CN112468216A - Constellation design method - Google Patents
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- CN112468216A CN112468216A CN202011311156.3A CN202011311156A CN112468216A CN 112468216 A CN112468216 A CN 112468216A CN 202011311156 A CN202011311156 A CN 202011311156A CN 112468216 A CN112468216 A CN 112468216A
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Abstract
The application discloses a constellation design method, which comprises the following steps: determining the area of an observed fixed region, and determining a corresponding circular coverage region when a single star is adopted to cover the observed fixed region according to the area; determining a field angle or a beam angle of the observed fixed area according to a preset field direction constraint condition, and calculating the track height of the single satellite according to the circular coverage area and the field angle or the beam angle; determining the number of satellites required for covering one latitudinal region, an orbital inclination angle and a difference value of true near point angles of two adjacent satellites in the same orbital plane according to the circular coverage region, and determining the number of the orbital planes according to the number of the satellites; and calculating the number of satellites in the same orbital plane according to the difference value, calculating the total satellite number and designing a satellite constellation according to the orbital plane number and the number of the satellites in the same orbital plane. The method and the device solve the technical problems that the constellation is not suitable for serving the ground fixed area and observing the fixed area in the celestial sphere in the prior art.
Description
Technical Field
The application relates to the technical field of satellite constellations, in particular to a constellation design method.
Background
With the rapid development of satellite communication technology, the low-orbit internet constellation represented by starlink and Kuiper can realize global seamless coverage, and the constellation can not only observe the ground area, but also can be converted into an observation constellation for celestial spheres, wherein the constellation is converted into the observation constellation for celestial spheres, so that the real-time property of astronomical observation and the coverage advantage of large-area celestial spheres can be fused, and new economic and industrial forms in the field of astronomical observation can be promoted, such as popular astronomical entertainment, consumption and education industries. However, because such constellations are large in scale and high in deployment and operation cost, on one hand, for some special low-orbit constellations supporting a ground fixed region, global coverage is both wasteful and unnecessary, for example, in tasks of remote sensing, communication support and the like of an earth fixed region, the low-orbit constellations with the orbit height of less than 1000km are adopted, so that service delay of a satellite-ground link can be remarkably reduced, the superiority of low-delay service is achieved, and meanwhile, the defect that the coverage area of a single satellite to the ground is small due to the low orbit height is also overcome; on the other hand, when the constellation is converted into an observation constellation for the celestial sphere, the constellation needs to be combined with a track design to determine a celestial sphere region capable of being continuously observed on the basis of carrying astronomical observation equipment, or a track optimization design is carried out according to the celestial sphere region needing to be continuously observed, so that the scale of the whole constellation is minimum.
At present, no constellation configuration orbit is adopted for a low-orbit constellation supported by a ground fixed region and a celestial sphere internal fixed region, and the ground fixed region and satellite nodes in a 24h continuously visible constellation of the celestial sphere internal fixed region can be realized by depending on the least number of constellation nodes, so that how to design a 24h continuously visible constellation of the earth or celestial sphere internal fixed region becomes an urgent problem to be solved.
Disclosure of Invention
The technical problem that this application was solved is: the method comprises the steps that a constellation is not suitable for serving a ground fixed area and observing a celestial sphere internal fixed area in the prior art, a constellation design method is provided, in the scheme provided by the embodiment of the application, a constellation configuration orbit which is adopted by the service of the ground fixed area and a low-orbit constellation supported by the celestial sphere internal fixed area is provided, and satellite nodes in the constellation which are continuously visible in the ground fixed area and 24h in the celestial sphere internal fixed area can be realized by means of the minimum number of constellation nodes, so that the 24h continuously visible constellation in the earth or celestial sphere internal fixed area is realized.
