CN117150184A - Satellite ephemeris-based space-based optical equipment measurement data simulation algorithm - Google Patents
Satellite ephemeris-based space-based optical equipment measurement data simulation algorithm Download PDFInfo
- Publication number
- CN117150184A CN117150184A CN202311408732.XA CN202311408732A CN117150184A CN 117150184 A CN117150184 A CN 117150184A CN 202311408732 A CN202311408732 A CN 202311408732A CN 117150184 A CN117150184 A CN 117150184A
- Authority
- CN
- China
- Prior art keywords
- space
- based optical
- optical device
- satellite
- shadow
- 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
Links
- 230000003287 optical effect Effects 0.000 title claims abstract description 165
- 238000005259 measurement Methods 0.000 title claims abstract description 39
- 238000004422 calculation algorithm Methods 0.000 title claims abstract description 22
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 claims abstract description 46
- 238000004088 simulation Methods 0.000 claims abstract description 39
- 238000000034 method Methods 0.000 claims abstract description 31
- 238000013461 design Methods 0.000 claims abstract description 21
- 238000004364 calculation method Methods 0.000 claims description 23
- 239000011159 matrix material Substances 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 description 9
- 238000011156 evaluation Methods 0.000 description 7
- 241000282414 Homo sapiens Species 0.000 description 2
- 241000764238 Isis Species 0.000 description 2
- HOWHQWFXSLOJEF-MGZLOUMQSA-N systemin Chemical compound NCCCC[C@H](N)C(=O)N[C@@H](CCSC)C(=O)N[C@@H](CCC(N)=O)C(=O)N[C@@H]([C@@H](C)O)C(=O)N[C@@H](CC(O)=O)C(=O)OC(=O)[C@@H]1CCCN1C(=O)[C@H]1N(C(=O)[C@H](CC(O)=O)NC(=O)[C@H](CCCN=C(N)N)NC(=O)[C@H](CCCCN)NC(=O)[C@H](CO)NC(=O)[C@H]2N(CCC2)C(=O)[C@H]2N(CCC2)C(=O)[C@H](CCCCN)NC(=O)[C@H](CO)NC(=O)[C@H](CCC(N)=O)NC(=O)[C@@H](NC(=O)[C@H](C)N)C(C)C)CCC1 HOWHQWFXSLOJEF-MGZLOUMQSA-N 0.000 description 2
- 108010050014 systemin Proteins 0.000 description 2
- 239000002253 acid Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011002 quantification Methods 0.000 description 1
- 238000011158 quantitative evaluation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000017105 transposition Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
- G06F17/10—Complex mathematical operations
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Mathematical Physics (AREA)
- Data Mining & Analysis (AREA)
- General Physics & Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Computational Mathematics (AREA)
- Pure & Applied Mathematics (AREA)
- Databases & Information Systems (AREA)
- Software Systems (AREA)
- General Engineering & Computer Science (AREA)
- Algebra (AREA)
- Navigation (AREA)
Abstract
The invention discloses a satellite ephemeris-based space-based optical equipment measurement data simulation algorithm, which comprises the following steps: s1, obtaining an observed target earth fixed system ephemeris and an observed space base optical device earth fixed system ephemeris, and configuring a space base optical device operation parameter file, a planet ephemeris file and an earth rotation parameter file; s2, calculating whether the geometry is visible; s3, viewing distanceAzimuth angleAnd pitch angleWhether the design index of the space-based optical device is satisfied; s4, calculating whether the observed target is in the ground shadow or the moon shadow; s5, opening angleDetermining whether the threshold is greater thanThe method comprises the steps of carrying out a first treatment on the surface of the S6, calculating the simulation data red warpDeclination of weftS7, traversing time periodThe simulation data is stored. According to the invention, through judging the observation conditions of various space-based optical devices, the simulation measurement data of the space-based optical devices are ensured to accord with the real tracking scene, so that theoretical support can be provided for the requirement demonstration before the space-based optical devices are on the day, and support is provided for other scenes needing the simulation of the measurement data of the space-based optical devices.
Description
Technical Field
The invention relates to the technical field of data measurement of space-based optical equipment, in particular to a satellite ephemeris-based space-based optical equipment measurement data simulation algorithm.
Background
With the development of satellite technology and the continuous enhancement of space entering and space utilization capability of human beings, the influence of space on human society is larger and larger, and the enhancement of space control is more and more necessary. The space monitoring system is an important means for space control, and mainly comprises a foundation space target monitoring system and a space-based space target monitoring system, wherein the space-based space target monitoring system is an effective supplementary means for the foundation space target monitoring system because the space-based space target monitoring system is not limited by weather conditions, has a wide working range and the like. Because the current space-based space target monitoring system mainly uses optical detection, in order to plan the space-based optical equipment satellite orbit, the space monitoring capability of the satellite after the satellite is on the sky is estimated, and the simulation work is very important. The method comprehensively considers various limiting factors such as various working indexes, tracking conditions and the like of the space-based optical equipment, simulates the tracking environment of the space-based optical equipment as far as possible, simulates and generates simulated tracking measurement data, and provides a basis for satellite orbit design, constellation design and satellite efficiency evaluation.
