CN106533530A - Communication constellation and establishing method thereof - Google Patents
Communication constellation and establishing method thereof Download PDFInfo
- Publication number
- CN106533530A CN106533530A CN201610898444.0A CN201610898444A CN106533530A CN 106533530 A CN106533530 A CN 106533530A CN 201610898444 A CN201610898444 A CN 201610898444A CN 106533530 A CN106533530 A CN 106533530A
- Authority
- CN
- China
- Prior art keywords
- satellite
- plane
- orbit
- orbit plane
- communication
- 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.)
- Pending
Links
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Electromagnetism (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention relates to a communication constellation. The communication constellation is composed of several satellites; the satellites are distributed on various orbital planes; a dihedral angle is formed between each orbital plane and the equatorial plane; phase factors exist among the various orbital planes; the various orbital planes are distributed on the equatorial plane according to the phase factors; and the communication constellation has a steady communication link, and can perform continuous communication. The invention further relates to an establishing method of the communication constellation. The communication constellation is established through the method.
Description
Technical field
A kind of the present invention relates to communications field, more particularly to communication satellite constellation.
The invention further relates to the method for building up of communication satellite constellation.
Background technology
Communication satellite constellation is the satellite network set up by multi-satellite.Communication satellite constellation is the important component part of communication system.
By iridium satellite project, sky arranges multi-satellite and has set up iridium communication constellation on earth for Motorola Inc..Iridium communication net
By the inter-satellite link set up between communication satellite constellation Satellite and satellite, communication terminal is made to carry out phase intercommunication in global optional position
Letter is achieved.But, iridium communication constellation Satellite is placed on the track of differing heights, the communication chain between satellite and satellite
Road is not fixed.So, the inter-satellite link between iridium satellite is caused according to periodic transformation.
The content of the invention
In order that inter-satellite link between satellite and satellite keeps constant, the invention provides a kind of communication satellite constellation, by counting
Satellite composition, the satellite distribution is on each orbit plane；There is between the orbit plane and the equatoriat plane dihedral angle, institute
State, the orbit plane is divided equally on the equatoriat plane according to the phase factor；The communication
Constellation has stable communication link；The stable communication link is by same rail communication link and different rail communication link structure
Into；The same rail communication link is made up of 2 satellites divided equally on same orbit plane；The different rail communication chain
Road is made up of 2 neighbouring satellites on 2 neighbouring different orbit planes, if selecting 1 track from the orbit plane
As central orbit plane, and 1 satellite is selected in the central orbit plane as central satellite, from the central track
After road plane is rotated respectively along the clockwise phase factor or phase factor counterclockwise, 2 different orbit planes are determined, and from institute
State select on 2 different orbit planes 4 satellites neighbouring with the central satellite and with the central satellite constitute 4 it is stable
Communication link.
Preferably, the satellite, its sum are 70；The orbit plane, its sum are 10；The orbit plane with
Dihedral angle between the equatoriat plane is 55 degree；Phase factor between the orbit plane is 18 degree.
Preferably, the satellite is provided with 6 laser communication machines, and wherein 2 are used for the same rail communication link, in addition
4 are used for the different rail communication link.
In order to realize communication satellite constellation, present invention also offers a kind of method for building up of communication satellite constellation, by several satellite distributions
On each orbit plane, there is between the orbit plane and the equatoriat plane dihedral angle, there is between the orbit plane phase factor,
The orbit plane is divided equally on the equatoriat plane according to the phase factor；
2 neighbouring satellites are arbitrarily selected in the satellite on same orbit plane from dividing equally, and set up one in-between
The stable communication link of bar, the communication link are same rail communication links；
1 track is selected from the orbit plane as central orbit plane, and in the central orbit plane
1 satellite is selected as central satellite；
Rotated along the clockwise phase factor or phase factor counterclockwise respectively from the central orbit plane, respectively obtained
2 different orbit planes；
2 satellites neighbouring with central satellite are respectively selected on 2 described different orbit planes, and are defended with described 4
The stabilized communication link constituted between star and the central satellite is used as different rail communication link.
