Satellite group orbit design method for geostationary orbit satellite distributed co-orbital flight

A technology of geosynchronous orbit and design method, which is applied to space navigation equipment, aircraft, space navigation equipment, etc., and can solve problems such as difficult to meet the multi-satellite co-orbit configuration design of geosynchronous orbit satellite groups, scarcity of orbital resources, etc.

CN107450578AActive Publication Date: 2017-12-08AIR FORCE UNIV PLA
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
Publication Date
2017-12-08

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Abstract

The invention relates to a satellite group orbit design method for geostationary orbit satellite distributed co-orbital flight. The method includes the following steps that: the position relationship model of a reference satellite and orbiting satellites is built; an orbiting satellite orbit model is built through using the position relationship model; the number of orbiting satellite orbits is calculated according to orbiting satellite orbit requirements; and the number of orbiting satellite group orbits is generated according to the number of the orbiting satellite orbits. Relative distance fluctuations of the orbiting satellite group orbits designed by using the method of the present invention and the reference satellite is small; the azimuth angle, elevation angle and distance relationships of the orbiting satellites and the reference satellite meet multi-satellite co-orbital spacing design requirements; the azimuth angles, elevation angles and distances of adjacent orbiting satellites satisfy inter-satellite link acquisition and tracking design requirements; defects such as weak function, poor anti-interference ability, unfavorability to miniaturization of a single-satellite node condition can be eliminated; and the orbiting satellites and the reference satellite collaborate with each other, and therefore, the anti-destruction ability and self-organizing ability of a system are improved.
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Description

technical field

[0001] The invention relates to the technical field of spacecraft orbital dynamics and control, in particular to a satellite group orbit design method for distributed co-orbital flight around geosynchronous orbit satellites. Background technique

[0002] Multi-satellite co-orbit refers to a satellite system that is composed of multiple small satellites that are densely distributed in space and work in a coordinated manner to achieve a specific function. Due to the adoption of the multi-satellite collaborative working method, the multi-satellite co-orbit mechanism has obvious advantages in the following aspects: First, the tasks completed by a single satellite in the past are distributed to each satellite in the constellation to form a large "Virtual satellite" to complete the tasks completed by a single large satellite, greatly improving the survivability of the system; second, multiple small satellites work together to achieve more functions, such as coopera...

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Embodiment Construction

[0095] In order to make the purpose, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0096] The orbital element is a set of parameters used to describe the state of the satellite in its orbit, including the semi-major axis of the orbit a, the eccentricity e, the orbital inclination i, the right ascension of the ascending node Ω, the argument of perigee ω and the mean anomaly angle M, Expressed in vector form as:

[0097]

[0098] In the formula, the orbital semi-major axis a determines the size and orbital period of the satellite orbit, the eccentricity e determines the orbital shape, the orbital inclination i, the right ascension of the ascending node Ω and the argument of perigee ω characterize the spatial orientation of the satellite’s orbital plane, and The mean anomaly M represents the instantaneous position of the satelli...