Patent document CN103093098B discloses a quantitative evaluation method for satellite optical sensor dynamic observation capability, which relates to a sensor space-time coverage capability value, a theme observation capability value, an observation environment value and a fuzzy comprehensive evaluation value for satellite optical sensor observation capability evaluation, and has the characteristics of quantification and dynamics, but also has the following steps: 1. the observation capability evaluation is limited to an entity optical satellite, and can not be used for calculating simulation observation of the satellite and evaluating space monitoring capability of the satellite after the satellite is on the day; 2. the satellite parameter range related to the observation capability evaluation is limited, and a basis cannot be provided for satellite orbit design, constellation design and satellite performance evaluation.
Disclosure of Invention
The invention aims to provide a satellite ephemeris-based space-based optical equipment measurement data simulation algorithm, which simulates limiting conditions of space-based optical equipment on measurement of an observed target, so that the acquired simulation measurement data accords with a real tracking scene, and more accurate simulation measurement data is acquired.
The aim of the invention can be achieved by the following technical scheme: a satellite ephemeris-based simulation algorithm for measuring data of a space-based optical device, comprising the following steps:
s1, obtaining the earth fixed ephemeris of the observed targetEarth fixed system ephemeris for space-based optical equipmentConfiguring an operation parameter file, a planet ephemeris file and an earth rotation parameter file of the space-based optical equipment, wherein；
S2, in the time periodIn, according to the set step length, calculating the timeGround tie-down position velocity of observed objectAnd earth-fixed system position speed of space-based optical equipmentThe method comprises the steps of carrying out a first treatment on the surface of the According toAndcalculating whether the observed object and the space-based optical device are geometrically visible;
s3, if the observed object is geometrically visible with the space-based optical device, thenAndrespectively transposed to the space-based optical equipment body coordinate systemIn the body coordinate systemNext, the distance of the observed object in the space-based optical device is calculatedAzimuth angleAnd pitch angleViewing distanceAzimuth angleAnd pitch angleWhether the design index of the space-based optical device is satisfied;
if the observed object is not visible to the space-based optical device geometry, returning to S2 for the next step size calculation;
s4, if the distanceAzimuth angleAnd pitch angleIf the design index of the space-based optical equipment is met, calculating whether the observed target is in the ground shadow or the moon shadow;
if the distance isAzimuth angleAnd pitch angleIf the design index of the space-based optical equipment is not met, returning to S2 to perform the next step calculation;
s5, if the observed object is not in the ground shadow or the moon shadow, calculating the solar vector of the space-based optical equipmentVector of observed target with space-based optical deviceOpening angle of (a)To the opening angleJudging whether the value is smaller than a threshold value;
if the observed target is in the ground shadow or the moon shadow, returning to S2 to perform the next step calculation;
s6, if the opening angleIf the measured data is not smaller than the threshold value, calculating the simulation measurement data of the space-based optical equipmentDeclination of weftThen returning to S2 for the next step calculation;
if the opening angleIf the step size is smaller than the threshold value, returning to S2 to perform next step size calculation;
s7, traversing the time period according to the set step lengthThe simulated measurement data is stored.
Further: the operation parameter file of the configured space-based optical device in the step S1 comprises the following steps: simulation start time, simulation end time, simulation data step length, observed target code number, space-based optical device code number.
Further: according to the S2Andthe formula for calculating whether the observed object and the space-based optical device are geometrically visible is as follows:
wherein:
RE is the earth radius, FE is the earth's flatness, SS, SA, SB, SC, DX, DY, DZ and G2 are process variables;、、is thatThree components of the three-dimensional vector are,、、is thatThree components of the three-dimensional vector;
when SS <0, the observed object is geometrically visible to the space-based optics.
Further: when SS is more than or equal to 0, according to the formulaThe method for judging whether the observed object and the space-based optical device are geometrically visible is as follows:
when SB (SB)<0, calculate，；
If K1<0 and K2<0, the observed object is geometrically visible with the space based optics;
when SB is more than or equal to 0, calculate，；
If K1>1 and K2>1, the observed object is geometrically visible with the space based optical device.
