CN111431590A - Moon surface communication satellite constellation - Google Patents
Moon surface communication satellite constellation Download PDFInfo
- Publication number
- CN111431590A CN111431590A CN202010378529.2A CN202010378529A CN111431590A CN 111431590 A CN111431590 A CN 111431590A CN 202010378529 A CN202010378529 A CN 202010378529A CN 111431590 A CN111431590 A CN 111431590A
- Authority
- CN
- China
- Prior art keywords
- communication
- lunar
- moon
- constellation
- satellites
- 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
Images
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
- H04B1/00—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission
- H04B1/005—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission adapting radio receivers, transmitters andtransceivers for operation on two or more bands, i.e. frequency ranges
-
- 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
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18517—Transmission equipment in earth stations
Landscapes
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention belongs to the field of deep space communication. The invention provides a lunar surface communication satellite constellation, wherein the lunar surface comprises the front and the back of a moon, the constellation comprises two lunar communication satellites, the constellation establishes communication links between bases on the lunar surface through the two lunar communication satellites, the running orbits of the two lunar communication satellites are respectively an orbit around Lagrange 1 point of the Earth moon and an orbit around Lagrange 2 point of the Earth moon, and the communication link between at least one lunar communication satellite and each base on the lunar surface adopts Ku, Ka, Q or V frequency band or adopts laser communication. The embodiment of the invention can realize the complete coverage of the front and back communication of the moon and can realize the high-capacity and high-bandwidth stable communication of the front and back of the moon.
Description
Technical Field
The invention belongs to the field of deep space communication, and particularly relates to a lunar surface communication satellite constellation.
Background
After the bases are established on the front side of the moon in the future, no effective direct communication means exists for communication among the bases which are far away from each other, and the cost and the difficulty of arrangement of a lunar wired communication link are too high. The diameter of the moon is about 3476 km, the curvature of the moon surface is large, and the height difference of the moon surface is also very large, up to 20 km. The wireless communication link cannot realize communication at a long distance due to the influence of lunar surface curvature and height difference. Assuming that 3 (or more) bases are distributed on the front surface of the moon, the distance between the bases is more than 1000 kilometers, and reliable communication is difficult to realize through methods such as lunar surface wired link, lunar surface relay base station or lunar surface direct wireless communication and the like under the influence of lunar surface curvature and lunar surface height difference.
In particular, the base stations between the front and back of the moon cannot communicate directly or through earth ground stations.
Disclosure of Invention
The embodiment of the invention mainly aims to provide a lunar surface communication satellite constellation which can realize complete coverage of front and back communication of a moon, and particularly can meet the requirements of high-capacity and high-bandwidth stable communication of the front and back of the moon.
In order to achieve the above object, an embodiment of the present invention provides a lunar surface communication satellite constellation, where the lunar surface includes a front surface and a back surface of a moon, the constellation includes two lunar communication satellites, the constellation establishes a communication link between bases on the lunar surface through the two lunar communication satellites, the running orbits of the two lunar communication satellites are an orbit around a lagrangian 1 point of the moon and an orbit around a lagrangian 2 point of the moon, and a communication link between at least one lunar communication satellite and each base on the lunar surface adopts a Ku, Ka, Q, or V frequency band, or adopts laser communication.
The lunar surface communication satellite constellation provided by the embodiment of the invention comprises two lunar communication satellites, wherein the constellation establishes communication links between bases on the lunar surface through the two lunar communication satellites, and the running orbits of the two lunar communication satellites are respectively an orbit around Lagrange 1 point of Earth moon and an orbit around Lagrange 2 point of Earth moon; according to the lunar surface communication satellite constellation provided by the embodiment of the invention, at least one communication link between the lunar communication satellite and each base on the lunar surface adopts a Ku, Ka, Q or V frequency band, or adopts laser communication, and when the lunar communication satellite serves communication between lunar surface bases, the requirement of high-capacity and high-bandwidth stable communication can be met by adopting the Ku, Ka, Q or V frequency band or laser communication due to no atmospheric interference and rain attenuation influence.