In a first aspect, an embodiment of the present application provides a constellation design method, where the method includes:
determining the area of an observed fixed region, and determining a corresponding circular coverage region when a single star is adopted to cover the observed fixed region according to the area;
determining a field angle or a beam angle of the observed fixed area according to a preset field direction constraint condition, and calculating the track height corresponding to the observed fixed area covered by the single satellite according to the circular coverage area and the field angle or the beam angle;
determining the number of satellites required for covering one latitudinal region, an orbital inclination angle and a difference value of true near point angles of two adjacent satellites in the same orbital plane according to the circular coverage region, and determining the number of orbital planes according to the number of the satellites;
and calculating the number of satellites in the same orbital plane according to the difference value, calculating the total satellite number according to the orbital plane number and the number of the satellites in the same orbital plane, and designing a satellite constellation according to the total satellite number, the orbital plane number, the orbital inclination angle, the orbital height and the number of the satellites in the same orbital plane.
In the scheme provided by the embodiment of the application, by determining the area of an observed fixed area, determining a corresponding circular coverage area when a single satellite is adopted to cover the observed fixed area according to the area, then determining a field angle or a beam angle of the observed fixed area according to a preset field pointing constraint condition, calculating an orbital height corresponding to the observed fixed area covered by the single satellite according to the circular coverage area and the field angle or the beam angle, then determining the number of satellites required for covering one latitudinal area, an orbital inclination angle and a difference value of true near point angles of two adjacent satellites in the same orbital plane according to the circular coverage area, determining the number of orbital planes according to the number of the satellites, then calculating the number of satellites in the same orbital plane according to the difference value, and calculating the total number of satellites according to the number of the orbital planes and the number of the satellites in the same orbital plane, and designing a satellite constellation according to the total satellite number, the orbital plane number, the orbital inclination angle, the orbital height and the number of satellites in the same orbital plane. Namely, the embodiment of the application provides a constellation configuration orbit for a low-orbit constellation supported by a ground fixed region and a celestial sphere internal fixed region, and can realize the 24h continuous visible constellation of the ground fixed region and the celestial sphere internal fixed region by depending on the least number of constellation nodes, thereby realizing the 24h continuous visible constellation of the earth or celestial sphere internal fixed region.
Optionally, the area of the observed fixed region includes an area of an observed region of an inner surface of the celestial sphere or an area of an observed region of the ground.
Optionally, determining, according to the circular coverage area, the number of satellites required for covering one latitudinal region, the orbital inclination angle, and the difference between true proximity angles of two adjacent satellites in the same orbital plane, includes:
determining the diameter of the circular coverage area and the geographic coordinate latitude of the circle center, and calculating the perimeter of a circle center geographic latitude line and the track inclination according to the geographic coordinate latitude and the diameter;
and calculating the number of the satellites required for covering one latitudinal zone area according to the perimeter and the diameter, and calculating the difference value of true near point angles of two adjacent satellites in the same orbital plane according to the diameter.
Optionally, calculating a perimeter of a circle center geographic latitude line and the track inclination angle according to the geographic coordinate latitude and the diameter includes:
calculating the perimeter of the circle center geographical latitude line and the track inclination angle by the following formula:
L＝2πr0cos(w)
wherein L represents the perimeter of the circle center geographical latitude line; r is0Represents the radius of the earth; w represents the geographical coordinate latitude of the circle center; d represents the diameter of the circular coverage area; i denotes the track inclination.
Optionally, calculating the number of satellites required to cover a latitudinal region according to the circumference and the diameter includes:
the number of satellites is calculated by the following formula:
wherein N represents the number of satellites; [] Indicating rounding.
Optionally, calculating a difference between true near point angles of two adjacent satellites in the same orbital plane according to the diameter includes:
calculating the difference value of the true near point angles of two adjacent satellites in the same orbital plane by the following formula:
wherein A represents the difference value of true near point angles of two adjacent satellites in the same orbital plane.
Optionally, calculating the number of satellites in the same orbital plane according to the difference includes:
calculating the number of satellites in the same orbital plane by the following formula:
wherein N ispAnd the number of satellites in the same orbital plane is shown.
