KR20000039745A - Method for maintaining and regulating position to three satellites sharing identified stop track position - Google Patents

Abstract

PURPOSE: A method for maintaining and regulating a position is provided to maintain and regulate a position for only one satellite per day by minimizing the work amount of a ground control station while regulating the position for more than three satellites within +/- 0.05 range and avoiding a physical collision and electrical wave interference. CONSTITUTION: A position error of a satellite is analyzed through an error analysis(11) on the track determination of stop trace satellite, and an area is distributed by all kinds of parameters through the box distribution of position maintenance and regulation. A method to minimize the work amount of a ground control station is set up through setting up a target value for regulating a trace to the three satellites. Simulation is performed to the three satellites based on the method. When there is a problem, the setup of the target value is corrected for the trace regulation to the three satellites. On the other hand, when there is no problem, the method is applied to the real satellite.

Description

Positioning Adjustment Method for Three Co-ordinated Satellites

The present invention relates to an orbital position adjusting method for a geostationary orbit satellite used for communication / broadcasting.

Geostationary satellites are useful for communication and broadcasting because they are always in a certain direction for users on Earth. However, the geolocation of geostationary orbits is finite, so the number of satellites that can be located on geostationary orbits is limited. In order to solve this problem and improve the reliability of the satellite system, a method of providing communication / broadcasting service by placing two or more satellites in a single geostationary position has been proposed and used. When placing two or more satellites in one geostationary position, the technology must maintain the position between satellites so that two or more satellite signals are captured by one antenna on the ground without physical collision or radio wave interference between them. This is necessary. In ground control stations that control satellites, a series of tasks like this must be scheduled to optimize the personnel and equipment of the station. The orbital maintenance interval for geostationary satellites depends on the frequency used for communication / broadcasting. Satellites using C-band are within ± 0.1 degrees and satellites using Ku-band are within ± 0.05 degrees. It must be located. Currently, satellite systems that share two or more satellites in a single orbit maintain the position of the satellite within ± 0.1 degrees using C-band. In the case of Korea's Mugunghwa satellite, two satellites using Ku-band The position is maintained within ± 0.05 degrees.

Accordingly, the present invention minimizes the workload of the ground control station to one satellite per day while avoiding physical collisions and radio wave interference between the satellites while maintaining the positioning of three or more satellites using Ku-band within a range of ± 0.05 degrees. The purpose of the present invention is to provide a positioning control method for three co-ordinated geostationary satellites, which is performed only for positioning.

In order to achieve the above object, the present invention calculates the target position by presenting the position form between the satellites according to the number of satellites located in the same position, and the position of one satellite per day when performing the ground control accordingly It is characterized by presenting a control schedule so that adjustments can be made.

FIG. 1 shows that the three geostationary satellites to which the present invention is applied are maintained within a range of ± 0.05 degrees while minimizing the physical collision and radio interference between the satellites while minimizing the workload of the ground control station. Flow chart of a task for extracting various parameters for performing positioning maintenance.

2 shows the assignment of a positioning box for one satellite.

3 is a diagram for explaining a method for adjusting orbital eccentricity vectors for three satellites.

4 illustrates a method for adjusting orbital inclination vectors for three satellites.

5 is a diagram illustrating a daily plan for performing orbital adjustment in a ground control station.

Hereinafter, with reference to the accompanying drawings will be described in detail the present invention.

FIG. 1 shows that the three geostationary satellites to which the present invention is applied are maintained within ± 0.05 degrees while minimizing the physical collision and radio wave interference between the satellites while minimizing the workload of the ground control station for only one satellite per day. A flowchart of a task for extracting various parameters for performing position maintenance adjustment.

First, the error analysis 11 for the determination of the trajectory of the geostationary orbiting satellite is analyzed to determine how much the positional error of the satellite at any position is allocated, and the area according to various parameters is allocated through the positioning box adjustment 12. By setting a target value 13 for orbit adjustment for three satellites, a method of minimizing the workload of the ground control station is established. According to the established method, the simulation of three satellites is performed (14). According to the results of the simulation, the method is examined to determine whether the method is correct (15). If there is a problem in the method, the target value setting 13 for adjusting the orbits for the three satellites is corrected. (16)

FIG. 2 shows the allocation of the positioning box set in the positioning box assignment 12 of FIG.

An error 21 in orbit determination and orbital adjustment, a change amount 22 due to the perturbation force of the sun and the moon, a change amount 23 due to the orbital eccentricity, and a change amount 24 due to the earth's gravity field are allocated.

FIG. 3 is a method for adjusting orbital eccentricity vectors for three satellites performed in setting target values 13 for orbital adjustment of three satellites in FIG. 2, and shows target values of three satellites' eccentricity vectors. . The three eccentricity vectors rotate around the circumference for one year while maintaining the triangle as shown by reference numeral 31. The parameter of the eccentricity vector circle for the three satellites is the same as that of 32.

FIG. 4 is a method for adjusting orbital inclination vectors for three satellites performed in setting target values 13 for orbit adjustment for three satellites of FIG. As in the case, it is adjusted to keep the triangle (41).

FIG. 5 shows a daily plan 51 for performing orbital adjustment at the ground control station according to the orbital eccentricity vector adjustment circle and orbital tilt angle adjustment box for the three satellites established in FIGS. 3 and 4. The adjustment for the orbital eccentricity is carried out every 1 week, and the adjustment for the orbital tilt angle is performed every 2 weeks. In the operation of the ground control station, orbital adjustments should be made to one satellite per day for the days except Sunday.

The present invention described above can be variously substituted, modified and changed within the scope without departing from the technical spirit of the present invention for those skilled in the art to which the present invention pertains and the accompanying drawings. It is not limited to.

As described above, according to the present invention, physical collisions and radio wave interference can be avoided and the operation of the ground control center can be minimized in the position maintenance adjustment of three communication / broadcasting satellites on the same position geostationary track using Ku band. Excellent effect

Claims (4)

In the position maintenance for three co-ordinated orbit satellites, Calculate the target position by suggesting the position type between satellites according to the number of satellites located at the same location, and present the control schedule so that the position adjustment of one satellite can be performed per day when ground control is performed accordingly. Position maintenance method for the three co-ordinate geostationary satellite. The method of claim 1, The positional form of each of the satellites, the orbital eccentricity vector and the orbital inclination angle vector is arranged in a triangle, the orbit maintenance adjustment for the three satellites, characterized in that for performing the same date for three satellites How to maintain position. The method of claim 2, The orbital inclination angle vector maintains the center and the radius of the eccentricity vector circle while maintaining the position adjustment section within a range of ± 0.05 degrees. The method of claim 1, In order to minimize the work of the ground control station for the orbit maintenance adjustment for the satellite, orbital adjustment for the three satellites in the same position characterized in that the dividing is performed by dividing the week or unit every two weeks How to maintain position.