Compared with prior art, it is an advantage of the current invention that arbitrary satellite in communication satellite constellation is as reference, itself and neighbour
Remain stable between nearly satellite.As the incidence relation between each satellite is stable all the time, make structure stable based on this
Communication link be possibly realized.On here basis, the invention provides the communication satellite constellation for carrying laser communication machine is more to complete
Interconnecting between satellite.Meanwhile, the present invention specifies the method for building up of communication satellite constellation, by this method with realization
State communication satellite constellation.
Description of the drawings
Fig. 1 is the schematic diagram for showing the first orbital plane in terms of reference plane direction from master.
Fig. 2 is the schematic diagram from the rib overlooked in terms of reference plane direction between the first orbital plane and reference plane.
Fig. 3 is from the schematic diagram for overlooking the first to the tenth orbital plane rib respectively between reference plane in terms of reference plane direction.
Specific embodiment
Below in conjunction with the accompanying drawings the specific embodiment of the present invention is described in detail.The invention provides a kind of COMSTAR Communication Star
Seat, is made up of 70 satellites.70 satellite distributions are on each track of communication satellite constellation.In this specific embodiment, from 70
It is to write for convenience that satellite is illustrated, and may determine number of satellite and number of tracks according to actual needs.As shown in figure 1,
Using above terrestrial equator sea level 6000 kilometers of position rings around the earth's core circular flat of a week as reference plane 0.Originally it is embodied as
Mode is for convenience of description from 6000 kilometers of positions above earth Equator plane.This put and can be changed.From reference
The main view direction in face 0 sees, the plane 1 formed by the first track and reference plane 0 are concentric circular, and the first track formed it is flat
Dihedral angle 13 between face 1 and reference plane 0 is 55 degree.As shown in Fig. 2 from terms of the overlook direction of reference plane, the first track institute shape
Into plane 1 intersect with reference plane 0 production dihedral angle rib 14.The center of circle of the rib 14 of dihedral angle by referring to face 0, and first
Track intersects at A11 points 11 and A12 points 12 with reference plane.
As shown in figure 3, the rib 14 of dihedral angle rotates in reference plane 18 along clockwise direction respectively, 36,54,72,90,
108th, 126,144 or 162 degree, then respectively obtain the second track, the 3rd track, the 4th track, the 5th track, the 6th track,
7th track, the 8th track, the 9th track or the tenth track.Second track and reference plane intersect at A21 points 21 and the
A22 points 22.3rd track intersects at A31 points 31 and A32 points 32 with reference plane.4th track and reference plane intersect at the
A41 points 41 and A42 points 42.5th track intersects at A51 points 51 and A52 points 52 with reference plane.6th track and reference
Face intersects at A61 points 61 and A62 points 62.7th track intersects at A71 points 71 and A72 points 72 with reference plane.8th
Track intersects at A81 points 81 and A82 points 82 with reference plane.9th track intersects at A91 points 91 and A92 with reference plane
Point 92.Tenth track intersects at A101 points 101 and A102 points 102 with reference plane.Between arbitrary track and reference plane 0 two
Face angle is 55 degree.This specific embodiment selects 55 for ease of explanation.The angle can change.
7 satellites are respectively provided with every track, and every satellite is evenly distributed in a rail according to the spacing less than 55 degree
On road.Communication satellite constellation amounts to 70 satellites, and each satellite angular velocity mould in orbit is identical.On each track, every satellite
Between geo-stationary.Communication link steady in a long-term is constituted with 2 satellites of the geo-stationary in front and back in orbital plane.
Arbitrary satellite on first track is respectively adjacent to two on two satellites and the second track on the tenth track
Satellite.
Arbitrary satellite on second track is respectively adjacent to two on the first track two satellites and the 3rd track
Satellite.
Arbitrary satellite on 3rd track is respectively adjacent to two on the second track two satellites and the 4th track
Satellite.
Arbitrary satellite on 4th track is respectively adjacent to two on two satellites and the 5th track on the 3rd track
Satellite.
