CN104038272B - Medium earth orbit (MEO) global coverage constellation under limit of illumination - Google Patents
Medium earth orbit (MEO) global coverage constellation under limit of illumination Download PDFInfo
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Abstract
The invention discloses a medium earth orbit (MEO) global coverage constellation under limit of illumination, relates to the technical field of satellite communications and aims to solve the problem of interference caused by anti-solar adjustment of global coverage and satellite attitude. The constellation is a Walker constellation 12/3/1 which uses an earth center ecliptic coordinate system as a reference surface, the phase factor is 1, and the orbit altitude of each MEO satellite is 20183.63km. According to the MEO global coverage constellation, positions of satellite orbit surfaces are reasonably configured, the included angle between sun incident light and a solar panel is still no less than 66.5 degrees in a year during in-orbit operation of the satellites, illumination of the solar panel is adequate, normal operation of the satellites can be guaranteed without a special anti-solar adjustment strategy for the satellite attitude, global one-coincidence real-time coverage rate reaches above 97.97%, and one-coincidence accumulation coverage rate reaches 100%. The MEO global coverage constellation under limit of illumination is applicable to the satellite communications.
Description
Technical field
The present invention relates to technical field of satellite communication, and in particular to one kind can provide Global coverage and the attitude of satellite not
Need to can guarantee that day adjustment in the middle rail Global coverage constellation under the illumination constraint of the enough power outputs of solar energy sailboard.
Background technology
As the development that deepens continuously of global IT application, global PMC business are skyrocketed through, people are to movement
The dependence of communication is strengthened, and to it more and more higher is required.However, merely by existing land mobile communication system also far from
Demand can be met.In the area that land mobile communication cannot be covered, it is necessary to reach as relay station by the satellite in space
To the requirement of communication.The satellite constellation of Global coverage is constituted using multi-satellite, nothing can be provided for the user in global range
Seam roams communication function anywhere or anytime.Therefore satellite constellation of the design with Global coverage ability becomes satellite mobile communication
One trend of development.
In recent years, with the development of satellite mobile communication technology, many researchers propose one after another different types of satellite
Constellation Design scheme.Low rail, middle rail and satellite constellation can be divided into from orbit altitude, they have respective spy
Point.
Communication service is moved using satellite possess many advantages：As single GEO satellite can be covered
The 42.2% of ball surface product, only needs in theory three GEO satellites just can be with covering the whole world；With respect to ground static, there is no switching
And Doppler frequency shift is little；Technology relative maturity is simple, invest relatively less, operation facilitates.But, GEO satellite also has and does not utilize
The shortcoming of communication, for example：Orbit altitude is up to 36000km, and communication distance is long, extends during call, is unfavorable for that voice leads in real time
Letter；Link load is big, it is impossible to make handheld terminal summary, miniaturization；There is coverage hole near the two poles of the earth；Use to high latitude area
Family offer hand-held set business is more difficult, and speed can not be too high.
LEO satellite communication systems then on the contrary, because track is low, bring link load little, time delay is short, low rail in addition
The track resources of satellite are enriched, and can realize including the Global coverage at the two poles of the earth, but cover to provide continuous covering and the whole world
Lid, needs the satellite of dozens or even hundreds of and corresponding numerous ground gateway station, not only involves great expense but also low orbit satellite
Movement velocity is fast, causes system handoff algorithms complicated.
Middle rail system is in a sense the compromise of low rail and stationary orbit constellation scheme, and rail system is set up complete in utilization
Ball mobile satellite communication system only needs several or more than ten satellites.The time delay of middle orbit system signal and link load are all more static
Track is little, is conducive to the simplification of ground based terminal, and the double jump communication of compact simplified mobile terminal.Therefore rail Global coverage star in
Seat is the development trend of Future Satellite Constellation Design.
Main energy sources of the satellite in space are provided by solar energy sailboard.Due to inclination of satellite orbit it is bigger than normal, satellite
Pose adjustment, the earth such as revolves around the sun at a variety of causes, satellite with respect to the sun orientation in constantly change, so as to cause
The illuminating area of the solar energy sailboard of satellite is too small, it is impossible to ensure the sufficient output power of solar energy sailboard.In order to improve the sun
Can windsurfing power output, solar incident angle is maintained in a less scope, need special to day adjustable strategies.But
Be it is lasting day adjustable strategies can be kept to the attitude of satellite, earth observation, the foundation of inter-satellite link bring larger interference,
The satellite system complexity of increase, can increase accordingly construction and the maintenance cost of system.