Further: calculating the distance of the observed object in the space-based optical device in the S3Azimuth angleAnd pitch angleThe process of (1) is as follows:
s31, willAndare respectively transposed toAn inertial coordinate system; obtaining the position and speed of the inertial coordinate system of the observation targetInertial coordinate system position and velocity of space-based optical device；
S32, willAndrespectively transposed to the space-based optical equipment body coordinate systemObtaining:
wherein the method comprises the steps ofIs thatInertial coordinate system to space-based optical equipment body coordinate systemIs a transposed matrix of (a);
s33, orderThen
Wherein (x, y, z) isIs provided with a plurality of position points,distance of the observed object in the space-based optical device;azimuth angle of observed object in space-based optical device；Is the pitch angle of the observed object in the space-based optical device.
Further: the ground shadow and the moon shadow in the step S4 respectively comprise a home shadow, a penumbra and an artifact.
Further: the process of calculating whether the observed target is in the ground shadow in S4 is as follows:
；
；
；
；
wherein the method comprises the steps ofAs a satellite-to-sun vector,as a modulus of this vector,is the solar opening angle of the earth satellite,in order to look at the radius of the sun on the satellite,in order to look at the radius of the earth on the satellite,is the earth radius;
when (when)，/>When the satellite is in the earth shadow area;
when (when)，/>The satellite is in the earth half-shadow area;
the process of calculating whether the observed object is in the moon shadow in the step S4 is as follows:
；
；
；
；
in the middle ofFor the satellite to moon vector, +.>Is a modulus of the vector, +.>Is the sun opening angle of the lunar satellite +.>To look at the radius of the sun on the satellite, +.>To look at the radius of the moon on the satellite, +.>Is the radius of moon;
when (when)，/> When the satellite is in the lunar originally-shadow area;
when (when)，/>，/>When the satellite is in the moon artifact area;
when (when)，/>The satellite is in the moon half-shadow.
Further: calculating solar vector of space-based optical equipment in S5Vector of observed target with space-based optical deviceOpening angle of (a)The formula of (2) is:
；
wherein,for the solar vector of the space-based optical device,the target vector is observed for the space-based optical device.
Further: calculating the simulation data red warp of the space-based optical equipment in the step S6Declination of weftThe formula of (2) is:
；
；
；
；
wherein the method comprises the steps ofIs thatIs provided with a plurality of position points,for simulating data right ascension，And (5) declination is performed for simulation data.
The invention has the beneficial effects that:
the invention provides a simulation algorithm for simulating measurement data of a space-based optical device, which considers whether an observed object is geometrically visible with the space-based optical device or not and the distance between the observed object and the space-based optical deviceAzimuth angleAnd pitch angleWhether the design index of the space-based optical device is satisfied, whether the observed object is in the ground shadow or the moon shadow, and the opening angleWhether the observation conditions of various space-based optical devices such as a threshold condition are larger or not is ensured, simulation measurement data of the space-based optical devices are in accordance with real tracking scenes, theoretical support can be provided for demand demonstration before the space-based optical devices are on the day, and support is provided for other scenes needing simulation of the measurement data of the space-based optical devices.
Drawings
FIG. 1 is a flow chart of a satellite ephemeris-based simulation algorithm for measuring data of a space-based optical device;
FIG. 2 is a schematic view of a cone-shaped ground shadow structure according to the present invention;
FIG. 3 is a schematic diagram of the geometrical relationships of the inventive space-based optical device, sun, moon and earth.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar symbols indicate like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are exemplary only for explaining the present invention and are not to be construed as limiting the present invention.
As shown in fig. 1-3, the invention discloses a satellite ephemeris-based space-based optical equipment measurement data simulation algorithm, which comprises the following steps:
s1, obtaining the earth fixed ephemeris of the observed targetEarth fixed system ephemeris for space-based optical equipmentConfiguring an operation parameter file, a planet ephemeris file and an earth rotation parameter file of the space-based optical equipment, wherein；
S2, in the time periodIn, according to the set step length, calculating the timeGround tie-down position velocity of observed objectAnd earth-fixed system position speed of space-based optical equipmentThe method comprises the steps of carrying out a first treatment on the surface of the According toAndcalculating whether the observed object and the space-based optical device are geometrically visible;
s3, if the observed object is geometrically visible with the space-based optical device, thenAndrespectively transposed to the space-based optical equipment body coordinate systemIn the body coordinate systemNext, the distance of the observed object in the space-based optical device is calculatedAzimuth angleAnd pitch angleViewing distanceAzimuth angleAnd pitch angleWhether the design index of the space-based optical device is satisfied;
if the observed object is not visible to the space-based optical device geometry, returning to S2 for the next step size calculation;
s4, if the distanceAzimuth angleAnd pitch angleIf the design index of the space-based optical equipment is met, calculating whether the observed target is in the ground shadow or the moon shadow;
if the distance isAzimuth angleAnd pitch angleIf the design index of the space-based optical equipment is not met, returning to S2 to perform the next step calculation;
s5, if the observed object is not in the ground shadow or the moon shadow, calculating the solar vector of the space-based optical equipmentVector of observed target with space-based optical deviceOpening angle of (a)To the opening angleJudging whether the value is smaller than a threshold value;
if the observed target is in the ground shadow or the moon shadow, returning to S2 to perform the next step calculation;
s6, if the opening angleIf the measured data is not smaller than the threshold value, calculating the simulation measurement data of the space-based optical equipmentDeclination of weftThen returning to S2 for the next step calculation;
if the opening angleIf the step size is smaller than the threshold value, returning to S2 to perform next step size calculation;
s7, traversing the time period according to the set step lengthThe simulated measurement data is stored.
