CN115396008B - Multi-stage relay satellite constellation inter-satellite navigation method, system and equipment - Google Patents
Multi-stage relay satellite constellation inter-satellite navigation method, system and equipment Download PDFInfo
- Publication number
- CN115396008B CN115396008B CN202210963098.5A CN202210963098A CN115396008B CN 115396008 B CN115396008 B CN 115396008B CN 202210963098 A CN202210963098 A CN 202210963098A CN 115396008 B CN115396008 B CN 115396008B
- Authority
- CN
- China
- Prior art keywords
- satellite
- relay satellite
- earth
- stage relay
- stage
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000013519 translation Methods 0.000 claims abstract description 9
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000004590 computer program Methods 0.000 claims description 11
- 238000005259 measurement Methods 0.000 claims description 10
- 238000004891 communication Methods 0.000 claims description 9
- 238000004364 calculation method Methods 0.000 claims description 3
- 238000004091 panning Methods 0.000 claims 2
- 201000003152 motion sickness Diseases 0.000 claims 1
- 238000001514 detection method Methods 0.000 abstract description 5
- 125000001475 halogen functional group Chemical group 0.000 description 27
- 238000010586 diagram Methods 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 5
- 230000006870 function Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 230000003287 optical effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
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
- H04B7/1851—Systems using a satellite or space-based relay
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/42—Determining position
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Signal Processing (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention discloses a method, a system and equipment for multi-stage relay satellite constellation inter-satellite navigation. The method comprises the following steps: 1) Arranging a plurality of earth orbit satellites to form a first-stage relay satellite constellation; arranging a plurality of satellites in a translation point setting area of an earth and moon gravitation system and a translation point setting area of an earth and sun gravitation system to form a second-stage relay satellite constellation; arranging a plurality of satellites around the earth in a translation point setting area of an earth and solar gravitation system and a corona orbit around the earth to form a third-level relay satellite constellation; each stage comprises at least four satellites; 2) The satellite ground station orbits the first-stage relay satellite, the orbits of the relay satellites are mutually determined among the relay satellite constellations of all stages, and then the navigation positioning of the interstellar deep space exploration satellite is realized through the multi-stage relay satellites. The invention builds a navigation positioning constellation based on the orbit of the translational point setting area, uses fewer satellites to realize the satellite navigation of the interplanetary detection from the earth to the sun, and can greatly save time and investment.
Description
Technical Field
The present disclosure relates to the field of satellite navigation, and in particular, to a method, system, and apparatus for implementing satellite navigation using a relay constellation composed of multiple satellites.
Background
At present, GPS, geronas, galileo, beidou and other global navigation positioning systems are mature technologies for navigation positioning of the earth surface and near-earth targets. The inter-planetary deep space detection of the sun, the planet and the asteroid in the solar system outside the earth orbit is the development direction of various aerospace major countries, and the related inter-planetary deep space detection technology is a hot spot developed in various countries. Navigation positioning of the interplanetary probe is one of the key technologies for deep space exploration. The patent document CN100501331C, CN108494472A, CN111536980B in China has relevant research and development and has relevant technology. However, there is no method and system for realizing satellite navigation and positioning between earth and sun by using multi-stage relay satellites.
Disclosure of Invention
The present disclosure is directed to a method and a system for implementing satellite navigation positioning by using a multi-level relay satellite constellation, which are used for solving at least one of the above technical problems.