Preferably, the communication link between the bases on the front and back of the moon is relayed by the moon communication satellite without passing back to the earth ground station. The communication between the lunar bases at all positions of the front and the back of the moon can be supported without returning the earth, so that the communication quality can be greatly improved, and the communication time delay is reduced. The time delay of a communication system between any two bases on the front side of the moon is about 500ms, the time delay of a communication system between any two bases on the back side of the moon is about 400ms, and the time delay of a communication system between the front side of the moon and the bases on the back side of the moon is about 800 ms.
Preferably, the lunar surface communication satellite constellation further comprises a lunar polar orbit communication satellite. Considering that the coverage of two communication satellites around Lagrange 1 point and Lagrange 2 point between earth months is insufficient for the north and south poles of the moon, one earth polar orbit communication satellite is added to form more sufficient communication coverage to serve the communication of the bases near the two poles of the moon.
Preferably, the orbital plane of the lunar polar orbital communication satellite is perpendicular to a line passing through lagrangian 1 and lagrangian 2 points of the earth moon. Therefore, more sufficient communication coverage can be formed, and the problem that the lunar surface coverage of two communication satellites which pass through Lagrange 1 points and Lagrange 2 points around the Earth moon is insufficient for a straight line which passes through the Lagrange 1 points and the Lagrange 2 points is solved.
Preferably, at least one of said lunar communication satellites relays communication from a lunar surface base to an earth ground station. This may reduce the system performance requirements for the lunar surface base to communicate with the earth.
Preferably, at least one of the lunar communication satellites orbits a circular orbit or an elliptical orbit. A lunar communication satellite operating in such an orbit operates more stably.
Preferably, laser communication is adopted between the lunar communication satellites as an inter-satellite communication link. This allows for communication with greater capacity, narrower beams, higher gain, faster speed, greater interference immunity, and better security.
Preferably, communications between at least one of said lunar communication satellites and an earth ground station use the S, C or Ku frequency band. Therefore, a certain communication bandwidth can be met, the rain attenuation resistance is good, the free space loss caused by low communication frequency is low in a large communication distance, and the long-term high-availability communication requirement can be met.
Preferably, at least one of said lunar communications satellites employs spot beam coverage to earth ground stations. This may reduce the transmit signal power requirements for a lunar communication satellite to communicate with the earth.
Preferably, at least one of said lunar communication satellites employs full lunar beam coverage of the front or back of the moon. Therefore, the comprehensive coverage of the bases on the front side of the moon or the bases on the back side of the moon can be guaranteed.
Preferably, 1 or 2 beams are used to cover the entire front face of the moon. This improves the quality and efficiency of coverage of the bases on the front of the moon.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive labor.
FIG. 1 is a constellation of lunar surface communication satellites.
Wherein 100-earth, 200-moon, L1-Lagrange 1 point and L2-Lagrange 2 point.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment of the invention provides a moon surface communication satellite constellation which can realize high-capacity and high-bandwidth stable communication of the front surface and the back surface of a moon. The present invention will be described in detail below with reference to the accompanying drawings.
As shown in fig. 1, an embodiment of the present invention provides a lunar surface communication satellite constellation, where a surface of a moon 200 includes a front side and a back side of the moon, the constellation includes two lunar communication satellites, the constellation establishes communication links between bases on the surface of the moon 200 through the two lunar communication satellites, the two lunar communication satellites respectively orbit around lagrangian 1 point L1 of the earth moon and orbit around lagrangian 2 point L2, lagrangian 1 point L1 between the moon 200 and the earth 100 is about 60957km from the surface of the moon 200, lagrangian 2 point L2 on the back side of the moon 200 is about 58105km from the surface of the moon 200, and a communication link between at least one of the lunar communication satellites and each base on the surface of the moon 200 adopts Ku, Ka, Q, or V frequency bands, or adopts laser communication.
The satellite communication services mainly include voice services and non-voice services, such as low-speed data, messages, faxes, and the like. Telephone communication is the most widely and commonly used basic communication means in people's daily life, and is also the basic service provided by satellite mobile communication systems. The demand of non-telephone service is increasing with the progress of society and the development of technology, and especially the development and application of computer and network technology will further promote the rapid development of non-telephone service. In addition, satellite communication can also provide high-speed data transmission services such as image information and multimedia information on the front or back of the moon.
