CN107526066A - A kind of echo simulation method and device - Google Patents

A kind of echo simulation method and device Download PDF

Info

Publication number
CN107526066A
CN107526066A CN201710642415.2A CN201710642415A CN107526066A CN 107526066 A CN107526066 A CN 107526066A CN 201710642415 A CN201710642415 A CN 201710642415A CN 107526066 A CN107526066 A CN 107526066A
Authority
CN
China
Prior art keywords
moon
echo
coordinate system
point
point target
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN201710642415.2A
Other languages
Chinese (zh)
Other versions
CN107526066B (en
Inventor
陈杰
王鹏波
谷昕炜
曾虹程
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beihang University
Original Assignee
Beihang University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Beihang University filed Critical Beihang University
Priority to CN201710642415.2A priority Critical patent/CN107526066B/en
Publication of CN107526066A publication Critical patent/CN107526066A/en
Application granted granted Critical
Publication of CN107526066B publication Critical patent/CN107526066B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/40—Means for monitoring or calibrating
    • G01S7/4052—Means for monitoring or calibrating by simulation of echoes

Landscapes

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

Abstract

This disclosure relates to a kind of echo simulation method and device, to solve the problems, such as that a moon base radar simulation can not be carried out in correlation technique.This method includes：Lunar orbit parameter is calculated according to moon almanac data；The systematic parameter of radar is set according to lunar orbit parameter and observation requirementses；According to moon almanac data determine echo simulation central instant and the moment corresponding to beam position；Point target is set in the range of beam position corresponding to central instant in echo simulation, the point target is target illuminated during echo simulation；Systematic parameter based on radar obtains the echo data of point target, and the program realizes a moon echo simulation for base radar.