In order to achieve the above objective, an aspect of the present disclosure provides a multistage relay satellite constellation inter-satellite navigation method, including:
the earth orbit satellites form a first-stage relay satellite constellation, the satellites on the orbit of the translational point setting region of the earth and lunar gravitation system and the satellites on the orbit of the translational point setting region of the earth and solar gravitation system form a second-stage relay satellite constellation, and the satellites on the orbit of the translational point setting region of the earth and solar gravitation system and the halo (halo) orbit satellites around the earth form a third-stage relay satellite constellation; the first, second and third relay satellite constellations, each relay satellite constellation is composed of at least four satellites; the satellite ground station orbits a first-stage relay satellite; the first-stage relay satellite orbits the second-stage relay satellite through the satellite-borne computing component according to the received measurement data of the second-stage relay satellite, and the second-stage relay satellite orbits the third-stage relay satellite through the satellite-borne computing component according to the received measurement data of the third-stage relay satellite; the third-stage relay satellite receives the measurement data of the second-stage relay satellite, the second-stage relay satellite orbits through the satellite-borne computing component, the second-stage relay satellite receives the measurement data of the first-stage relay satellite, and the first-stage relay satellite orbits through the satellite-borne computing component; because the opening angles of the first stage and the third stage are too small, the orbit determination of the first stage from the first stage to the third stage or from the third stage to the first stage is not easy to realize, and therefore, a second-stage satellite needs to be arranged as a relay constellation. The invention utilizes the first, second and third relay satellites to form a constellation for navigating the interplanetary satellites. After the inter-satellite is transmitted from the earth, when reaching the coverage area of the first-stage relay satellite, receiving the navigation signal of the first-stage relay satellite, and positioning and navigating the inter-satellite entering the coverage area by using the first-stage relay satellite; when the interplanetary satellite reaches the coverage area of the second-stage relay satellite, receiving a navigation signal of the second-stage relay satellite, and positioning and navigating the interplanetary satellite entering the coverage area by using the second-stage relay satellite; when the interplanetary satellite reaches the coverage area of the third-stage relay satellite, receiving a navigation signal of the third-stage relay satellite, and positioning and navigating the interplanetary satellite entering the coverage area by using the third-stage relay satellite; the relay satellite communication data of each stage and the communication data of the inter-satellite are communicated with the satellite ground station or the relay satellite of each stage through a satellite communication component.
Optionally, the first-stage relay satellite is a geosynchronous orbit satellite.
Optionally, setting a second-stage relay satellite on an area orbit by a translation point of the earth-moon gravitation system, wherein the translation point is a fourth point, a fifth point and a second point of the earth-moon Lagrange; and setting a second-stage relay satellite on the regional orbit of the translational point of the earth and solar gravitation system, wherein the translational point is a first point and a second point of the earth-solar Lagrangian. Wherein the satellite orbit is a halo (halo) orbit about each translational point.
Optionally, the earth and solar gravitation system translational points set a third-stage relay satellite on the regional orbit, wherein the translational points are the fourth point and the fifth point of the earth-solar Lagrange; the halo (halo) orbit around the earth is a halo orbit radius of less than 0.2 times the earth-daily distance (0.2 AU), and the halo orbit surface is a satellite orbit not parallel to the yellow orbit surface.
Another aspect of the present disclosure proposes a system for multi-stage relay satellite constellation inter-satellite navigation, comprising:
the first, second and third relay satellite forms a planetary navigation constellation, and each stage of relay satellite constellation at least comprises four satellites; the earth orbit satellites form a first-stage relay satellite constellation, the satellites on the orbit of the translational point setting region of the earth and lunar gravitation system and the satellites on the orbit of the translational point setting region of the earth and solar gravitation system form a second-stage relay satellite constellation, and the satellites on the orbit of the translational point setting region of the earth and solar gravitation system and the halo (halo) orbit satellites around the earth form a third-stage relay satellite constellation; the satellite ground station is used for navigating the first-stage relay satellite; the first-stage relay satellite navigates to the second-stage relay satellite, and the second-stage relay satellite navigates to the third-stage relay satellite; the third-level relay satellite navigates the second-level relay satellite, and the second-level relay satellite navigates the first-level relay satellite; the first, second and third relay satellites navigate the interplanetary satellites.
Optionally, the first-stage relay satellite is a geosynchronous orbit satellite.
Optionally, the earth and moon gravitation system translates the second-stage relay satellite on the regional orbit of the point setting region, wherein translate the point to be the earth-moon Lagrangian fourth point, the fifth point, the second point; setting a second-stage relay satellite on a regional orbit of a translational point of an earth-solar gravitation system, wherein the translational point is a first point and a second point of the earth-solar Lagrangian; the satellite orbit is a halo (halo) orbit around each translational point.
Optionally, the earth and solar gravitation system translational points set a third-stage relay satellite on the regional orbit, wherein the translational points are the fourth point and the fifth point of the earth-solar Lagrange; the halo (halo) orbit around the earth is a satellite orbit with a halo orbit radius less than 0.2 times the earth-daily distance (0.2 AU), the halo orbit plane not being parallel to the yellow orbit plane.