According to the simulation requirement, the observed target and the space-based optical equipment are set, various limiting factors such as the working index, the tracking condition and the like of the space-based optical equipment are required to be comprehensively considered, the tracking environment of the space-based optical equipment is simulated, and the simulated tracking measurement data are generated in a simulation mode.
The method can set the simulation start time, the simulation end time, the simulation data step length and the observed target code of the space-based optical equipment by configuring the running parameter file of the space-based optical equipment, can simulate the working index of the space-based optical equipment by the files such as the planet ephemeris file, the earth rotation parameter and the like, can simulate various limiting factors such as the working environment, the tracking condition and the like of the space-based optical equipment, and provides a basis for the track design, the constellation design and the evaluation of the efficiency of the space-based optical equipment.
After the simulation environment setting of the space-based optical device is completed, the time period is thatIn, obtain the earth fixed ephemeris of the observed targetEarth fixed system ephemeris for space-based optical equipment。
Setting the step length to be uniform time interval according to the set step lengthLong through configuration of space-based optical equipment operation parameter file acquisition, in time periodInternal computingCalculating the observed target ground fixed system position speed of the required time T by adopting an interpolation algorithmAnd earth-fixed system position speed of space-based optical equipmentThe interpolation algorithm adopts a classical Lagrange interpolation algorithm, which is a public technology and will not be described here.
By passing throughAndit can be calculated whether both are occluded by the earth, if not, it is indicated inThe observed object at the moment is visible relative to the geometry of the space-based optical equipment at the moment, and the next calculation is continued;
if there is occlusion, then it is indicated inThe observed object is invisible relative to the space-based optical device at the moment, and the observed object and the space-based optical device are described in the followingThe simulation measurement data is not required to be further calculated at any time, and the next step can be directly calculated according to the set step.
In particular, according toAndthe formula for calculating whether the observed object and the space-based optical device are geometrically visible is as follows:
wherein:
RE is the earth radius, and FE is the earth flatness; SS, SA, SB, SC, DX, DY, DZ and G2 are process variables;
when SS <0, the observed object is geometrically visible with the space-based optics;
when SS is more than or equal to 0: when SB (SB)<0, calculate，The method comprises the steps of carrying out a first treatment on the surface of the When SB is more than or equal to 0, calculate，The method comprises the steps of carrying out a first treatment on the surface of the If K1<0 and K2<0, the observed object is geometrically visible with the space-based optical device; if K1>1 and K2>1, the observed object is geometrically visible to the space-based optical device.
For the observed object meeting geometric visibility and the space-based optical device, continuously calculating the distance of the observed object in the space-based optical deviceAzimuth angleAnd pitch angleViewing the distance of an observed object in a space-based optical deviceAzimuth angleAnd pitch angleWhether the design index of the space-based optical device is satisfied;
if the distance of the observed object in the space-based optical deviceAzimuth angleAnd pitch angleDoes not meet the design index of the space-based optical equipment, and indicates that the observed object and the space-based optical equipment are in the same stateThe simulation measurement data is not required to be further calculated at any time, and the next step can be directly calculated according to the set step.
Specifically, the distance of the observed object in the space-based optical device is calculatedAzimuth angleAnd pitch angleThe process of (1) is as follows:
will beAndtransposed from ground-fixed system coordinates toThe inertial coordinate system adopts a transposition algorithm in the prior art, which is not described herein, and the position and speed of the inertial coordinate system of the observation target are obtained through transpositionInertial coordinate system position and velocity of space-based optical device。
And then will beAndrespectively transposed to the space-based optical equipment body coordinate systemObtaining:
wherein the method comprises the steps ofIs thatInertial coordinate system to space-based optical equipment body coordinate systemIs a transposed matrix of (a);
reams theThen
Wherein (x, y, z) isIs provided with a plurality of position points,distance of the observed object in the space-based optical device;in space-based optical devices for objects to be observedAzimuth angle；Is the pitch angle of the observed object in the space-based optical device.