Optionally, calculating the total number of satellites according to the number of orbital planes and the number of satellites in the same orbital plane, including:
calculating the total number of satellites by the following formula:
NT＝Nplane·Np
wherein N isTRepresenting the total number of satellites; n is a radical ofplaneIndicating the number of track surfaces.
Optionally, designing a satellite constellation according to the total number of satellites, the number of orbital planes, the orbital inclination, the orbital altitude, and the number of satellites in the same orbital plane, includes:
calculating the phase difference step length of the adjacent orbital planes according to the total satellite number, and determining the arrangement phase difference of the adjacent planes according to the phase difference step length of the adjacent orbital planes, wherein the arrangement phase difference is odd times of the phase difference step length;
and designing to obtain the satellite constellation according to the total satellite number, the arrangement phase difference, the orbital plane number, the orbital inclination angle, the orbital height and the number of satellites in the same orbital plane.
Optionally, determining the arrangement phase difference of the adjacent planes according to the phase difference step of the adjacent track planes includes:
the arrangement phase difference is calculated by the following formula:
Pphase＝K·P
wherein, PphaseRepresenting the arrangement phase difference; p represents the adjacent track plane phase difference step,
k represents an odd number and K is less than or equal to Nplane。
Drawings
Fig. 1 is a schematic flowchart of a constellation design method according to an embodiment of the present application;
FIG. 2 is a schematic diagram of a contour of a ground observation fixed area according to an embodiment of the present disclosure;
FIG. 3 is a schematic diagram of a circular coverage area provided by an embodiment of the present application;
fig. 4 is a schematic structural diagram of a constellation provided in the embodiment of the present application.
Detailed Description
In the solutions provided in the embodiments of the present application, the described embodiments are only a part of the embodiments of the present application, 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 application.
A constellation design method provided in the embodiments of the present application is further described in detail below with reference to the drawings in the specification, and a specific implementation manner of the method may include the following steps (a method flow is shown in fig. 1):
step 101, determining the area of the observed fixed area, and determining a corresponding circular coverage area when the observed fixed area is covered by a single star according to the area.
Specifically, in the scheme provided by the embodiment of the present application, since the satellite constellation can observe a ground fixed region, it can also be used to observe an area within the celestial sphere.
In one possible implementation, the area of the observed fixed region includes an area of an observed region of an inner surface of the celestial sphere or an area of an observed region of the ground.
Specifically, the observed fixed region may be a regular region or an irregular region, and therefore, the area of the observed fixed region may be a regular area or an irregular area, which is not limited herein. For example, if the area of the observed region is the area of the observed region of the celestial sphere inner surface, determining the area of the observed region of the celestial sphere inner surface includes setting the inner surface radius (with the geocenter as the sphere center) of the virtual celestial sphere as R; acquiring an irregular area S of an observed fixed area on the inner surface of the celestial sphere; and obtaining an irregular area profile S', S ═ S of the equivalent ground served fixed area.
Further, the observed fixed area is covered with a single star, wherein the single star covers the observed fixed area with a circular coverage area, i.e. the observed fixed area is located within the circular coverage area.
And 102, determining a field angle or a beam angle of the observed fixed area according to a preset field direction constraint condition, and calculating the track height corresponding to the observed fixed area covered by the single star according to the circular coverage area and the field angle or the beam angle.
Specifically, in the scheme provided by the embodiment of the application, the preset field orientation constraint conditions include an on-satellite load to sky field orientation constraint condition and an on-satellite load to earth field orientation constraint condition; the field angle is the field angle for the area within the celestial sphere, and the beam angle is the beam angle for the area under the star.
Further, after determining the field angle or the beam angle of the observed fixed area, the track height corresponding to the observed fixed area covered by a single star needs to be calculated according to the circular coverage area and the field angle or the beam angle. Specifically, the track height corresponding to the observation fixed area covered by a single star is calculated by the following formula:
wherein h represents the track height corresponding to the observation fixed area covered by the single star; θ represents a field angle or a beam angle; d represents the diameter of the circular coverage area.