In yet another aspect, the present disclosure proposes a computer device, including a memory and a processor, where the memory stores a computer program executable on the processor, and the processor executes the computer program to implement the steps of the method for multi-level relay satellite inter-satellite navigation.
Optionally, the satellite navigation signals calculated and processed by the computing device are transmitted to each level of relay satellite and inter-satellite through the ground station, each level of relay satellite ephemeris and inter-satellite ephemeris data are transmitted to the ground station through the satellite communication component, and the ground station receives the ephemeris data and performs calculation processing through the computing device.
Optionally, the satellite navigation signals calculated and processed by the computing device are transmitted to each level of relay satellite and inter-satellite through the satellite communication component, each level of relay satellite ephemeris and inter-satellite ephemeris data are transmitted to each level of relay satellite and inter-satellite through the satellite communication component, and satellite receiving ephemeris data are calculated and processed by the computing device.
The beneficial effects are that:
the method establishes a navigation positioning constellation composed of multistage relay satellites by selecting translational points among solar systems to set regional orbits. The orbits of the relay satellites are mutually determined among the multi-stage relay satellite constellations, and then the navigation positioning of the interstellar deep space exploration satellites is realized through the multi-stage relay satellites. The method is based on the orbit of the translational point setting area, a stable navigation positioning constellation is built, the satellite navigation is realized by using fewer satellites to realize the interplanetary detection satellite navigation from the earth to the sun, and the time and the investment can be greatly saved.
Drawings
Fig. 1A shows a first level relay satellite constellation schematic.
Fig. 1B shows a second level relay satellite constellation schematic.
Fig. 1C shows a third level relay satellite constellation schematic.
Fig. 2 schematically illustrates a flow chart of a navigation method in an embodiment of the present disclosure.
Fig. 3 schematically illustrates a block diagram of a computer device of another embodiment of the present disclosure.
Detailed Description
For a better understanding of the objects, technical solutions and advantages of the present disclosure, the present disclosure will be further described in detail below with reference to the drawings.
Navigation positioning of an inter-satellite detector is one of key technologies of deep space detection, and a method for realizing inter-satellite navigation positioning by arranging multi-stage relay satellites between the earth and the sun is not yet available. Based on this, the present disclosure provides a method of interplanetary satellite navigation.
Fig. 1 shows a schematic diagram of an implementation system of a method for multi-level relay satellite inter-satellite navigation of the present disclosure, where the system for multi-level relay satellite inter-satellite navigation includes a three-level relay satellite constellation as shown in fig. 1. As shown in fig. 1A, the earth-orbiting satellites constitute a first-order relay satellite constellation, and the first-order relay satellites are geosynchronous satellites. As shown in fig. 1B, satellites in the orbit of the translational point setting area of the earth-lunar gravitation system and satellites in the orbit of the translational point setting area of the earth-lunar gravitation system form a second-stage relay satellite constellation, and the second-stage relay satellite is partially located on a halo (halo) orbit near the translational point of the earth-lunar gravitation system, where the translational point is the fourth, fifth and second points of the earth-lunar lagrangian. The second-stage relay satellite part is positioned on a halo (halo) orbit near a translational point of the earth-sun gravitation system, wherein the translational point is a first point and a second point of the earth-sun Lagrangian. As shown in fig. 1C, satellites in the orbit of the set area of the translational points of the earth-solar attraction system and the halo (halo) orbit satellite around the earth form a third-stage relay satellite constellation, the third-stage relay satellite is partially located in the halo (halo) orbit of the set area of the translational points of the earth-solar attraction system, the translational points are the fourth and fifth points of the earth-solar lagrangian, the third-stage relay satellite is partially located in the orbit in which the halo (halo) orbit around the earth is an orbit with a radius smaller than 0.2 times of the earth-sun distance (0.2 AU), and the preferred halo orbit plane is perpendicular to the yellow road plane.
Fig. 2 schematically illustrates a flow chart of a navigation method in an embodiment of the present disclosure. As shown in fig. 2, the method for implementing satellite navigation positioning by using the multi-stage relay satellite comprises the following steps:
the satellite ground station orbits a first-stage relay satellite; the first-stage relay satellite orbits a second-stage relay satellite, and the second-stage relay satellite orbits a third-stage relay satellite; the third-stage relay satellite orbits a second-stage relay satellite, and the second-stage relay satellite orbits a first-stage relay satellite; the first, second and third relay satellites navigate and position the interplanetary satellites.