Description

A kind of echo simulation method and device
Technical field
This disclosure relates to technical field of radar simulation, in particular it relates to a kind of echo simulation method and device.
Background technology
With progressively going deep into natural science area research, the mankind gradually appreciate the presence of " earth tide ", concurrently The weather ring that the large scale dynamic change that the earth is showed during long-term nature evolution directly affects the earth is showed Border.At present, SAR (Synthetic Aperture Radar, synthetic aperture radar) system is for various reasons in spreadability side Face can not meet the measurement scale demand of crustal plate rank, and in view of the performance characteristics of artificial satellite, it is seen that passing through The properties of traditional platform are improved to improve the thinking of radar observation ability and the most rational solution route of non-problems, it is necessary to There is the carrier platform of new model to break through the bottleneck that artificial satellite platform is faced.
The moon makes to put down by carrier of the moon as the unique natural satellite of the earth, its special " tide locking " phenomenon Platform, the possibility for being envisioned with realizing of moon base earth observation radar is established in moonscape.The moon is averaged more than 370,000 kms Observation oblique distance makes that only 2 degree of radar bearing can cover whole earth to beam angle in moonscape.Meanwhile the moon is flat Equal radius reaches 1737 kms, and laying multiple sensors in moonscape diverse location makes moon base interferometer radar have that realizes to dive Power.And the moon is close to 7.3 × 1022Kg huge quality is also the strong guarantee of platform stabilization.
In recent years, the conception that association area is applied to moon base SAR is varied all the more, and to moon base SAR echoing characteristics Analyze the primary stage but remained in based on satellite-borne SAR theory.Month base SAR big oblique distance characteristic causes it emulating There is very big difference on algorithm with traditional satellite-borne SAR, many approximate conditions are no longer applicable, and unique geometrical relationship imply that echo As a result entirely different property will be shown.The nutating of celestial body and libration phenomenon also can produce very big shadow to actual ghosts Ring, simple two body Model is not suitable for a moon base radar simulation.
The content of the invention
The purpose of the disclosure is to provide a kind of echo simulation method and device, to solve that the moon can not be carried out in correlation technique The problem of base radar simulation.
Present disclose provides a kind of radar return data capture method, including：Moon rail is calculated according to moon almanac data Road parameter；The systematic parameter of radar is set according to the lunar orbit parameter and observation requirementses；According to the moon ephemeris number According to beam position corresponding to the central instant and the moment for determining the echo simulation；In the beam position In the range of point target is set, the point target is target illuminated during the echo simulation；Joined based on the system Number obtains the echo data of the point target.
Alternatively, described central instant and moment pair that the echo simulation is determined according to the moon almanac data The beam position answered, including：Emulated according to position of the antenna phase center in moon celestial body coordinate system and the moon Position of the aiming point that wave beam is determined in the position in rotating geocentric coordinate system of central instant in geocentric coordinate system is rotated；Root According to the coordinate of position acquisition beam center point of the aiming point of wave beam in geocentric coordinate system is rotated, and the center point coordinate Corresponding longitude and latitude；Position corresponding to beam center is chosen, and is defined as at the time of by the position correspondence described imitative True central instant.
Alternatively, it is described that point target is set in the range of the beam position, including：It is determined that imitated in the echo True first position of the start time antenna phase center in terrestrial coordinate system is rotated；It is determined that in the echo simulation start time The second place of the point target in terrestrial coordinate system is rotated；According to the relative of the first position and the second place Radius vector judges whether the point target is arrived by beam；Obtain the phase of echo of the point target arrived by beam.
Alternatively, the lunar orbit parameter includes at least one of following：Orbital eccentricity, perigee position, ascending node Position, the red footpath of ascending node, argument of pericenter and orbit inclination angle.
Alternatively, the systematic parameter of the radar includes at least one of following：Transmitted wave frequency modulation rate, the pulse duration, Beam time, antenna look angle, antenna size and radar site.
The disclosure additionally provides a kind of radar return data acquisition facility, including：Computing module, for according to moon ephemeris Data calculate lunar orbit parameter；First setup module, for setting thunder according to the lunar orbit parameter and observation requirementses The systematic parameter reached；Determining module, for determined according to the moon almanac data echo simulation central instant and Beam position corresponding to the moment；Second setup module, for the set-point mesh in the range of the beam position Mark, the point target is target illuminated during the echo simulation；Acquisition module, for based on the systematic parameter Obtain the echo data of the point target.
Alternatively, the determining module, including：First determining unit, for according to antenna phase center in moon celestial body The position in geocentric coordinate system is rotated at position and the moon in coordinate system heart moment in simulations determines the aiming of wave beam Position of the point in geocentric coordinate system is rotated；First acquisition unit, geocentric coordinate system is being rotated for the aiming point according to wave beam In position acquisition beam center point coordinate, and longitude and latitude corresponding to the center point coordinate；Second determines Unit, it is defined as the simulation centre moment for choosing position corresponding to beam center, and at the time of by the position correspondence.
