CN114545462A - Complex heterogeneous navigation constellation implementation method based on low, medium and high orbit - Google Patents
Complex heterogeneous navigation constellation implementation method based on low, medium and high orbit Download PDFInfo
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Abstract
The invention provides a method for realizing a complex heterogeneous navigation constellation based on low, medium and high orbits, which determines that the complex heterogeneous navigation constellation comprises a low orbit sub-constellation and a medium and high orbit sub-constellation; designing a low-orbit sub-constellation which can be independent of a medium-high orbit sub-constellation for navigation work, determining that the configuration of the low-orbit sub-constellation comprises a low-orbit Walker constellation if the coverage of south and north poles does not need to be considered, and designing a first variable of the low-orbit Walker constellation; if the coverage of north and south poles needs to be considered, determining that the configuration of the low-orbit sub-constellation comprises a low-orbit Walker constellation and a polar-orbit constellation, and designing a first variable of the low-orbit Walker constellation and a second variable of the polar-orbit constellation; the method is characterized in that a medium-high orbit sub-constellation which can be independent of a low orbit sub-constellation for navigation work and meets the requirement of a space service domain is designed, and in the high orbit sub-constellation and the medium orbit sub-constellation, inter-satellite links are adopted for interconnection and intercommunication between satellites, so that the high orbit sub-constellation and the medium orbit sub-constellation can also work under the condition that partial satellites are invalid, and the requirements of the space service domain and the navigation war can be met.
Description
Technical Field
The invention belongs to the field of design of complex heterogeneous constellations, and particularly relates to a complex heterogeneous navigation constellation implementation method based on low and medium high orbits.
Background
high-Orbit navigation (or navigation enhancement) satellite constellations, which mainly use Medium Earth Orbit (MEO), Geostationary Orbit (GEO), and Inclined Geosynchronous Orbit (IGSO), are the schemes used by most constellations today. The main advantages of the high orbit navigation satellite constellation are: (1) the height is higher, the single satellite is wide in the ground coverage area, and the target area coverage and navigation positioning capacity can be met by fewer satellites; (2) the subsatellite point track of the inclined geosynchronous orbit has good coverage on a specific area, is static to the ground or moves slowly, and can meet long-term visible and continuous navigation enhancement service.
However, the high orbit navigation satellite constellation also has its inherent drawbacks: (1) the landing signal is weak, so that the navigation and positioning requirements of complex scenes such as urban building compact areas, mountainous canyons and the like, sheltered environments in rooms and the like and seamless indoor and outdoor connection are difficult to meet; (2) the change of the space geometric configuration of the satellite to the ground is not obvious, so that the precision single-point positioning convergence time is longer, and the real-time high-precision positioning operation efficiency is influenced.
The existing regional navigation constellation mainly comprises GEO and IGSO satellites, the global navigation constellation is added with MEO satellites, and a complex heterogeneous navigation constellation implementation method based on low-medium high orbit is still lacked at present, so that the requirements of a space service domain and navigation war are met.
Disclosure of Invention
In order to meet the requirements of a space service domain and navigation war, the invention provides a complex heterogeneous navigation constellation implementation method based on low, medium and high orbit.
The invention provides a method for realizing a complex heterogeneous navigation constellation based on low, medium and high orbit, which comprises the following steps:
determining that the complex heterogeneous navigation constellation comprises a low-orbit sub-constellation and a medium-high orbit sub-constellation;
designing a low orbit subsatellite which can be independent of a medium and high orbit subsatellite for navigation work comprises:
judging whether the coverage of north and south poles needs to be considered:
if the coverage of north and south poles does not need to be considered, determining that the configuration of the low-orbit sub-constellation comprises a low-orbit Walker constellation, and designing a first variable of the low-orbit Walker constellation, wherein the first variable comprises orbit height, orbit inclination angle, satellite number, orbit surface number and phase factor;
if the coverage of south and north poles needs to be considered, determining that the configuration of the low-orbit sub-constellation comprises a low-orbit Walker constellation and a polar-orbit constellation, and designing a first variable of the low-orbit Walker constellation and a second variable of the polar-orbit constellation, wherein the second variable comprises a precession speed, a regression orbit, polar-orbit constellation parameters and a rising-crossing right ascension;
designing a medium and high orbit sub-constellation which can carry out navigation work independently of the low orbit sub-constellation and meet the requirement of a space service domain comprises the following steps:
determining that the medium and high orbit sub-constellation comprises a high orbit sub-constellation and a medium orbit sub-constellation which are independent from each other and perform navigation work;
in the high-orbit sub-constellation and the medium-orbit sub-constellation, inter-satellite links are adopted for interconnection and intercommunication between satellites, so that the high-orbit sub-constellation and the medium-orbit sub-constellation can work under the condition that part of the satellites fail.