Arbitrary satellite on 5th track is respectively adjacent to two on two satellites and the 6th track on the 4th track
Satellite.
Arbitrary satellite on 6th track is respectively adjacent to two on two satellites and the 7th track on the 5th track
Satellite.
Arbitrary satellite on 7th track is respectively adjacent to two on two satellites and the 8th track on the 6th track
Satellite.
Arbitrary satellite on 8th track is respectively adjacent to two on two satellites and the 9th track on the 7th track
Satellite.
Arbitrary satellite on 9th track is respectively adjacent to two on two satellites and the tenth track on the 8th track
Satellite.
Arbitrary satellite on tenth track is respectively adjacent to two on two satellites and the first track on the 9th track
Satellite.
If selecting 1 orbit plane from 10 orbit planes as central orbit plane, and select in central orbit
Fixed 1 satellite is used as central satellite；Then 18 degree of phase factors clockwise and 18 degree of phases counterclockwise can be pressed by the central orbit
There are 4 satellites neighbouring with central satellite on location factor rotation determination 2 different orbit planes, and 2 different orbit planes.4
Such satellite constitutes 4 stable communication links with central satellite.
Arrange satellite in this way, then can be between any two neighbouring satellites in any two different orbital planes
Set up a communication link steady in a long-term.
AnIridium satellite constellation is that satellite is arranged in different orbital planes, and communication link is not fixed.This constellation and iridium
Star seat is compared, and its satellite is all distributed on same sphere, can set up steady in a long-term between the satellite on different tracks
Communication link.
Laser communication technology requires there is communication link steady in a long-term between laser communication machine.Led to using steady in a long-term
Letter link, then can be used for communicating by laser communication machine.Therefore, the communication satellite constellation that the present invention is provided provides the foundation for laser communication
Carrier.
Especially, laser communication machine is installed to realize carrying out high-speed communication with laser on such communication link.Per
6 laser communication machines are at least installed on satellite, wherein 2 for being communicated with same orbiter, order it is outer 4 for different rail
Road satellite is communicated.
During communication satellite constellation is set up, the present invention proposes a kind of method for building up of communication satellite constellation, by 70 satellites
It is distributed on 10 orbit planes, the dihedral angle between the orbit plane and the equatoriat plane is 55 degree, between the orbit plane
Phase factor is 18 degree, and the orbit plane is divided equally on the equatoriat plane according to the phase factor.
From the first orbit plane, the second orbit plane, the 3rd orbit plane, the 4th orbit plane, the 5th orbit plane,
Arbitrary track in six orbit planes, the 7th orbit plane, the 8th orbit plane, the 9th orbit plane and the tenth orbit plane is put down
An orbit plane is chosen in face.Then, in 7 satellites from the orbit plane, 2 satellites are arbitrarily selected.This two are defended
Star is neighbouring.It is neighbouring to refer to there are no other satellites between a satellite and another satellite on sphere.Defended with this two
Star can make up a stable communication link.The communication link is same rail communication link.
From the first orbit plane, the second orbit plane, the 3rd orbit plane, the 4th orbit plane, the 5th orbit plane,
Arbitrary track in six orbit planes, the 7th orbit plane, the 8th orbit plane, the 9th orbit plane and the tenth orbit plane is put down
An orbit plane is chosen in face as central orbit plane.
Rotated from the central orbit plane respectively along 18 degree of phase factors clockwise or 18 degree of phase factors counterclockwise,
Respectively obtain 2 different orbit planes.
If using the first orbit plane as central orbit plane, from the first orbit plane along 18 degree of phase factors clockwise
Or 18 degree of phase factors counterclockwise rotate respectively, respectively obtain the second orbit plane or the tenth orbit plane.Second track
Plane is respectively 2 different orbit planes of the first orbit plane with the tenth orbit plane.
1 satellite is selected in 7 satellites from the first orbit plane arbitrarily as central satellite.