Alternatively, second setup module, including：3rd determining unit, for determining to start in the echo simulation First position of the moment antenna phase center in terrestrial coordinate system is rotated；4th determining unit, for determining in the echo Emulate the second place of the point target in terrestrial coordinate system is rotated described in start time；Judging unit, for according to described first The relative radius vector of position and the second place judges whether the point target is arrived by beam；Second acquisition unit, use In the phase of echo for obtaining the point target arrived by beam.
Alternatively, the lunar orbit parameter includes at least one of following：Orbital eccentricity, perigee position, ascending node Position, the red footpath of ascending node, argument of pericenter and orbit inclination angle.
Alternatively, the systematic parameter of the radar includes at least one of following：Transmitted wave frequency modulation rate, the pulse duration, Beam time, antenna look angle, antenna size and radar site.
Pass through above-mentioned technical proposal, lunar orbit parameter is calculated according to moon almanac data and determined in echo simulation Beam position corresponding to heart moment and the moment；The system that radar is set according to lunar orbit parameter and observation requirementses Parameter；Point target is set in the range of beam position, the systematic parameter based on setting, obtains the number of echoes of point target According to realizing a moon echo simulation for base radar, the echo data based on acquisition, the echoing characteristics of moon base radar can be divided Analysis.
Other feature and advantage of the disclosure will be described in detail in subsequent specific embodiment part.
Brief description of the drawings
Accompanying drawing is for providing further understanding of the disclosure, and a part for constitution instruction, with following tool Body embodiment is used to explain the disclosure together, but does not form the limitation to the disclosure.In the accompanying drawings：
Fig. 1 is the flow chart of the echo simulation method according to an exemplary embodiment.
Fig. 2 is the geometry site schematic diagram of the earth and moon relative position according to an exemplary embodiment.
Fig. 3 is the schematic diagram of moon position in ephemeris according to an exemplary embodiment.
Fig. 4 is the single-point target echo result schematic diagram according to an exemplary embodiment.
Fig. 5 is the imaging schematic diagram of the single-point target echo simulation according to an exemplary embodiment.
Fig. 6 is 9 dot matrix simulation imaging schematic diagrames according to an exemplary embodiment.
Fig. 7 is the structured flowchart of the echo simulation device according to an exemplary embodiment.
Embodiment
The embodiment of the disclosure is described in detail below in conjunction with accompanying drawing.It should be appreciated that this place is retouched The embodiment stated is merely to illustrate and explained the disclosure, is not limited to the disclosure.
To solve the above problems, present disclose provides a kind of echo simulation method is described, moon base is simulated using this method The course of work of radar, and the echo simulation data under different condition can be obtained by adjusting radar system parameters, to test Performance of the card system under different system parameter.
Fig. 1 is the flow chart of the echo simulation method according to an exemplary embodiment, as shown in figure 1, the disclosure carries The echo simulation method of confession includes following processing：
S101：Lunar orbit parameter is calculated according to moon almanac data；
Example, in the disclosure, moon almanac data can use JPL ephemeris parameters, and, radar can be SAR.
Due to the influence of lunar nutation, there is periodically variable phenomenon in the moon around the revolution orbit of the earth, and the ground moon is relative Geometry site is as shown in Figure 2.Echo simulation determines the irradiation moment firstly the need of the moon almanac data used in Orbit parameter, as follows is required to moon almanac data：
Moon almanac data will embody nutating and the libration information of the moon；Moon almanac data entirety time span must be big In 27.4 days but it can not be longer than 30 days, adjacent data time interval is up to 1h, and is interpolated into the second；Moon almanac data palpus Position and velocity information comprising the moon；The referential of almanac data, which should be elected as, does not rotate geocentric reference system, i.e. earth the earth's core is Origin, it be X-axis positive direction that the first point of Aries is pointed in the earth's core, and it is Z axis positive direction that the earth arctic is pointed in the earth's core, the vertical simultaneously structure of Y-axis and X, Z axis Into right hand reference system；According to moon almanac data, the lunar orbit parameter obtained can include：In the current lunar period of revolution, The parameters such as the eccentricity of lunar orbit, perigee position, the red footpath of ascending node, argument of pericenter.
Above-mentioned moon almanac data can obtain in the following way：
Wherein, JPL almanac datas are in addition to celestial body position, speed, and also comprising a lot of other information, orbital eccentricity e is just It is one of them；JPL moon ephemeris includes the moon positional information in geocentric coordinate system is not rotated, and the earth is that moon revolution is ellipse One focus of circular orbit, calculate per the moment moon relative to the radius vector r (n) in the earth's core：
| r (n) |=rmin (1)
| r (n) | position is perigee position.
It is positive and negative along direction traversal moon Z axis from West to East according to ephemeris moon position, when meeting following condition, obtain n。
Wherein, position n is ascending node position.
After ascending node position is obtained, the angle of the point and X-axis positive direction is calculated, just obtains the red footpath of ascending node.