There is rainfall attenuation in the normal earth 100 satellite signal transmission path. Rain attenuation results from the absorption and scattering of electromagnetic energy by raindrops. When the frequency band is higher than 10 GHz, rainfall is the most dominant atmospheric attenuation factor in the radio wave propagation process. The Ku frequency band comprises 11-14 GHz, and attenuation caused by rainfall is quite large. The Ka frequency band comprises 20-30 GHz, and is particularly susceptible to serious influence of rainfall and water vapor condensate in the atmosphere, and the radio wave transmission loss is large. The Q frequency band comprises 30-50 GHz. The V frequency band comprises 50-75 GHz. The working frequency band of the wireless laser communication comprises 326-365 THz. Therefore, the Ku, Ka, Q, or V frequency band, or laser communication, is not a preferred frequency band for the terrestrial 100 satellite communication service because of its severe rainfall attenuation, so as to avoid the influence of weather such as rainfall, and the signal quality is unstable. These frequency bands are mainly used for services such as broadcast television transmission. Satellite communication services differ from broadcast television transmission services in their signal transmission requirements.
Those skilled in the field of satellite communication are mainly engaged in the design of the earth 100 satellite communication system, and it is commonly considered that Ku, Ka, Q or V frequency bands, or laser communication, rainfall attenuation is severe, signal quality is unstable, and the system is not used as a preferred frequency band of satellite communication service. Such knowledge may also affect the design of a lunar 200 satellite communication system, and persons of ordinary skill in the satellite communication art do not consider using Ku, Ka, Q, or V bands, or laser communication for lunar 200 satellite communication services. According to the embodiment of the invention, according to the special condition that the moon 200 has no rainfall and thin air, and therefore has no rainfall attenuation, Ku, Ka, Q or V frequency bands or laser communication are adopted to provide communication links between each base on the surface of the moon 200 and the moon communication satellite, and the frequency bands are high in frequency and wide in available frequency band, so that the high-capacity and high-bandwidth communication requirements can be met, the influence of rainfall attenuation cannot be caused, and the signal quality is stable.
The lunar 200 surface communication satellite constellation provided by the embodiment of the invention comprises two lunar communication satellites, wherein the constellation establishes communication links between all bases on the lunar 200 surface through the two lunar communication satellites, and the running orbits of the two lunar communication satellites are respectively an orbit around Lagrange 1 point of the lunar and an orbit around Lagrange 2 point of the lunar, so that the embodiment of the invention can cover most of the surface of the lunar 200, can provide reliable communication means between all bases on the front surface and the back surface of the lunar 200 surface, especially can realize the communication between the front surface and the back surface of the lunar 200, and save huge engineering quantity and huge cost for constructing communication infrastructures on the lunar 200 surface; according to the lunar 200 surface communication satellite constellation provided by the embodiment of the invention, at least one communication link between the lunar communication satellite and each base on the lunar 200 surface adopts a Ku, Ka, Q or V frequency band, or adopts laser communication, and when the lunar communication satellite serves communication between the lunar 200 surface bases, the requirement of high-capacity and high-bandwidth stable communication can be met by adopting the Ku, Ka, Q or V frequency band or laser communication due to no atmospheric interference and rain attenuation influence.
Preferably, the communication link between the bases on the front and back of the moon 200 is relayed by the moon communication satellite without the need to return to the earth 100 ground station. The communication between the lunar 200 bases at all positions on the front and back of the lunar 200 can be supported without returning the earth 100, so that the communication quality can be greatly improved, and the communication delay can be reduced. The communication system delay between any two bases on the front side of the moon 200 is about 500ms, the communication system delay between any two bases on the back side of the moon 200 is about 400ms, and the communication system delay between the front side and the back side of the moon 200 is about 800ms, so that the system delay is remarkably reduced compared with the system delay of the relay communication from the earth 100 ground station.
Considering the insufficient coverage of the north and south poles of the moon 200 by the two communication satellites around the lagrange 1 point L1 and the lagrange 2 point L2 between the geodetic months, one polar orbit communication satellite of the moon 200 is added to form more sufficient communication coverage to serve the communication of the bases near the two poles of the moon 200.
Preferably, the orbital plane of the polar orbital communication satellite of the moon 200 is perpendicular to the line passing through the Lagrangian 1 point L1 and the Lagrangian 2 point L2 of the Earth's moon this provides more adequate communication coverage and solves the above-described problem of insufficient coverage of the surface of the moon 200 by two communication satellites between Lagrangian 1 point L1 and Lagrangian 2 point L2 around Earth's moon to the line passing through the Lagrangian 1 point L1 and the Lagrangian 2 point L2 of the Earth's moon.
