• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.217-221
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• 2007

In this study, forced vibrations analysis was performed for main wing of small scale WIG vehicle which is equipped two-stroke pusher type propeller engine, in terms of structural. for the frequency response analysis, excitations were assumed by H-mode(Horizontal mode), X-mode(Twisted mode) which is main vibration mode of engine, and for the transient response analysis, excitations were assumed by L-mode(Longitudinal mode) with propeller thrust which is occurred when it revolution.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2001.11a
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• pp.26-26
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• 2001

소형항공기용 IO-540 왕복엔진을 대상으로 추진기관의 성능에 미치는 배압 특성을 조사하기 위해서 지상 성능시험을 수행하였다. 본 시험은 6가지 배기조건에 대해서 엔진의 배압과 흡기압력, 토크, 그리고 프로펠러의 정지추력을 측정하였다. 엔진의 배압은 대체로 머플러를 장착할 경우와 배기관 끝단이 상대적으로 직경이 작고 길이가 길수록 증가하였다. 배압 특성은 특히 엔진의 회전속도가 고속 영역으로 갈수록 프로펠러 추력에 변화를 나타냈으며 전반적으로 추진기관 성능에 미세한 영향을 미치는 것으로 나타났다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.7-12
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• 2007

Previously study on structural design of the main wing of the twenty-seat class WIG (Wing in Ground Effect) craft. In the final design, three spars construction was selected for safety in the critical flight load, and the Carbon-Epoxy material was selected for lightness and structural stability. In this study, the forced vibration analysis was performed on the composite main wing structure of the twenty-seat class WIG craft with two-stroke pusher type reciprocating engine. The vibration analysis based on the finite element method was performed using a commercial FEM code, MSC/NASTRAN. Excitations for the frequency response analysis were assumed as the Y-mode (lateral mode), the Z-mode (vertical mode) and the $M_{xyz}$-mode (twisted mode) which are typical main vibration modes of engine. And excitations for the transient response analysis were assumed as the X-mode (longitudinal mode) with the oscillating propeller thrust which occurs in operation.

• Bulletin of the Society of Naval Architects of Korea
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• v.32 no.1
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• pp.28-31
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• 1995

워터제트(Waterjet) 추진의 개념은 선박용 스크류 프로펠러 만큼이나 오래 되었지만, 1960년대 까지도 많은 이용이 없었다. 왜냐하면 스크류 프로펠러가 더 간단하고 가벼우면서 훨씬 더 효 율적인 추진도구로 간주되어 왔기 때문이었다. 그러나 최근 수년 사이에 워터제트로 추진되는 세계적인 선박들 및 제작회사들의 수가 괄목할만한 증가를 보이고 있고, 선진국의 초고속선 개 발과 관령하여 워터제트 추진방식에 대한 새로운 시각에서의 연구가 활발히 진행되어지고 있 다[1]. 21세기 해상교통수당을 선도할 수 있으리라 판단되고 있는 초고속선 개발 연구를 수행하고 있는 선박·해양공학연구센터에서도 초고속선용 추진 장치로서 워터제트 추진기를 선택하였었 다[2]. 이러한 대표적인 이유로서는 종래의 일반적인 선박용 스크류 프로펠러로서는 고속 추진에 한계를 가지고 있는 반면, 워터제트 추진방식은 각 요소들의 최적 설계를 통해 고속에서의 추 진효율 향상을 꾀할 수 있기 때문이었다. 선진국에서는 이미 이러한 워터제트 추진에 대한 성 능해석 기법이 정립되어 있고[3], 중.소형 워터제트 추진기 제작을 통한 경험을 바탕으로 대출력 워터제트 추진기 개발도 가능한 단계이다[4]. 그러나 국내에서는 이에 대한 연구가 거의 없어 외국의 기술에 의존하고 있는 실정이다. 본 고에서는 워터제트 추진기의 기본적인 개념과 당 연구센타에서 수행하고 있는 모형시험법 개발 연구의 일부를 소개하고자 한다.

• Journal of Korea Ship Safrty Technology Authority
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• v.15
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• pp.17-30
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• 2004

중, 소형 선박의 추진시스템은 주 동력원인 4행정 디젤엔진, 프로펠러의 추진 효율을 증대시키기 위한 감속장치, 진동 및 충격토크를 절연시키는 탄성커플링, 동력을 전후방향의 추력으로 전환하는 추진기로 구성되어 있다.<중략>

• Journal of Aerospace System Engineering
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• v.18 no.3
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• pp.76-85
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• 2024

Recently, from a global perspective, the use of small unmanned aerial vehicles in terrorism and warfare is increasing, and the need for anti-drone shooting training targeting small UAVs is increasing. However, in reality, there are many cases in Korea where anti-drone shooting training is restricted, due to complaints such as noise. In this paper, we describe the development and testing of an electric-powered direct strike type high-speed, low-noise small aerial target drone. To achieve the flight speed and endurance required for shooting training, target drone sizing was performed, and aerodynamic performance analysis was conducted using a CFD program. Based on the performance analysis, the motor propulsion system was selected and a variable pitch propeller system was designed, and performance tests were performed on a ground test rig. Finally, the target flight speed, flight time, and flight noise level were confirmed through flight tests.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.20 no.4
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• pp.1491-1500
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• 1996

Unstable performance deterioration was found on the performance curve of a small propeller fan with a back plate. To investigate this phenomenon and the effects of the back-plate on the performance of the fan, performance tests and flow measurement using 3-hole pitot tube were carried out. Measurements showed that when the flow rate is small, the radial flow dominates, and when the flow rate is large, the axial flow dominates. Performance characteristic of the propeller fan changes from radial to axial type as the flow rate increases. Unstable performance changes are the result of type change of the flow through the fan.

• 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.

• Proceedings of the KIEE Conference
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• 2015.07a
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• pp.886-887
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• 2015

선진 각국에서는 고효율, 친환경 에너지 공급 및 이용 기술, 그리고 효율적인 에너지 절약 기술 개발에 관한 연구 개발이 활발히 진행되고 있다. 이러한 연구 중 항공기 분야에서는 전동기로 프로펠러를 회전시키는 전기추진 항공기에 대한 관심과 수요가 증가하고 있다. 소형 항공기 추진용 전동기는 엔진과 함께 소형 항공기의 주 구동원으로서 중요성이 강조되고 있다. 또한 근래에 전동기의 비중이 커짐에 따라 고출력, 고효율화 되고 있는 추세이다. 본 논문에서는 항공 운항 패턴 중 이륙, 상승, 순항구간에 따라 각각 요구하는 성능을 만족하는 고출력, 고효율 전동기 개발에 대해 다루었다.

• The Journal of the Acoustical Society of Korea
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• v.36 no.2
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• pp.89-99
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• 2017

Multi-rotor type UAV (Unmanned Aerial Vehicle)s are expanding their applications not only for military purposes but also for private industries such as aerial photography and unmanned delivery vehicles. For wider use of unmanned aerial vehicles, studies should be carried out to improve aerodynamic efficiency and reduce noise of propellers, which can be achieved based on techniques of predicting aerodynamic performance and noise in a given environment. In this study, aerodynamic and noise prediction techniques were developed for a small unmanned aerial vehicle propeller, and it was verified by comparing it with actual measurement results. Thrust and torque due to the change of r/min and the frequency spectral prediction at a given position secured the reliability of the prediction method, which provides a basis for the shape design of the propeller.