Apparatus and method for controlling geostationary orbit satellite

• US 9,399,527 B2
• Filed: 06/07/2013
• Issued: 07/26/2016
• Est. Priority Date: 06/07/2012
• Status: Active Grant

• Current Assignee: Electronics and Telecommunications Research Institute
• Original Assignee: Electronics and Telecommunications Research Institute
• Inventors: Lee, Byoung Sun, Hwang, Yoo La
• Primary Examiner(s): Nguyen, Nga X
• Application Number:
  US13/913,005
• Publication Number:
  US 20130327893A1
• Time in Patent Office: 1,145 Days
• Field of Search: 244/158.8, 2441584-1586
• US Class Current: 1/1
• CPC Class Codes: B64G 1/1007 Communications satellites
• CPC Class Codes: B64G 1/24 Guiding or controlling apparatus, e.g. for attitude control
• CPC Class Codes: B64G 1/242 Orbits and trajectories
• CPC Class Codes: B64G 1/2425 Geosynchronous orbits
• CPC Class Codes: B64G 1/2427 Transfer orbits
• CPC Class Codes: B64G 1/52 Protection, safety or emergency devices; Survival aids

Abstract

An apparatus and method for controlling a geostationary orbit satellite is provided. The method including generating remote measurement data by measuring a state of a geostationary orbit satellite, transmitting the remote measurement data, receiving a remote command signal, and controlling an orbit and a pose of the geostationary orbit satellite relative to inclined geosynchronous space debris.

Claims

1. An apparatus for controlling a geostationary orbit satellite, the apparatus comprising:

a data processing unit to generate remote measurement data by measuring a state of a geostationary orbit satellite;

a signal transmitting/receiving unit to receive a remote command signal and to transmit the remote measurement data; and

a satellite control unit to control an orbit and a pose of the geostationary orbit satellite relative to inclined geosynchronous space debris,

wherein the geostationary orbit satellite is maintained at a predetermined safe distance from the inclined geosynchronous space debris when the inclined geosynchronous pace debris passes through an equatorial plane of earth,

wherein the satellite control unit controls a radial separation between the geostationary orbit satellite and the inclined geosynchronous space debris to maintain the predetermined safe distance for collision avoidance when the inclined geosynchronous space debris passes through the equatorial plane of the Earth, and

wherein the satellite control unit adjusts a velocity of the geostationary orbit satellite to maintain the predetermined safe distance for collision avoidance between the geostationary orbit satellite and the inclined geosynchronous space debris.

2. The apparatus of claim 1, wherein the data processing unit converts the remote measurement signal to control command data for the geostationary orbit satellite, and transmits the control command data to the satellite control unit.

3. The apparatus of claim 1, further comprising:

a power supply unit to supply power to the geostationary orbit satellite by controlling the satellite control unit.

4. The apparatus of claim 1, further comprising:

a satellite propulsion unit to control the orbit and the pose of the geostationary orbit satellite by controlling the satellite control unit.

5. The apparatus of claim 1, wherein the satellite control unit comprises:

a detection unit to detect an orbital element of the inclined geosynchronous space debris; and

a determination unit to determine, based on the detected orbital element, a time and a direction of an orbital maneuver of the geostationary orbit satellite being performed.

6. The apparatus of claim 5, wherein the satellite control unit further comprises:

a distance output unit to output a closest approach distance between the geostationary orbit satellite and the inclined geosynchronous space debris after performing the orbital maneuver of the geostationary orbit satellite.

7. The apparatus of claim 5, wherein the detection unit detects a perigee location of the inclined geosynchronous space debris.

8. A method of controlling a geostationary orbit satellite, the method comprising:

generating remote measurement data by a data processing unit by measuring a state of a geostationary orbit satellite;

transmitting the remote measurement data by a signal transmitting/receiving unit;

receiving a remote command signal by the signal transmitting/receiving unit; and

controlling an orbit and a pose of the geostationary orbit satellite relative to inclined geosynchronous space debris by a satellite control unit,

wherein the satellite control unit maintains the geostationary orbit satellite at a predetermined safe distance from the inclined geosynchronous space debris when the inclined geosynchronous pace debris passes through an equatorial plane of earth,

wherein controlling an orbit comprise controlling a radial separation between the geostationary orbit satellite and the inclined geosynchronous space debris by the satellite control unit to maintain the predetermined safe distance for collision avoidance when the inclined geosynchronous space debris passes through the equatorial plane of the Earth, and

wherein the satellite control unit adjusts a velocity of the geostationary orbit satellite to maintain the predetermined safe distance for collision avoidance between the geostationary orbit satellite and the inclined geosynchronous space debris.

9. The method of claim 8, further comprising:

detecting an orbital element of the inclined geosynchronous space debris by a detection unit; and

determining by a determination unit, based on the detected orbital element, a time and a direction of an orbital maneuver of the geostationary orbit satellite being performed.

10. The method of claim 9, further comprising:

outputting by a distance output unit a closest approach distance between the geostationary orbit satellite and the inclined geosynchronous space debris after performing the orbital maneuver of the geostationary orbit satellite.

11. The method of claim 9, wherein the detecting of the orbital element comprises detecting a perigee location of the inclined geosynchronous space debris.

12. The method of claim 8, further comprising:

adjusting a velocity of the geostationary orbit satellite by the satellite unit to maintain the predetermined safe distance for collision avoidance between the geostationary orbit satellite and the inclined geosynchronous space debris.