Preferably, at least one of said lunar communication satellites relays communication from the surface base of the moon 200 to a ground station of the earth 100. This may reduce system performance requirements for the surface base of moon 200 to communicate with earth 100.
Preferably, at least one of the lunar communication satellites orbits a circular orbit or an elliptical orbit. A lunar communication satellite operating in such an orbit operates more stably.
Preferably, laser communication is adopted between the lunar communication satellites as an inter-satellite communication link. This allows for communication with greater capacity, narrower beams, higher gain, faster speed, greater interference immunity, and better security.
Preferably, communications between at least one of said lunar communication satellites and earth 100 ground stations use the S, C or Ku frequency band. Therefore, a certain communication bandwidth can be met, the rain attenuation resistance is good, the free space loss caused by low communication frequency is low in a large communication distance, and the long-term high-availability communication requirement can be met.
Preferably, at least one of the lunar communication satellites employs spot beam coverage for ground stations on the earth 100. This may reduce the transmit signal power requirements for a lunar communication satellite to communicate with the earth 100.
Preferably, at least one of said lunar communication satellites employs full moon 200 beam coverage on the front or back of moon 200. This ensures full coverage of the various bases on the front of the moon 200.
Preferably, 1 or 2 beams are used to cover the entire front face of the moon 200. This may improve the quality and efficiency of coverage of the various bases on the front of the moon 200.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (11)
1. A constellation of lunar surface communication satellites, the lunar surface comprising a front and a back of the moon, the constellation comprising two lunar communication satellites through which the constellation establishes communication links between bases on the lunar surface, characterized in that: the operation orbits of the two lunar communication satellites are respectively an orbit around a Lagrange 1 point of the Earth moon and an orbit around a Lagrange 2 point of the Earth moon, and a communication link between at least one lunar communication satellite and each base on the lunar surface adopts a Ku, Ka, Q or V frequency band or adopts laser communication.
2. The constellation of lunar surface communication satellites as recited in claim 1, wherein: the communication links between the lunar surface bases are relayed by the lunar communication satellite.
3. The constellation of lunar surface communication satellites as recited in claim 1, wherein: the lunar surface communication satellite constellation further comprises a lunar polar orbit communication satellite.
4. A constellation of lunar surface communication satellites as defined in claim 3, wherein: the orbital plane of the lunar polar orbital communication satellite is perpendicular to a line passing through lagrangian 1 and lagrangian 2 points of the earth moon.
5. A constellation of lunar surface communication satellites as claimed in claim 1 or claim 3, characterized in that: at least one of the lunar communication satellites relays communication from the lunar surface base to the earth ground station.
6. A constellation of lunar surface communication satellites as claimed in claim 1 or claim 3, characterized in that: at least one of the lunar communication satellites orbits a circular orbit or an elliptical orbit.
7. A constellation of lunar surface communication satellites as claimed in claim 1 or claim 3, characterized in that: and laser communication is adopted among the lunar communication satellites as an inter-satellite communication link.
8. A constellation of lunar surface communication satellites as claimed in claim 1 or claim 3, characterized in that: communications between at least one of the lunar communication satellites and the earth ground station use the S, C or Ku band.
9. A constellation of lunar surface communication satellites as claimed in claim 1 or claim 3, characterized in that: at least one of the lunar communication satellites employs spot beam coverage for a terrestrial ground station.
10. A constellation of lunar surface communication satellites as claimed in claim 1 or claim 3, characterized in that: at least one of said lunar communication satellites employs full lunar beam coverage of the front or back of the moon.