According to perigee position and ascending node position, calculate the two and just obtain lunar orbit relative to the angle of the earth's core radius vector Argument of pericenter.
Orbit inclination angle can be obtained directly from almanac data.
S102：The systematic parameter of radar is set according to lunar orbit parameter and observation requirementses；
The observations such as mapping bandwidth as needed, resolution ratio, irradiation duration require to set the systematic parameter of radar, the system Parameter can include：Antenna size, transmitted wave carrier frequency f0, frequency modulation rate Kr, PRF (Pulse Recurrence Frequency, arteries and veins Rush repetition rate), antenna look angle, radar site etc..Following requirement is provided with to these parameters：Radar beam need to cover the earth While do not produce substar echo；PRF is sufficiently high to ensure echo bearing to not aliasing；Radar is laid in moon equator, emulation Central instant face the earth's core.Wherein, transmitted wave frequency modulation rate KrAnd pulse duration TrDetermine transmitted wave bandwidth, i.e. distance To resolution ratio.Accumulated time TaDetermine azimuth resolution.Antenna look angle θaAnd antenna size determine wave beam sensing and Coverage, meanwhile, wave beam can not deviate the earth.Think radar heart moment face earth geocentric position in simulations.And the moon There is angle between equator and moon revolution track, equivalent moon carrier yaw angle yaw=0, angle of pitch pitch=0, roll angle Roll=6.67 °.
S103：According to moon almanac data determine echo simulation central instant and the moment corresponding to beam position Put；
Step S103 can include following processing procedure：
Do not rotated in object time according to position of the antenna phase center in moon celestial body coordinate system and the moon Position in geocentric coordinate system determines position of the aiming point of wave beam in geocentric coordinate system is rotated；Existed according to the aiming point of wave beam Rotate the coordinate of the position acquisition beam center point in geocentric coordinate system, and longitude and latitude corresponding to center point coordinate Degree；Position corresponding to beam center is chosen, and is defined as the simulation centre moment at the time of by the position correspondence.
Example, above-mentioned processing procedure can be accomplished by the following way.
By moon almanac data interpolation to PRI (Pulse Repetition Interval, pulse repetition period), the moon is taken Ball was 0 moment when being located at perigee of orbit, while thought during 0 moment the earth first meridian just past the first point of Aries, in ephemeris Moon position information it is as shown in Figure 3.
Any instant t is taken, calculates the moon eccentric angle E and nearly heart angle θ at the moment；
The eccentric angle E and nearly heart angle θ of the moment moon are calculated according to formula (11) (12) (13) successively；
M=nt (3)
Wherein, M is the averagely near heart angle of the moon, and n is that the moon averagely revolves round the sun angular speed.
It is assumed that antenna phase center (antenna coordinate system origin) is (x relative to the position of moon celestial body coordinate systeme,ye, ze)；Moon moment t in the geocentric coordinate system not rotated position (x is obtained according to the almanac data after interpolationos,yos,zos), That is position of the satellite platform coordinate origin in motionless geocentric coordinate system；Establish any point (x in antenna coordinate systema,ya, za) coordinate (x in the geocentric coordinate system of rotationg,yg,zg) expression formula, i.e.,：
Wherein, Ago、Aov、Avr、Are、AeaIt is as follows for the used matrix of coordinate system conversion：
Coordinate is never rotated to geocentric coordinate system and is transformed into rotation geocentric coordinate system, HG For Greenwich hour angle (GHA).
By coordinate from orbit plane coordinate System, which is transformed into, does not rotate geocentric coordinate system, and Ω is the red footpath of ascending node,iFor orbit inclination angle, ω is argument of pericenter.
Coordinate is transformed into orbit plane coordinate from satellite platform coordinate system System,|γ|≤90°。
Coordinate is transformed into satellite platform coordinate system from satellite health coordinate system.
By coordinate antenna coordinate system from being transformed into satellite health coordinate system, it is believed that emulation Central instant yaw angle yaw=0, angle of pitch pitch=0, roll=6.67 ° of roll angle.
Because the Y-axis of antenna coordinate system overlaps with antenna boresight, thus in coordinate system aiming point coordinate (0, y, 0), Expression formula (1) is substituted into, the coordinate of the antenna aiming point in the geocentric coordinate system just rotated：
Bring formula (7) into earth model shown in formula (8), solving y (getting the small value), generation returns formula (7) again, tries to achieve aiming point and exists Rotate the coordinate (x in geocentric coordinate systemgo,ygo,zgo)；
The then longitude Λ of the moment beam center point, latitude φ are respectively as shown in formula (9), (10)：
From t, all moon positions, beam center point coordinates corresponding to acquisition are traveled through by PRF step-lengths；Take needs Beam center position longitude and latitude, and will corresponding moment t0As the simulation centre moment.
S104：Point target is set in the range of beam position, and point target is being shone during echo simulation Penetrate target；
Step S104 can include following processing procedure：
It is determined that the first position in echo simulation start time antenna phase center in terrestrial coordinate system is rotated；It is determined that The second place of the echo simulation start time point target in terrestrial coordinate system is rotated；According to first position and the second place Judge whether point target is arrived by beam with respect to radius vector；The phase of echo of the point target arrived by beam is obtained, according to imitative True to need, the diverse location cloth around heart moment beam center point sets up an office or dot matrix in simulations, for example, the target used is laid Form can be single-point target and be respectively perpendicular to orientation and distance to 9 dot matrix.
S105：The echo data of point target is obtained based on systematic parameter.