By the determined distanceAzimuth angleAnd pitch angleIf the distance of the observed object in the space-based optical deviceAzimuth angleAnd pitch angleAnd if the design index of the space-based optical equipment is met, the next calculation is continued, and whether the observed target is in the ground shadow or the moon shadow is judged.
If the observed object is in the ground shadow or moon shadow, the observed object cannot be detected by the space-based optical device, which means that the observed object and the space-based optical device are in the ground shadow or moon shadowThe simulation measurement data is not required to be further calculated at any time, and the next step can be directly calculated according to the set step.
As shown in fig. 2 and 3, the ground shadow and the moon shadow include a home shadow, a penumbra and an artifact, respectively; interpolation calculation by reading the ephemeris fileCalculating the positions of the sun and moon at the moment and calculating the observed targetIn the case of the ground shadow or the moon shadow, since the observed object is not irradiated with light at this time, and is theoretically visible from the spatial relationship, the observed object is not detected by the optical device, and therefore, the observed object must be calculated to enter the ground shadow or the moon shadow.
Taking ground shadow as an example, the sun is an effective radiusThe distance between the sun and the earth is about 1.5 x 10 x 8km, so that the real ground shadow is conical, and a certain half shadow area exists, as shown in fig. 2 and 3, S is the sun, E is the earth, two outer common tangents of the sun and an extension line of SE intersect at a point A, two inner common tangents of the sun and SE intersect at a point B, and shadows caused by the earth are divided into a penumbra, a penumbra and a pseudo penumbra.
To determine whether the observed object is in the ground shadow, and in that portion of the shadow of the ground shadow, the following method may be used to calculate:
and (3) calculating and obtaining:
；
；
；
；
wherein the method comprises the steps ofIs a satellite-to-sun vector, +.>Is a modulus of the vector, +.>Sun opening angle of earth satellite, < >>To look at the radius of the sun on the satellite, +.>To look at the radius of the earth on the satellite, +.>Is the earth radius;
when (when)，/>Judging that the satellite is in the earth shadow area;
when (when)，/>When the satellite is located in the earth half-shadow area, the satellite is determined.
Similarly, to determine whether the observed object is in a moon shadow, and in that portion of the shadow of the moon shadow, the following method may be employed for calculation:
and (3) calculating and obtaining:
；
；
；
；
in the middle ofFor the satellite to moon vector, +.>Is a modulus of the vector, +.>Is the sun opening angle of the lunar satellite +.>To look at the radius of the sun on the satellite, +.>To look at the radius of the moon on the satellite, +.>Is the radius of moon;
when (when)，/> Judging that the satellite is in the lunar originally-shadow area;
when (when)，/>，/>When the satellite is in the moon artifact area, judging that the satellite is in the moon artifact area;
when (when)，/>And judging that the satellite is in the moon half-shadow area.
If the observed object is not in the ground shadow or the moon shadow through calculation, the observed object is not influenced by the ground shadow or the moon shadow, the next step can be continued, and the solar vector of the space-based optical equipment is calculatedVector of observed target with space-based optical deviceOpening angle of (a)And judging.
If the opening angleIf the value is too small and smaller than the threshold value, the space-based optical device is disturbed by sunlight or moon reflection, the space-based optical device cannot observe normally, and the observed object and the space-based optical device are positioned in the same spaceThe simulation measurement data is not required to be further calculated at any time, and the next step can be directly calculated according to the set step.
Specifically, the opposite opening angleCan be determined by
Acquiring solar vector of space-based optical deviceAnd an observed target vector of the space-based optical deviceAngle of openingThe formula of (2) is:the opening angle can be obtained through calculation。
If the opening angleAbove the threshold, it is stated that the observation between the day-based optical device and the observed object is not disturbed by sunlight or moon reflection.
By the calculation, the distance between the observed object and the space-based optical device is geometrically visibleAzimuth angleAnd pitch angleMeets the design index of the space-based optical equipment, and the observed object is not in the ground shadow or the moon shadowThe observed object larger than the threshold value condition and the space-based optical device can carry out simulation measurement on the data red warpDeclination of weftIs calculated by the computer.
Specifically, the simulation data is right throughDeclination of weftThe formula of (2) is:
；
；
；
；
is thatIs provided with a plurality of position points,for the purpose of simulating the data to be the right ascension,and (5) declination is performed for simulation data.
