• Journal of the KSME
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• v.32 no.9
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• pp.777-787
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• 1992

21세기를 향한 여객선의 추세는 초고속화, 대형화(국제화), 성에너지화, 우수한 내항성능, 저진동 및 저소음 등을 갖춘 선박을 요구하고 있다. 이런 관점에서 초고속선으로 속력에 한계가 있는 단동선 (monohull), 쌍동배수량형(catamaran), 최소수면 쌍동선(SWATH)의 선형과 대형화가 곤란한 수중익선 (hydrofoil)보다는 속력면에서 유리하고 대형화가 가능한 표면 효과선 또는 앞 에서 언급한 고속 선형의 장점을 복합시킨 각종 복합선형이 개발되리라고 생각한다. 그러나 복 합선형이 실용화되기까지는 경제적인 건조비, 운항자세 제어 시스템, 신소재를 이용한 경구조화, 진동과 소음, 추진 시스템 등에 대한 요소 기술의 개발이 선행되어야 한다. 끝으로 선박의 속력이 50노트가 넘는 초고속선을 설계, 제작, 운항을 하는데 있어 그 개념이 조선공학에서 다루어지는 통상 선박기술의 연장이라고 그 영역을 정리하는 경향이 있다. 이 글을 정리하면서 느낀 것이 지만 해상교통 수단의 초고속화가 이루어질수록 그 지지기술 및 자세제어기술 등에 있어서는 항공기 기술에 가까워짐을 알게 되었다. 그러한 뜻에서 초고속선 개발에는 항공기 기술에서 얻 어진 노하우를 잘 활용하는 일도 중요하리라 생각된다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1995.04a
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• pp.270-275
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• 1995

본 논문에서는 3자유도를 갖는 2차원 강체날개의 플러터 속도를 향상시키는 축차 제어기를 설계하는 기법을 연구하였다. 먼저 2차원 강체날개의 운동방정식을 유도하고 플러터 해석을 수행하였다. 다음 수동계의 플러터 속도를 향상시키는 능동제어기를 설계한 후 제어기의 차수를 축차하는 기법을 적용하여 저차의 능동제어기를 구성하였다. 제어기 축차기법으로는 BACR을 사용하였으며 전차 제어기의 상태변수를 약 80%정도 줄일 수 있다. 축차된 제어기를 사용한 능동시스템과 전차 제어기를 사용한 능동시스템의 제어효과의 차이는 무시 할 수 있을 정도로 매우 작다. 따라서, BACR을 사용하여 얻은 축차된 제어기를 사용하면 상당한 계산량 감소효과와 실시간 단축효과를 얻을 수 있음을 확인하였다. 또한 동일한 돌풍입력에 대한 각각의 능동 시스템의 시간응답도 매우 양호한 결과를 얻을 수 있었으며, 전차 제어기를 사용한 능동시스템의 돌풍응답과 축차된 제어기를 사용한 능동시스템의 돌풍 응답 사이의 차이도 매우 작게 나타났다. 그러므로, 항공기 날개의 능동 플러터억제에는 BACR을 이용하여 설계한 축차된 제어기가 플러터 능동제어에 매우 유용하다고 할 수 있다. 그러나 BACR을 사용하기 위해서는 요구되는 정확도와 계산량에 대한 상호 절충과정이 반드시 필요하다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.04a
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• pp.299-299
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• 2011

In this study, transonic aeroelastic response analyses have been conducted for the business jet aircraft configuration considering shockwave and flow separation effects. The developed fluid-structure coupled analysis system is applied for aeroelastic computations combining computational structural dynamics(CSD), finite element method(FEM) and computational fluid dynamics(CFD) in the time domain. It can give very accurate and useful engineering data on the structural dynamic design of advanced flight vehicles. For the nonlinear unsteady aerodynamics in high transonic flow region, Navier-Stokes equations using the structured grid system have been applied to wing-body configurations. In transonic flight region, the characteristics of static and dynamic aeroelastic responses have been investigated for a typical wing-body configuration model. Also, it is typically shown that the current computation approach can yield realistic and practical results for aircraft design and test engineers.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.10a
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• pp.191-195
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• 2011

