KR100237174B1 - Automization method of real time orbit determination and ground track display for the multiple satellite - Google Patents

Abstract

The present invention relates to a method for automating real-time trajectory determination and trajectory display for multiple satellites. The present invention relates to a method for displaying a satellite's past and future locations on a map with the orbit determined by trajectory determination with satellite tracking data. An automatic trajectory determination and trajectory marking method is proposed to minimize the human and physical resources required to control multiple satellites on the ground by automating the process of the process.

Description

Automated Real-time Orbital Determination and Trajectory Marking for Multiple Satellites

The present invention relates to an automated method of real-time orbit determination and trajectory display method of satellites in the field of satellite control technology, and in particular, human and physical resources for satellite control by automating the real-time orbit determination and real-time trajectory display process for a plurality of satellites. Real time trajectory determination and trajectory display automation method for a plurality of satellites to minimize the number of satellites.

In general, satellite orbits are obtained by conducting an orbiting process that collects and processes tracking data obtained by tracking satellites with ground antennas. The orbital determination method of the satellite can be divided into two methods in terms of time. One is trajectory determination by batch process method that collects tracking data one by one and processes them all at once, and the other is trajectory determination by sequential process method which processes tracking data one by one. Real-time trajectory determination is impossible because the orbital determination by batch processing method collects the data, but the orbital determination by the sequential processing method can obtain the tracking data for satellite and determine the orbit at that time. The decision can be made.

The trajectory representation of a satellite is a projection of the satellite's orbit on a world map or a map of a particular region, which tells us what point on earth the satellite has passed and over. The trajectory representation of the satellite is implemented by performing trajectory prediction for the initial trajectory value. The satellite display can be displayed in real time for satellite operation or in real time for satellite analysis.

Conventional satellite control method uses satellite tracking data to determine the trajectory of the satellite, separates the sequence of displaying the satellite's trajectory by using the determined orbital data as the initial trajectory without automating and separately by manpower of the control station. To be performed. This method could be performed without any burden on human resources and physical resources of satellite control station for orbit determination and trajectory marking for one satellite. However, when the number of satellites increases, more manpower and equipment of more control stations have to be put in place. Control of satellites could be performed.

Therefore, the present invention automates the process of trajectory determination and trajectory display for satellites, so that even in the control of a large number of satellites, it is possible to determine trajectories and display trajectories in real time with limited human and physical resources. Its purpose is.

The present invention for achieving the above object is the first step of entering the standby state after initializing the system by reading the initial trajectory data, and the second step of checking whether new tracking data or system stop command is input in the standby state; A third step of confirming whether or not the tracking data is a system stop command if the result of the check is; and after performing the tracking data or trajectory prediction of the check result, displaying the trajectory on the world map and returning to the standby state of the second step. In the fourth step and the third step, in the third step, the observation data of the tracking data is modeled, the observations of the tracking data for the orbit prediction are calculated, the difference between the observations and the calculated values is calculated, and the Kalman filtering process is performed. A fifth step of generating new trajectory data after the operation; and the newly generated in the fifth step The sixth step of returning to the standby state of the second stage after the trajectory prediction is performed by the operation orbit data, the trajectory is displayed on the world map, and the system stop command is input in the standby state of the second stage. And a seventh step of ending the track display according to the present invention.

1 is a configuration diagram of a satellite control system to which the present invention is applied.

2 is a conceptual diagram illustrating a method for automating real-time trajectory determination and trajectory display for a plurality of satellites to which the present invention is applied.

3 is a flowchart of a method for automating real-time trajectory determination and trajectory display for a plurality of satellites according to the present invention.

4 is a conceptual diagram showing a trajectory display on a world map for a plurality of satellites to which the present invention is applied;

<Description of the symbols for the main parts of the drawings>

11: Satellite mission analysis and planning subsystem 12: Orbital and attitude dynamics processor

13: Mission Planning Department 14: Antenna

15: antenna subsystem 16: LAN

17: Image Processing Subsystem 18: Satellite Operation Subsystem

19: Satellite Simulator Subsystem

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

1 is a configuration diagram of a satellite control system to which the present invention is applied, and a satellite mission analysis and planning sub-system 11 includes an orbital and attitude dynamics processing unit 12 and a user for enabling a satellite to properly perform a given mission. It consists of a mission planning unit 13 for planning the mission of the satellite at the request of. The orbital and attitude dynamics processing unit 12 is a local area network (16) based on a satellite tracking antenna and the data related to the orbits and attitudes of the satellite from the tracking data received from the antenna sub-system 15 through the satellite tracking antenna 14 ), Satellite control data and antenna control data are generated by orbit determination, trajectory prediction, trajectory display, and attitude determination. The satellite control data and the antenna control data are provided to the antenna subsystem 15 through the local area network 16 together with the data planned by the mission planning unit 13. In addition, the orbital and attitude dynamics processing unit 12 generates orbits and attitude data of the satellites necessary for processing the image data transmitted from the satellites, and the generated data is transmitted through the local area network 16 to the image processing sub-system ( 17) is provided. The satellite operation sub-system 18 is a place where the state of the satellite is checked and the necessary commands are generated for the low-orbit satellite, and the satellite simulator sub-system 19 for checking the operation procedure prior to the actual satellite control is also performed. It is part of the satellite control system.

2 is a conceptual diagram illustrating a method of automating real-time trajectory determination and trajectory display for a plurality of satellites to which the present invention is applied.

The system controller 21 is responsible for real-time trajectory determination and control of the entire trajectory display automation system, and reads the initial trajectory data 22 at system startup to initialize the system and determines the trajectory data when the trace data is input (23). It sends to section 25 to determine a new trajectory and stops the entire system when the system stop command 24 is entered. In addition, the system control unit 21 has a timer and activates the trajectory prediction unit 26 when the tracking data 23 or the system stop command 24 are not input for a predetermined time. The orbit determiner 25 and the orbit predictor 26 have N programs to perform orbit determination and orbit prediction for each satellite, so that orbit determination and orbit prediction for a plurality of satellites are possible. When the new tracking data is input, the trajectory determination unit 25 generates a new trajectory parameter by performing real-time trajectory determination using a Kalman filter. The trajectory predicting unit 26 has a function of calculating trajectories for each time by predicting the trajectory for a predetermined period with the trajectory parameter. The trajectory predictor 26 is driven by the trajectory determiner 25 or the system controller 21, and when driven by the trajectory determiner 25, the trajectory predictor 26 uses the new trajectory parameters generated by the trajectory determiner 25. When driven by the controller 21, the trajectory is predicted using the trajectory parameters determined in the past. Each time trajectory calculated by the trajectory predictor 26 is displayed on the world map by the trajectory display unit 27. At this time, the trajectory of the past and the future is displayed based on the present time, and the position of the satellite with respect to the present time is displayed in the shape of satellite. The trajectory display unit 27 can display satellite parameters and trajectories for satellites 1 to N inputted from the orbit predictor 26. After the satellite trajectory is displayed on the trajectory display unit 27, the timer goes to the system control unit 21 and the timer is operated and waits for the tracking data 23 or the system stop command 24.

3 is a flowchart of a method for automating real-time trajectory determination and trajectory display for a plurality of satellites to which the present invention is applied.

When the system starts, it reads the initial trajectory data (31) and initializes the system (32). At this time, it initializes with respect to how many satellites the system will operate and what identification number each satellite will have. The trajectory is predicted (31) to produce a trajectory about the current time. The trajectory data generated through the orbit prediction 31 is displayed 33 on the world map to indicate the position of the current satellite and the satellite trajectories of the past and the future. After that, the timer enters an activated standby state (33) and waits for a new trace data or system stop command (34) for a certain period of time. When the system stop command 34 is input during the standby state, it is determined (35) and the system is stopped. When a new tracking data is input, the system is determined (36) and the Kalman filter begins with observation modeling (39) for the tracking data. Real-time trajectory determination is performed. If there is no input during the standby state (33) (35), the system goes to the orbit prediction (37) state and predicts the orbit with the orbital data of the past (37) to display the trajectory on the world map (38). . The initial orbital data for several satellites is input (31) to automate trajectory determination and trajectory display during standby (33). When new tracking data is input (36), a real-time trajectory determination process is performed by Kalman filter, which includes observation modeling of tracking data (39), calculation of tracking data by track prediction (40), and differences between observations and calculations. New orbital data is generated through the process of calculation 41 and Kalman filtering 42 (43). When a new orbital data is generated, the orbital prediction 37 is performed with this, and the trajectory of the satellite is displayed on the world map (38). The system then enters a standby state and waits for new tracking data or a system stop command 35 for a period of time. The entire system automates the real-time trajectory determination and trajectory display process by repeating the above process.

4 is a conceptual diagram illustrating a trajectory display on a world map of a plurality of satellites to which the present invention is applied.

The location of the satellites for the current time is indicated by the name of the satellite or the satellite icon, respectively (51) and the satellite coverage at this time is indicated (52). In the trajectory of the satellite, the trajectory indication 53 of the past state where the tracking data is processed and the predicted trajectory indication 54 when the tracking data is not processed are displayed differently so that the user can easily know the processing state of the tracking data. Do it. Selecting the displayed satellite icon or name displays various parameters for the satellite (55), allowing the user to easily obtain satellite information immediately.

As described above, according to the present invention, a plurality of satellites are grounded by automating a series of processes of displaying the satellite's past position and future position on a map with the determined orbit by making orbit determination in real time with the tracking data of the satellite. There is an excellent effect of drastically reducing the human and physical resources required to control the system.

Claims (1)

The first step of initializing the system by reading the initial orbital data and then entering the standby state; A second step of checking whether a new trace data or a system stop command is input in the standby state; A third step of confirming whether or not the trace data is the system stop command if the check result; A fourth step of returning to the standby state of the second step after performing tracking data or orbit prediction of the verification result and displaying a trajectory mark on a world map; In the third step, if the confirmation data is the tracking data, model the observations for the tracking data, calculate the observations of the tracking data for the orbital prediction, calculate the difference between the observations and the calculations, and perform the Kalman filtering process. A fifth step of generating orbital data; A sixth step of returning to the standby state of the second step after displaying the trajectory on the world map after predicting the orbit using the new orbital data generated in the fifth step; And a seventh step of terminating the track display according to the trajectory prediction when the system stop command is input in the standby state of the second step.

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