• Proceedings of the Korean Society of Broadcast Engineers Conference
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• 2008.02a
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• pp.69-72
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• 2008

최근 PKI-less 공개키 암호 시스템에 대한 연구가 진척되면서, 페어링(Pairing) 기반의 암호 시스템이 주목을 받고 있다. 페어링 기반의 암호 시스템은 두 개의 타원 곡선 상의 점을 유한체의 값으로 보내는 양방향 선형성(Bilinearity)을 가지는 페어링 함수를 기반으로 구성되는 암호 시스템이다. 페어링 기반의 암호 시스템 구현을 위해서는 페어링 연산 알고리즘이 필수적이며, 효율적인 페어링 연산을 위한 많은 연구가 진행되고 있다. 이러한 페어링 알고리즘에도 기존의 타원곡선 스칼라곱 알고리즘에서 야기되었던 부채널 공격이 동일하게 적용되기 때문에, 안전한 페어링 알고리즘을 위해서는 부채널 공격에 대한 저항성을 갖는 알고리즘이 필요하다. 이에 본 논문에서는 부채널 공격에도 안전하면서 비교적 효율적인 이진 필드 상의 페어링 알고리즘을 제시한다. 본 페어링 알고리즘은 기존의 부체널 공격 저항성을 갖는 페어링 알고리즘 중 가장 효율적인 알고리즘에 비해 효율성이 17% 정도 향상되었다.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.34 no.1A
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• pp.12-17
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• 2009

We consider an OFDM based multiple AF relaying systems. Since the channel between first hop (source station-relay station) and second hop (relay station -destination station) varies independently, the subcarrier in the first hop can be paired to another subcarrier in the second hop for the increase of the system capacity. The conventional pairing which uses the brute force searching requires large complexity while giving optimal pairing for maximum system capacity. In this paper, we present sub-optimal subcarrier pairing scheme with low complexity. Every RS firstly pairs the subcarrier with the highest channel gain in the first hop to the subcarrier with highest channel gain in the second hop. The pair with the highest SNR among all the pairs is determined as final selected pair and the corresponding subcarriers are not selected at other RSs in the next paring iteration. This process is repeated until all the subcarriers are paired. Simulation results show the proposed pairing scheme achieves near optimal performance with low complexity.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.4
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• pp.289-296
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• 2011

In this study, fairing configurations for an aircraft are designed and the aerodynamic analyses of the fairings are performed to find the best choice for the aircraft. Fairings considered are wing-tip fairing and wing-body fairing. Wing alone analyses are done for the wing-tip faring selection, while wing-body-tail analyses are done for the wing-body fairing selection. A 3-D RANS solver with Menter's ${\kappa}-{\omega}$ SST turbulence model are used for the aerodynamic analyses. The effects on the drag of the aircraft are examined by comparing the analysis results with and without the farings.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.6
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• pp.76-82
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• 2005

Cable fairings of guided missiles are generally used for protection of electric cables under aerodynamic heating and mechanical loading. The stress distributions between a cable fairing and missile main body along a cable fairing are necessary for its design. In this paper, a method for bonding stress and strength analysis of a cable fairing has been investigated and its computer program developed. Tensile and three-point bending tests of generally used bonding materials were also conducted to supply basic material properties for design of cable fairings.

• Journal of Aerospace System Engineering
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• v.16 no.6
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• pp.64-73
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• 2022

This study aimed to design a 3D fairing shape to reduce the air resistance of commercial vehicles. Rankine Half Body was applied to design the fairing shape, and the design was verified through aerodynamic analysis. Aerodynamic loads were calculated considering the speed conditions of commercial vehicles and gust conditions to ensure the structural safety of the fairing. A glass fibre/epoxy composite material was used to design a fairing structure that satisfied the safety factor 3. The structural safety of the lightest fairing was confirmed through structural analysis.

• Proceeding of EDISON Challenge
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• 2012.04a
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• pp.85-88
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• 2012

루프 페어링은 화물차의 주행저항 및 유도항력을 줄이기 위해 설치되는 장치 중 하나이다. 이 장치는 화물차의 지붕 윗부분에 설치하여 화물차가 받는 항력을 줄이는데 사용이 된다. 이번 과제에서는 루프 페어링의 효과에 대해 유체역학적인 증명 및 확인을 위해 루프 페어링의 설치 전-후 트럭의 형상에 따른 유동의 변화와 항력계수의 값을 EDISON CFD를 사용하여 구한 후 각각 비교 하였다. 이를 위해 EDISON CFD의 압력 contour와 stream line, 정압계수(Cp)그래프를 통해 트럭의 주행 중 발생하는 박리현상을 가시적으로 확인하였고, 항력계수(Cd)값을 비교하는 것을 통해 루프 페어링을 설치한 경우가 미설치된 경우보다 주행 시 더욱 유리하다는 것으로 결론을 내렸다.

• Proceedings of the Korea Information Processing Society Conference
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• 2011.11a
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• pp.739-742
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• 2011

스마트폰의 보급과 함께 등장한 스마트지갑은 스마트폰을 이용한 지불 시스템이다. 스마트지갑을 이용하여 결제를 수행하기 위해서는 결제단말과 스마트폰의 페어링 과정이 필요하다. 페어링을 통해 결제가 이루어지는 만큼 페어링 과정의 보안이 중요하다. 하지만 현재의 페어링과정에 적용되는 보안절차는 이미지 비교, 바코드, 사운드 등의 원시적인 차원의 보안절차만이 적용되어 있는 수준으로 보안강도가 낮다. 본 논문에서는 일회용 패스워드를 이용하여 기존의 페어링의 취약점을 보완하려고 한다. 일회용 패스워드를 이용하기 위해서는 사용자의 모바일ID를 검증하는 인증서버가 필요하다. 인증서버와 사용자 인증을 수행하는 단말사이의 통신은 해시 값을 이용하여 통신함으로 보안성을 높일 수 있다. 또한, 일회용 패스워드 기반의 스마트 지갑은 지불 서비스 이외에도 출입인증수단으로 이용될 수 있다.

• Journal of the Korea Institute of Information Security & Cryptology
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• v.21 no.2
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• pp.83-90
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• 2011

Recently, pairings over elliptic curve have been applied for various ID-based encryption/signature/authentication/key agreement schemes. For efficiency, the $Eta_T$ pairings over GF($P^n$) (P = 2, 3) were invented, however, they are vulnerable to side channel attacks such as DPA because of their symmetric computation structure compared to other pairings such as Tate, Ate pairings. Several countermeasures have been proposed to prevent side channel attacks. Especially, Masaaki Shirase's method is very efficient with regard to computational efficiency, however, it has security flaws. This paper examines closely the security flaws of RVA-based countermeasure on $Eta_T$ Pairing algorithm from the implementation point of view.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.10
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• pp.753-763
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• 2020

A wind tunnel test of 29.7% scaled model of NASA Common Research Model with belly model support was performed in small low speed wind tunnel. The static aerodynamic forces and moments of CRM were measured with belly sting support configuration. Pitching moments of belly sting with various fairings were compared and small interference fairing shape was found. The belly sting model support interference and reducing effect of fairing shapes with CFD analysis.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.126-134
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• 2005

Before the launch, launch vehicle is set up a few days ago at launch pad to check process and to supply fuels, etc. During the prelaunch process, the payload is exposed to the thermal environments. The purpose of a prelaunch thermal analysis is to predict maximum/minimum liftoff temperature of payload fairing and to evaluate air conditioning performance. The prelaunch thermal analysis of Delta II PLF is performed using Sinda/fluint, general thermal/fluid analyzer. The results are analyzed and compared with Delta II report.