CN113654512A - Spatial target optical visibility analysis method - Google Patents
Spatial target optical visibility analysis method Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C1/00—Measuring angles
- G01C1/02—Theodolites
Abstract
The invention discloses a space target optical visibility analysis method, which comprises the steps of establishing a coordinate system under the conditions of given time and space, calculating the solar position of a horizon coordinate system, judging terrestrial light constraint, judging terrestrial shadow constraint and sky light constraint, judging the target to be optically visible if the constraint is met, providing a more accurate solar position calculation method, providing a multi-factor coupled space target visibility constraint algorithm, using a vector mode, and being more friendly in mathematical calculation.
Description
Technical Field
The invention belongs to the technical field of mathematical computation, and particularly relates to an astronomical mathematical computation technology.
Background
The photoelectric theodolite observes a space target in a visible light wave band and is an important means for monitoring a space-based space target, so that the optical visibility analysis of the space target is one of the key problems of a space-based space target monitoring system. The photoelectric theodolite is often influenced by factors such as earth shielding, ground light, sunlight, ground shadow and the like in a task of detecting a space target in a visible light wave band. In the process of observing a space target, the photoelectric theodolite needs the target to be measured to have visibility, and the optical visibility analysis is to calculate the time and the position of the photoelectric theodolite to observe the space target.
To ensure the observation condition, it must first be ensured that the relative height of the space target and the photoelectric theodolite meets the observation condition. Secondly, the spatial target itself does not emit light and must reflect sunlight to be observed. Finally, it is also necessary that the spatial target is captured by the electro-optic theodolite in a sufficiently dark sky background. In order to directly calculate the influence of the factors on the photoelectric theodolite to detect the space target in a task planning stage, the optical visibility analysis research of the space target is developed, and an algorithm for quickly and accurately calculating the visibility of the space target in the task planning is provided.
Based on the principle, the space relative position relation among the space target, the photoelectric theodolite and the sun is a fundamental factor for limiting the optical visibility of the space target. Therefore, it is necessary to accurately predict the optical visibility of the satellite in consideration of the constraints such as shading, ground light, sky light, and earth shadow.
An article, namely, on-orbit target space-based optical observation visibility forecasting and analysis, in 2008, 12.35, volume 12, utilizes the geometric relationship among an on-orbit target, an observation satellite, the earth, the sun and the moon, comprehensively considers the earth shielding and the earth light condition, the earth shadow condition, the sunlight condition and the moon light condition, deduces an optical visibility judgment model of the target to the observation satellite, and establishes a space-based optical observation visibility forecasting method. However, no calculation of sun position and sun vector is mentioned herein.
Electro-optical and control periodical 2015, journal, volume 5, month 5, 22, article "analysis of visible condition and visible light characteristic of spatial target" based on the geometric position relationship of spatial target, space-based observation station and sun and the performance of CCD detection system, the visible condition of spatial target relative to observation station is studied, the visible light characteristic of spatial target is studied based on bidirectional reflection distribution function, a visible light reflection model of spatial target surface is established more finely, and simultaneously, the CCD detection system is modeled. However, the calculation of the sun position and the sunlight vector is not mentioned, and the position calculation of the sun at different times needs to be further researched.
Disclosure of Invention
The invention provides a space target optical visibility analysis method for solving the problems in the prior art, which is used for analyzing the optical visibility of a photoelectric theodolite in any time and space to a specific space target.
Under the condition of given time and space, a coordinate system is established by taking an equatorial plane as a reference plane and a meridian passing through an intersection point of the equatorial plane and a ecliptic plane as a meridian, an included angle between the meridian passing through the position where the sun is located and the meridian passing through a spring and autumn branch point is taken as an ascent Ra, and an included angle between a sun-geocentric connecting line and the equatorial plane is taken as an declination delta, the sun position of the equatorial coordinate system is calculated, the coordinate system is established by taking the plane where an observer is located as the reference plane, lon represents longitude, lat represents latitude, an included angle between the connecting line of the sun and the observer and the ground plane is taken as a height angle alt, and an included angle between the direction where the sun is located and the north is taken as an azimuth angle az, and the sun position of the horizon coordinate system is calculated.
