• Current Industrial and Technological Trends in Aerospace
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• v.7 no.2
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• pp.59-67
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• 2009

Computer Aided Engineering(CAE) technology as well as Design(CAD) and Manufacturing(CAM) have been widely adopted in the aerospace industry in order to develop the structure of airplanes, satellites and launch vehicles. Among them, CAE softwares based on finite element methods such as NASTRAN, ABAQUS and ANSYS have gained many engineers' interest in various industries such as automobiles, civils, aircraft and spacecraft. The softwares usually consist of several modules: Static, Dynamic, Vibration, Impact etc. that make analysis specific to meet the design goals of the structure systems. Recent enhancement in the computer hardwares and numerical algorithms enables us to perform complex analysis like multi-physics, optimum design. Also, they make it possible to deal with a large scale problem easily. This paper reviews structural analysis softwares in aerospace industry and gives a summary on its recent development.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.147-150
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• 2005

Space launch vehicles mainly use the liquid-propellant propulsion system which has easy thrust control ability and high specific impulse for that the payload like satellite and spacecraft should be entered into exact orbit. However, the liquid-propellant propulsion system is very difficult to develop because it is more complicate than the solid rocket propulsion system and demands very high technology. In space launch vehicle developing procedure the system design level is very important thing to reduce cost, shorten schedule, and improve the performance. The system design process was introduced for selecting the best liquid-propellant propulsion system on this paper.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.65-71
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• 2005

Pyro-shock measurement system in launch vehicle is necessary to validate structural robustness and to prepare environmental qualification criteria for launch vehicle systems. This paper describes design, development and function test of prototype pyro-shock recorder to be employed on KSLV-I in the near future. Due to the limitation of telemetry transmission rate, pyro-shock recorder acquires and stores the shock sensor data with high sampling rate in short period and sends the data to the KSLV-I telemetry system with lower data rate. Signal conditioning in pyro-shock recorder is designed to enhance signal-to-noise ratio through proper placement of anti-aliasing filter.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.17 no.10 s.113
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• pp.993-999
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• 2006

This paper presents the design simulation, implementation, and measurement of a miniaturized DCS, PCS / Satellite DMB dual-band stacked chip antenna with double coupled line for mobile communication terminals. A stacked meander is realized by using a via hole with height of 0.8 mm and a diameter of 0.35 mm to connect upper- and lower-layer meander sections for a reduction of the dimensions of the antenna. In addition the stacked meander chip antenna is extended by a double coupled-line to achieve two different radiation modes. A ratio of the first frequency and second frequency vary with the geometrical parameter of coupled lines. The fabricated antenna used FR-4 substrate with relative permittivity of 4.2. And its dimensions are $15.2{\times}7{\times}0.8mm^3$. The measured impedance bandwidth(VSRW<2) are 244 and 120 MHz at the operating frequency, respectively.

• Journal of Advanced Navigation Technology
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• v.7 no.2
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• pp.101-107
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• 2003

In this study, we provide a single element log-periodic antenna that the feeding networks and array structures are aperture coupled and series dipole array type. We made the antenna for direct receiving the Moogoongwha satellite broadcasting signal. The transmission power was able to feed the patch dipole in series due to lay perpendicularly 8 series patch dipole on tapered slot. The patch dipole radiation pattern which fed in series power, make the main beam direction up $37^{\circ}{\sim}42^{\circ}$ within the BS/CS bandwidth. The main beam gain was measured 9.31~11.03 dBi. Using 32 elements to array the elements properly, we acquire $4{\times}8$ array structure on limited PCB board. As a result, it has been found that the new planar DBS antenna structure have high gain over 10dBi and acceptable elevation angle over 42 degree, and we can apply this result to commercial DBS reception antenna manufacturing.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.10
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• pp.867-875
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• 2018

Conventional nylon wire cutting-type holding and release mechanisms (HRMs) are limited to securely hold the solar panel under launch environment as the size of the panel increases because the nylon wire is tightened directly on the surface of the solar panel. In this study, we proposed a nylon wire cutting-type HRM for 6U CubeSat's solar panel applying elliptic-shaped bracket with a Ball & Socket interface. The proposed HRM has the advantage of higher holding capability along in-plane and out-of plane directions of solar panel and simplicity in tightening process of nylon wire. The design drivers of structural design of CubeSat's solar panel with the proposed HRM were defined by structural analysis under launch loads. In addition, The design effectiveness of the proposed HRM was verified through the functional tests according to the thickness of nylon wire and the number of wire winding under various temperature conditions.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.92-98
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• 2006

An 1 lbf of NASA standard monopropellant thruster, MRE-1, is used for KOMPSAT (Korea Multi-Purpose Satellite) which is launched in 2006 and provides reliable and cost-effective means for attitude and maneuvering control system. The monopropellant thruster obtains required thrust by thermal decomposition process of propellant through catalyst bed. During firing, the decomposition plays a role of a heat source that may occur an excessive radiation heat transfer to peripheral structures and electronics in relatively low temperature condition.Therefore, the radiation heat shield is needed to prevent the critical radiative heat exchange between thruster and satellite during firing. This paper summarizes an overall development process of radiation heat shield from the design engineering up to the manufacturing.

• Journal of Satellite, Information and Communications
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• v.12 no.1
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• pp.13-17
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• 2017

This paper presents an approach to enable a typical GPS receiver to be much less susceptible to intentional disruption such as jamming and change in link environment. In order for the GPS receiver to cope with jamming and to get adaptivity, a $4{\times}4$ beamforming antenna is designed using metamaterials. The design results show the antenna gain much higher than 5 dBi and the movable beam.

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.46 no.9
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• pp.52-59
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• 2009

In this paper, the planar waveguide slotted array antenna is presented, which has the 3-layered structure of feeding networks for a high gain. Due to the ionosphere which generates 'Faraday rotation', the skew is happened between the signal radiated from an artificial satellite and the receiving antenna. This causes a polarization loss. In this paper, to remove this polarization loss, the dumbbell shaped linear polarizer using a single layer film is proposed. The gain of proposed antenna is 29.4dB.

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.46 no.2
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• pp.126-133
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• 2009

In this paper, The planar waveguide slotted antenna is presented for a satellite communication of vehicles. In stead of the microstrip patch array antenna having a dielectric loss and a feeding loss, the proposed antenna has the 3-layered waveguide feeding network structure for assembling easily. Also this antenna can receive mechanically both RHCP and LHCP transmitted from a satellite using a polarizer made from a thin single layer film. The Gain of the proposed 4X8 array antenna is 27.5dB and the gain of 8X16 array antenna is 32dB.