2 with central satellite neighbouring satellites are selected on 2 different orbit planes respectively.With this 4 satellites respectively with center
Satellite sets up 4 stable communication links as different rail communication link.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
Member, under the premise without departing from the principles of the invention, can also make some improvements and modifications, and these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (5)
1. a kind of communication satellite constellation, it is characterised in that be made up of several satellites, the satellite distribution is on each orbit plane；
There is between the orbit plane and the equatoriat plane dihedral angle, there is between the orbit plane phase factor, the track is put down
Face is divided equally on the equatoriat plane according to the phase factor；
The communication satellite constellation has stable communication link；The stable communication link is by same rail communication link and different track
Communication link is constituted；The same rail communication link is made up of 2 satellites divided equally on same orbit plane；It is described different
Rail communication link is made up of 2 neighbouring satellites on 2 neighbouring different orbit planes, if selecting from the orbit plane
Fixed 1 track is used as central orbit plane, and selectes 1 satellite in the central orbit plane as central satellite, from
After the central orbit plane is rotated respectively along the clockwise phase factor or phase factor counterclockwise, determine that 2 different tracks are put down
Face, and 4 satellites neighbouring with the central satellite are selected from 2 different orbit planes and with the central satellite structure
Into 4 stable communication links.
2. communication satellite constellation according to claim 1, it is characterised in that the satellite, its sum are 70；The track is put down
Face, its sum are 10；Dihedral angle between the orbit plane and the equatoriat plane is 55 degree；Phase place between the orbit plane because
Son is 18 degree.
3. communication satellite constellation according to claim 1, it is characterised in that the satellite is provided with 6 laser communication machines, wherein 2
Platform is used for the same rail communication link, and 4 are used for the different rail communication link in addition.
4. a kind of method for building up of communication satellite constellation, it is characterised in that by several satellite distributions on each orbit plane, the track
There is between plane and the equatoriat plane dihedral angle, there is between the orbit plane phase factor, the orbit plane is according to the phase
Location factor is divided equally on the equatoriat plane；
2 neighbouring satellites are arbitrarily selected in the satellite on same orbit plane from dividing equally, and set up one in-between surely
Fixed communication link, the communication link are same rail communication links；
1 track is selected from the orbit plane as central orbit plane, and in the central orbit plane selects 1
Satellite is used as central satellite；
Rotated along the clockwise phase factor or phase factor counterclockwise respectively from the central orbit plane, respectively obtain 2
Different orbit plane；
Respectively select 2 satellites neighbouring with central satellite on 2 described different orbit planes, and with 4 satellites and
The stabilized communication link constituted between the central satellite is used as different rail communication link.
5. the method for building up of communication satellite constellation according to claim 4, it is characterised in that the satellite, its sum are 70；Institute
Orbit plane is stated, its sum is 10；Dihedral angle between the orbit plane and the equatoriat plane is 55 degree；Between the orbit plane
Phase factor be 18 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610898444.0A CN106533530A (en) | 2016-10-14 | 2016-10-14 | Communication constellation and establishing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610898444.0A CN106533530A (en) | 2016-10-14 | 2016-10-14 | Communication constellation and establishing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106533530A true CN106533530A (en) | 2017-03-22 |
Family
ID=58331874
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610898444.0A Pending CN106533530A (en) | 2016-10-14 | 2016-10-14 | Communication constellation and establishing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106533530A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112865859A (en) * | 2021-01-15 | 2021-05-28 | 东方红卫星移动通信有限公司 | Method for testing laser communication between incoming planet and outgoing planet by adopting double laser satellites |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2271902B (en) * | 1992-10-20 | 1996-11-20 | Caterpillar Inc | Method and apparatus for predicting the position of a satellite in a satellite based navigation system |