In some implementations, the designing a first variable of the low-orbit Walker constellation includes:
designing a rail height, comprising: preliminarily estimating the radius range of the track; estimating the regression turns of the satellite by using a regression condition; calculating the operation period of the satellite by using the regression condition again; calculating the orbit radius by using the operation period of the satellite, and further calculating the orbit height;
designing an inclination angle of the track, comprising: designing a track inclination angle for a coverage area except the south and north poles;
the number of satellites, the number of orbital planes, and the phase factor are designed.
In some implementations, designing a second variable of the polar constellation includes:
selecting the precession speed of the polar orbit constellation to keep the same as the precession speed of the low orbit Walker constellation;
preliminarily determining the orbit inclination angle range and the orbit height range of the polar orbit constellation;
selecting a regression orbit of the polar orbit constellation, and selecting a polar orbit constellation parameter with the best coverage performance enhancement effect by taking an orbit inclination angle range and an orbit height range as optimization parameter boundaries;
and selecting ascending crossing right ascension differences according to the set step length, analyzing the coverage performance of the mixed configuration of the low-orbit Walker constellation and the polar-orbit constellation under the condition of different ascending crossing right ascension differences, and selecting the ascending crossing right ascension with the best coverage performance.
In some implementations, the high-orbital constellation includes GEO orbital satellites and IGSO orbital satellites.
In some implementations, the mid-orbit sub-constellation includes MEO orbital satellites.
In some implementations, the designing the number of satellites, the number of orbital planes, and the phase factor includes:
the number of satellites, the number of orbital planes and the phase factor are designed with the goal of providing at least two coverage and/or as many satellites in view as possible to the service area.
In some implementations, the preliminary determining the range of orbit inclination angles and the range of orbit heights of the polar orbit constellation includes:
the track inclination angle range of the polar orbit constellation is preliminarily determined to be 80-100 degrees, and the track height range of the polar orbit constellation is preliminarily determined to be 700-1500 km.
In some implementations, the set step size is 10 °.
In some implementations, the designing a medium-high orbit sub-constellation capable of performing navigation work independently of a low orbit sub-constellation and satisfying space service domain requirements further includes:
deploying the middle orbit sub-constellation on an orbit which is beneficial to improving the navigation performance of the high orbit sub-constellation at the current moment;
when the medium and high orbit sub-constellation needs to be expanded to the global range for navigation, the orbit of the medium and high orbit sub-constellation is adjusted to realize constellation reconstruction.
In some implementations, the designing a medium-high orbit sub-constellation capable of performing navigation work independently of a low orbit sub-constellation and satisfying space service domain requirements further includes:
the performance of a space service domain of the constellation satellite is improved by using the performance of a main lobe edge and a side lobe of the navigation antenna so as to meet the requirement of the space service domain.
The invention can at least bring the following beneficial effects:
according to the method for realizing the complex heterogeneous navigation constellation based on the low-medium high orbit, the low-orbit sub-constellation can realize the navigation function independently of the medium-high orbit constellation; medium and high orbit satellites can also work independently of low orbit constellations; the low rail sub-constellation design includes: determining a constellation configuration, determining an orbit height, determining an orbit inclination angle, and determining the number of satellites, the number of orbit planes and a phase factor; the requirement analysis of the constellation implementation method comprises the following steps: analyzing the requirements of a space service domain and a navigation war; the medium-high orbit constellation satellite and the low orbit constellation satellite transmit information through inter-satellite link, and the integrated design of the high-medium-low orbit satellite based on the inter-satellite link is realized. On one hand, the achieved heterogeneous navigation constellation can utilize a low-orbit sub-constellation to enhance a navigation signal under the condition that a constellation system is normal; on the other hand, under the condition that the satellite of the low-orbit (or medium-high orbit) constellation fails, the service can be supplemented through the medium-high orbit (or low-orbit) constellation, and the navigation positioning performance and the service availability of the service area are kept.