If radar illumination time span is Ta, then need to begin stepping through along PRI step-lengths from irradiation initial time, any time tPEcho simulation process it is as follows：
If tPPosition of the moment moon in geocentric coordinate system is not rotated is (xps,yps,zps), seek tPMoment, antenna phase Position (x of the center in terrestrial coordinate system is rotatedap,yap,zap)：
Wherein, A is calculatedreWhen required yaw angle yaw because the influence of longitude libration is not now 0.
Yaw=ρ1-ρ2 (12)
In formula (12), ρ1For the moment to simulation centre moment moon revolution angle, ρ2For the moment to simulation centre when Carve moon rotation angle.
If position vector of the moment point target in geocentric coordinate system is rotated is (xtar,ytar,ztar), it can calculate Relative vector of the point target with antenna phase center in same coordinate system be：
It can judge whether this moment point target is within wave beam 3dB width according to Δ R；Covered for being in wave beam 3dB Point target in the range of lid, its echo phase information can be expressed as：
In formula (14), c is the light velocity, and t is the time that electromagnetic wave comes and goes experience；The moment echo data is recorded, and is carried out Emulate in next step.Complete TaAfter interior all moment simulation results, echo data and key parameter are preserved.
Point target emulation is carried out to the echo data that the radar return data capture method provided using the disclosure is got Checking, single-point echo result are as shown in Figure 4.And imaging checking is carried out to single-point and 9 echo results.Table 1, which gives, to be emulated The part radar parameter of journey.
Fig. 5 is the imaging schematic diagram of the single-point target echo simulation according to an exemplary embodiment, based on the imaging Schematic diagram can verify the correctness of echo.Wherein, the black star-shaped section shown in Fig. 5 is point target, white portion in figure For the part in the absence of point target, it is necessary to illustrate, in actually detected obtained image, the part in the absence of point target is Black, point target part be present then has certain brightness, is only a kind of schematic diagram for being used for highlighting point target in Fig. 5. Fig. 6 (part of point target is consistent with Fig. 5 with the method for expressing of the part in the absence of point target in the Fig. 6) is exemplary according to one Implement the 9 dot matrix simulation imaging schematic diagrames exemplified, diverse location can be can be seen that according to the simulation imaging result of 9 dot matrix Point target can obtain effective energy compression, demonstrate the echo simulation method of disclosure offer have it is higher correct Property and validity.
Table 1
The disclosure additionally provides a kind of echo simulation device, and Fig. 7 is the echo simulation according to an exemplary embodiment The structured flowchart of device, as shown in fig. 7, the device 70 includes following part：
Computing module 71, for calculating lunar orbit parameter according to moon almanac data；
Wherein, lunar orbit parameter includes at least one of following：Orbital eccentricity, perigee position, ascending node position, liter The red footpath of intersection point, argument of pericenter and orbit inclination angle.
First setup module 72, for setting the systematic parameter of radar according to lunar orbit parameter and observation requirementses；
Wherein, the systematic parameter of radar can include at least one of following parameter：
Transmitted wave frequency modulation rate, pulse duration, beam time, antenna look angle, antenna size and radar site.
Determining module 73, for being determined according to moon almanac data corresponding to central instant and moment of echo simulation Beam position；
Second setup module 74, for setting point target in the range of beam position, point target is to be imitated in echo Illuminated target during true；
Acquisition module 75, for obtaining the echo data of point target based on systematic parameter.
Example, above-mentioned determining module 73 can include：First determining unit, for according to antenna phase center in the moon The position in geocentric coordinate system is rotated at position and the moon in celestial body coordinate system heart moment in simulations determines wave beam Position of the aiming point in geocentric coordinate system is rotated；First acquisition unit, the earth's core seat is being rotated for the aiming point according to wave beam The coordinate of position acquisition beam center point in mark system, and longitude and latitude corresponding to center point coordinate；Second determines Unit, it is defined as the simulation centre moment for choosing position corresponding to beam center, and at the time of by the position correspondence.
Example, above-mentioned second setup module 74 can include：3rd determining unit, for determining to start in echo simulation First position of the moment antenna phase center in terrestrial coordinate system is rotated；4th determining unit, for determining in echo simulation The second place of the start time point target in terrestrial coordinate system is rotated；Judging unit, for according to first position and second The relative radius vector of position judges whether point target is arrived by beam；Second acquisition unit, for obtaining what is arrived by beam The phase of echo of point target.
The preferred embodiment of the disclosure is described in detail above in association with accompanying drawing, still, the disclosure is not limited to above-mentioned reality The detail in mode is applied, in the range of the technology design of the disclosure, a variety of letters can be carried out to the technical scheme of the disclosure Monotropic type, these simple variants belong to the protection domain of the disclosure.
It is further to note that each particular technique feature described in above-mentioned embodiment, in not lance In the case of shield, it can be combined by any suitable means.In order to avoid unnecessary repetition, the disclosure to it is various can The combination of energy no longer separately illustrates.
In addition, it can also be combined between a variety of embodiments of the disclosure, as long as it is without prejudice to originally Disclosed thought, it should equally be considered as disclosure disclosure of that.