The content of the invention
The invention aims to solve Global coverage and the attitude of satellite because the interference problem brought to day adjustment, carries
A kind of middle rail Global coverage constellation under for illumination constraint.
Middle rail Global coverage constellation under a kind of illumination constraint of the present invention is on the basis of geocentric-ecliptical system
The Walker constellations 12/3/1 in face, phase factor is 1, i.e.,：The constellation includes that 12 MEO being evenly distributed on three tracks are defended
Star；The solar energy sailboard of every MEO satellite is not less than 66.5o with the angle of sunshine incident direction.
The orbit altitude of every MEO satellite is 20183.63km.
Three described tracks are respectively a track, No. two tracks and No. three tracks, and three tracks are with the earth's core equator
The orbit parameter in face is on the basis of coordinate system：
A number track：I=40.40 °, Ω=32.19 °, ωk1=32.19 °, ωk2=122.19 °, ωk3=212.19 °,
ωk4=302.19 °；
No. two tracks：I=0 °, Ω=0 °, ωk1=30 °, ωk2=120 °, ωk3=210 °, ωk4=300 °；
No. three tracks：I=40.40 °, Ω=327.81 °, ωk1=27.90 °, ωk2=117.90 °, ωk3=
207.90 °, ωk4=297.90 °；
Wherein, i is orbit inclination angle, and Ω is dextrorotation right ascension of ascending node, and ω is argument of perigee, and k represents k-th orbital plane.
Middle rail Global coverage constellation under a kind of illumination constraint of the present invention, by reasonable disposition satellite orbit face
Position, when making satellite in orbit, sun incident light is remained in the larger context (no with solar energy sailboard among 1 year
Less than 66.5 °), solar energy sailboard illumination is sufficient, the attitude of satellite need not adopt it is special to day adjustable strategies it is ensured that defending
The normal work of star, on this basis, is arranged in the orbital plane for meet condition to realize to the whole world using 12 middle rail satellites
Covering.Above-mentioned constellation to the whole world the real-time coverage rate of a weight reach 97.97～98.88%, and one again accumulation coverage rate reach
100%, the ability with Global coverage；The attitude of satellite need not adopt it is special day adjustable strategies can guarantee that sunshine with
The angle of solar energy sailboard is not less than 66.5 °, makes solar energy sailboard illumination sufficient so as to ensure enough power output and radiating
Ability；Every satellite can be communicated for 24 hours with China earth station indirectly directly or by inter-satellite link, be realized real
When communication and information transfer.
Description of the drawings
Fig. 1 is the structural representation of the Satellite of present embodiment one, wherein 1 represents sunshine incident direction, 2 represent the sun
Energy windsurfing, 3 represent satellite orbits；
Fig. 2 is the three-dimensional distribution map of the constellation described in embodiment four, wherein 11,12,13 and 14 represent respectively a rail
Four satellites on road, i.e. satellite 11, satellite 12, satellite 13 and satellite 14,21,22,23 and 24 are represented respectively on No. two tracks
Four satellites, i.e. satellite 21, satellite 22, satellite 23 and satellite 24,31,32,33 and 34 represent respectively four on No. three tracks
Satellite, i.e. satellite 31, satellite 32, satellite 33 and satellite 34；
Fig. 3 is the simulation result of the real-time coverage rate of a weight in embodiment four and accumulation coverage rate；
Fig. 4 is that in embodiment four, 4 satellites on a track are tied with the visibility analysis of Sanya earth station
Really；
Fig. 5 is that in embodiment four, the solar energy sailboard of the satellite of three orbital planes is tied with the emulation of the angle of sunshine
Really.