Fig. 3 schematically illustrates a block diagram of a computer device suitable for implementing the method of multi-level relay satellite constellation inter-satellite navigation described above, in accordance with an embodiment of the present disclosure. Those skilled in the art will appreciate that the architecture shown in fig. 3 is merely a block diagram of some of the architecture relevant to the embodiments of the present disclosure and is not limiting of the computer device to which the embodiments of the present disclosure apply, and that a particular computer device may include more or fewer components than shown, or may combine some of the components, or have a different arrangement of components.
As shown in fig. 3, the computer device 300 includes a memory 310 and a processor 320. The computer device 300 may perform methods according to embodiments of the present disclosure.
In particular, processor 320 may include, for example, a general purpose microprocessor, an instruction set processor, and/or an associated chipset and/or a special purpose microprocessor (e.g., an Application Specific Integrated Circuit (ASIC)), or the like. Processor 320 may also include on-board memory for caching purposes. Processor 320 may be a single processing unit or multiple processing units for performing different actions in accordance with the method flows of the disclosed embodiments.
The memory 310 of the computer device may be, for example, a non-volatile computer-readable storage medium, specific examples of which include, but are not limited to: magnetic storage devices such as magnetic tape or hard disk (HDD); optical storage devices such as compact discs (CD-ROMs); a memory, such as a Random Access Memory (RAM) or a flash memory; etc.
The memory 310 may include a computer program 311, which computer program 311 may include code/computer executable instructions that, when executed by the processor 320, cause the processor 320 to perform a method according to an embodiment of the present disclosure or any variation thereof.
The computer program 311 may be configured with computer program code comprising computer program modules, for example. For example, in an example embodiment, code in computer program 311 may include one or more program modules, including for example 311A, modules 311B, … …. It should be noted that the division and number of modules is not fixed, and that a person skilled in the art may use suitable program modules or combinations of program modules according to the actual situation, which when executed by the processor 320, enable the processor 320 to perform the method according to the embodiments of the present disclosure or any variations thereof.
The present disclosure also provides a computer-readable storage medium that may be embodied in the apparatus/device/system described in the above embodiments; or may exist alone without being assembled into the apparatus/device/system. The computer-readable storage medium carries one or more programs which, when executed, implement methods in accordance with embodiments of the present disclosure.
According to embodiments of the present disclosure, the computer-readable storage medium may be a non-volatile computer-readable storage medium, which may include, for example, but is not limited to: a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the context of this disclosure, a computer-readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present disclosure. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams or flowchart illustration, and combinations of blocks in the block diagrams or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The above examples are merely illustrative of the preferred embodiments of the present disclosure and are not intended to limit the scope of the present disclosure, and various modifications and improvements made by those skilled in the art to the technical solutions of the present disclosure should fall within the scope of protection defined by the claims of the present disclosure without departing from the spirit of the design of the present disclosure.
Claims (8)
1. A multi-stage relay satellite constellation inter-satellite navigation method comprises the following steps:
1) Arranging a plurality of earth orbit satellites to form a first-stage relay satellite constellation; arranging a plurality of satellites in a translation point setting area of an earth and moon gravitation system and a translation point setting area of an earth and sun gravitation system to form a second-stage relay satellite constellation; arranging a plurality of satellites around the earth in a translation point setting area of an earth and solar gravitation system and a corona orbit around the earth to form a third-level relay satellite constellation; each stage of relay satellite constellation at least comprises four satellites;
2) The satellite ground station orbits the first-stage relay satellite, the first-stage relay satellite receives measurement data of the second-stage relay satellite, the second-stage relay satellite orbits through a satellite-borne computing component, the second-stage relay satellite receives measurement data of the third-stage relay satellite, and the third-stage relay satellite orbits through the satellite-borne computing component; after the inter-satellite is transmitted from the earth, when reaching the coverage area of the first-stage relay satellite, receiving the navigation signal of the first-stage relay satellite, and positioning and navigating the inter-satellite entering the coverage area by using the first-stage relay satellite; when the interplanetary satellite reaches the coverage area of the second-stage relay satellite, receiving a navigation signal of the second-stage relay satellite, and positioning and navigating the interplanetary satellite entering the coverage area by using the second-stage relay satellite; when the interplanetary satellite reaches the coverage area of the third-stage relay satellite, receiving a navigation signal of the third-stage relay satellite, and positioning and navigating the interplanetary satellite entering the coverage area by using the third-stage relay satellite; the relay satellite communication data of each stage and the communication data of the inter-satellite are communicated with the satellite ground station or the relay satellite of each stage through a satellite communication component.