11. A constellation of lunar surface communication satellites as defined in claim 10 wherein: at least one of the lunar communication satellites covers the entire front face of the moon with one or two beams.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010378529.2A CN111431590A (en) | 2020-05-07 | 2020-05-07 | Moon surface communication satellite constellation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010378529.2A CN111431590A (en) | 2020-05-07 | 2020-05-07 | Moon surface communication satellite constellation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111431590A true CN111431590A (en) | 2020-07-17 |
Family
ID=71558730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010378529.2A Pending CN111431590A (en) | 2020-05-07 | 2020-05-07 | Moon surface communication satellite constellation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111431590A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114745043A (en) * | 2022-05-05 | 2022-07-12 | 鹏城实验室 | Earth-moon L2 point Halo track relay network, construction method and control method |
| CN115483973A (en) * | 2022-09-13 | 2022-12-16 | 广州爱浦路网络技术有限公司 | Earth-moon communication system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104965982A (en) * | 2015-06-17 | 2015-10-07 | 中国人民解放军63920部队 | Earth-moon libration point constellation arrangement method |
| CN105486314A (en) * | 2015-11-24 | 2016-04-13 | 南京航空航天大学 | Lagrange navigation constellations for seamless coverage of moon space, and construction method thereof |
| CN108827323A (en) * | 2018-08-16 | 2018-11-16 | 西安空间无线电技术研究所 | A kind of unidirectional autonomous navigation method of cislunar space spacecraft |
-
2020
- 2020-05-07 CN CN202010378529.2A patent/CN111431590A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104965982A (en) * | 2015-06-17 | 2015-10-07 | 中国人民解放军63920部队 | Earth-moon libration point constellation arrangement method |
| CN105486314A (en) * | 2015-11-24 | 2016-04-13 | 南京航空航天大学 | Lagrange navigation constellations for seamless coverage of moon space, and construction method thereof |
| CN108827323A (en) * | 2018-08-16 | 2018-11-16 | 西安空间无线电技术研究所 | A kind of unidirectional autonomous navigation method of cislunar space spacecraft |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114745043A (en) * | 2022-05-05 | 2022-07-12 | 鹏城实验室 | Earth-moon L2 point Halo track relay network, construction method and control method |
| CN114745043B (en) * | 2022-05-05 | 2024-05-14 | 鹏城实验室 | Relay network of earth-moon L2 point Halo orbit, construction method and control method |
| CN115483973A (en) * | 2022-09-13 | 2022-12-16 | 广州爱浦路网络技术有限公司 | Earth-moon communication system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JPH09121184A (en) | System for transmitting radio signal via geostationary communication satellite | |
| CN112152695A (en) | Low-orbit satellite constellation measuring, operation and control system and method thereof | |
| CN111431590A (en) | Moon surface communication satellite constellation | |
| Hokazono et al. | Extreme coverage extension in 6G: Cooperative non-terrestrial network architecture integrating terrestrial networks | |
| CN111541478A (en) | Communication system for communication among bases on front side of moon | |
| Gharanjik et al. | Spatial multiplexing in optical feeder links for high throughput satellites | |
| CN111431589A (en) | Mars surface communication constellation based on Mars geostationary orbit satellite | |
| Zheng et al. | Research on Key Technologies of Satellite Mobile Communication System | |
| Kozhemyako et al. | Energy calculation of a satellite communication system | |
| Anderson et al. | Technical feasibility of satellite-aided land mobile radio | |
| Brussaard et al. | Propagation considerations in satellite communication systems | |
| RU2169433C1 (en) | Multifunctional space telecommunication system | |
| Kliovan | A model of telecommunication system using VSAT satellite technology | |
| ALBAJI et al. | INVESTIGATION OF THE SATELLITE MOBILE TELEPHONE PERSPECTIVES IN LIBYA | |
| Baird et al. | Odyssey system overview | |
| Fortuny et al. | Mobile satellite systems at Ku and Ka-band | |
| Chang et al. | Basic capacity calculation methods and benchmarking for MF-TDMA and MF-CDMA communication satellites | |
| Shuqian et al. | Research on Ground Station Selection for Ka-band Satellite Communication Considering Rain Attenuation | |
| Li et al. | On Ka-Band Utilization Towards Non-Terrestrial Networks | |
| Allen | Satellite Communications | |
| Fang et al. | A low-cost thin route digital communications system for the Pacific Ocean nations | |
| Ananasso et al. | 20/30 GHz satellite services-An economic analysis | |
| Newland | AUSSAT mobilesat system description | |
| CN114499623A (en) | Constellation system for mobile communication system | |
| Park et al. | Coexistence of gateway uplinks for high altitude platform station with uplink for the fixed-satellite service in 6 GHz band |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200717 |
|
| RJ01 | Rejection of invention patent application after publication |