Drawings
To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, and it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope.
Fig. 1 is a schematic flow chart of a complex heterogeneous navigation constellation implementation method based on low and medium high orbits according to an embodiment of the present invention;
FIG. 2 is a schematic representation of a single star coverage scenario;
figure 3 is a schematic diagram of a satellite signal space service geometry.
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. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
The regional navigation constellation in the related technology mainly comprises GEO and IGSO satellites, the global navigation constellation is added with MEO satellites, the low-orbit constellation is mainly used for navigation enhancement, and a complex heterogeneous navigation constellation implementation method based on low, medium and high orbits is lacked at present, so that the requirements of a space service domain and navigation war are met.
The Low Earth Orbit (LEO) navigation satellite constellation can solve the problem of the traditional high Orbit constellation, and is an important component of the current widely developed communication and remote integrated satellite constellation. The LEO orbit height is about 200-2000 km, and the navigation signal transmission distance of broadcasting is short, and the power of signal that falls to the ground is high, and anti-interference, ability such as prevent deceiving also promote to some extent. In addition, the low-orbit satellite has high movement speed relative to the ground, the constellation configuration of the visible satellite changes quickly, the problem of calculating precise single-point positioning is effectively solved, the convergence time of the low-orbit satellite is shortened, and the problem of practical application of the global navigation satellite constellation is expected to be fundamentally solved.
The method for implementing the complex heterogeneous navigation constellation based on the low, medium and high orbit, as shown in fig. 1, includes steps S110 to S130:
step S110, determining that the complex heterogeneous navigation constellation comprises a low-orbit sub-constellation and a medium-high-orbit sub-constellation;
in some implementations, the high-orbit sub-constellation includes GEO-orbit satellites (geosynchronous orbit satellites) and IGSO-orbit satellites (tilted geosynchronous orbit), the medium-orbit sub-constellation includes MEO-orbit satellites (medium-earth-orbit satellites), and the orbits are circular orbits with eccentricity e equal to 0 and near-location argument ω equal to 0.
Step S120, designing a low orbit sub-constellation which can perform navigation work independently of the medium and high orbit sub-constellation, comprising the following steps:
step S1201, judging whether the coverage of north and south poles needs to be considered:
if the coverage of north and south poles is not required to be considered, step S1202 is executed;
step S1202, determining that the configuration of the low-orbit sub-constellation comprises a low-orbit Walker constellation, and designing a first variable of the low-orbit Walker constellation, wherein the first variable comprises orbit height, orbit inclination, satellite number, orbit surface number and phase factor;
in the embodiment, under the condition that the coverage of south and north poles does not need to be considered in the design process of the complex heterogeneous constellation, the configuration of the globally covered low-orbit sub-constellation is determined to be the low-orbit Walker constellation, so that the cost can be reduced, and the navigation service quality can be ensured.
In some implementations, designing a first variable of a low-rail Walker constellation includes:
(1) designing a rail height, comprising:
firstly, preliminarily estimating a track radius range;
in some cases, the range of track heights is around 1000km, which can be determined from practical considerations. Radius of the earth Re6378.137 km. And adding the two to obtain the preliminarily estimated orbit radius range.
Secondly, estimating the regression turn number n of the satellite by using a regression condition;
in practical application, the regression orbit or quasi-regression orbit for realizing global coverage is superior to other types of orbits, so that the orbit of the low-orbit Walker constellation satellite is selected as the regression orbit for global coverage in the embodiment, that is, the track of the subsatellite point of the satellite is repeated every day, and the selected coverage characteristic takes the day as a period.
