram at the controlling antenna wave beam to point angle of the geostationary orbit circle mark SAR imaging of the employing beam point steering of one embodiment of the invention;
Fig. 3 is the time dependent schematic diagram of beam position of the geostationary orbit circle mark SAR imaging of the employing beam point steering of one embodiment of the invention.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are explained.
Fig. 1 shows the observation schematic diagram of the geostationary orbit circle mark SAR imaging adopting beam point steering according to an embodiment of the invention.In the present embodiment, assuming that the target being imaged observation is GuangZhou, China area, the centre coordinate of imaging region is 23.0962 ° of N, 113.2936E °.
Geostationary orbit circle mark SAR formation method according to the employing beam point steering of one embodiment of the invention comprises the following steps:
The first step, according to the position of terrain object being observed imaging, selected there is zero excentricity, sub-satellite track be that the geostationary satellite of " 8-shaped " is as the Texas tower second step justifying mark SAR, designed path parameter, makes sub-satellite track certain half " 8-shaped " cover the target area that ground makes a reservation for be observed imaging.
Particularly, design excentricity is the track of the geostationary satellite of zero, half " 8-shaped " making this geostationary satellite be in Northern Hemisphere sub-satellite track covers the predetermined terrain object region being observed imaging, and its concrete orbit parameter is: track major semi-axis a=42164.17km, eccentric ratio e=0, orbit inclination i=50 °, right ascension of ascending node Ω=115 °, argument of perigee ω=0 ° and mean anomaly M=0 °.The relation of imageable target and geostationary satellite sub-satellite track as shown in Figure 1.
3rd step, with the angle in SAR antenna beam center line and substar direction for distance points to angle, with the angle in antenna beam center line and satellite orbit motion direction for bearing sense angle, as shown in Figure 2.Assuming that SAR antenna beam points to target all the time, and represent beam position with wave beam distance sensing angle and beam positional sensing angle, calculate distance and point to angle and bearing sense angle rule over time.。
Particularly, take the satellite transit period corresponding to the sub-satellite track of the Northern Hemisphere half " 8-shaped " as the observation cycle of circle mark SAR imaging, if t is the time variable of satellite motion and spends the ascending node moment for imaging initial zero moment with satellite.At geostationary satellite in the process of earth movements, assuming that radar antenna wave beam points to the terrain object of observation imaging all the time, the time dependent distance of any time t beam position calculated within half " 8-shaped " corresponding observation cycle points to angle and bearing sense angle.
This calculation procedure is as follows:
1) calculating t substar connects firmly the longitude and latitude in coordinate system in earth the earth's core
φ s(t)＝arcsin(sinisinω st)(1a)
λ s(t)＝arctan(cositanω st)-ω e·t+Ω(1b)
Wherein, λ st () is geostationary satellite substar longitude, φ st () is geostationary satellite substar longitude, i, Ω are inclination of satellite orbit, right ascension of ascending node respectively, ω sfor satellite mean angular velocity of satellite motion, ω efor earth rotation mean angular velocity.
2) calculating t satellite orbit connects firmly the rectangular coordinate position in coordinate system in earth the earth's core
x s(t)＝acosφ s(t)cosλ s(t)(2a)
y s(t)＝acosφ s(t)sinλ s(t)(2b)
z s(t)＝asinφ s(t)(2c)
Wherein, x s(t), y s(t), z st () is the track rectangular coordinate of geostationary satellite, a is satellite orbit major semi-axis.
3) calculating t satellite connects firmly the rectangular coordinate speed in coordinate system in earth the earth's core
x · s ( t ) = x s ( t + 1 ) - x s ( t ) Δ t - - - ( 3 a )
y · s ( t ) = y s ( t + 1 ) - y s ( t ) Δ t - - - ( 3 b )
z · s ( t ) = z s ( t + 1 ) - z s ( t ) Δ t - - - ( 3 c )
Wherein, be the cartesian component of satellite motion speed, Δ t is the difference in neighborhood calculation moment.
4) distance that compute beam center line points to respectively points to angle θ rwith bearing sense angle θ afor:
Wherein, x t, y t, z tfor center, imageable target region to connect firmly rectangular coordinate, the radar beam center line pointing vector of coordinate system in the earth's core geo-synchronous orbit satellite connects firmly coordinate system rectangular coordinate position vector in the earth's core is geostationary orbit connects firmly coordinate system rectangular coordinate velocity in the earth's core is
The time dependent distance sensing angle of beam central line sensing calculated according to one embodiment of the invention and bearing sense angle are as shown in Figure 3.See Fig. 3, be initial zero moment with the moment of geostationary satellite sub-satellite track crossing the line, satellite runs along the order of A → B → C → D.
