• Bulletin of the Korean Space Science Society
• /
• 2006.10a
• /
• pp.113-113
• /
• 2006

• Bulletin of the Korean Space Science Society
• /
• 2006.10a
• /
• pp.144-144
• /
• 2006

• The Transactions of The Korean Institute of Electrical Engineers
• /
• v.57 no.7
• /
• pp.1285-1289
• /
• 2008

In this paper, we design COMS system bus that the 1553 Data Bus is able to link all the units of the satellite managed by the SCU using one Prime Data Bus and on Redundant Data Bus. Also we analyze MIL-STD-1553B bus load and relevant exchange memory budgets in system bus of the COMS satellite. This data is used in the satellite mission and software design by system engineer.

• Bulletin of the Korean Space Science Society
• /
• 2006.10a
• /
• pp.145-145
• /
• 2006

• Proceedings of the KIEE Conference
• /
• 2009.07a
• /
• pp.1013_1014
• /
• 2009

In this paper, the electrical interfaces used in between COMS satellite bus and Ka-band communication payload are analyzed to verify the robustness of data bus. The purpose of the serial data bus of satellite is to allow serial data transfer between one bus controller or source equipment to several user terminals or slave equipments. A serial data bus in COMS satellite is mainly used for Channel Amplifier and Digital Control Unit of Ka-band Payload.

• 제어로봇시스템학회:학술대회논문집
• /
• 1989.10a
• /
• pp.71-75
• /
• 1989

Structural analysis of a satellite bus is carried out by using a finite element program NISA II. It is assumed that the bus is composed of bars, plates and shells made of CFRP composite materials and aluminum alloys. Displacements and stresses are calculated as static analysis under accelerated motion and frequencies and mode shapes are computed as dynamic analysis.

• Proceedings of the KSRS Conference
• /
• 2005.10a
• /
• pp.637-640
• /
• 2005

In the development of a electronic system for a optical payload comprising mainly EOS(Electro-Optical Sub-system) and PDTS(Payload Data Transmission Sub-system), many aspects should be investigated and discussed for the easy implementation, for th e higher reliability of operation and for the effective ness in cost, size and weight as well as for the secure interface with components of a satellite bus, etc. As important aspects the interfaces between a satellite bus and a payload, and some design features of the CEU(Camera Electronics Unit) inside the payload are described in this paper. Interfaces between a satellite bus and a payload depend considerably on whether t he payload carries the PMU(Payload Management Un it), which functions as main controller of the Payload, or not. With the PMU inside the payload, EOS and PDTS control is performed through the PMU keep ing the least interfaces of control signals and primary power lines, while the EOS and PDTS control is performed directly by the satellite bus components using relatively many control signals when no PMU exists inside the payload. For the CEU design the output channel configurations of panchromatic and multi-spectral bands including the video image data inter face between EOS and PDTS are described conceptually. The timing information control which is also important and necessary to interpret the received image data is described.

• Aerospace Engineering and Technology
• /
• v.11 no.2
• /
• pp.33-38
• /
• 2012

A LEO Satellite performs automatic initial operations by FSW after separation from a launch vehicle. After initial operation by FSW is finished, preparation for normal operation is performed by ground during bus initial activation and checkout phase. First of all, we check state of health of the satellite including solar array deployment status. After then, each unit of spacecraft bus is activated and checked. After activation and checkout of every units used for normal operation, we check maneuver performance for imaging mission and orbit maintenance performance. Because the Bus IAC is performed during limited ground contact time, every detailed procedure must be designed considering ground contact. Therefore, the Bus IAC procedure is separated into several parts based on ground contact duration. In addition, the procedures for every possible operation including expected situation as results of IAC procedures and unexpected contingency situation must be prepared. The contingency operation is also designed based on ground contact duration. The LEO satellite was successfully launched and the Bus IAC was successfully performed. In this paper, we explain design concepts and execution results of Bus IAC.

• Journal of Aerospace System Engineering
• /
• v.11 no.6
• /
• pp.76-83
• /
• 2017

The MIL-STD-1553 standard has been used for over 40 years as a data bus technology for high-reliability mobile systems. However, 1 Mbps transmission speed is absolutely insufficient to implement sensor data convergence, which is an essential requirement of modern aerospace systems. In this paper, we analyze the hierarchical structure of the MIL-STD-1553B version specification and describe several methods to increase the transmission speed without losing the advantages of the existing MIL-STD-1553 bus. In addition, we analyzed the R & D cases of the high-speed MIL-STD-1553 technology, which have been conducted in leading aerospace countries.

• Proceedings of the KIPE Conference
• /
• 2004.11a
• /
• pp.85-89
• /
• 2004

This paper presents Power Control and Distribution Unit development of GEO satellite with 3kW power output. The sensing error of bus voltage produce control signal of the shunt switch assembly and battery power converter, and the tolerance of error signals generated decide the stability of proposed system. The dynamic characteristics of main bus according to the load changing and the control logic of FPGA are simulated. In order to verify the proposed design, the simulation and experimental results for solar array shunt switch, battery power converter and bus controller are shown.