Claims (10)

  1. A kind of 1. echo simulation method, it is characterised in that including：
    Lunar orbit parameter is calculated according to moon almanac data；
    The systematic parameter of radar is set according to the lunar orbit parameter and observation requirementses；
    According to the moon almanac data determine the echo simulation central instant and the moment corresponding to beam position Put；
    Point target is set in the range of the beam position, and the point target is to be shone during the echo simulation The target penetrated；
    The echo data of the point target is obtained based on the systematic parameter.
  2. 2. according to the method for claim 1, it is characterised in that described that the echo is determined according to the moon almanac data Beam position corresponding to the central instant of emulation and the moment, including：
    According to position of the antenna phase center in moon celestial body coordinate system and the moon in simulations the heart moment in the rotationally heart Position in coordinate system determines position of the aiming point of wave beam in geocentric coordinate system is rotated；
    According to the coordinate of position acquisition beam center point of the aiming point of wave beam in geocentric coordinate system is rotated, and the center Longitude and latitude corresponding to point coordinates；
    Choose position corresponding to the beam center, and be defined as the simulation centre moment at the time of by the position correspondence.
  3. 3. according to the method for claim 1, it is characterised in that the set-point in the range of the beam position Target, including：
    It is determined that the first position in the echo simulation start time antenna phase center in terrestrial coordinate system is rotated；
    It is determined that in the second place of the point target in terrestrial coordinate system is rotated described in the echo simulation start time；
    Judge whether the point target is arrived by beam according to the relative radius vector of the first position and the second place；
    Obtain the phase of echo of the point target arrived by beam.
  4. 4. according to the method for claim 1, it is characterised in that the lunar orbit parameter includes at least one of following：
    Orbital eccentricity, perigee position, ascending node position, the red footpath of ascending node, argument of pericenter and orbit inclination angle.
  5. 5. according to the method described in Claims 1-4 any one, it is characterised in that the systematic parameter of the radar include with It is at least one of lower：
    Transmitted wave frequency modulation rate, pulse duration, beam time, antenna look angle, antenna size and radar site.
  6. A kind of 6. echo simulation device, it is characterised in that including：
    Computing module, for calculating lunar orbit parameter according to moon almanac data；
    First setup module, for setting the systematic parameter of radar according to the lunar orbit parameter and observation requirementses；
    Determining module, the central instant and the moment for determining the echo simulation according to the moon almanac data are corresponding Beam position；
    Second setup module, for setting point target in the range of the beam position, the point target is described Illuminated target during echo simulation；
    Acquisition module, for obtaining the echo data of the point target based on the systematic parameter.
  7. 7. device according to claim 6, it is characterised in that the determining module, including：
    First determining unit, for according to position of the antenna phase center in moon celestial body coordinate system and the moon in simulations Position of the aiming point that wave beam is determined in the position in rotating geocentric coordinate system at heart moment in geocentric coordinate system is rotated；
    First acquisition unit, for position acquisition beam center point of the aiming point according to wave beam in geocentric coordinate system is rotated Coordinate, and longitude and latitude corresponding to the center point coordinate；
    Second determining unit, it is defined as institute for choosing position corresponding to the beam center, and at the time of by the position correspondence State the simulation centre moment.
  8. 8. device according to claim 6, it is characterised in that second setup module, including：
    3rd determining unit, for determining in the echo simulation start time antenna phase center in terrestrial coordinate system is rotated First position；
    4th determining unit, for determining in point target described in the echo simulation start time in terrestrial coordinate system is rotated The second place；
    Judging unit, for whether judging the point target according to the relative radius vector of the first position and the second place Arrived by beam；
    Second acquisition unit, for obtaining the phase of echo of the point target arrived by beam.
  9. 9. device according to claim 6, it is characterised in that the lunar orbit parameter includes at least one of following：
    Orbital eccentricity, perigee position, ascending node position, the red footpath of ascending node, argument of pericenter and orbit inclination angle.
  10. 10. according to the device described in claim 6 to 9 any one, it is characterised in that the systematic parameter of the radar include with It is at least one of lower：
    Transmitted wave frequency modulation rate, pulse duration, beam time, antenna look angle, antenna size and radar site.
CN201710642415.2A 2017-07-31 2017-07-31 Echo simulation method and device Active CN107526066B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710642415.2A CN107526066B (en) 2017-07-31 2017-07-31 Echo simulation method and device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710642415.2A CN107526066B (en) 2017-07-31 2017-07-31 Echo simulation method and device