4th step, points to angle and bearing sense angle rule over time according to calculated distance, within the observation cycle of circle mark SAR imaging, take step-by-step method to carry out two-dimensional antenna beam point steering.This step comprises further:
1) calculate satellite motion speed along distance to orientation to ground velocity component be respectively
v r = R e a | V → | cosθ r - - - ( 8 a )
v a = R e a | V → | cosθ a - - - ( 8 b )
Wherein, the range value of satellite orbit motion velocity, v r, v asatellite motion distance speed component and orientation speed component, R earthward earthward respectively eit is earth radius.
2) with reference to the time step of the width selection beam point steering of antenna beam
Press antenna radiation pattern distance respectively to, orientation to width, choose the time step that controlling antenna wave beam to point controls
t 0 r = ϵ r · W r v r - - - ( 9 a )
t 0 a = ϵ a · W a v a - - - ( 9 b )
In formula, t 0afor orientation is to step size, t 0rfor distance is to step size, W a, W rfor mapping band orientation is to, distance to width, ε a, ε rcontrol ratio for antenna bearingt to, distance to wave beam and have 0≤ε a≤ 1,0≤ε r≤ 1.
3) distance calculated according to described 3rd step points to angle and bearing sense angle rule over time, difference temporally step-length t 0rand t 0acarry out distance to orientation to step size, within the SAR imaging observation cycle, carry out two-dimensional antenna beam point steering, the center, target area antenna beam being pointed to all the time be imaged.
Above-described specific embodiment; object of the present invention, technical scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.

Claims (5)

1. adopt a geostationary orbit circle mark SAR formation method for beam point steering, it is characterized in that, the method comprises the following steps:
The first step, according to the position of terrain object being observed imaging, selectedly has zero excentricity, sub-satellite track be that the geostationary satellite of " 8-shaped " is as the Texas tower justifying mark SAR;
Second step, designed path parameter, makes sub-satellite track certain half " 8-shaped " cover the target area that ground makes a reservation for be observed imaging;
3rd step, with the angle in SAR antenna beam center line and substar direction for distance points to angle, with the angle in antenna beam center line and satellite orbit motion direction for bearing sense angle, assuming that SAR antenna beam points to target all the time, and represent beam position with wave beam distance sensing angle and beam positional sensing angle, calculate distance and point to angle and bearing sense angle rule over time;
4th step, points to angle and bearing sense angle rule over time according to the described distance calculated, within the observation cycle of circle mark SAR imaging, take step-by-step method to carry out two-dimensional antenna beam point steering.
2. the method for claim 1, it is characterized in that, the track that described geostationary satellite 24 hours runs one week in space around the earth is circuit orbit, and described sub-satellite track forms the closed border circular areas of two and half " 8-shaped " respectively at Southern And Northern Hemispheres of The Earth, described border circular areas is symmetrical about north and south, equator.
3. method as claimed in claim 2, it is characterized in that, the observation cycle of described round mark SAR imaging is specially:
Half " 8-shaped " sub-satellite track residing for select target region, by the observation cycle being set to described round mark SAR imaging 12 hour satellite period partly corresponding to " 8-shaped " sub-satellite track.
4. method as claimed in claim 3, is characterized in that, described in calculate distance point to angle and bearing sense angle over time rule comprise further:
If t is the time variable of geostationary satellite motion, and spend the ascending node moment for imaging initial zero moment with geostationary satellite, then for described round mark SAR imaging observation cycle within any time t, the calculation procedure that the distance that antenna beam center line points to points to angle and bearing sense angle is as follows:
1) calculating t substar connects firmly the longitude and latitude in coordinate system in earth the earth's core
φ s(t)＝arcsin(sinisinω st)(1a)
λ s(t)＝arctan(cositanω st)-ω e·t+Ω(1b)
Wherein, λ st () is geostationary satellite substar longitude, φ st () is geostationary satellite substar latitude, i is inclination of satellite orbit, and Ω is ascending node of satellite orbit right ascension, ω sfor the mean angular velocity of satellite motion of geostationary satellite, ω efor earth rotation mean angular velocity;
2) calculating t satellite orbit connects firmly the rectangular coordinate position in rectangular coordinate system in earth the earth's core
x s(t)＝acosφ s(t)cosλ s(t)(2a)
y s(t)＝acosφ s(t)sinλ s(t)(2b)
z s(t)＝asinφ s(t)(2c)
Wherein, x s(t), y s(t), z st () is the track cartesian component of geostationary satellite, a is the track major semi-axis of geostationary satellite;
3) calculating t geostationary satellite connects firmly the rectangular coordinate speed in coordinate system in earth the earth's core
x · s ( t ) = x s ( t + 1 ) - x s ( t ) Δ t - - - ( 3 a )
y · s ( t ) = y s ( t + 1 ) - y s ( t ) Δ t - - - ( 3 b )
z · s ( t ) = z s ( t + 1 ) - z s ( t ) Δ t - - - ( 3 c )
Wherein, be the cartesian component of satellite motion speed, Δ t is the difference in neighborhood calculation moment;
4) distance that compute beam center line points to respectively points to angle θ rwith bearing sense angle θ afor
θ r = cos - 1 ( - r → · S T → | r → | · | S T → | ) , θ a = cos - 1 ( S T → · V → | S T | · | V → | ) - - - ( 7 )
Wherein, SAR antenna beam center line pointing vector S T → = [ x T - x S ( t ) , y T - y S ( t ) , z T - z S ( t ) ] T , X t, y t, z tfor the center in imageable target region to connect firmly the rectangular coordinate of coordinate system in the earth's core, geostationary satellite connects firmly the rectangular coordinate position vector of coordinate system in the earth's core geostationary satellite connects firmly the rectangular coordinate velocity of coordinate system in the earth's core V → = [ x · S ( t ) , y · S ( t ) , z · S ( t ) ] T .