Specific embodiment
Specific embodiment one：Present embodiment is illustrated with reference to Fig. 1, under a kind of illumination constraint described in present embodiment
Middle rail Global coverage constellation, the constellation is the Walker constellations 12/3/1 in the face on the basis of geocentric-ecliptical system, phase factor
For 1, i.e.,：The constellation includes 12 MEO satellites being evenly distributed on three tracks；The solar energy sailboard of every MEO satellite with
The angle of sunshine incident direction is not less than 66.5 °.
Middle rail Global coverage constellation under a kind of illumination constraint described in present embodiment is to be with geocentric-ecliptical system
The Walker constellations 12/3/1 of datum level design, phase factor is that 1, Walker constellations have widely in many real systems
Using with ideal coverage property.
As shown in figure 1, the angle of solar energy sailboard and sunshine incident direction refer to solar energy sailboard place plane with too
The angle of sunlight incident direction, solar incident angle is defined as the angle of sunshine incident direction and satellite orbit plane.The angle
Can change with respect to the change in the orientation of the sun with satellite during satellite transit, cause solar wing to be powered if becoming conference
The reduction of efficiency and the decline of satellite heat-sinking capability.The angle is due to orbital plane and the inconsistent generation of ecliptic plane.Affecting should
The factor of angle has 2, orbit inclination angle and right ascension of ascending node (RAAN).Orbit inclination angle closer to ecliptic obliquity (about 23.5 °), too
Positive angle is less；Right ascension of ascending node (RAAN) is less, and sun angle is less.When orbital plane overlaps with ecliptic plane, the angle is most
Little is 0, and solar energy sailboard is maximum by illuminating area.Therefore, if it is desired to sun incidence angle is minimum, inclination angle should be as close possible to Huang
Road face, i.e. orbit inclination angle are close 23.5 °, right ascension of ascending node RAAN=0.Solar incident angle is less, sunshine and solar energy sailboard
Angle bigger (both are into complementary angle relation), i.e., bigger by illuminating area, solar energy sailboard power supplying efficiency is higher.Solar incident angle
It is as shown in Figure 1 with the angle of solar energy sailboard with sunshine.
Orbit parameter in satellite be all defined in the equatorial coordinates of the earth's core, in order to reduce the complexity of design, first with
Face carries out MEO Constellation Designs on the basis of geocentric-ecliptical system, then again that the Parameter Switch for designing is red to corresponding the earth's core
In road coordinate system.The origin of geocentric equatorial polar coordinate is located at earth centroid, and the face on the basis of the equatorial plane, X-axis points to the first point of Aries, Z
Axle points to zenith direction, and Y-axis meets right-hand rule, and satellite orbit parameters are all based on what the coordinate system was obtained；The earth's core is yellow
The origin of road coordinate system also is located at earth centroid, the face on the basis of ecliptic plane, and X-axis points to the first point of Aries, and Z axis point to ecliptic plane normal
Direction.Introducing the coordinate system contributes to the relative position relation of the apparent statement sun and satellite.
The clas sical orbit six roots of sensation number being defined under geocentric equatorial polar coordinate is：Semi-major axis of orbit a, orbital eccentricity e, track
Inclination angle i, dextrorotation right ascension of ascending node Ω, argument of perigee ω, true anomaly f.The track six being defined under geocentric-ecliptical system
Radical is：Semi-major axis of orbit aQ, orbital eccentricity eQ, orbit inclination angle iQ, dextrorotation right ascension of ascending node ΩQ, argument of perigee ωQ, very
Perigee angle fQ, be apparent from represent track size and shape orbital tracking be with clas sical orbit radical as, i.e. aQ=a, eQ=
E, understands that true perigee angle is also the same, i.e. f by definitionQ=f.Due to the presence of ecliptic obliquity, iQ、ΩQ、ωQWith i, Ω,
ω is general different.There is relationship below, wherein ε is ecliptic obliquity：
If satellite orbit face is θ with the angle of ecliptic plane, as iQ, sunshine is α with the angle of orbital plane, because the sun
LightAlways in ecliptic plane, then there is relational expression α≤iQ(θ).Sunshine is not less than 66.5 ° with the angle of solar energy sailboard, then
Angle of incidence of sunlight needs to be maintained within 23.5 °, i.e. α≤23.5 °, therefore geocentric-ecliptical system lower rail road inclination needs full
Sufficient iQ≤23.5°.Therefore orbit inclination angle iQDuring less than or equal to 23.5 °, every satellite one surely meets the bar of illumination constraint in constellation
Part.