Publications (2)

Publication Number Publication Date
CN107526066A true CN107526066A (en) 2017-12-29
CN107526066B CN107526066B (en) 2020-08-28

Family

ID=60680374

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710642415.2A Active CN107526066B (en) 2017-07-31 2017-07-31 Echo simulation method and device

Country Status (1)

Country Link
CN (1) CN107526066B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108896038A (en) * 2018-05-15 2018-11-27 中国科学院遥感与数字地球研究所 Month base optical sensor imaging method
CN111025246A (en) * 2019-11-28 2020-04-17 北京遥测技术研究所 Simulation system and method for composite scene imaging of sea surface and ship by using stationary orbit SAR
CN114254485A (en) * 2021-11-25 2022-03-29 清华大学 Radar signal simulation method for micro-motion state of artificial satellite

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090224964A1 (en) * 2007-05-08 2009-09-10 Raney Russell K Synthetic aperture radar hybrid-polarity method and architecture for obtaining the stokes parameters of a backscattered field
US20110078498A1 (en) * 2009-09-30 2011-03-31 United States Of America As Represented By The Administrator Of The National Aeronautics And Spac Radiation-hardened hybrid processor
CN102565799A (en) * 2012-01-31 2012-07-11 北京航空航天大学 Unified simulation realization method of multiple-platform multiple-mode SAR (Specific Absorption Rate) echo
CN102879768A (en) * 2012-09-14 2013-01-16 北京航空航天大学 Satellite-borne synthetic aperture radar (SAR) high-fidelity echo simulation method based on steady-state radar cross section (RCS)

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090224964A1 (en) * 2007-05-08 2009-09-10 Raney Russell K Synthetic aperture radar hybrid-polarity method and architecture for obtaining the stokes parameters of a backscattered field
US20110078498A1 (en) * 2009-09-30 2011-03-31 United States Of America As Represented By The Administrator Of The National Aeronautics And Spac Radiation-hardened hybrid processor
CN102565799A (en) * 2012-01-31 2012-07-11 北京航空航天大学 Unified simulation realization method of multiple-platform multiple-mode SAR (Specific Absorption Rate) echo
CN102879768A (en) * 2012-09-14 2013-01-16 北京航空航天大学 Satellite-borne synthetic aperture radar (SAR) high-fidelity echo simulation method based on steady-state radar cross section (RCS)