The regression conditions were: (24 hours/day)/(T0 hours/day) n circles/D day, and the number of days on the return track D1, so n ranges [13 or 14 ].
Thirdly, calculating the running period of the satellite by using the regression condition;
here, the operating period T of the satellite is calculated again using the regression condition (24 hr/day)/(T0 hr/circle) of n circles/D days and the number of regression orbit days D of 1, the range of n [13 or 14 ].
The operating cycle satisfying the number of turns of the regression trajectory is obtained as shown in the following table:
| number of return turns | 13 | 14 |
| Period of operation | 110.7692min | 102.8571min |
Finally, calculating the orbit radius by using the running period of the satellite, and further calculating the orbit height;
substituting the running period T into the following formula to obtain the track radius a and the track height h;
h＝a-Re
where μ represents an earth gravity constant.
The track radius and track height for the turns are shown in the following table:
| operating period T | 110.7692min | 102.8571min |
| Radius of track a | 7639250m | 7271950.9m |
| Height h of track | 126111m | 893814m |
(2) Designing an inclination angle of the track, comprising: designing a track inclination angle for a coverage area except the south and north poles;
when the constellation is required to cover the regions except the north and south poles, the coverage areas of 70 degrees to 70 degrees of south latitude are respectively developed and designed, the inclination angle of the track covering the 70 degrees to 70 degrees of north latitude is about 55 degrees through the optimized design, and in the practical application, the refined design is further carried out by further combining the constellation configuration.
(3) The number of satellites, the number of orbital planes, and the phase factor are designed.
In some implementations, the number of satellites, the number of orbital planes, and the phase factor are designed, including:
the number of satellites, the number of orbital planes and the phase factor are designed with the goal of providing at least two coverage and/or as many satellites in view as possible to the service area.
For providing double coverage to a service area according to the requirement of constellation design, the service quality can be measured by the coverage performance of the constellation to the area, for example, the larger the number of visible satellites, the better.
A schematic of the coverage of a single star is shown in fig. 2, where, gamma is the elevation angle of observation,
is the satellite view angle. Only when the elevation angle of the satellite to the user is higher than gamma, the user can establish contact with the satellite, and the ground coverage area corresponding to the under-satellite viewing angle is the coverage area of the satellite.
Angle of view under the satellite
The formula for calculating the center angle theta and the coverage radius r of the ground coverage is as follows:
r＝Reθ
since the satellite moves in orbit, the coverage area of the satellite moves on the ground, and therefore, coverage time slots and coverage gaps are generated for the ground service area. In order to improve the coverage rate of a certain area, a constellation is formed by a plurality of satellites, and the coverage of the target area by each satellite is finished by mutual connection of the coverage time slots of the target area. The purpose of constellation optimization is to improve the performance of the system with as little satellite resources as possible or with a reasonable orbital configuration given the number of satellites.
If the coverage of north and south poles needs to be considered, step S1203 is executed;
step S1203, determining that the configuration of the low-orbit sub-constellation includes a low-orbit Walker constellation and a polar-orbit constellation, and designing a first variable of the low-orbit Walker constellation and a second variable of the polar-orbit constellation, where the second variable includes a precession speed, a regression orbit, a polar-orbit constellation parameter, and a right ascension of the ascending intersection point.
In this embodiment, when coverage of north and south poles needs to be considered, it is determined that the low-orbit sub-constellation configuration is a mixed constellation of a low-orbit Walker constellation and a polar-orbit constellation, after step S1202 is executed, design of the polar-orbit constellation needs to be added, and step S1203 is executed.
The orbit inclination angle is a key factor influencing the uniform distribution of the navigation performance of the LEO constellation, in the global coverage including south and north poles, the polar orbit constellation plays the role of a skeleton sub-constellation, the low orbit walker constellation is an effective supplement for encrypting multiple coverage in low and medium latitude areas, and the two are keys for improving the uniformity of the navigation performance.