The obtained trabecular acidDeclination of weftNamely, isThe time-of-day based optical device simulates measurement data for an observed object,after the data acquisition at the moment is completed, according to the step length, the calculation of the simulation measurement data at the next moment is continued, and the time period is traversedAnd storing the simulation measurement data, and obtaining a final simulation data observation structure.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (9)
1. A satellite ephemeris-based simulation algorithm for measuring data of a space-based optical device, comprising the following steps:
s1, obtaining the earth fixed ephemeris of the observed targetAnd space-based optics earth-fixed ephemeris +.>Configuring an operation parameter file, a planetary ephemeris file and an earth rotation parameter file of the space-based optical equipment, wherein +.>；
S2, in the time periodIn, according to the set step length, calculating the moment +.>Ground tie-down position velocity of observed objectAnd the ground fixation system position speed of the space-based optical device +.>The method comprises the steps of carrying out a first treatment on the surface of the According to->And->Calculating whether the observed object and the space-based optical device are geometrically visible;
s3, if the observed object is geometrically visible with the space-based optical device, thenAndtransposed to the space-based optical device body coordinate system respectively>In the body coordinate system->Next, the distance of the observed object in the space-based optical device is calculated +.>Azimuth angle->And pitch angle->Viewing distance +.>Azimuth angle->And pitch angle->Whether the design index of the space-based optical device is satisfied;
if the observed object is not visible to the space-based optical device geometry, returning to S2 for the next step size calculation;
s4, if the distanceAzimuth angle->And pitch angle->If the design index of the space-based optical equipment is met, calculating whether the observed target is in the ground shadow or the moon shadow;
if the distance isAzimuth angle->And pitch angle->If the design index of the space-based optical equipment is not met, returning to S2 to perform the next step calculation;
s5, if the observed object is not in the ground shadow or the moon shadow, calculating the solar vector of the space-based optical equipmentVector of observed target with space-based optical device +.>Opening angle->For opening angle->Judging whether the value is smaller than a threshold value;
if the observed target is in the ground shadow or the moon shadow, returning to S2 to perform the next step calculation;
s6, if the opening angleIf the value is not smaller than the threshold value, calculating the space-based lightSimulation measurement data of the learning device, red warp +.>And (d) declination->Then returning to S2 for the next step calculation;
if the opening angleIf the step size is smaller than the threshold value, returning to S2 to perform next step size calculation;
s7, traversing the time period according to the set step lengthThe simulated measurement data is stored.
2. The satellite ephemeris-based space-based optical device measurement data simulation algorithm of claim 1, wherein: the operation parameter file of the configured space-based optical device in the step S1 comprises the following steps: simulation start time, simulation end time, simulation data step length, observed target code number, space-based optical device code number.
3. The satellite ephemeris-based space-based optical device measurement data simulation algorithm of claim 1, wherein: according to the S2And->The formula for calculating whether the observed object and the space-based optical device are geometrically visible is as follows:
；
wherein:
；
；
；
；
；
；
；
RE is the earth radius, FE is the earth's flatness, SS, SA, SB, SC, DX, DY, DZ and G2 are process variables;、、/>is->Three components of the three-dimensional vector, +.>、/>、Is->Three components of the three-dimensional vector;
when SS <0, the observed object is geometrically visible to the space-based optics.
4. A satellite ephemeris-based sky-based optical device measurement data simulation algorithm of claim 3, wherein: when SS is more than or equal to 0, according to the formulaThe method for judging whether the observed object and the space-based optical device are geometrically visible is as follows:
when SB (SB)<0, calculate，/>；
If K1<0 and K2<0, the observed object is geometrically visible with the space based optics;
when SB is more than or equal to 0, calculate，/>；
If K1>1 and K2>1, the observed object is geometrically visible with the space based optical device.
5. The satellite ephemeris-based space-based optical device measurement data simulation algorithm of claim 1, whereinIn the following steps: calculating the distance of the observed object in the space-based optical device in the S3Azimuth angle->And pitch angle->The process of (1) is as follows:
s31, willAnd->Transposed to +.>An inertial coordinate system; obtaining the position speed of the inertial coordinate system of the observation target>And inertial coordinate system position speed of space-based optical device>；
S32, willAnd->Transposed to the space-based optical device body coordinate system respectively>Obtaining:
；
；
wherein the method comprises the steps ofIs->Inertial coordinate System to space-based optical device body coordinate System +.>Is a transposed matrix of (a);
s33, orderThen
；
；
；
；
Wherein (x, y, z) isPosition points in->Distance of the observed object in the space-based optical device; />Azimuthal angle of the object to be observed in the space-based optical device +.>；/>Is the pitch angle of the observed object in the space-based optical device.
6. The satellite ephemeris-based space-based optical device measurement data simulation algorithm of claim 1, wherein: the ground shadow and the moon shadow in the step S4 respectively comprise a home shadow, a penumbra and an artifact.