And 103, determining the number of satellites required for covering one latitudinal region, the orbital inclination angle and the difference value of true near point angles of two adjacent satellites in the same orbital plane according to the circular coverage region, and determining the number of orbital planes according to the number of the satellites.
Specifically, in the solution provided in the embodiment of the present application, there are various ways to determine the number of satellites required to cover one latitudinal region, the orbital inclination angle, and the difference between the true proximity angles of two adjacent satellites in the same orbital plane according to the circular coverage region, and a preferred way is described as an example below.
In a possible implementation manner, determining, from the circular coverage area, the number of satellites required to cover a latitudinal strip area, the orbital inclination angle, and the difference between true proximity angles of two adjacent satellites in the same orbital plane includes: determining the diameter of the circular coverage area and the geographic coordinate latitude of the circle center, and calculating the perimeter of a circle center geographic latitude line and the track inclination according to the geographic coordinate latitude and the diameter; and calculating the number of the satellites required for covering one latitudinal zone area according to the perimeter and the diameter, and calculating the difference value of true near point angles of two adjacent satellites in the same orbital plane according to the diameter.
Further, in a possible implementation manner, calculating the circumference of the circle center geographic latitude line and the track inclination angle according to the geographic coordinate latitude and the diameter includes:
calculating the perimeter of the circle center geographical latitude line and the track inclination angle by the following formula:
L＝2πr0cos(w)
wherein L represents the perimeter of the circle center geographical latitude line; r is0Represents the radius of the earth; w represents the geographical coordinate latitude of the circle center; d represents the diameter of the circular coverage area; i denotes the track inclination.
Further, in one possible implementation, calculating the number of satellites required to cover a latitudinal region based on the perimeter and the diameter includes: the number of satellites is calculated by the following formula:
wherein N represents the number of satellites; [] Indicating rounding.
Further, in a possible implementation manner, calculating a difference value between true near point angles of two adjacent satellites in the same orbital plane according to the diameter includes:
calculating the difference value of the true near point angles of two adjacent satellites in the same orbital plane by the following formula:
wherein A represents the difference value of true near point angles of two adjacent satellites in the same orbital plane.
And 104, calculating the number of satellites in the same orbital plane according to the difference, calculating the total number of satellites according to the number of orbital planes and the number of satellites in the same orbital plane, and designing a satellite constellation according to the total number of satellites, the number of orbital planes, the orbital inclination angle, the orbital height and the number of satellites in the same orbital plane.
In a possible implementation manner, calculating the number of satellites in the same orbital plane according to the difference includes:
calculating the number of satellites in the same orbital plane by the following formula:
wherein N ispAnd the number of satellites in the same orbital plane is shown.
Further, in a possible implementation manner, calculating the total number of satellites according to the number of orbital planes and the number of satellites in the same orbital plane includes:
calculating the total number of satellites by the following formula:
NT＝Nplane·Np
wherein N isTRepresenting the total number of satellites; n is a radical ofplaneIndicating the number of track surfaces.
Further, in a possible implementation manner, designing a satellite constellation according to the total number of satellites, the number of orbital planes, the orbital inclination, the orbital altitude, and the number of satellites in the same orbital plane includes: calculating the phase difference step length of the adjacent orbital planes according to the total satellite number, and determining the arrangement phase difference of the adjacent planes according to the phase difference step length of the adjacent orbital planes, wherein the arrangement phase difference is odd times of the phase difference step length; and designing to obtain the satellite constellation according to the total satellite number, the arrangement phase difference, the orbital plane number, the orbital inclination angle, the orbital height and the number of satellites in the same orbital plane.
Further, in a possible implementation manner, determining the arrangement phase difference of the adjacent planes according to the adjacent track plane phase difference step includes:
the arrangement phase difference is calculated by the following formula:
Pphase＝K·P
wherein, PphaseRepresenting the arrangement phase difference; p represents the adjacent track plane phase difference step,
k represents an odd number and K is less than or equal to Nplane。
To facilitate an understanding of the construction process of the satellite constellation, a brief description is given below by way of example.