2. The method of claim 1, wherein the satellites that make up the first-order relay satellite constellation are geosynchronous orbit satellites.
3. The method of claim 1, wherein the earth and moon gravitational system panning points for deployment of a second level relay satellite are earth-moon lagrangian fourth, fifth, second points; the smooth points of the earth and solar gravitation system used for laying the second-stage relay satellite are earth-solar Lagrange first points and second points; the orbit of the second-stage relay satellite is selected from the fourth point, the fifth point and the second point of the earth-moon Lagrange, and the vignetting orbit of the first point and the second point of the earth-sun Lagrange is set.
4. The method of claim 1, wherein the earth and sun gravitational system panning points for deployment of third level relay satellites are earth-sun lagrangian fourth and fifth points; the earth-orbiting radius is less than 0.2 times the earth-daily distance and the earth-orbiting surface is not parallel to the satellite orbit of the orbit surface.
5. The method of claim 1, wherein each stage of relay satellites generates ephemeris data and navigation signals for the interplanetary satellites.
6. The method of claim 1, wherein when the first stage relay satellite is unable to communicate with the satellite ground station, orbit the first stage relay satellite according to ephemeris data of a second stage relay satellite constellation, orbit the second stage relay satellite according to ephemeris data of a third stage relay satellite; and orbit-determining the second-stage relay satellite according to the ephemeris data of the first-stage relay satellite constellation, and orbit-determining the third-stage relay satellite according to the ephemeris data of the second-stage relay satellite.
7. The system for satellite navigation of the multistage relay satellite constellation is characterized by comprising a satellite ground station and a three-stage relay satellite constellation, wherein each stage of relay satellite constellation comprises at least four satellites; wherein,,
the first-stage relay satellite constellation consists of a plurality of earth orbit satellites;
the second-stage relay satellite constellation consists of a plurality of satellites distributed in a translational point setting area of an earth and moon gravitation system and a translational point setting area of an earth and sun gravitation system;
the third-level relay satellite constellation consists of a translation point setting area of an earth and solar attraction system and a plurality of satellites distributed around the earth's motion sickness;
the satellite ground station is used for orbit determination of the first-stage relay satellite; the first-stage relay satellite is used for orbit determination of the second-stage relay satellite through the satellite-borne calculation component according to the received measurement data of the second-stage relay satellite; the second-stage relay satellite is used for orbit determination of the third-stage relay satellite through the satellite-borne calculation component according to the received measurement data of the third-stage relay satellite; the third-stage relay satellite is used for orbit determination of the second-stage relay satellite through the satellite-borne computing component according to the received measurement data of the second-stage relay satellite, and the second-stage relay satellite is used for orbit determination of the first-stage relay satellite through the satellite-borne computing component according to the received measurement data of the first-stage relay satellite; the first, second and third relay satellites are respectively used for navigation and positioning of the inter-satellite satellites entering the coverage range of the first, second and third relay satellites.