7. The satellite ephemeris-based space-based optical device measurement data simulation algorithm of claim 6, wherein: the process of calculating whether the observed target is in the ground shadow in S4 is as follows:
；
；
；
；
wherein the method comprises the steps ofIs a satellite-to-sun vector, +.>Is a modulus of the vector, +.>Sun opening angle of earth satellite, < >>To look at the radius of the sun on the satellite, +.>To look at the radius of the earth on the satellite, +.>Is the earth radius;
when (when)，/>When the satellite is in the earth shadow area;
when (when)，/>The satellite is in the earth half-shadow area;
the process of calculating whether the observed object is in the moon shadow in the step S4 is as follows:
；
；
；
；
in the middle ofFor the satellite to moon vector, +.>Is a modulus of the vector, +.>Is the sun opening angle of the lunar satellite +.>To look at the radius of the sun on the satellite, +.>To look at the radius of the moon on the satellite, +.>Is the radius of moon;
when (when)，/> When the satellite is in the lunar originally-shadow area;
when (when)，/>，/>When the satellite is in the moon artifact area;
when (when)，/>The satellite is in the moon half-shadow.
8. The satellite ephemeris-based space-based optical device measurement data simulation algorithm of claim 1, wherein: calculating solar vector of space-based optical equipment in S5Vector of observed target with space-based optical device +.>Opening angle->The formula of (2) is:
；
wherein,sun vector for space-based optical device, +.>The target vector is observed for the space-based optical device.
9. The satellite ephemeris-based space-based optical device measurement data simulation algorithm of claim 1, wherein: calculating the simulation data red warp of the space-based optical equipment in the step S6And (d) declination->The formula of (2) is:
；
；
；
；
wherein the method comprises the steps ofIs->Position points in->For simulation data>，/>And (5) declination is performed for simulation data.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311408732.XA CN117150184B (en) | 2023-10-27 | 2023-10-27 | Satellite ephemeris-based space-based optical equipment measurement data simulation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311408732.XA CN117150184B (en) | 2023-10-27 | 2023-10-27 | Satellite ephemeris-based space-based optical equipment measurement data simulation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117150184A true CN117150184A (en) | 2023-12-01 |
| CN117150184B CN117150184B (en) | 2024-03-26 |
Family
ID=88910372
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311408732.XA Active CN117150184B (en) | 2023-10-27 | 2023-10-27 | Satellite ephemeris-based space-based optical equipment measurement data simulation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117150184B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104792347A (en) * | 2015-02-15 | 2015-07-22 | 中国科学院光电研究院 | Indoor simulation method for space target optical characteristic actual measurement conditions |
| CN105466477A (en) * | 2015-12-07 | 2016-04-06 | 中国科学院光电研究院 | A space-based observation simulation system and method targeted at satellite targets and fixed star targets |
| WO2019062166A1 (en) * | 2017-09-30 | 2019-04-04 | 中国科学院遥感与数字地球研究所 | Method for automatic geometric correction of cross-platform moon-based earth observation imaging |
| WO2021052511A1 (en) * | 2019-09-16 | 2021-03-25 | 中国民航大学 | Method and system for testing raim performance conformance of beidou on-board device |
| CN112731281A (en) * | 2020-12-23 | 2021-04-30 | 中国人民解放军63921部队 | Simulation method for space debris angle measurement data |
| CN113568889A (en) * | 2021-07-30 | 2021-10-29 | 上海无线电设备研究所 | Air target feature library for space-based optical detection and construction method thereof |
| CN115905800A (en) * | 2022-11-24 | 2023-04-04 | 上海卫星工程研究所 | Space target track determination precision analysis method and system based on optical observation |
| CN116108314A (en) * | 2022-12-20 | 2023-05-12 | 北京开运平行空间技术有限公司 | Method for determining space target track based on multi-sensor combination measurement |
-
2023
- 2023-10-27 CN CN202311408732.XA patent/CN117150184B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104792347A (en) * | 2015-02-15 | 2015-07-22 | 中国科学院光电研究院 | Indoor simulation method for space target optical characteristic actual measurement conditions |
| CN105466477A (en) * | 2015-12-07 | 2016-04-06 | 中国科学院光电研究院 | A space-based observation simulation system and method targeted at satellite targets and fixed star targets |
| WO2019062166A1 (en) * | 2017-09-30 | 2019-04-04 | 中国科学院遥感与数字地球研究所 | Method for automatic geometric correction of cross-platform moon-based earth observation imaging |