5. method as claimed in claim 4, it is characterized in that, described 4th step comprises further:
1) calculate geostationary satellite movement velocity along distance to orientation to ground velocity component be respectively
v r = R e a | V → | cosθ r - - - ( 8 a )
v a = R e a | V → | cosθ a - - - ( 8 b )
Wherein, the range value of satellite orbit motion velocity, v r, v ageostationary satellite move distance speed component and orientation speed, R earthward earthward respectively eit is earth radius;
2) time step of beam point steering is selected according to the width of antenna beam
Press respectively antenna radiation pattern distance to orientation to width, choose distance that controlling antenna wave beam to point controls to step size and orientation to step size,
t 0 r = ϵ r · W r v r - - - ( 9 a )
t 0 a = ϵ a · W a v a - - - ( 9 b )
Wherein, t 0afor orientation is to step size, t 0rfor distance is to step size, W a, W rfor mapping band orientation is to, distance to width, ε a, ε rfor antenna bearingt controls ratio to wave beam to, distance, and has 0≤ε a≤ 1,0≤ε r≤ 1;
3) distance calculated according to described 3rd step points to angle and bearing sense angle rule over time, difference temporally step-length t 0rand t 0acarry out distance to orientation to step size, thus realize circle the mark SAR imaging observation cycle within carry out two-dimensional antenna beam point steering, make antenna beam point to the center of the target area being observed imaging all the time.
CN201511022581.XA 2015-12-30 2015-12-30 Geosynchronous orbit circular track SAR imaging method using beam pointing control Pending CN105403888A (en)

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CN106950565A (en) * 2017-01-24 2017-07-14 王洋 Space-borne SAR Imaging jitter compensation method, imaging method
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CN105842668A (en) * 2016-03-22 2016-08-10 中国科学院电子学研究所 Circular SAR-based dihedral corner reflector optimal imaging azimuth determining method
CN108205328A (en) * 2016-12-16 2018-06-26 英西图公司 Establish the system and method for the flight schema adjacent with target followed for the vehicles
CN106772276B (en) * 2016-12-21 2019-05-21 南京信息工程大学 A kind of geostationary orbit circular track SAR horizontal plane two dimension side lobe suppression method
CN106772276A (en) * 2016-12-21 2017-05-31 南京信息工程大学 A kind of geostationary orbit circular track SAR horizontal planes two dimension side lobe suppression method
CN106950565A (en) * 2017-01-24 2017-07-14 王洋 Space-borne SAR Imaging jitter compensation method, imaging method
CN107425892A (en) * 2017-06-22 2017-12-01 清华大学 Air-ground coordination communication means and device based on multi-beam multicast
CN107425892B (en) * 2017-06-22 2019-02-26 清华大学 Air-ground coordination communication means and device based on multi-beam multicast
CN109474326A (en) * 2018-11-16 2019-03-15 清华大学 Beam switching method and device
CN109474326B (en) * 2018-11-16 2019-08-30 清华大学 Beam switching method and device
CN109738928A (en) * 2018-12-29 2019-05-10 中国科学院长春光学精密机械与物理研究所 The satellite imagery paths planning method of space vascular envelope Distributed Three-dimensional target
CN109738928B (en) * 2018-12-29 2020-07-10 中国科学院长春光学精密机械与物理研究所 Satellite imaging path planning method for space vessel envelope distributed three-dimensional target
EP3809152A1 (en) * 2019-10-14 2021-04-21 ThinKom Solutions, Inc. Non-tle-based pointing acquisition of inclined-geostationary satellite
CN113239773A (en) * 2021-05-08 2021-08-10 重庆邮电大学 Human body posture non-contact sensing method based on CSAR three-dimensional imaging
CN113472421A (en) * 2021-06-29 2021-10-01 中国人民解放军军事科学院国防科技创新研究院 Low-orbit network satellite inter-satellite beam pointing Lagrange interpolation method
CN113472421B (en) * 2021-06-29 2022-06-14 中国人民解放军军事科学院国防科技创新研究院 Low-orbit network satellite inter-satellite beam pointing method based on Lagrange interpolation

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