CN114491999A - Method for designing constellation of medium orbit elliptical orbit remote sensing satellite - Google Patents
Method for designing constellation of medium orbit elliptical orbit remote sensing satellite Download PDFInfo
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Abstract
The invention relates to a constellation design method for a medium orbit elliptical orbit remote sensing satellite, which comprises the following steps: s1, designing an ellipse freezing orbit of the medium orbit ellipse orbit remote sensing satellite by utilizing the characteristic that the ellipse orbit of the medium orbit ellipse orbit remote sensing satellite resides in a long distance place; specifically, the method comprises the following steps: s11, selecting a track inclination angle i; s12, height h of perigeepHeight h from distant placeaSelecting; s13, selecting an argument omega of the perigee; s14, selecting a rising crossing right ascension omega; s2, aiming at the characteristic that the oval orbit of the medium orbit oval orbit remote sensing satellite is a non-uniform orbit with high near-to-site movement speed and low far-to-site movement speed, designing a special Walker constellation of the medium orbit oval orbit remote sensing satellite; specifically, the method comprises the following steps: s21, calculating a mean anomaly of the satellite in the orbital plane; s22, calculating the number S of satellites in each orbital plane; and S23, calculating the angle difference of the adjacent track surfaces. The method has the advantages of being oriented to the optical remote sensing satellite, revisiting targets in the hotspot area and revising the targets in the hotspot areaHigh temporal resolution and high spatial resolution monitoring.
Description
[ technical field ] A method for producing a semiconductor device
The invention relates to the technical field of spaceflight, in particular to a constellation design method for a remote sensing satellite with a medium orbit elliptical orbit.
[ background of the invention ]
The remote sensing satellite can quickly and effectively acquire global earth surface changes and is widely applied to the fields of homeland surveying and mapping, meteorological monitoring, ocean coast surveying and mapping and the like. The main development target of the remote sensing satellite is higher space and time resolution, the orbit determines the position distribution of the satellite in the space, and the position distribution is inseparable from the imaging resolution and the breadth of the optical remote sensing satellite, so that the method has important significance in reasonably designing and optimizing the orbit of the optical remote sensing satellite.
The circular orbit satellite has the unique advantages of global coverage, uniform ground resolution and the like, but when the circular orbit satellite is used for imaging a key attention area, the circular orbit satellite cannot ensure that a target in the key attention area is revisited quickly. The elliptical orbit has the characteristics of slow movement speed of the apogee, large coverage area, long residence time relative to the ground and the like, so that the aim height in the counterweight area can be revisited by utilizing the apogee characteristic. The medium orbit satellite can effectively make up for the natural defects of long revisit time of the low orbit satellite and low resolution of the high orbit satellite, and the high time resolution and the high spatial resolution of the hot spot target can be monitored through constellation networking.
The medium orbit earth satellite mainly refers to an earth satellite with a satellite orbit which is 2000-20000 km away from the earth surface, belongs to an earth nonsynchronous satellite, is mainly used for supplementing and expanding a land mobile communication system, is organically combined with a ground public network to realize global personal mobile communication, and can also be used as a satellite navigation system.
The Walker constellation is a constellation arrangement in which the orbit of a general satellite is a circular orbit, each orbit plane is evenly distributed, and the satellites in the orbit plane are evenly distributed. The configuration code of a Walker constellation is: N/P/F (number of satellites/number of orbital planes/phase factor), a common Walker constellation is Walker24/3/2 constellation, i.e., 24 satellites in total, divided into three orbital planes.
The invention makes technical improvement on the design method of the medium orbit elliptical orbit and the constellation of the facing optical remote sensing satellite.
[ summary of the invention ]
The invention aims to provide a design method of a middle orbit elliptical orbit and a constellation, which is oriented to an optical remote sensing satellite, can realize high revisiting on targets in a hotspot area and can monitor the hotspot targets with high time resolution and high spatial resolution.