| WO2021052511A1 (en) * | 2019-09-16 | 2021-03-25 | 中国民航大学 | Method and system for testing raim performance conformance of beidou on-board device |
| CN112731281A (en) * | 2020-12-23 | 2021-04-30 | 中国人民解放军63921部队 | Simulation method for space debris angle measurement data |
| CN113568889A (en) * | 2021-07-30 | 2021-10-29 | 上海无线电设备研究所 | Air target feature library for space-based optical detection and construction method thereof |
| CN115905800A (en) * | 2022-11-24 | 2023-04-04 | 上海卫星工程研究所 | Space target track determination precision analysis method and system based on optical observation |
| CN116108314A (en) * | 2022-12-20 | 2023-05-12 | 北京开运平行空间技术有限公司 | Method for determining space target track based on multi-sensor combination measurement |
Non-Patent Citations (9)
| Title |
|---|
| ROBERTO LUPO ET AL.: "Lighthouse: A spacebased mission concept for the surveillance of geosynchronous space debris from low earth orbit", ADVANCES IN SPACE RESEARCH, vol. 62, no. 12, pages 3305 - 3317 * |
| YUANZHEN REN ET AL.: "Simulation Study of Geometric Characteristics and Coverage for Moon-Based Earth Observation in the Electro-Optical Region", IEEE JOURNAL OF SELECTED TOPICS IN APPLIED EARTH OBSERVATIONS AND REMOTE SENSING, vol. 10, no. 6, pages 2431, XP011656896, DOI: 10.1109/JSTARS.2017.2711061 * |
| 周庆勇;杜兰;蓝朝桢;: "天基光学监视系统空间目标定轨精度仿真分析", 系统仿真学报, no. 11 * |
| 曾德贤;杜小平;: "空间目标在天基光学探测中的特性分析与仿真", 空间科学学报, no. 06, pages 56 - 62 * |
| 潘晓刚;周海银;王炯琦;: "基于天基测控的同步轨道卫星联合定轨方法研究", 宇航学报, no. 05 * |
| 潘晓刚;李济生;段晓君;周海银;: "天基空间目标监视与跟踪系统轨道确定技术研究", 自然科学进展, no. 11, pages 28 - 41 * |
| 蓝朝桢;李建胜;马赛金;徐青;: "在轨目标天基光学观测可见性预报与分析", 光电工程, no. 12, pages 27 - 31 * |
| 赵砚等: "基于天基光学观测的空间目标可见性分析", 飞行器测控学报, vol. 26, no. 3, pages 5 - 12 * |
| 黄丽霞;彭鑫;刘书豪;赵华;: "高轨光学成像卫星动目标跟踪策略设计与仿真", 航天器工程, no. 04, pages 16 - 22 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117150184B (en) | 2024-03-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Matzarakis et al. | Sky view factor as a parameter in applied climatology-rapid estimation by the SkyHelios model | |
| Erdélyi et al. | Three-dimensional SOlar RAdiation Model (SORAM) and its application to 3-D urban planning | |
| CN107132542B (en) | A kind of small feature loss soft landing autonomic air navigation aid based on optics and Doppler radar | |
| Temmer et al. | On flare-CME characteristics from Sun to Earth combining remote-sensing image data with in situ measurements supported by modeling | |
| CN104216031B (en) | Variable-step-size obscuration forecasting method | |
| Gao et al. | Development and calibration of an accurate 6-degree-of-freedom measurement system with total station | |
| CN110849331B (en) | Monocular vision measurement and ground test method based on three-dimensional point cloud database model | |
| CN112946784B (en) | SuperDARN radar convection diagram short-term forecasting method based on deep learning | |
| CN108364279A (en) | Determine the method that stationary orbit remote sensing satellite is directed toward deviation | |
| CN105352500A (en) | Adaptive satellite selection method and system with celestial body interference | |
| Díaz et al. | An adaptive solar radiation numerical model | |
| CN103743488B (en) | Infrared imaging simulation method for globe limb background characteristics of remote sensing satellite | |
| Jackson et al. | Three-dimensional tomography of interplanetary disturbances | |
| CN109374136B (en) | Method and processing device for acquiring lunar surface temperature | |
| Alam et al. | Detecting shadow for direct radiation using CityGML models for photovoltaic potentiality analysis | |
| CN112857306B (en) | Method for determining continuous solar altitude angle of video satellite at any view direction point | |
| Cellura et al. | A photographic method to estimate the shading effect of obstructions | |
| CN117150184B (en) | Satellite ephemeris-based space-based optical equipment measurement data simulation method | |
| Steffen et al. | Hydrodynamical velocity fields in planetary nebulae | |
| Zhang et al. | A new PHD-SLAM method based on memory attenuation filter | |
| CN115307646B (en) | Multi-sensor fusion robot positioning method, system and device | |
| CN107992677B (en) | Infrared weak and small moving target tracking method based on inertial navigation information and brightness correction | |
| CN114187399A (en) | Method and system for generating illumination simulation image on surface of extraterrestrial star | |
| CN105095586A (en) | Method for multi-uniting real-time visual simulation based on satellite tool kit (STK) | |
| Ranalli et al. | Sensitivity of shading calculations to horizon uncertainty |
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 |