Constellation design method suitable for orthogonal circular orbit constellation configuration

A design method and technology of orthogonal circles, applied in the field of satellite networking, can solve problems such as waste of satellite resources in high-latitude areas, changes in satellite communication topology, and mismatched density distribution

Active Publication Date: 2020-03-27
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, 79.4% of the global population is concentrated in areas between 20° and 60° north latitude, which means that satellite communication services will mainly be concentrated in low- and middle-latitude areas. Serious waste of satellite resources
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  • Constellation design method suitable for orthogonal circular orbit constellation configuration
  • Constellation design method suitable for orthogonal circular orbit constellation configuration
  • Constellation design method suitable for orthogonal circular orbit constellation configuration

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Embodiment Construction

[0012] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments.

[0013] The purpose of orthogonal circular orbit constellation design is to ensure continuous global coverage. The traditional coverage-based design method makes the coverage area boundaries of polar orbit satellite constellations and equatorial orbit satellite constellations coincide, so as to meet global coverage requirements. However, this method is not a fine-grained continuous coverage design, and its coverage is redundant when the condition of single coverage is guaranteed. In the area below the latitude of the lowest continuous coverage of the polar orbiting constellation, there is no situation that the polar orbiting satellite cannot cover at all, but there will be a "gap" in the coverage of the area at a certain moment. And the position and size of the gap will change with the movement of the satellite. As the latitude increases, the d...

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Abstract

The invention discloses a constellation design method suitable for orthogonal circular orbit constellation configuration. Based on motion characteristics and coverage characteristics of polar orbit constellation satellites, the characteristics of a coverage gap generated in an area which does not meet the continuous coverage requirement are analyzed, then in combination with the characteristics ofan equatorial orbit constellation satellite, an orthogonal circular orbit constellation design method based on geometric analysis is provided, and the minimum earth coverage half-width angle parameter of the equatorial satellite is accurately determined through an analytical method. According to the method, the ground minimum communication elevation angle of medium and low latitudes can be effectively improved on the premise of ensuring global complete continuous coverage, and the simulation result of STK shows the effectiveness of the constellation designed by the method.

Description

technical field [0001] The invention belongs to the field of satellite networking, in particular to a constellation design method suitable for orthogonal circular orbit constellation configurations. Background technique [0002] Satellite communication has ushered in a new round of development boom in recent years. Constellation design technology is the basis of satellite communication system. How to design a low-cost constellation configuration that is more conducive to satellite networking is also a hot issue. The polar orbit constellation is composed of several satellites with the same height and circular polar orbits, and the number of satellites in each orbital plane is the same, and the satellites are equally spaced in the orbital plane. Obviously, the polar orbit constellation is evenly distributed in the longitude dimension, but in the latitude dimension, the distribution of satellites becomes denser as the latitude increases. However, 79.4% of the global population...

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Application Information

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IPC IPC(8): H04B7/185H04W16/18H04W84/06
CPCH04B7/1851H04W16/18H04W84/06
Inventor 雷磊包翔李志林黄加红沈高青蔡圣所张莉涓
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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