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A Method for Determining Semi-major Axis of Equatorial Orbit for Timed Return of Subsatellite Point

A technology of equatorial orbit and sub-satellite point is applied in the field of semi-major axis determination of equatorial orbit. Effect

Active Publication Date: 2021-08-10
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

Although some patents proposed the height of the return orbit, they did not propose a specific return orbit design method, and it was not designed according to the illumination conditions of the ground imaging of the remote sensing satellite, and it was impossible to return to the same place in the same area in different days

Method used

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  • A Method for Determining Semi-major Axis of Equatorial Orbit for Timed Return of Subsatellite Point
  • A Method for Determining Semi-major Axis of Equatorial Orbit for Timed Return of Subsatellite Point
  • A Method for Determining Semi-major Axis of Equatorial Orbit for Timed Return of Subsatellite Point

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Embodiment

[0043] The present invention includes the design of the prograde equatorial regression orbit with an inclination of 0° and the retrograde equatorial regression orbit with an inclination of 180°.

[0044] 1. Definition of orbital period

[0045] One of the characteristics of equatorial orbit satellites is that the track of the sub-satellite point strictly coincides with the equator, and can realize the return of the sub-satellite point at a fixed time, which is difficult for other satellites whose orbital plane does not coincide with the equatorial plane. But this also raises the question of the definition of "orbital period".

[0046] Generally, under the influence of perturbation, the actual orbit of the satellite is not closed, and the definitions of the orbital period are as follows:

[0047] (1) Kepler period T 0 : That is, the period determined by the satellite's instantaneous semi-major axis a(t).

[0048]

[0049] The average orbital motion of the Kepler period is...

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Abstract

A method for determining the semi-major axis of the equatorial orbit of a sub-satellite point regular return, comprising: 1) selecting the forward and retrograde motion of the equatorial circular orbit; 2) selecting the return times of the satellite in a single day, and calculating the sub-satellite point return cycle hours N according to the formula; 3 ) Calculate the return period of the satellite in the inertial space according to the number of hours N of the return period of the sub-satellite point; 4) Calculate the semi-major axis corresponding to the prograde and retrograde equatorial return orbits according to the return period of the inertial space. The invention proposes a concept of an equatorial orbit capable of realizing sub-satellite point return at multiple specific times each day, and provides a method for determining the semi-major axis of the equatorial orbit. Equatorial satellites based on this orbit can realize hour-level revisiting of any region in the middle and low latitudes by a single satellite, and realize regular revisiting of the region multiple times a day.

Description

technical field [0001] The invention relates to a method for determining the semi-major axis of an equatorial orbit for timing regression of sub-satellite points, and belongs to the field of spacecraft orbit design. It is suitable for remote sensing satellites with medium and low latitude ground fast revisit requirements, and communication and navigation enhancement satellites. Background technique [0002] Remote sensing satellites are an important part of artificial earth satellites, and have played an irreplaceable role in natural resource supervision and investigation, ecological environment monitoring, agriculture and rural areas, meteorology, disaster prevention and mitigation, and emergency rescue. At present, remote sensing satellites mainly operate in sun-synchronous orbits, which are generally retrograde circular orbits with an inclination of about 97°-99° and a height of no more than 6000km. Through orbit design, the orbit of sub-satellite points can be returned w...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/02G06F17/10
CPCG01C21/02G06F17/10
Inventor 白宇辰白照广尹欢朱军高涵
Owner AEROSPACE DONGFANGHONG SATELLITE
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