Sub-satellite point circular geosynchronous orbit design method

Abstract

Disclosed is a sub-satellite point circular geosynchronous orbit design method. The method includes: (1) analyzing and determining sub-satellite point circular geosynchronous orbit generating conditions including that (1.1) an orbital semi-major axis is 42164km, (1.2) a satellite drifts back and forth in the north-south direction every day, (1.3) the satellite drifts back and forth in the east-west direction every day, (1.4) the distance of north-south direction drift is equal to that of east-west direction drift, and (1.5) the satellite passes the equator twice every day with relative distance of sub-satellite points when the satellite passes the equator twice equal to east-west direction drift distance of the satellite; (2) according to the conditions in the step (1), determining orbital parameters, satisfying the five conditions at the same time, namely the orbital semi-major axis a, eccentricity ratio e, inclination angle i, right ascension of ascending node Omega, argument of perigee omega and true anomaly theta. Design of a sub-satellite point circular geosynchronous orbit is completed by utilizing the determined orbital parameters.

Description

technical field

[0001] The invention relates to a method for designing an orbit of an artificial earth satellite, which is suitable for the orbit parameter design of a geosynchronous orbit whose sub-satellite point trajectory presents a circle. Background technique

[0002] The geosynchronous orbit refers to the satellite orbit in which the satellites in orbit run from west to east, and the orbit period is synchronized with the earth's rotation period. The time for a satellite to operate in this orbit is one cycle of the earth's rotation. The period of the earth's rotation is 1 sidereal day, that is, the time interval between the vernal equinox passing through the upper meridian of the same meridian of the earth twice, and the duration of 1 sidereal day is 23h56min4.1s (86164.1s). Obviously, to form a geosynchronous orbit, the orbital period should also be 23h56min4.1s, and the semi-major axis of the geosynchronous orbit can be calculated from the orbital period to be 42164k...

Examples

Embodiment

[0093] The present invention aims at the geosynchronous orbit whose sub-satellite point circle center is located at 100° east longitude and the circle radius is 1500km, respectively provides the design method and result of each orbit parameter according to the steps, and draws the trajectory. Then according to this specific design method, calculate the corresponding orbit parameter values ​​as the radius of the circle track changes from 500km to 9000km, and draw the trajectory. details as follows:

[0094] (1) Orbital semi-major axis a

[0095] Since the orbit is a geosynchronous orbit, the semi-major axis a of the orbit is selected as 42164km.

[0096] (2) Orbit inclination i

[0097] The radius Rcircle of the sub-satellite point is 1500km, and the radius RE of the earth's equator is 6378.137km. According to (Formula 1), the value of the orbital inclination i is 13.47°.

[0098] (3) Argument of perigee ω

[0099] According to the above analysis, the argument of perigee ω ...

technical field

[0001] The invention relates to a method for designing an orbit of an artificial earth satellite, which is suitable for the orbit parameter design of a geosynchronous orbit whose sub-satellite point trajectory presents a circle. Background technique

[0002] The geosynchronous orbit refers to the satellite orbit in which the satellites in orbit run from west to east, and the orbit period is synchronized with the earth's rotation period. The time for a satellite to operate in this orbit is one cycle of the earth's rotation. The period of the earth's rotation is 1 sidereal day, that is, the time interval between the vernal equinox passing through the upper meridian of the same meridian of the earth twice, and the duration of 1 sidereal day is 23h56min4.1s (86164.1s). Obviously, to form a geosynchronous orbit, the orbital period should also be 23h56min4.1s, and the semi-major axis of the geosynchronous orbit can be calculated from the orbital period to be 42164k...

Examples

Embodiment

[0093] The present invention aims at the geosynchronous orbit whose sub-satellite point circle center is located at 100° east longitude and the circle radius is 1500km, respectively provides the design method and result of each orbit parameter according to the steps, and draws the trajectory. Then according to this specific design method, calculate the corresponding orbit parameter values ​​as the radius of the circle track changes from 500km to 9000km, and draw the trajectory. details as follows:

[0094] (1) Orbital semi-major axis a

[0095] Since the orbit is a geosynchronous orbit, the semi-major axis a of the orbit is selected as 42164km.

[0096] (2) Orbit inclination i

[0097] The radius Rcircle of the sub-satellite point is 1500km, and the radius RE of the earth's equator is 6378.137km. According to (Formula 1), the value of the orbital inclination i is 13.47°.

[0098] (3) Argument of perigee ω

[0099] According to the above analysis, the argument of perigee ω ...

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