Referring to fig. 2, a schematic contour diagram of a ground observed fixed area is provided in the embodiment of the present application. The specific satellite constellation construction process comprises the following steps:
(1) determining the outline area of the observed fixed area in fig. 2, and calculating the diameter of a circular coverage area covering the area by using a single star, wherein the circular coverage area completely covers the irregular area of the earth surface, the diameter of the circular area is D, and the diameter D of the specific circular coverage area is 3000 as shown in fig. 3.
(2) And determining the width of the on-satellite load to the ground field of view to be +/-60 degrees. The beam angle theta of the ground area covering the satellite points is 120 DEG
(3) And (3) obtaining the orbit height required by the single satellite to cover the area according to the area of the circular coverage area in the step (1) and the coverage beam angle in the step (2), wherein the orbit height is as follows: h 866 km.
(4) Determining the geographic coordinate latitude of the circle center and the perimeter L of the circle center geographic latitude line according to the circle center geographic position of the circular coverage area in the step (1), and specifically: the latitude value w is 22 degrees, and L is 37115 km.
(5) And (3) according to the circumference of the circle center geographical latitude line of the circular coverage area in the step (4) and the diameter of the circular coverage area in the step (1), determining the star number required for covering one latitude area by the following formula:
(6) determining the number of orbital planes according to the number of stars required for covering one latitudinal zone in the step (5) by the following formula:
(7) and (3) calculating the required track inclination angle according to the diameter of the coverage area in the step (1), wherein the track inclination angle i is 22.67 degrees.
(8) And (2) calculating the difference value of the true proximal angles of two adjacent stars in the plane according to the diameter of the coverage area in the step (1), wherein the specific difference value A of the true proximal angles of two adjacent stars in the plane is 26.97 degrees.
(9) Calculating the number of the satellites in the plane according to the difference value of the true near point angles of the two adjacent satellites in the plane in the step (8), and specifically calculating the number of the satellites in the plane according to the following formula:
(10) and (3) calculating the total number of the stars according to the number of the orbital planes in the step (6) and the number of the satellites in the planes in the step (9), specifically, calculating the total number of the stars according to the following formula:
NT＝Nplane·Np＝182
(11) and (5) calculating the phase difference step length between the adjacent orbital planes according to the total star number in the step (10): p is 2 °.
(12) Adjusting the arrangement phase difference between the adjacent surfaces according to the phase difference step length between the adjacent track surfaces in the step (11), wherein the arrangement phase difference between the adjacent surfaces is odd-number times of the phase step length:
Pphase＝K·P
wherein K is less than or equal to Nplane。
In the scheme provided by the embodiment of the application, the K value with the lowest coverage area overlapping rate is selected as: k is 5. And (5) constructing a satellite constellation according to the parameters calculated in the steps (1) to (12), specifically, referring to fig. 4 for the configuration of the satellite constellation.
Specifically, the constellation shown in fig. 4 has the following relationship with the parameters calculated in the steps (1) to (12):
1. the constellation consists of a plurality of satellites distributed on a plurality of orbital planes;
2. the number of track surfaces is determined by the step (6) above;
3. the track height is determined by the step (3);
4. the track inclination angle is determined by the step (7);
5. the number of the in-plane satellites is determined by the step (9);
6. the phase difference between adjacent track surfaces is determined in step (12).