In some implementations, designing a second variable of the polar constellation includes:
selecting the precession speed of the polar orbit constellation to keep the same as the precession speed of the low orbit Walker constellation;
preliminarily determining the orbit inclination angle range and the orbit height range of the polar orbit constellation, wherein the method comprises the following steps: preliminarily determining the track inclination angle range of the polar orbit constellation to be 80-100 degrees, and preliminarily determining the track height range of the polar orbit constellation to be 700-1500 km;
selecting a regression orbit of the polar orbit constellation, and selecting a polar orbit constellation parameter with the best coverage performance enhancement effect by taking an orbit inclination angle range and an orbit height range as optimization parameter boundaries;
selecting ascending crossing point right ascension differences according to set step lengths, analyzing the coverage performance of a configuration in which a low-orbit Walker constellation and a polar-orbit constellation are mixed under the condition of different ascending crossing point right ascension differences, selecting the ascending crossing point right ascension with the best coverage performance, and setting the step length to be 10 degrees under some conditions.
The polar orbit constellation portion design is described below in conjunction with an example:
analyzing the low orbit Walker constellation scheme designed in step S1202, and in order to maintain the stability of the relative constellation configuration, the precession speed of the selected polar orbit constellation should be as consistent as possible with the precession speed of the designed low orbit Walker constellation. Preliminarily determining the track inclination angle range of the polar orbit constellation to be 80-100 degrees, the track height range to be 700-1500 km, and analyzing to know that the precession speed decreases along with the increase of the height and decreases along with the increase of the track inclination angle. And selecting a regression orbit of the polar orbit constellation, and selecting the polar orbit constellation parameter with the best coverage performance enhancement effect by taking the orbit inclination angle range and the orbit height range as the optimization parameter boundary. And selecting ascending intersection right ascension differences with the step length of 10 degrees, and analyzing the coverage performance of a mixed constellation scheme of the polar orbit constellation and the low orbit Walker constellation selected under the condition of different ascending intersection right ascension differences, so as to select the better ascending intersection right ascension.
It should be understood that the second variable designed for polar-orbit constellation in practical application may also include other variables, and this embodiment is not illustrated.
Step S130, designing a medium and high orbit sub-constellation which can perform navigation work independently of the low orbit sub-constellation and meet the requirement of a space service domain, comprising the following steps:
step S1301, determining that the medium and high orbit sub-constellation comprises a high orbit sub-constellation and a medium orbit sub-constellation which are independent of each other and perform navigation work; the geostationary orbit satellite navigation system comprises a GEO orbit satellite and an IGSO orbit satellite, and can realize the regional navigation function by using a small number of satellites by using a heterogeneous constellation consisting of the GEO orbit satellite and the IGSO orbit satellite.
Step S1302, in the high-orbit sub-constellation and the medium-orbit sub-constellation, inter-satellite links are used for interconnection and intercommunication between satellites, so that the high-orbit sub-constellation and the medium-orbit sub-constellation can also work under the condition that a part of satellites fail. The heterogeneous constellation composed of the medium and high orbit satellites in this embodiment can realize independent navigation, has good elasticity, adopts inter-satellite links to perform interconnection and intercommunication among the satellites, and can work under the condition that part of the satellites fail.
In the embodiment, a low-orbit sub-constellation and a medium-orbit sub-constellation which have independent navigation capacity are designed, and inter-constellation satellites adopt inter-satellite links to realize information transmission, so that the autonomous navigation performance of a complex heterogeneous navigation constellation can be improved, and the requirements of a space service domain and navigation war of the complex heterogeneous navigation constellation are met. On one hand, under the condition that a constellation system is normal, the navigation signal can be enhanced by using a low-orbit sub-constellation; on the other hand, under the condition that the satellite of the low-orbit (or medium-high orbit) constellation fails, the service can be supplemented through the medium-high orbit (or low-orbit) constellation, and the navigation positioning performance and the service availability of the service area are kept.
In some implementations, designing a medium high orbit sub-constellation that can perform navigation work independently of low orbit sub-constellations and meet space service domain requirements further includes:
deploying the middle orbit sub-constellation on an orbit which is beneficial to improving the navigation performance of the high orbit sub-constellation at the current moment;
when the medium and high orbit sub-constellation needs to be expanded to the global range for navigation, the orbit of the medium and high orbit sub-constellation is adjusted to realize constellation reconstruction.