In order to achieve the purpose, the technical scheme adopted by the invention is a method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite, which comprises the following steps:
s1, designing an ellipse freezing orbit of the medium orbit ellipse orbit remote sensing satellite by utilizing the characteristic that the ellipse orbit of the medium orbit ellipse orbit remote sensing satellite resides in a long distance place; specifically, the method comprises the following steps:
s11, selecting an inclination angle i of the oval freezing orbit;
s12 height h of near point of oval freezing orbitpHeight h from distant placeaSelecting;
s13, selecting an argument omega of the perigee of the oval freezing orbit;
s14, selecting an oval freezing orbit ascending intersection point right ascension omega;
s2, aiming at the characteristic that the oval orbit of the medium orbit oval orbit remote sensing satellite is a non-uniform orbit with high near-to-site movement speed and low far-to-site movement speed, designing a special Walker constellation of the medium orbit oval orbit remote sensing satellite; specifically, the method comprises the following steps:
s21, calculating a flat near point angle of the satellite in the special Walker constellation orbit plane;
s22, calculating the number S of satellites in each orbital plane of the special Walker constellation;
and S23, calculating the approximate point angle difference of the adjacent orbital planes of the special Walker constellation.
Preferably, step S11: make the near-location argument omega of the elliptic freezing orbit precession every day
Selecting an elliptic freezing orbit inclination angle i for zero, namely the argument omega of the near place is constant, wherein ReIs the earth radius, e is the ellipse freeze orbit eccentricity, a is the ellipse freeze orbit semi-major axis.
Preferably, the elliptical freeze orbit is a non-sun-synchronous orbit of i 63.4 °, or a sun-synchronous orbit of i 116.6 °.
Preferably, step S12: approximate height h of elliptic freezing orbitpHeight h from distant placeaIs selected from the range
Preferably, when the elliptical freezing orbit is a sun-synchronous orbit of i ═ 116.6 °, the perigee height h ispHeight h from distant placeaSatisfy the requirement of
Wherein R iseIs the earth radius, e is the ellipse freeze orbit eccentricity, a is the ellipse freeze orbit semi-major axis.
Preferably, step S13: argument omega of near place and latitude of observation target point
In relation to (2)
And freezing the apogee above the observation target point by adjusting the apogee argument omega to select the perigee argument omega of the elliptic freezing orbit.
Preferably, step S14: when the elliptical freezing orbit is a sun synchronous orbit with i being 116.6 degrees, the right ascension omega of the ascending intersection point of the elliptical freezing orbit meets the light condition constraint, so that when the satellite ascends and tracks through the target point, the local time of the target point is near noon.
Preferably, step S21: the satellites in the orbit plane of the special Walker constellation are uniformly distributed according to the period, namely the flat near point angle of the satellites in the same orbit plane
Wherein p is the number of satellites in the orbital plane.
Preferably, step S22: number of satellites in each orbital plane of special Walker constellation
Wherein T is the orbital period, T1The average observation time length is single star.
Preferably, step S23: mean and near point angle difference of adjacent orbital planes of special Walker constellation
Wherein f is a phase factor.
The method for designing the medium orbit elliptical orbit remote sensing satellite constellation has the following beneficial effects: the method comprises the steps that the design of a medium orbit elliptical orbit and a constellation of an optical remote sensing satellite is oriented by utilizing the characteristic that the elliptical orbit resides in a long distance place and according to the characteristics of special orbits such as a critical dip angle orbit, solar synchronization, regression and the like, and the design of an elliptical freezing orbit and a constellation is given; the medium orbit elliptical orbit remote sensing satellite constellation designed by the method has the characteristics of low remote place movement speed, large coverage area, long residence time relative to the ground and the like, can revisit targets in a hotspot area, can effectively make up for the natural defects of long revisit time of low orbit satellites and low resolution of high orbit satellites, and monitors high time resolution and high spatial resolution of hotspot targets.
[ description of the drawings ]
FIG. 1 is a diagram of a method for designing a constellation of a remote sensing satellite with a medium orbit elliptical orbit.