| US6219617B1 (en) * | 1998-02-16 | 2001-04-17 | Contraves Space Ag | Method for determining the orbital positions of satellites in LEO networks |
| AU2005292573A1 (en) * | 2004-09-30 | 2006-04-13 | Exelis Inc. | Method and apparatus for multicast packet distribution in a satellite constellation network |
| US20140027576A1 (en) * | 2012-07-25 | 2014-01-30 | Planet Labs Inc. | Earth Observation Constellation Methodology & Applications |
| CN104601363A (en) * | 2014-12-03 | 2015-05-06 | 上海交通大学 | Orbit and domain partition type double-layer satellite network system and management method |
| CN105511483A (en) * | 2015-12-02 | 2016-04-20 | 上海宇航系统工程研究所 | Bird nest type constellation and design method thereof |
-
2016
- 2016-10-14 CN CN201610898444.0A patent/CN106533530A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2271902B (en) * | 1992-10-20 | 1996-11-20 | Caterpillar Inc | Method and apparatus for predicting the position of a satellite in a satellite based navigation system |
| US6219617B1 (en) * | 1998-02-16 | 2001-04-17 | Contraves Space Ag | Method for determining the orbital positions of satellites in LEO networks |
| AU2005292573A1 (en) * | 2004-09-30 | 2006-04-13 | Exelis Inc. | Method and apparatus for multicast packet distribution in a satellite constellation network |
| US20140027576A1 (en) * | 2012-07-25 | 2014-01-30 | Planet Labs Inc. | Earth Observation Constellation Methodology & Applications |
| CN104601363A (en) * | 2014-12-03 | 2015-05-06 | 上海交通大学 | Orbit and domain partition type double-layer satellite network system and management method |
| CN105511483A (en) * | 2015-12-02 | 2016-04-20 | 上海宇航系统工程研究所 | Bird nest type constellation and design method thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112865859A (en) * | 2021-01-15 | 2021-05-28 | 东方红卫星移动通信有限公司 | Method for testing laser communication between incoming planet and outgoing planet by adopting double laser satellites |
| CN112865859B (en) * | 2021-01-15 | 2021-11-16 | 东方红卫星移动通信有限公司 | Method for testing laser communication between incoming planet and outgoing planet by adopting double laser satellites |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Draim | Three-and four-satellite continuous-coverage constellations | |
| Mikołajewska | Symbiotic stars: observations confront theory | |
| CN105743717B (en) | Incorporate Information Network system and communication means based on SDN technology | |
| RU2278472C2 (en) | Improved system and method for organization of system of non-geostationary satellites, not creating any interference with operation of satellites, positioned on geostationary ring | |
| CN1254408C (en) | System and method for implementing a constellation of non-geostationary satellites that provides simplified satellite tracking | |
| CN106464343A (en) | Satellite constellation | |
| KR20200107962A (en) | Data transmission system and method using satellite to satellite radio link | |
| CN103632053A (en) | Combined scheduling method of satellite-ground measurement and control resources of low-mid-orbit satellite constellation based on orbit determination constraint satisfaction | |
| AU2017316680B2 (en) | Radio system using nodes | |
| US10843822B1 (en) | Satellite constellations | |
| US20200036437A1 (en) | Non-Geosynchronous Orbit Satellite Constellations | |
| JP7313571B2 (en) | surveillance systems, surveillance satellites, communication satellites | |
| US5911389A (en) | Wave based satellite constellation | |
| CN108028699A (en) | The satellite group of LEO, every satellite include being used to make satellite roll axis rotation around it to ensure the gesture stability module of Terrestrial Radio covering | |
| CN106533530A (en) | Communication constellation and establishing method thereof | |
| CN110266366A (en) | A kind of satellite navigation system data transmission cross-layer efficiently exchanges method | |
| CN108270477A (en) | Determining method and device, the terminal of serving satellite | |
| CN110096746A (en) | A kind of satellite cluster preliminary orbit design method and device | |
| US3706037A (en) | Communication satellite system | |
| US6050525A (en) | Asymmetric open rosette constellations | |
| CN114584200A (en) | Low-orbit satellite network routing method using relationship matrix and link monitoring | |
| CN108199763B (en) | Repeater satellite method for scheduling task and system | |
| CN112019258B (en) | GEO and LEO mixed constellation and design method thereof | |
| RU2535375C1 (en) | Method of viewing surface of planet from space and space satellite system for implementing said method | |
| CN109413662A (en) | A kind of low rail communication satellite constellation is connected to planing method with subscriber station |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170322 |