The airframe ground vibration tests were conducted on the KC-100 aircraft according to the regulation requirement, KAS 23.629(a)(2) and the modal characteristics for the target modes were measured. To make FE model tuning, a design sensitivity approach with engineering judgment was implemented using MSC/Nastran and Attune, a genetic algorithm based parameter optimization software. Based on the comparison between initial prediction and test results, design variables such as beam cross-sectional properties and spring stiffnesses were devised. As the results, the correlation of the FE model to the GVT results was made appropriately, meeting the goal of matching the target frequencies within 5%.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.19 no.12
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• pp.1315-1321
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• 2009

In the present work, vibration control performance of active camera mount system for unmanned aero vehicle(UAV) is evaluated. An active mount featuring inertia type of piezostack actuator is designed and manufactured. Then, vibration control performances are experimentally evaluated. A camera mount system with four active mounts is constructed and mechanical model is established. The governing equation for the camera mount system is obtained and control model is constructed in state space model. Sliding mode controller which has inherent robustness to external disturbance is designed and implemented to the system. Vibration control performances are evaluated at each mount and center of gravity point. Effective vibration performances are obtained and presented in time and frequency domains.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.18 no.12
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• pp.1278-1285
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• 2008

This paper presents an inertia type of piezostack based active mount fur unmanned aero vehicle (UAV) camera system. After identifying the stiffness and damping properties of the rubber element and piezostack a mechanical model of the active mount system is established. The governing equation of mount is then derived and expressed in a state space form. Subsequently, a sliding mode controller which is robust to uncertain parameters is designed in order to reduce the vibration imposed according to the military specification associated with UAV camera mount system operation. Control performances such as acceleration and transmitted force are evaluated through both computer simulation and experimental implementation.

• Journal of the Korea Institute of Military Science and Technology
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• v.21 no.6
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• pp.790-798
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• 2018

Discrete noise signals from a small scale tactical unmanned aerial vehicle(UAV) propeller were predicted numerically using time domain approach. Two-bladed 29 inch propeller in diameter and 150 kgf in gross weight were used for main parameters of the UAV based on the actual size of the similar scale vehicle. Panel method and Farassat formula A1 were adopted for aerodynamic and aeroacoustic analysis respectively. Time domain signals of both thickness and loading noises were transformed into frequency domain to analyze the discrete noise characteristics. Directivity pattern in a plane perpendicular to the rotating disc plane and attenuation of noise intensity according to double distance were also presented.

• The Korean Journal of Air & Space Law and Policy
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• v.32 no.1
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• pp.355-384
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• 2017

In Korea, a Law on Airport Noise Prevention and Noise Control Area Support has been in effect since 2010. And also, airport noise measures project and residents support project conducted following the Law on Airport Noise Prevention and Noise Control Area Support. However, a Law on Airport Noise Prevention and Noise Control Area Support does not apply to military airfield. Many city residents already complain about military airport noise, but there are no countermeasures. They claim the noise from the military airfield is an intrusion on their lives, and some people brought a class action against the government. In the 20th National Assembly, some congressmen already proposed some legislations that aims to support residents adjacent to the military airfield. Nevertheless, relevant legislations are currently pending at the 20th National Assembly. Legislation preventing aircraft noise and providing support measures is essential to residents life who near by military airfield. At first, this study looked at legislations proposed by congressmen in the 20th National Assembly. And also, this study looked at A Law on the Improvement of Living Environment around the Defence Facilities of Japan. Based on this study, we did an analysis of the problem of legislation and proposed improvement suggestion. I hope so that this study could someday help congressmen make a legislation about military airfield noise. We hope the 20th National Assembly will pass the legislation finally to help the residents who near by military airfield relieve their pain by noise and restore their human dignity.

• 한국항공운항학회:학술대회논문집
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• 2005.05a
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• pp.79-82
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• 2005

• The Korean Journal of Air & Space Law and Policy
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• v.13
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• pp.231-248
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• 2001