8. A computer device comprising a memory and a processor, the memory having stored thereon a computer program executable on the processor, characterized in that the processor, when executing the computer program, implements the steps of the method according to any of claims 1-6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210963098.5A CN115396008B (en) | 2022-08-11 | 2022-08-11 | Multi-stage relay satellite constellation inter-satellite navigation method, system and equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210963098.5A CN115396008B (en) | 2022-08-11 | 2022-08-11 | Multi-stage relay satellite constellation inter-satellite navigation method, system and equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115396008A CN115396008A (en) | 2022-11-25 |
| CN115396008B true CN115396008B (en) | 2023-06-23 |
Family
ID=84117877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210963098.5A Active CN115396008B (en) | 2022-08-11 | 2022-08-11 | Multi-stage relay satellite constellation inter-satellite navigation method, system and equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115396008B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116707623B (en) * | 2023-08-09 | 2023-09-29 | 银河航天(北京)通信技术有限公司 | Method, device and storage medium for transmitting data based on target relay satellite |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108494472A (en) * | 2018-02-12 | 2018-09-04 | 中国科学院国家空间科学中心 | A kind of space-based deep space trunking traffic Satellite Networking system |
| CN109917431A (en) * | 2019-04-02 | 2019-06-21 | 中国科学院空间应用工程与技术中心 | A kind of method that space-based realizes GNSS satellite independent navigation |
| WO2021129068A1 (en) * | 2019-12-26 | 2021-07-01 | 西安空间无线电技术研究所 | Moon navigation system based on earth gnss and moon navigation enhancement satellite |
-
2022
- 2022-08-11 CN CN202210963098.5A patent/CN115396008B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108494472A (en) * | 2018-02-12 | 2018-09-04 | 中国科学院国家空间科学中心 | A kind of space-based deep space trunking traffic Satellite Networking system |
| CN109917431A (en) * | 2019-04-02 | 2019-06-21 | 中国科学院空间应用工程与技术中心 | A kind of method that space-based realizes GNSS satellite independent navigation |
| WO2021129068A1 (en) * | 2019-12-26 | 2021-07-01 | 西安空间无线电技术研究所 | Moon navigation system based on earth gnss and moon navigation enhancement satellite |
Non-Patent Citations (1)
| Title |
|---|
| 月球中继卫星轨道设计分析;孙宝升;张俊丽;;载人航天(04);71-77 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115396008A (en) | 2022-11-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Winternitz et al. | New high-altitude GPS navigation results from the magnetospheric multiscale spacecraft and simulations at Lunar distances | |
| Silva et al. | Weak GNSS signal navigation to the moon | |
| Ashman et al. | GPS operations in high earth orbit: Recent experiences and future opportunities | |
| Capuano et al. | Orbital filter aiding of a high sensitivity GPS receiver for lunar missions | |
| CN115396008B (en) | Multi-stage relay satellite constellation inter-satellite navigation method, system and equipment | |
| Slavinskis et al. | Nanospacecraft fleet for multi-asteroid touring with electric solar wind sails | |
| CN115378490B (en) | Ground station-based multi-stage relay satellite constellation inter-satellite navigation method | |
| Schonfeldt et al. | A system study about a lunar navigation satellite transmitter system | |
| Bhamidipati et al. | Design considerations of a lunar navigation satellite system with time-transfer from Earth-GPS | |
| Hill et al. | Autonomous orbit determination from lunar halo orbits using crosslink range | |
| Sutton et al. | Toward accurate physics‐based specifications of neutral density using GNSS‐enabled small satellites | |
| Choi et al. | Analysis of the angle-only orbit determination for optical tracking strategy of Korea GEO satellite, COMS | |
| Carpenter et al. | Libration point navigation concepts supporting the vision for space exploration | |
| Giralo et al. | Precise real-time relative orbit determination for large-baseline formations using gnss | |
| Yoon et al. | Spacecraft orbit determination using GPS navigation solutions | |
| Sundararajan | Mangalyaan-Overview and Technical Architecture of India's First Interplanetary Mission to Mars | |
| Romero et al. | Spatial chronogram to detect Phobos eclipses on Mars with the MetNet Precursor Lander | |
| Montenbruck et al. | Autonomous and precise navigation of the PROBA-2 spacecraft | |
| Golikov | THEONA—a numerical-analytical theory of motion of artificial satellites of celestial bodies | |
| Winternitz et al. | A high-fidelity performance and sensitivity analysis of X-ray pulsar navigation in near-Earth and cislunar orbits | |
| Strange et al. | Mission design for the titan saturn system mission concept | |
| Anzalone et al. | Lunar navigation beacon network using global navigation satellite system receivers | |
| Fateev et al. | The use of GNSS technologies for high-precision navigation geostationary spacecraft | |
| İmre et al. | Orbital dynamics system of TUBITAK UZAY for earth orbiting spacecraft | |
| Betto et al. | Advanced stellar compass deep space navigation, ground testing results |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |