Low-orbit/middle-orbit double-layer satellite optical network structure system and design calculation method

A network structure and low-orbit satellite technology, applied in the field of satellite network structure, can solve problems such as large network delay and no consideration of inter-satellite laser link characteristics, and achieve the effects of reducing handover, strengthening implementation management, and simplifying network routing

Inactive Publication Date: 2009-12-16
AIR FORCE UNIV PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

The system does not consider the characteristics of the inter-satellite laser link. The middl

Method used

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  • Low-orbit/middle-orbit double-layer satellite optical network structure system and design calculation method
  • Low-orbit/middle-orbit double-layer satellite optical network structure system and design calculation method
  • Low-orbit/middle-orbit double-layer satellite optical network structure system and design calculation method

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Embodiment 1

[0117] Let H be the altitude of the satellite, R be the radius of the Earth, and ε be the elevation angle of the ground station to the satellite. exist Figure 8 In the schematic diagram of the coverage zone shown, two satellites form a coverage zone, θ is the radius of a single satellite coverage circle, and its value is:

[0118] ①, θ=arccos[Rcosε / (R+H)]-ε

[0119] Ψ is the half-angle of the coverage zone, and 2π / S is the distance between two satellites in the orbital plane, which is known from the spherical right triangle theorem:

[0120] ②、Ψ=arccos[cosθ / cos(π / S)]

[0121] The satellite positions of the orbit B closest to the reference satellite (ahead of satellite A) are:

[0122] ③,

[0123] The constraints to satisfy continuous coverage are:

[0124] ④, α′≤Ψ+arccos[cosθ / cosδ B ]

[0125] Using the spherical right triangle theorem, we know that the actual right ascension difference:

[0126] ⑤、sinα=sinα′ / sini

[0127] The relationship between the actual phase ...

Embodiment 2

[0135] Let H be the altitude of the satellite, R be the radius of the Earth, and ε be the elevation angle of the ground station to the satellite. exist Figure 8 In the schematic diagram of the coverage zone shown, two satellites form a coverage zone, θ is the radius of a single satellite coverage circle, and its value is:

[0136] ①, θ=arccos[Rcosε / (R+H)]-ε

[0137] Ψ is the half-angle of the coverage zone, and 2π / S is the distance between two satellites in the orbital plane, which is known from the spherical right triangle theorem:

[0138] ②、Ψ=arccos[cosθ / cos(π / S)]

[0139] The satellite positions of the orbit B closest to the reference satellite (ahead of satellite A) are:

[0140] ③,

[0141] The constraints to satisfy continuous coverage are:

[0142] ④, α′≤Ψ+arccos[cosθ / cosδ B ]

[0143] Using the spherical right triangle theorem, we know that the actual right ascension difference:

[0144] ⑤、sinα=sinα′ / sini

[0145] The relationship between the actual phase ...

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Abstract

The invention discloses a low-orbit/middle-orbit double-layer satellite optical network structure system. Global coverage low-orbit satellite constellation designed on the basis of a coverage zone method and middle-orbit satellite constellation form a double-layer satellite optical network structure system. The system is connected with at least 76 satellites, wherein, a low-orbit satellite layer is provided with at least 7 orbits, and each orbit is connected with at least 10 satellites; a middle-orbit satellite layer is composed of an outer orbit and an inner orbit, wherein, the outer orbit is respectively connected with the satellites, and the inner orbit is respectively connected with the satellites. The calculation method is as follows: calculating the radius theta of a single satellite covering circle; calculating the halfangle psi of the covering zone; calculating delta B; calculating alpha'; calculating sin alpha; and calculating the distribution of P orbits on the equator. The structure is stable topological structure, the changes of inter-satellite links pitch angle and azimuth angle are smaller than the changes of the inter-satellite links pitch angle and the azimuth angle of the non-zero phase constellation, satellite switch is reduced, satellite-carried resources are saved, and management of the low-orbit satellite layer is effectively strengthened; the middle-orbit satellite constellation is least affected by space radiation, and the system life cycle is lengthened.

Description

technical field [0001] The invention relates to a satellite network structure, in particular to a global coverage low-orbit / medium-orbit double-layer satellite optical network structure system and a design calculation method. Background technique [0002] The existing microwave link satellite constellation systems "Skybridge", "Globalstar" and "Ellipiso" face two problems: insufficient bandwidth and no inter-satellite link. Compared with microwave satellite communication, satellite optical communication has the advantages of wide bandwidth, large capacity, low power consumption, small terminal size, high confidentiality and good anti-interference. [0003] In recent years, the United States, Europe, and Japan have successively carried out research on satellite laser link networking. Among them, the Information and Decision Systems Laboratory of the Massachusetts Institute of Technology has been committed to the research of satellite optical networks. Without considering the ...

Claims

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Application Information

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IPC IPC(8): H04B10/00H04B10/27
Inventor 吴继礼李勇军赵尚弘蒙文石磊刘兰赵顾颢易鹏占生宝
Owner AIR FORCE UNIV PLA
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