In practical applications, when a regional navigation system (a medium and high orbit sub-constellation composed of GEO and IGSO satellites) needs to be expanded to a global navigation system and navigation performance is improved, addition of MEO satellites needs to be considered. Firstly, an MEO satellite (also adopting walker constellation configuration) is deployed on an orbit which is beneficial to improving the performance of the regional navigation system at the moment, and then when the regional navigation system needs to be expanded to global navigation, the orbit of the satellite is adjusted to realize constellation reconstruction.
According to the method for realizing the complex heterogeneous navigation constellation based on the low-orbit, the medium-orbit and high-orbit subspaces, the low-orbit subspaces and the medium-orbit subspaces are operated jointly in a link mode between the satellites. The space service domain requirement of the satellite constellation is met, and the autonomous operation of the constellation is realized by the satellites of the satellite constellation through the self measurement information and the autonomous navigation algorithm.
In some implementations, designing a medium and high orbit sub-constellation that can perform navigation work independently of low orbit sub-constellations and meet space service domain requirements further includes:
the performance of a space service domain of the constellation satellite is improved by using the performance of a main lobe edge and a side lobe of the navigation antenna so as to meet the requirement of the space service domain.
FIG. 3 is a geometric diagram of a satellite signal space service, which is required to consider compatibility and interoperability with other global navigation constellation satellite systems to improve the performance of a complex heterogeneous navigation constellation space service domain, and improve the availability and performance of constellation satellite system signals; when a navigation system is designed, the performance of a space service domain of a constellation satellite needs to be improved by using the main lobe edge and the side lobe performance of the navigation antenna according to the characteristics of the satellite antenna.
According to the method for implementing the low-medium orbit-based complex heterogeneous navigation constellation, the constellation design can be further optimized by using the constellation autonomous navigation technology, so that the orbit distribution is more reasonable, the constellation autonomous navigation capability is improved by using the technologies such as inter-satellite links and the like, and the constellation maintenance and ephemeris update can be autonomously completed. The complex heterogeneous constellation of low, medium and high orbit is utilized to meet the requirement of navigation war, and the elasticity of the constellation system is ensured.
In the implementation method of the invention, the LEO satellite can form a combination of multiple high, medium and low orbit types with satellites with different orbit heights such as MEO, GEO, IGSO and the like to form a complex and heterogeneous navigation constellation, thereby enriching the space structure of a navigation system and greatly improving the precision, integrity, uniformity and the like of navigation positioning. Meanwhile, the complex heterogeneous navigation constellation has certain system elasticity capability, and the requirements of a space service domain and a navigation war can be better met.
In the embodiments provided in the present invention, it should be understood that the disclosed system and method can be implemented in other ways. The system and method embodiments described above are merely illustrative.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Although the embodiments of the present invention have been described above, the above descriptions are only for the convenience of understanding the present invention, and are not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A complex heterogeneous navigation constellation implementation method based on low, medium and high orbit is characterized by comprising the following steps:
determining that the complex heterogeneous navigation constellation comprises a low-orbit sub-constellation and a medium-high orbit sub-constellation;
designing a low orbit subsatellite which can be independent of a medium and high orbit subsatellite for navigation work comprises:
judging whether the coverage of north and south poles needs to be considered:
if the coverage of north and south poles does not need to be considered, determining that the configuration of the low-orbit sub-constellation comprises a low-orbit Walker constellation, and designing a first variable of the low-orbit Walker constellation, wherein the first variable comprises orbit height, orbit inclination angle, satellite number, orbit surface number and phase factor;
if the coverage of south and north poles needs to be considered, determining that the configuration of the low-orbit sub-constellation comprises a low-orbit Walker constellation and a polar-orbit constellation, and designing a first variable of the low-orbit Walker constellation and a second variable of the polar-orbit constellation, wherein the second variable comprises a precession speed, a regression orbit, polar-orbit constellation parameters and a rising-crossing right ascension;
designing a medium and high orbit sub-constellation which can carry out navigation work independently of the low orbit sub-constellation and meet the requirement of a space service domain comprises the following steps:
determining that the medium and high orbit sub-constellation comprises a high orbit sub-constellation and a medium orbit sub-constellation which are independent from each other and perform navigation work;
in the high-orbit sub-constellation and the medium-orbit sub-constellation, inter-satellite links are adopted for interconnection and intercommunication between satellites, so that the high-orbit sub-constellation and the medium-orbit sub-constellation can work under the condition that part of the satellites fail.