Given year Y, month M, date D, rounding algorithm INT, then
Correction factor
Julian day JD ═ INT (365.25 (Y +4716)) + INT (30.6001 (M +1)) + D + B-1524.5
Yellow-red crossing angle OE (23.4393-3.563X 10)-7×JD
The argument ω of the near-sun point is 282.9404+4.70935 × 10-5×JD
Mean approximate point angle g of 356.0470+0.9856002585 × JD
Revolution orbit eccentricity e is 0.016709-1.151 x 10-9×JD
Culture century
Greenwich mean time of the sun s0＝280.460618+360.98565×(JD-2451545)+0.0003879×JC2
Solar hour angle H ═ s0+lon-Ra
Angle of approach point
The distance d between the sun and the ground and the true near point angle v satisfy
And d × cosv ═ cosE-e, and the right ascension Ra and the right ascension delta satisfy
And sin δ is sinOE × sin (v + ω), alt is sin-1(sinlat. times.sin. delta. + coslat. times.cos. delta. times.cosH) and
height h from ground by critical visual axis0As an index of the terrestrial light condition, RERepresenting the radius of the earth to observe the vector r of the object O with respect to the electro-optic theodoliteopVector-r of electro-optic theodolite relative to earth centerpThe included angle theta between the critical visual axis and the earth center is larger than the included angle theta between the critical visual axis and the earth center0As a constraint condition, a terrestrial light constraint is calculated.
If it is
The terrestrial light constraint is assumed to be satisfied.
Assuming that sunlight is parallel light and a ground shadow area is a cylinder, the earth center vector r of the target is takenoGeocentric vector r with the sunsThe included angle beta between the two is smaller than or larger than a semicircle but the vector roAt and vector rsComponent mode length in the vertical plane being greater than the earth radius REAs a constraint condition, a map shadow constraint is calculated.
If it is
Or
The terrain constraint is deemed satisfied.
To observe the vector r of the target relative to the electro-optic theodoliteopVector r of sun relative to photoelectric theodolitespThe included angle between the two is larger than the sum alpha of the apparent radius of the sun and the light scattering angle0As a constraint condition, a sky-light constraint is calculated.
If it is
The daylight constraint is deemed to be satisfied.
The invention has the beneficial effects that: a more accurate sun position calculation method is provided, a multi-factor coupling space target visibility constraint algorithm is provided, a vector mode is used, and mathematical calculation is more friendly.
Drawings
Fig. 1 is a schematic diagram of a terrestrial light constraint condition, fig. 2 is a schematic diagram of a terrestrial shadow constraint condition, and fig. 3 is a schematic diagram of a celestial light constraint condition.
Detailed Description
The technical scheme of the invention is specifically explained in the following by combining the attached drawings.
1) Calculating sun position information
Firstly, inputting the current date, calculating the julian day and the solar hour angle, calculating the relevant parameters of the solar orbit according to the julian day, and then calculating the solar right ascension and declination under an equatorial coordinate system and the solar altitude angle and azimuth under a horizontal coordinate system.
2) Calculating the constraint conditions of the earth light
As shown in fig. 1, it is determined whether the observation target meets the terrestrial light constraint.
3) Computing terrain constraint conditions
As shown in fig. 2, it is determined whether the observation target meets the terrestrial shadow constraint.
4) Calculating sky-light constraint conditions
As shown in fig. 3, it is determined whether the observation target meets the daylight constraint.
The above-described embodiments are not intended to limit the present invention, and any modifications, equivalents, improvements, etc. made within the spirit and principle of the present invention are included in the scope of the present invention.
Claims (5)
1. A method for analyzing optical visibility of a spatial target, comprising: under the conditions of given time and space, establishing a coordinate system by taking an equatorial plane as a reference plane and a meridian passing through an intersection point of the equatorial plane and a ecliptic plane as a meridian, taking an included angle between the meridian passing through the position where the sun is located and the meridian passing through a spring and autumn branch point as an ascension Ra, and taking an included angle between a sun-geocentric connecting line and the equatorial plane as an declination delta, calculating the sun position of the equatorial coordinate system, establishing the coordinate system by taking the plane where an observer is located as the reference plane, lon represents longitude, lat represents latitude, and calculating the sun position of the terrestrial coordinate system by taking the included angle between the connecting line of the sun and the observer and the ground plane as a height angle alt and the included angle between the direction where the sun is located and the north as an azimuth angle az; height h from ground by critical visual axis0As an index of the terrestrial light condition, RERepresenting the radius of the earth to observe the vector r of the object O with respect to the electro-optic theodoliteopVector-r of electro-optic theodolite relative to earth centerpThe included angle theta between the critical visual axis and the earth center is larger than the included angle theta between the critical visual axis and the earth center0As a ground light constraint condition, judging ground light constraint; assuming that sunlight is parallel light and a ground shadow area is a cylinder, the earth center vector r of the target is takenoGeocentric vector r with the sunsThe included angle beta between the two is smaller than or larger than a semicircle but the vector roAt and vector rsComponent mode length in the vertical plane being greater than the earth radius REAs a ground shadow constraint condition, judging a ground shadow constraint; to observe the vector r of the target relative to the electro-optic theodoliteopVector r of sun relative to photoelectric theodolitespThe included angle between the two is larger than the sum alpha of the apparent radius of the sun and the light scattering angle0As a daylight constraint condition, judging the daylight constraint; and if the target meets the ground light constraint, the ground shadow constraint and the sky light constraint, judging that the target is optically visible.
