http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
다양한 비행환경에서의 공력 및 음향 하중을 고려한 고속비행체의 진동응답 예측
은원종(WonJong Eun),김진형(JinHyung Kim),박서룡(SeoRyong Park),신상준(SangJoon Shin),이수갑(SooGab Lee) 한국소음진동공학회 2015 한국소음진동공학회 학술대회논문집 Vol.2015 No.10
High speed flight vehicle, such as spacecraft and missile, is usually a cylindrical shape and is composed of thin plate skin structures. It installs a high-performance electronic unit sensitive to vibratory loads. Such light-weight structures are usually exposed to external dynamic loads which consist of random vibration, shock, and acoustic loads created from adverse operational environment. Such electronic units need to be designed and qualified considering its robustness. The final objective of this paper is to develop a methodology which helps to establish design specification for the dynamic loads acting both upon the vehicle and electronic units at an arbitrary location inside the vehicle.
Enhancement of SNUF Active Trailing-edge Flap Blade Mechanism Design
은원종(Natarajan, Balakumaran),신상준(Eun, WonJong) 한국소음진동공학회 2013 한국소음진동공학회 논문집 Vol.23 No.7
Seoul National University flap(SNUF) blade is a small-scale rotor blade incorporating a small trailing-edge flap control surface driven by piezoelectric actuators at higher harmonics for vibration attenuation. Initially, the blade was designed using two-dimensional cross-section analysis and geometrically exact one-dimensional beam analysis, and its material configuration was finalized. A flap-deflection angle of ${\pm}4^{\circ}$ was established as the criterion for enhanced vibration reduction based on an earlier simulation. The flap-linkage mechanism was designed and static bench tests were conducted for verifying the performance of the flap-actuation mechanism. Different versions of test beds were developed and tested with the designed flap and the selected APA 200M piezoelectric actuators. Through significant improvements, a maximum deflection of ${\pm}3.7^{\circ}$ was achieved. High-frequency experiments were conducted for evaluating the performance, and the transfer function of the test bed was determined experimentally. With the static tests almost complete, the rotor power required for testing the blade in a whirl tower (centrifugal environment) was calculated, and further preparations are underway.
헬리콥터의 진동하중 저감을 위한 능동 뒷전플랩의 기구학적 설계 개선 및 검증
강정표(JungPyo Kang),은원종(WonJong Eun),임재훈(JaeHoon Lim),Umberto Visconti,신상준(SangJoon Shin) 한국소음진동공학회 2014 한국소음진동공학회 학술대회논문집 Vol.2014 No.10
In this paper, an improved small-scaled blade prototype was designed with the flap-driving mechanism classified as an active vibration reduction method, in order to reduce vibratory load in the helicopter. In detail, the previous Active Trailing-Edge Flap based on piezoelectric actuator, called SNUF(Seoul National University Flap), failed to achieve the target value (±4°) of the flap deflection angle. Therefore, the flap-driving mechanism design was improved, and a new piezoactuator was selected to accomplish the target value of the flap deflection angle in both static and rotating situations.
비행 조건의 영향을 고려한 쿼드콥터형 무인비행체의 로터 공력 특성 예측
박선후(SunHoo Park),은원종(WonJong Eun),신상준(SangJoon Shin) 한국항공우주학회 2018 韓國航空宇宙學會誌 Vol.46 No.10
본 연구에서는 무임 회전익기의 종류인 쿼드콥터의 로터 블레이드에 대해 바람 및 비행 조건의 따른 공력특성을 예측하고자 한다. 돌풍 및 비행 조건들을 고려하기 위해 바람의 좌표계 변환 개념을 제시하였다. 강체 블레이드 플래핑 운동방정식을 고려한 깃 요소 및 운동량 이론을 이용해 개별 로터의 제자리, 전지, 상승 비행을 해석하였다. XFOIL을 사용하여 공력결과를 도출하였고, 개발된 BEMT를 이용하여 제자리 비행, 전진, 상승 조건의 검증을 수행했다. 또한 제자리 비행 실험 환경 구축 및 실험 결과와 개발된 BEMT의 비교 및 검증을 수행하였다. This paper aims to predict the aerodynamic characteristics of individual rotor for the gust and flight conditions. Transformation procedure into the wind frame is conducted to analyze the gust. Hover, forward, and climb flight conditions of an individual rotor are analyzed using the blade element momentum theory (BEMT) considering the rigid blade flapping motion. XFOIL is used to derive aerodynamic results. Validation for hover, forward flight, and climb conditions are conducted using the present BEMT. In addition, a static experimental environment is constructed. The experimental results and the present BEMT are compared and verified.