• Journal of Satellite, Information and Communications
• /
• v.5 no.2
• /
• pp.8-13
• /
• 2010

Satellite structure should be designed to accommodate and support safely the payload and equipments necessary for its own missions and to secure satellite and payloads from severe launch environments. The launch environments imposed on satellites are quasi-static accelerations, aerodynamic loads, acoustic loads and shock loads. Especially when optical payload is accommodated, satellite structure usually adopts the optical bench consisting of composite material not only to support and secure but also to guarantee good pointing stability against extreme thermal environments. This paper deals with optical bench and support structure which shall be designed to minimize the loads transferred to optical payloads from satellite.

• Journal of Satellite, Information and Communications
• /
• v.9 no.4
• /
• pp.42-46
• /
• 2014

In this paper, a coil typed electromagnetic band gap (EBG) structure to be inserted in the printed circuit board (PCB) inner layer in order to stabilize the PCB power line is proposed and implemented for global-navigation satellite service (GNSS) with the bandwidth from 1.55GHz to 1.81GHz. From the measurement result of the PCB board including EBG structure, the insertion loss(S21) was measured below about -50dB. From these results, it is expected that the stabilization of power delivery network (PDN) structure in the PCB circuit design should be improved and the preparation to EMI will be effective.

• International Journal of Aeronautical and Space Sciences
• /
• v.3 no.2
• /
• pp.40-45
• /
• 2002

A radiation analysis is performed for the Ka and Ku-band transponder of the Communications and Broadcasting Satellite (CBS) that is planned for launch into the geo-synchronous orbit. A particular attention is given to calculation of Total Ionizing Dose (TID) for the mission life time of 15 + 3 years. A numerical modeling of the charged particles at the geo-synchronous orbit is undertaken. The charged particles from the modeling are then transported through the mechanical structure and component housings of the transponder. A set of locations are selected for the detailed calculation of TID. The results from the present calculation show that three-dimensional modeling of the component housings as well as the mechanical structure of the spacecraft is requisite in order to acquire a reliable calculation of TID.

• Journal of Satellite, Information and Communications
• /
• v.5 no.1
• /
• pp.75-79
• /
• 2010

Satellite structure is distorted by thermal load in orbit. The structural distortion induces the pointing errors of observation unit that is difference between initial pointing direction at ground integration and at in-orbit. In that case, satellite is not able to point along required direction. As observation capability becomes higher, structural distortion due to thermal load should be smaller to achieve successful mission. In this paper, the method to predict pointing error and results are described.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.38 no.7
• /
• pp.727-736
• /
• 2010

A satellite that has an all-composite structure, STSAT-3(science and technology satellite), was initially developed in Korea. Partially use of advanced composites in space applications such as solar panel is well developed, however the application of an all-composite satellite bus has never been achieved in Korea. This study emphasizes the application of composite technology to the design and fabrication of an all-composite spacecraft bus for small-class satellite STSAT-3. Moreover its structure design concept is totally different from the one that was used in the previous satellites developed in Korea.

• Journal of Satellite, Information and Communications
• /
• v.2 no.1
• /
• pp.56-62
• /
• 2007

UWB(Ultra Wide Band) system can transmits information with low power but it can achieve high transmission rate using broad frequency bands. Using CR(Cognitive Radio) technology, we can use and share frequency efficiently without interfere to satellite communication system. However, passive characteristics of satellite receiver makes it hard to implement. This paper propose additional structure of satellite receiver which add amplifier and antenna to local oscillator. Proposing structure emits satellite receiver's local oscillator signal and UWB terminal detects it by energy detection. We can find out the possibility of co-existence of UWB system and satellite communication system through the simulation result.

• Journal of the Korean Society for Precision Engineering
• /
• v.30 no.11
• /
• pp.1203-1210
• /
• 2013

Korea's first Naro-Science small class satellite was launched by Naro launcher in 2013. The structure of the satellite is mostly composed of aluminum honeycomb and frame. The honeycomb structure is homogenized with asymptotic homogenization method and its mechanical properties were used for the numerical analysis. There have been some difficulties to modeling the honeycomb sandwich panels for FEA. In the present study, the mechanical characteristics of the sandwich panel composite were numerically computed and used for the simulation. This methodology makes it easy to overcome the weakness of modeling of complicated sandwich panels. Both an experiment of vibration test and numerical analyses were conducted simultaneously. The analysis results from the current homogenization were compared with that of experiment. It shows a good agreement on the dynamic responses and certified the reliability of the present methodology when manipulate sandwich panel structure.

• The Journal of Korean Institute of Communications and Information Sciences
• /
• v.37 no.7A
• /
• pp.552-559
• /
• 2012

In this paper, we introduce a frame structure of the satellite TDMA network and the synchronization method thereof. The primary station transmits a special burst called reference burst which provides reference time to network. By using this reference burst all nodes achieve initial acquisition and synchronization. We consider time drift due to the node and satellite mobility, time shift due to the node position, Doppler shift due to the node mobility and frequency offsets as important factors of the frame structure. Simulation results show that the proposed frame structure and synchronization method guarantee accurate synchronization performance when the node is even in low SNR as well as 25 kHz frequency offsets.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.37 no.9
• /
• pp.916-922
• /
• 2009

Because thermal design of satellite carrying out mission in space is performed by thermal analysis result using thermal mathematical model, accuracy of thermal mathematical model is important and it can be improved by model correlation. Correlation steps of satellite thermal math model are composed of modeling of satellite configuration placed in thermal vacuum chamber, verification of correspondence between thermal math model and real satellite configuration, and adjustment of modeling parameters from major part to minor part etc. In this study, correlation success criteria was established and correlation for satellite thermal math model was performed using result of thermal vacuum test of satellite structure-thermal model to meet the success criteria. The overall results satisfied the criteria and this correlated thermal model was applied for detailed thermal design of satellite.

• Proceedings of the Korean Society For Composite Materials Conference
• /
• 2002.10a
• /
• pp.1-4
• /
• 2002

The present study aims to design a multiplayer microstrip antenna with composite sandwich construction and to estimate structural behavior of this multiplayer structure for the next generation of structural surface technology. This is termed Surface-Antenna-Structure indicating that structural surface becomes antenna. Constituent materials were selected considering electrical properties as well as mechanical properties. For the antenna performance, antenna elements inserted into structural layers were designed for satellite communication at a resonant frequency of 12.5 GHz and final demonstration article was $16\times16$ array antenna. From electrical measurements it was shown that antenna performances were in good agreement with design requirements. Structural analysis showed this antenna structure was well designed for the mechanical rigidity. All constituent materials were characterized independently. The SAS concept is the first serious attempt at integration for both antenna and composite engineers and promises innovative future communication technology.