In the scheme provided by the embodiment of the application, by determining the area of an observed fixed area, determining a corresponding circular coverage area when a single satellite is adopted to cover the observed fixed area according to the area, then determining a field angle or a beam angle of the observed fixed area according to a preset field pointing constraint condition, calculating an orbital height corresponding to the observed fixed area covered by the single satellite according to the circular coverage area and the field angle or the beam angle, then determining the number of satellites required for covering one latitudinal area, an orbital inclination angle and a difference value of true near point angles of two adjacent satellites in the same orbital plane according to the circular coverage area, determining the number of orbital planes according to the number of the satellites, then calculating the number of satellites in the same orbital plane according to the difference value, and calculating the total number of satellites according to the number of the orbital planes and the number of the satellites in the same orbital plane, and designing a satellite constellation according to the total satellite number, the orbital plane number, the orbital inclination angle, the orbital height and the number of satellites in the same orbital plane. Namely, the embodiment of the application provides a constellation configuration orbit for a low-orbit constellation supported by a ground fixed region and a celestial sphere internal fixed region, and can realize the 24h continuous visible constellation of the ground fixed region and the celestial sphere internal fixed region by depending on the least number of constellation nodes, thereby realizing the 24h continuous visible constellation of the earth or celestial sphere internal fixed region.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. A method for constellation design, comprising:
determining the area of an observed fixed region, and determining a corresponding circular coverage region when a single star is adopted to cover the observed fixed region according to the area;
determining a field angle or a beam angle of the observed fixed area according to a preset field direction constraint condition, and calculating the track height corresponding to the observed fixed area covered by the single satellite according to the circular coverage area and the field angle or the beam angle;
determining the number of satellites required for covering one latitudinal region, an orbital inclination angle and a difference value of true near point angles of two adjacent satellites in the same orbital plane according to the circular coverage region, and determining the number of orbital planes according to the number of the satellites;
and calculating the number of satellites in the same orbital plane according to the difference value, calculating the total satellite number according to the orbital plane number and the number of the satellites in the same orbital plane, and designing a satellite constellation according to the total satellite number, the orbital plane number, the orbital inclination angle, the orbital height and the number of the satellites in the same orbital plane.
2. The method of claim 1, wherein the area of the observed fixed region comprises an area of an observed region of an inner surface of the celestial sphere or an area of an observed region of the ground.
3. The method of claim 2, wherein determining from the circular coverage area the number of satellites required to cover a latitudinal region, the orbital inclination, and the difference between the true proximity angles of two adjacent satellites in the same orbital plane comprises:
determining the diameter of the circular coverage area and the geographic coordinate latitude of the circle center, and calculating the perimeter of a circle center geographic latitude line and the track inclination according to the geographic coordinate latitude and the diameter;
and calculating the number of the satellites required for covering one latitudinal zone area according to the perimeter and the diameter, and calculating the difference value of true near point angles of two adjacent satellites in the same orbital plane according to the diameter.
4. The method of claim 3, wherein calculating the perimeter of the circle-center geographic latitude line and the track inclination from the geographic coordinate latitude and the diameter comprises:
calculating the perimeter of the circle center geographical latitude line and the track inclination angle by the following formula:
L＝2πr0cos(w)
wherein L represents the perimeter of the circle center geographical latitude line; r is0Represents the radius of the earth; w represents the geographical coordinate latitude of the circle center; d represents the diameter of the circular coverage area; i denotes the track inclination.
5. The method of claim 4, wherein calculating the number of satellites needed to cover a latitudinal region based on the circumference and the diameter comprises:
the number of satellites is calculated by the following formula:
wherein N represents the number of satellites; [] Indicating rounding.
6. The method of claim 5, wherein calculating the difference between true paraxial angles of two adjacent satellites in the same orbital plane according to the diameter comprises:
calculating the difference value of the true near point angles of two adjacent satellites in the same orbital plane by the following formula:
wherein A represents the difference value of true near point angles of two adjacent satellites in the same orbital plane.
7. The method according to any one of claims 1 to 6, wherein calculating the number of satellites in the same orbital plane according to the difference comprises:
calculating the number of satellites in the same orbital plane by the following formula:
wherein N ispAnd the number of satellites in the same orbital plane is shown.