2. The method for implementing a low-medium high-orbit-based complex heterogeneous navigation constellation according to claim 1, wherein the designing a first variable of a low-orbit Walker constellation comprises:
designing a rail height, comprising: preliminarily estimating the radius range of the track; estimating the regression turns of the satellite by using a regression condition; calculating the running period of the satellite by using the regression condition again; calculating the orbit radius by using the operation period of the satellite, and further calculating the orbit height;
designing an inclination angle of the track, comprising: designing a track inclination angle for a coverage area except the south and north poles;
the number of satellites, the number of orbital planes, and the phase factor are designed.
3. The method for implementing a low-medium high orbit-based complex heterogeneous navigation constellation according to claim 1, wherein designing a second variable of the polar orbit constellation comprises:
selecting the precession speed of the polar orbit constellation to keep the same as the precession speed of the low orbit Walker constellation;
preliminarily determining the orbit inclination angle range and the orbit height range of the polar orbit constellation;
selecting a regression orbit of the polar orbit constellation, and selecting a polar orbit constellation parameter with the best coverage performance enhancement effect by taking an orbit inclination angle range and an orbit height range as optimization parameter boundaries;
and selecting ascending crossing right ascension differences according to the set step length, analyzing the coverage performance of the mixed configuration of the low-orbit Walker constellation and the polar-orbit constellation under the condition of different ascending crossing right ascension differences, and selecting the ascending crossing right ascension with the best coverage performance.
4. The method of claim 1, wherein the high-orbit sub-constellation comprises GEO-orbit satellites and IGSO-orbit satellites.
5. The method according to claim 1, wherein the medium-high orbit based complex heterogeneous navigation constellation comprises MEO orbit satellites.
6. The method for implementing a low and medium high orbit-based complex heterogeneous navigation constellation according to claim 2, wherein the designing the number of satellites, the number of orbital planes and the phase factor comprises:
the number of satellites, the number of orbital planes and the phase factor are designed with the goal of providing at least two coverage and/or as many satellites in view as possible to the service area.
7. The method according to claim 3, wherein the preliminarily determining the orbit inclination angle range and the orbit height range of the polar orbit constellation comprises:
the track inclination angle range of the polar orbit constellation is preliminarily determined to be 80-100 degrees, and the track height range of the polar orbit constellation is preliminarily determined to be 700-1500 km.
8. The method according to claim 3, wherein the step size is 10 °.
9. The method for implementing a low-medium high orbit-based complex heterogeneous navigation constellation according to claim 1, wherein the method designs a medium-high orbit sub-constellation which can perform navigation work independently of a low orbit sub-constellation and meet a requirement of a spatial service domain, and further comprises:
deploying the middle orbit sub-constellation on an orbit which is beneficial to improving the navigation performance of the high orbit sub-constellation at the current moment;
when the medium and high orbit sub-constellation needs to be expanded to the global range for navigation, the orbit of the medium and high orbit sub-constellation is adjusted to realize constellation reconstruction.
10. The method for implementing a low-medium high orbit-based complex heterogeneous navigation constellation according to claim 1, wherein the method designs a medium-high orbit sub-constellation which can perform navigation work independently of a low orbit sub-constellation and meet a requirement of a spatial service domain, and further comprises:
the performance of a space service domain of the constellation satellite is improved by using the performance of a main lobe edge and a side lobe of the navigation antenna so as to meet the requirement of the space service domain.
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| CN117252113B (en) * | 2023-11-17 | 2024-02-23 | 中国人民解放军战略支援部队航天工程大学 | Low-orbit hybrid constellation optimization design method for medium-orbit navigation constellation satellite failure |
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