Fig. 2 is a diagram of the height of a far place corresponding to different heights of a near place of a sun synchronous orbit when an orbit inclination angle i of a medium orbit elliptical orbit remote sensing satellite constellation design method is 116.6 degrees.
Fig. 3 shows a design method of a medium orbit elliptical orbit remote sensing satellite constellation, which is 12 am at a 26 ° north latitude target point in a local place: and 00, local time graphs corresponding to different latitude targets.
Fig. 4 is a diagram of average coverage weight of constellation design example 1 along with change of latitude in a constellation design method of a medium orbit elliptical orbit remote sensing satellite.
[ detailed description ] embodiments
The invention is further described with reference to the following examples and with reference to the accompanying drawings.
Examples
The embodiment realizes a constellation design method for the medium orbit elliptical orbit remote sensing satellite.
FIG. 1 is a diagram of a method for designing a constellation of a remote sensing satellite with a medium orbit elliptical orbit. As shown in fig. 1, the method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to the embodiment provides a flow of elliptical freezing orbit and constellation design according to characteristics of a critical dip orbit, sun synchronization, regression and other special orbits by using a characteristic that an elliptical orbit resides long in a remote place, and performs analysis and summary.
1. Step of track design
(1) Track Tilt i selection
The earth oblateness can cause the variation of the argument omega of the perigee, and directly cause the variation of the perigee of the orbit, so that the semilong axis of the orbit has rotation in an inertia space, namely the precession of the arch wire. Omega precession per day is
From the above formula, when i is 63.4 ° or 116.6 °. The argument omega of the near place is fixed and unchanged, therefore the orbit dip angle is selected to be 63.4 degrees or 116.6 degrees, and the argument omega of the near place is reasonably set, so that the far place can be frozen above the target latitude.
It is noted that when the inclination angle i is 116.6 °, the ascent point of the right ascension channel Ω advances eastwardly, and the height h of the near point is reasonably setpHeight h from distant placeaCan be further provided withThe system is designed as a sun synchronous orbit, the illumination condition of the sun synchronous orbit is stable, and the energy and heat design of the remote sensing satellite can be simpler.
(2) Height of near place hpHeight h from distant placeaSelecting
Considering the influence of space environment such as space atomic oxygen, aerodynamic resistance and the like, and the height h of the near placepShould not be less than 500 km. High-energy particles in a Van Allen radiation band cause space radiation effect (such as total radiation dose, single-particle upset, single-particle latch and the like) on electronic equipment in a spacecraft, the radiation band is divided into an inner band (about 1500 km-5500 km) and an outer band (about 12000 km-22000 km), so the Van Allen radiation band should be avoided when the orbit height is selected, namely the ranges of less than 1500km, 5500 km-12000 km and more than 22000km, the requirements on the load of an optical remote sensing satellite are considered, and the height h of a near site is consideredpHeight h from distant placeaThe selection ranges are as follows:
500km≤hp≤1500km
5500km≤ha≤12000km
fig. 2 is a diagram of the height of a far place corresponding to different heights of a near place of a sun synchronous orbit when an orbit inclination angle i of a medium orbit elliptical orbit remote sensing satellite constellation design method is 116.6 degrees. As shown in the attached figure 2, if the solar synchronous orbit is further designed to be a solar synchronous orbit, the height h of the near place ispHeight h from distant placeaThe following relationships are required:
(3) selection of argument omega of near site
The remote place can be frozen above the observation target point by adjusting the argument omega of the near place, and the argument omega of the near place and the latitude of the observation target point
The relationship of (1) is:
(4) selection of elevation crossing right ascension omega
If the orbit is designed to be a sun synchronous orbit with i being 116.6 degrees, considering that the optical load is restricted by the illumination condition, the ascent point right ascent channel omega is adjusted to make the local place of the target point be near noon when the satellite is elevated and orbited by the target point.
Fig. 3 shows a design method of a medium orbit elliptical orbit remote sensing satellite constellation, which is 12 am at a 26 ° north latitude target point in a local place: and 00, local time graphs corresponding to different latitude targets. As shown in fig. 3, at the local place at the target point (north latitude 26 °) at noon 12: and 00, observing local places corresponding to targets with different latitudes by the satellite.
2. Constellation design method
By networking a plurality of satellites, the reasonable layout can realize wider-range observation and quick revisit. At present, remote sensing satellites are mostly circular orbits, a common constellation deployment mode is a Walker constellation, but the configuration of the Walker constellation is global and uniform and symmetrical, and in consideration of non-uniform orbits with high near-location motion speed and low far-location motion speed of an elliptical orbit, special constellation design needs to be carried out on the orbits, and the design principle is as follows:
(1) the satellites in the orbit plane are uniformly distributed according to the period, namely, the satellites in the same orbit plane are uniformly distributed at the same plane and near point angle.
Wherein p is the number of satellites in the orbital plane.
(2) If the inclination angle i of the track is 116.6 degrees, the track is designed to be a sun synchronous track, the load observation is restricted by the illumination angle, and the track surfaces are uniformly distributed in the illumination area; if the track inclination angle i is equal to 63.4 degrees, the track surfaces are uniformly distributed.
(3) The number of satellites s in each orbital plane can be calculated as follows
Wherein T is the orbital period, T1The average observation time length is single star.
(4) The phase difference of the adjacent orbital satellites is calculated according to the mean-near-point angle, and by analogy with the concept of a phase factor f in a Walker constellation, the mean-near-point angle difference of the adjacent orbital satellites can be expressed as:
3. constellation design examples
The task requires full coverage of an illumination area in a latitude range of 10-50 degrees of north latitude, the minimum observation angle of the satellite is 15 degrees, and two constellations are designed according to the design method of the orbit and the constellation: a sun-synchronous orbit constellation with orbit inclination i of 116.6 ° and a non-sun-synchronous orbit with orbit inclination i of 63.4 °.
(1) Constellation 1 (non-sun synchronous orbit)
3 satellites are deployed in each orbital plane of the satellite, the satellites in the planes are uniformly distributed according to a period, 4 orbital planes are deployed in total, the orbital planes are uniformly distributed, the phase difference of the satellites on the adjacent orbital planes is 0, and the detailed parameters of the satellites are shown in the following table:
4 track surfaces are uniformly distributed and can fully cover an illumination area in a northern latitude 10-50 degrees area.
Fig. 4 is a diagram of average coverage weight of constellation design example 1 along with change of latitude in a constellation design method of a medium orbit elliptical orbit remote sensing satellite. As shown in fig. 4, the average coverage weight of the constellation 1 varies with the latitude, and it can be seen that the coverage weight increases with the increase of the latitude, and the coverage is better for the middle and high latitude areas.
(2) Constellation 2 (Sun synchronous orbit)
3 satellites are deployed in each orbital plane of the satellite, the satellites in the planes are uniformly distributed according to a period, 2 orbital planes are deployed in total, and when the orbital planes are respectively deployed at a target local point position, 9: 30 and 14: 30, the phase difference between adjacent orbital satellites is 0, and the detailed parameters of each satellite are shown in the following table:
as can be seen from the real-time coverage area diagram of the satellite, 2 orbital planes are distributed in the illumination area, and can fully cover the illumination area in the northern latitude 10-50 degrees.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware related to instructions of a computer program, which can be stored in a computer readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. The storage medium may be a magnetic disk, an optical disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), or the like.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and additions can be made without departing from the principle of the present invention, and these should also be considered as the protection scope of the present invention.