8. The method according to any one of claims 1 to 6, wherein calculating the total number of satellites based on the number of orbital planes and the number of satellites in the same orbital plane comprises:
calculating the total number of satellites by the following formula:
NT＝Nplane·Np
wherein N isTRepresenting the total number of satellites; n is a radical ofplaneIndicating the number of track surfaces.
9. The method of claim 8, wherein designing a satellite constellation based on the total number of satellites, the number of orbital planes, the orbital inclination, the orbital altitude, and the number of satellites in the same orbital plane comprises:
calculating the phase difference step length of the adjacent orbital planes according to the total satellite number, and determining the arrangement phase difference of the adjacent planes according to the phase difference step length of the adjacent orbital planes, wherein the arrangement phase difference is odd times of the phase difference step length;
and designing to obtain the satellite constellation according to the total satellite number, the arrangement phase difference, the orbital plane number, the orbital inclination angle, the orbital height and the number of satellites in the same orbital plane.
10. The method of claim 9, wherein determining the phase difference of the arrangement of the adjacent planes according to the phase difference step of the adjacent orbital planes comprises:
the arrangement phase difference is calculated by the following formula:
Pphase＝K·P
wherein, PphaseRepresenting the arrangement phase difference; p represents the adjacent track plane phase difference step,
k represents an odd number and K is less than or equal to Nplane。
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030095064A1 (en) * | 2001-11-21 | 2003-05-22 | Branscombe Steven L. | Method of configuring satellite constellation design using multiple discrete switchable spot beams |
| US20140128059A1 (en) * | 2011-06-16 | 2014-05-08 | Astrium Sas | Device and method for optimizing the ground coverage of a hybrid space system |
| CN106249253A (en) * | 2016-07-20 | 2016-12-21 | 中国人民解放军装备学院 | Low rail communication and navigation strengthen the Optimization Design of hybrid constellation |
| CN109639338A (en) * | 2018-11-27 | 2019-04-16 | 中国空间技术研究院 | One kind being suitable for the distant integral application Global coverage constellation of admittance and its design method |
| CN111164924A (en) * | 2017-06-26 | 2020-05-15 | 苹果公司 | Reference signal collision handling |
| CN111416657A (en) * | 2020-03-19 | 2020-07-14 | 西安电子科技大学 | Satellite network route updating maintenance system and maintenance method |
| CN111585635A (en) * | 2020-04-17 | 2020-08-25 | 中国人民解放军国防科技大学 | Satellite internet system design method based on space-frequency hybrid multiple access mode |
-
2020
- 2020-11-20 CN CN202011311156.3A patent/CN112468216B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030095064A1 (en) * | 2001-11-21 | 2003-05-22 | Branscombe Steven L. | Method of configuring satellite constellation design using multiple discrete switchable spot beams |
| US20140128059A1 (en) * | 2011-06-16 | 2014-05-08 | Astrium Sas | Device and method for optimizing the ground coverage of a hybrid space system |
| CN106249253A (en) * | 2016-07-20 | 2016-12-21 | 中国人民解放军装备学院 | Low rail communication and navigation strengthen the Optimization Design of hybrid constellation |
| CN111164924A (en) * | 2017-06-26 | 2020-05-15 | 苹果公司 | Reference signal collision handling |
| CN109639338A (en) * | 2018-11-27 | 2019-04-16 | 中国空间技术研究院 | One kind being suitable for the distant integral application Global coverage constellation of admittance and its design method |
| CN111416657A (en) * | 2020-03-19 | 2020-07-14 | 西安电子科技大学 | Satellite network route updating maintenance system and maintenance method |
| CN111585635A (en) * | 2020-04-17 | 2020-08-25 | 中国人民解放军国防科技大学 | Satellite internet system design method based on space-frequency hybrid multiple access mode |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115469340A (en) * | 2022-08-17 | 2022-12-13 | 南京信息工程大学 | Method for estimating number of visible satellites of navigation constellation |
| CN115469340B (en) * | 2022-08-17 | 2023-08-04 | 南京信息工程大学 | Method for estimating number of visible satellites of navigation constellation |
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