Middle rail Global coverage constellation under a kind of illumination constraint described in present embodiment is covered in real time to a weight in the whole world
Rate be 97.97～98.88%, and one again accumulation coverage rate reach 100%, the ability with Global coverage；The attitude of satellite is not required to
Sunshine is not less than 66.5 ° with the angle of solar energy sailboard to adopt special can guarantee that to day adjustable strategies, makes solar energy
Windsurfing illumination is sufficient so as to ensureing enough power outputs and heat-sinking capability；Every satellite can be directly or by between inter-satellite link
Connect and communicated within 24 hours with China earth station, realize communication and information transfer in real time.
Specific embodiment two：With reference to explanation present embodiment, present embodiment is to the one kind described in embodiment one
The further restriction of the middle rail Global coverage constellation under illumination constraint, in present embodiment, the orbit altitude of every MEO satellite is
20183.63km。
Satellite orbital altitude is 20183.63km, and the corresponding orbital period is that 1/2nd of a sidereal day, i.e., 12 are little
When, meet the requirement of regression orbit, facilitate the point and track towards of earth station.
Specific embodiment three：With reference to Fig. 2 and Fig. 4 explanation present embodiments, present embodiment is to the institute of embodiment one
The further restriction of the middle rail Global coverage constellation under a kind of illumination constraint stated, in present embodiment, the constellation adopts 6 ground
Face station is tracked, and 6 earth stations are respectively Beijing Station, Xiamen station, Sanya station, Keshen station, Jiamusi station and Chongqing station.
Present embodiment is carried out using 6 domestic earth stations by star ground and inter-satellite link to 12 satellites in constellation
Tracking, remote control and remote measurement and carries out data information transfer.6 earth stations are located at respectively Beijing, Xiamen, Sanya, Keshen, good wood
This, Chongqing.Above-mentioned 6 earth stations covers substantially the east, south, west, north and middle part of China.Sanya is Chinese territory southernmost end
Earth station, the observability of 4 satellites in the orbital plane of a lower number track of surface analysis and Sanya.Selection is carried out for 24 hours one day
Simulation analysis, as shown in figure 4, Sanya can directly or indirectly be communicated with the round-the-clock satellite with an orbital plane.For example, from
In this time period of T1 to T2, Sanya can be directly visible with satellite 12, and satellite 13 and satellite 11 can be by orbital planes
Inter-satellite link communicates with Sanya indirectly via satellite 12, and satellite 14 then needs to arrive satellite 12 again through satellite 13 or 11, totally 2 jumps star
Between communication could return the country earth station.
Specific embodiment four：Present embodiment is illustrated with reference to Fig. 2, Fig. 3 and Fig. 5, present embodiment is to embodiment party
The further restriction of the middle rail Global coverage constellation under a kind of illumination constraint described in formula one, in present embodiment, described three
Individual track is respectively a track, No. two tracks and No. three tracks, three track faces on the basis of geocentric equatorial polar coordinate
Orbit parameter is：
A number track：I=40.40 °, Ω=32.19 °, ωk1=32.19 °, ωk2=122.19 °, ωk3=212.19 °,
ωk4=302.19 °；
No. two tracks：I=0 °, Ω=0 °, ωk1=30 °, ωk2=120 °, ωk3=210 °, ωk4=300 °；
No. three tracks：I=40.40 °, Ω=327.81 °, ωk1=27.90 °, ωk2=117.90 °, ωk3=
207.90 °, ωk4=297.90 °；
Wherein, i is orbit inclination angle, and Ω is dextrorotation right ascension of ascending node, and ω is argument of perigee, and k represents k-th orbital plane.
When orbit inclination angle is bigger, coverage property is better, therefore the inclination angle of orbital plane takes iQ=23.5 °.In order to cover low latitude
Degree area, an orbital plane is placed on equatorial plane, while the covering in order to take into account high latitude area and polar regions, adopts two
Individual orbit inclination angle iQ=23.5 ° of orbital plane.4 satellites are uniformly distributed in each orbital plane.Satellite orbit parameter in constellation
It is shown in Table 1.