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
丁翼星等: ""基于JPL星历的月基SAR多普勒参数估算方法"", 《北京航空航天大学学报》 *
丁翼星等: ""月基对地观测合成孔径雷达系统性能初探"", 《2011第二十四届全国空间探测学术交流会论文》 *
帅平等: "《X射线脉冲星导航系统原理与方法》", 31 July 2009, 中国宇航出版社 *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108896038A (en) * 2018-05-15 2018-11-27 中国科学院遥感与数字地球研究所 Month base optical sensor imaging method
CN108896038B (en) * 2018-05-15 2022-03-25 中国科学院遥感与数字地球研究所 Imaging method of lunar-based optical sensor
CN111025246A (en) * 2019-11-28 2020-04-17 北京遥测技术研究所 Simulation system and method for composite scene imaging of sea surface and ship by using stationary orbit SAR
CN111025246B (en) * 2019-11-28 2021-09-07 北京遥测技术研究所 Simulation system and method for composite scene imaging of sea surface and ship by using stationary orbit SAR
CN114254485A (en) * 2021-11-25 2022-03-29 清华大学 Radar signal simulation method for micro-motion state of artificial satellite
CN114254485B (en) * 2021-11-25 2024-04-19 清华大学 Radar signal simulation method for microscale state of artificial satellite

Also Published As

Publication number Publication date
CN107526066B (en) 2020-08-28

Similar Documents

Publication Publication Date Title
CN102565797B (en) Geometric correction method for spotlight-mode satellite SAR (synthetic aperture radar) image
Konopliv et al. The Vesta gravity field, spin pole and rotation period, landmark positions, and ephemeris from the Dawn tracking and optical data
CN107238824B (en) Satellite-borne SAR image geometric accurate correction method based on priori dem data
CN101915920B (en) High-resolution imaging method for earth synchronous orbit synthetic aperture radar satellite
CN103605887B (en) A kind of satellite in orbit imaging rough water sun glitter simulation model for space-time distribution
CN105158777B (en) The data source generation method positioned for passive direction finding
CN107765226B (en) SAR satellite radar echo simulation method, system and medium
CN101414003B (en) Star-loaded SAR image geocoding method based on star ground coordinate transformation
CN103197291B (en) Satellite-borne synthetic aperture radar (SAR) echo signal simulation method based on non-stop walking model
Ren et al. Simulation study of geometric characteristics and coverage for moon-based earth observation in the electro-optical region
CN106767705A (en) Imaging posture modeling method during a kind of Optical remote satellite point target observation mission is dynamic
CN102621994B (en) Control method of geosynchronous earth orbit (GEO) synthetic aperture radar (SAR) for covering all over China
CN107526066A (en) A kind of echo simulation method and device
CN102819019B (en) Method for determining intersection coordinates of satellite wave beam and earth
CN105067120A (en) Dynamic filtering and re-sampling method and dynamic filtering and re-sampling device for brightness temperature observation of space-borne microwave radiometer
CN109521424A (en) The spaceborne Sliding spotlight SAR attitude of satellite and PRF sequence design methodology
CN101846740B (en) Satellite-loaded SAR specified latitude area echo simulation method
CN105444778A (en) Star sensor in-orbit attitude determination error obtaining method based on imaging geometric inversion
CN103675773A (en) Scaler and satellite pointing alignment determination method
CN110929427A (en) Remote sensing satellite video imaging rapid simulation method
CN103344958B (en) Based on the satellite-borne SAR high-order Doppler parameter evaluation method of almanac data
CN104123461A (en) Lighting visual relation calculating method for photometric analysis of space object
CN111856423A (en) Satellite-borne SAR echo simulation processing method, device and equipment
Campbell et al. The mean rotation rate of Venus from 29 years of Earth-based radar observations
CN108896038B (en) Imaging method of lunar-based optical sensor

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant