In Jun Kim

Preliminary design for satellite mission operation from mission request to command planning

Communication, ocean, and meteorological satellite (COMS) is a geostationary satellite system which performs multi-mission such as communications services, ocean data acquisition, and meteorological data acquisition. Each mission is operated by different users, but it is the COMS satellite ground control system (SGCS) that practically controls all missions at an end. Therefore, all requests for performing the COMS mission have to be collected into COMS SGCS, and then the gathered mission requests shall be converted into the command to be transmitted to satellite after scheduling the requested mission in an optimal schedule. This paper introduces mission planning system and process which gathers mission requests, performs interactive mission scheduling, and generates command plan in order to carry out the various satellite missions of the COMS. First of all, we will see the system configuration and developing environment for mission planning. This paper will describe the main functions such as mission request gathering, mission scheduling, mission timeline reporting, and command planning. It deals with the role and design of each function in detail, and finally represents the operation concept to have the operator perform the mission planning efficiently when the COMS will be on orbit later on

Design and prototyping of high availability architecture for satellite ground control system

A satellite ground control system (SGCS) that monitors and controls a geostationary satellite 24 hours a day has to achieve the distributed architecture assuring high-level availability. The SGCS for communication, ocean, and meteorological satellite (COMS) is currently being developed in Korea, which is implemented to satisfy high availability, expansibility, and compatibility in design. In order to implement the system architecture to meet these characteristics, this paper introduces the concept of the real-time distributed system structure based on fault detection and recovery, data replication and sharing using CORBA middleware and redundancy scheme. This paper also describes down-sized hardware and software configuration to perform the mission operation of geostationary satellite, and the prototyped services for 24-hour operation SGCS assuring high availability is presented in detail

Architecture design of ground telecommand encryption function for spacecraft

The status of equipment which comprises a satellite should be controlled and monitored to operate the satellite and accomplish its mission. A satellite which performs the missions such as imaging of the specific target areas should continue to send the satellite command to shoot for targets. A communication satellite has to be commanded to configure a communications payload. Therefore normal satellite operation will be achieved through mutual communication between the satellite and its satellite ground control system. However, if any person with malicious intent sends commands which the operator does not recognize, or even by accident, any person without permission transmits commands, it can be a fatal problem and in worst case, could cause loss of the satellite [1][2][3]. Thus, the encryption system for telecommand has to be adopted to prevent a situation that the satellite has an impact due to abnormal commands [1]. This paper describes the ground TeleCommand Encryption Function (hereafter TCEF) implemented for the security of a satellite and the ROS developed for the operation of it, and presents the architectural design of the encryption key management and the encryption function. We also explain how they interface with each other.

Development of the Satellite Ground Control System for Multi-mission Geostationary Satellite COMS

A multi-mission GEO satellite, COMS has three payloads including Ka-band communications, GOCI, and MI. COMS SGCS is the only system for monitor and control of the satellite in orbit. In order to fulfill the mission operations of the three payloads and spacecraft bus, COMS SGCS performs the following functions such as reception and processing of telemetry data via S-band link, planning and transmission of telecommand, tracking and ranging of the satellite, control and monitoring of SGCS equipment, analysis and simulation of the satellite, processing and analysis of flight dynamics data, and mission scheduling and reporting. By the proper functional allocations, COMS SGCS is divided into five subsystems such as TTC, ROS, MPS, FDS, and CSS. COMS SGCS is linked with MSC, KOSC, and IDACS for satellite related data exchange. The software in the COMS SGCS is designed using the object-oriented methodology and implemented using Microsoft C# .NET environment on Intel microprocessor based computers. The hardware in the COMS SGCS includes 13-m S-band mono-pulse Cassegrain antenna and RF/BB equipment. In this paper, development of the COMS SGCS is described with respect to system functional allocations, software and hardware design, system implementation, and system test.