The orbit parameter in the face on the basis of geocentric-ecliptical system of table 1
| Track | iQ | ΩQ | ωQk1 | ωQk2 | ωQk3 | ωQk4 |
| A number track | 23.5° | 60° | 0° | 90° | 180° | 270° |
| No. two tracks | 23.5° | 180° | 30° | 120° | 210° | 300° |
| No. three tracks | 23.5° | 300° | 60° | 150° | 240° | 330° |
Wherein k is k-th orbital plane.
The orbit parameter on the basis of the ecliptic plane of the earth's core is mapped to the orbit parameter in the face on the basis of the equatorial plane using formula 1
As shown in table 2.From position all closely ecliptics of the orbital plane of following table, the orbital plane of a track and No. three tracks
Face.
The orbit parameter in the face on the basis of geocentric equatorial polar coordinate of table 2
| Track | i | Ω | ωk1 | ωk2 | ωk3 | ωk4 |
| A number track | 40.40° | 32.19° | 32.19° | 122.19° | 212.19° | 302.19° |
| No. two tracks | 0 | 0 | 30° | 120° | 210° | 300° |
| No. three tracks | 40.40° | 327.81° | 27.90° | 117.90° | 207.90° | 297.90° |
The three-dimensional distribution map of the Global coverage constellation being made up of 12 MEO is as shown in Figure 2.
What Fig. 3 was given is the simulation result of the real-time coverage rate of the weight of the constellation whole world one and accumulation coverage rate, and the communication elevation angle is
15°.It can be seen that the real-time coverage rate of a weight of the constellation is 97.97～98.88%, a weight in the whole world is covered in real time
Lid rate reached more than 97.97%, and one again accumulation coverage rate reach 100%, therefore with the function of Global coverage constellation.
Fig. 5 gives the satellite of three orbital planes solar energy sailboard and sunshine incident direction within 365 days 1 year
The simulation result figure of the change of angle.Number track, No. two tracks and a No. three track Satellite solar energy sailboards and sunshine
Angle is between 66.5 °～90 °.Being continually changing with the relative solar azimuth of satellite in 1 year, in this in rail constellation scheme,
Disclosure satisfy that solar energy sailboard is more than 66.5 ° with the minimum angle of sunshine, it is ensured that the sufficient illuminating area of solar energy sailboard
And power output.
Therefore the middle rail Global coverage constellation under illumination constraint can keep sunshine to enter with whole year without pose adjustment
Penetrate direction to be more than 66.5 ° with the angle of solar energy sailboard and can guarantee that good coverage property.
Claims (2)
1. the middle rail Global coverage constellation under a kind of illumination constraint, it is characterised in that：The constellation is to be with geocentric-ecliptical system
The Walker constellations 12/3/1 of datum level, phase factor is 1, i.e.,：The constellation includes 12 be evenly distributed on three tracks
MEO satellite, the solar energy sailboard of every MEO satellite is not less than 66.5 ° with the angle of sunshine incident direction,
The orbit altitude of every MEO satellite is 20183.63km,
Three described tracks are respectively a track, No. two tracks and No. three tracks, and three tracks are with the earth's core equatorial coordinates
The orbit parameter in face is on the basis of system：
A number track：I=40.40 °, Ω=32.19 °, ωk1=32.19 °, ωk2=122.19 °, ωk3=212.19 °, ωk4
=302.19 °；
No. two tracks：I=0 °, Ω=0 °, ωk1=30 °, ωk2=120 °, ωk3=210 °, ωk4=300 °；
No. three tracks：I=40.40 °, Ω=327.81 °, ωk1=27.90 °, ωk2=117.90 °, ωk3=207.90 °, ωk4
=297.90 °；
Wherein, i is orbit inclination angle, and Ω is dextrorotation right ascension of ascending node, and ω is argument of perigee, and k represents k-th orbital plane.
2. the middle rail Global coverage constellation under a kind of illumination constraint according to claim 1, it is characterised in that：The constellation is adopted
It is tracked with 6 earth stations, 6 difference Beijing Stations of earth station, Xiamen station, Sanya station, Keshen station, Jiamusi station and the Chongqing
Stand.
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