Efficient routing method for orthogonal circular orbit configuration satellite constellation

A satellite constellation and orthogonal circle technology, applied in the field of satellite networking, can solve the problems of less utilization of constellation topology, inapplicability of satellite systems, and failure to fully exert the strong regularity of communication satellite constellations.

Active Publication Date: 2020-06-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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However, the existing satellite dynamic topology update algorithms are generally modified and adapted on the basis of ground routing algorithms. The exchange of network information between satellite nodes is too frequent, and the utilization of constellation topology is too little, ...

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  • Efficient routing method for orthogonal circular orbit configuration satellite constellation
  • Efficient routing method for orthogonal circular orbit configuration satellite constellation
  • Efficient routing method for orthogonal circular orbit configuration satellite constellation

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Embodiment Construction

[0020] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0021] Orthogonal circular orbit constellations can better achieve continuous global coverage. Its advantage is that the ground coverage is more uniform than that of polar orbit constellations, and the inter-satellite link is also relatively stable. The constellation consists of N orbits passing through the north and south poles and an orbit above the equator, numbered 0, 1, ..., N, a total of N+1 orbits, and the orbit number 0 indicates the equatorial orbit. There are M satellites on each polar orbit, and 2N satellites on the equatorial orbit, and the phase difference between adjacent satellites in the orbit is half of the phase difference between adjacent satellites in the same orbit. The satellites in the constellation can be marked by the orbit number plus the satellite number. For example, in a constellation system with 4 polar orbits and...

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Abstract

The invention discloses an efficient routing method for an orthogonal circular orbit configuration satellite constellation. According to the invention, the method comprises the steps: proposing a principle of proximity, a principle of approach and an equatorial orbit satellite active periodic updating mechanism according to a constellation link model to ensure the rationality and the cheapness ofa network link; proposing a link priority algorithm based on hop count prediction on the basis of the link model; enabling a satellite to send out a data packet according to the priority of each linkthrough sequential decisions of a link actual on-off state, a link pseudo-off state caused by a non-backhaul strategy, a destination node direction, a link congestion degree and a link propagation delay factor; carrying out discussion in four situations according to the categories of the source satellite node and the destination satellite node, and providing a hop count prediction method for sending data packets from different links for each situation according to satellite numbers and state information.

Description

technical field [0001] The invention belongs to the field of satellite networking, in particular to an efficient routing method for satellite constellations with orthogonal circular orbit configurations. Background technique [0002] With the wide application of Internet technology and the rapid development of the aerospace industry, the use of satellite networks to carry out Internet services has become a hot issue, and inter-satellite routing technology is the key. According to the implementation mechanism, these routing methods can be divided into three categories: routing algorithms based on virtual topology, routing algorithms based on virtual nodes, and dynamic topology update routing algorithms. [0003] The basic idea of ​​the routing algorithm based on virtual topology is to divide the constellation period into several small time segments according to the periodicity of satellite operation. Highly dynamic topological properties of satellites. Generally, the routin...

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Application Information

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IPC IPC(8): H04B7/185H04L12/707H04L12/721H04L12/759H04L45/24H04L45/28
CPCH04B7/18521H04L45/028H04L45/124H04L45/24H04L45/44
Inventor 雷磊包翔寇克灿葛以震沈高青李志林蔡圣所张莉涓宋晓勤
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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