Claims (10)
1. A method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite is characterized by comprising the following steps:
s1, designing an ellipse freezing orbit of the medium orbit ellipse orbit remote sensing satellite by utilizing the characteristic that the ellipse orbit of the medium orbit ellipse orbit remote sensing satellite resides in a long distance place; specifically, the method comprises the following steps:
s11, selecting an inclination angle i of the oval freezing orbit;
s12 height h of near point of oval freezing orbitpHeight h from distant placeaSelecting;
s13, selecting an argument omega of the perigee of the oval freezing orbit;
s14, selecting an oval freezing orbit ascending intersection point right ascension omega;
s2, aiming at the characteristic that the oval orbit of the medium orbit oval orbit remote sensing satellite is a non-uniform orbit with high near-to-site movement speed and low far-to-site movement speed, designing a special Walker constellation of the medium orbit oval orbit remote sensing satellite; specifically, the method comprises the following steps:
s21, calculating a flat near point angle of the satellite in the special Walker constellation orbit plane;
s22, calculating the number S of satellites in each orbital plane of the special Walker constellation;
and S23, calculating the approximate point angle difference of the adjacent orbital planes of the special Walker constellation.
2. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 1, characterized in that the step S11: make the near-location argument omega of the elliptic freezing orbit precession every day
Selecting an elliptic freezing orbit inclination angle i for zero, namely the argument omega of the near place is constant, wherein ReIs the earth radius, e is the eccentricity of the elliptical freeze orbit, and a is the semi-major axis of the elliptical freeze orbit.
3. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 2, characterized in that: the elliptical freezing orbit is a non-sun-synchronous orbit with i equal to 63.4 degrees, or a sun-synchronous orbit with i equal to 116.6 degrees.
4. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 2, characterized in that the step S12: approximate height h of elliptic freezing orbitpHeight h from distant placeaIs selected from the range
5. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 4, characterized in that: when the elliptical freezing orbit is a sun synchronous orbit with i being 116.6 degrees, the altitude of the perigee is highhpHeight h from distant placeaSatisfy the requirements of
Wherein R iseIs the earth radius, e is the ellipse freeze orbit eccentricity, a is the ellipse freeze orbit semi-major axis.
6. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 4, wherein the step S13 is as follows: argument omega of near place and latitude of observation target point
In relation to (2)
And freezing the apogee on the observation target point by adjusting the apogee argument omega to select the perigee argument omega of the elliptic freezing orbit.
7. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 6, wherein the step S14 is: when the elliptical freezing orbit is a sun synchronous orbit with i being 116.6 degrees, the right ascension omega of the ascending intersection point of the elliptical freezing orbit meets the light condition constraint, so that when the satellite ascends and tracks through the target point, the local time of the target point is near noon.
8. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 7, wherein the step S21 is: the satellites in the orbit plane of the special Walker constellation are uniformly distributed according to the period, namely the flat near point angle of the satellites in the same orbit plane
Wherein p is the number of satellites in the orbital plane.
9. The method for designing a constellation of medium orbit elliptical orbit remote sensing satellites as defined in claim 8 whereinStep S22: number of satellites in each orbital plane of special Walker constellation
Wherein T is the orbital period, T1The average observation time length is single star.
10. The method for designing a constellation of a medium orbit elliptical orbit remote sensing satellite according to claim 9, characterized in that the step S23: mean and near point angle difference of adjacent orbital planes of special Walker constellation
Wherein f is a phase factor.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115149995A (en) * | 2022-05-16 | 2022-10-04 | 亚太卫星通信(深圳)有限公司 | HEO constellation orbit design method |
| CN117885914A (en) * | 2024-03-14 | 2024-04-16 | 中国科学院地质与地球物理研究所 | Space detection method of coplanar orbit and satellite load |
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- 2022-01-13 CN CN202210038730.5A patent/CN114491999A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115149995A (en) * | 2022-05-16 | 2022-10-04 | 亚太卫星通信(深圳)有限公司 | HEO constellation orbit design method |
| CN115149995B (en) * | 2022-05-16 | 2023-11-24 | 亚太卫星通信(深圳)有限公司 | HEO constellation orbit design method |
| CN117885914A (en) * | 2024-03-14 | 2024-04-16 | 中国科学院地质与地球物理研究所 | Space detection method of coplanar orbit and satellite load |
| CN117885914B (en) * | 2024-03-14 | 2024-06-07 | 中国科学院地质与地球物理研究所 | Space detection method of coplanar orbit and satellite load |
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