2. The method for spatial target optical visibility analysis according to claim 1, wherein the calculating the sun position in the horizon coordinate system comprises:
given year Y, month M, date D, rounding algorithm INT, then
Correction factor
Julian day JD ═ INT (365.25 (Y +4716)) + INT (30.6001 (M +1)) + D + B-1524.5
Yellow-red crossing angle OE (23.4393-3.563X 10)-7×JD
The argument ω of the near-sun point is 282.9404+4.70935 × 10-5×JD
Mean approximate point angle g of 356.0470+0.9856002585 × JD
Revolution orbit eccentricity e is 0.016709-1.151 x 10-9×JD
Culture century
Greenwich mean time of the sun s0＝280.460618+360.98565×(JD-2451545)+0.0003879×JC2
Solar hour angle H ═ s0+lon-Ra
Angle of approach point
The distance d between the sun and the ground and the true near point angle v satisfy
And d × cosv ═ cosE-e, and the right ascension Ra and the right ascension delta satisfy
And sin δ is sinOE × sin (v + ω), alt is sin-1(sinlat. times.sin. delta. + coslat. times.cos. delta. times.cosH) and
3. the method for spatial target optical visibility analysis according to claim 1, wherein the determining the terrestrial light constraint comprises: if it is
The terrestrial light constraint is assumed to be satisfied.
4. The method for analyzing the optical visibility of a spatial target according to claim 1, wherein the determining the terrain constraint comprises: if it is
Or
The terrain constraint is deemed satisfied.
5. The method for analyzing optical visibility of a spatial target according to claim 1, wherein the determining the daylight constraint includes: if it is
The daylight constraint is deemed to be satisfied.
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|---|---|---|---|---|
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| WO2005123507A1 (en) * | 2004-06-22 | 2005-12-29 | Japan Aerospace Exploration Agency | Ultrahigh altitude sun synchronous orbit satellite system |
| CN107576305A (en) * | 2017-07-11 | 2018-01-12 | 天津世纪经纬测量仪器制造有限公司 | A kind of green laser alignment electronic theodolite |
| CN109991635A (en) * | 2019-03-29 | 2019-07-09 | 中国空间技术研究院 | A kind of tracking segmental arc calculation method of IGSO satellite to ground moving target |
| CN111637896A (en) * | 2020-05-12 | 2020-09-08 | 北京控制工程研究所 | Autonomous astronomical navigation method based on ephemeris constraint assistance |
| CN212080728U (en) * | 2020-04-27 | 2020-12-04 | 福建芗江工程项目管理有限公司 | Tripod for electronic theodolite |
| CN112686509A (en) * | 2020-12-21 | 2021-04-20 | 长光卫星技术有限公司 | Space target guided imaging task planning method based on agile optical remote sensing satellite |
-
2021
- 2021-08-13 CN CN202110928816.0A patent/CN113654512A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1081459A1 (en) * | 1999-08-31 | 2001-03-07 | Leica Geosystems AG | Tacheometer-telescope |
| WO2001049565A1 (en) * | 2000-01-04 | 2001-07-12 | The Johns Hopkins University | Method and apparatus for autonomous solar navigation |
| WO2005123507A1 (en) * | 2004-06-22 | 2005-12-29 | Japan Aerospace Exploration Agency | Ultrahigh altitude sun synchronous orbit satellite system |
| CN107576305A (en) * | 2017-07-11 | 2018-01-12 | 天津世纪经纬测量仪器制造有限公司 | A kind of green laser alignment electronic theodolite |
| CN109991635A (en) * | 2019-03-29 | 2019-07-09 | 中国空间技术研究院 | A kind of tracking segmental arc calculation method of IGSO satellite to ground moving target |
| CN212080728U (en) * | 2020-04-27 | 2020-12-04 | 福建芗江工程项目管理有限公司 | Tripod for electronic theodolite |
| CN111637896A (en) * | 2020-05-12 | 2020-09-08 | 北京控制工程研究所 | Autonomous astronomical navigation method based on ephemeris constraint assistance |
| CN112686509A (en) * | 2020-12-21 | 2021-04-20 | 长光卫星技术有限公司 | Space target guided imaging task planning method based on agile optical remote sensing satellite |
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