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보간법을 이용한 옥타브 밴드폭 음향 하중 SPL의 시계열 데이터 생성
고은수,김인걸,전민혁,조현준,박재상,김민성,Go, Eun-Su,Kim, In-Gul,Jeon, Minhyeok,Cho, Hyun-Jun,Park, Jae-Sang,Kim, Min-Sung 한국군사과학기술학회 2021 한국군사과학기술학회지 Vol.24 No.1
Thermal protection system structures such as double-panel structures are used on the skin of the fuselage and wings to prevent the transfer of high heat into the interior of an high supersonic/hypersonic aircraft. The thin-walled double-panel skin can be exposed to acoustic loads by high power engine noise and jet flow noise, which can cause sonic fatigue damage. In order to predict the fatigue life of the skin, the octave bandwidth SPL should be calculated as narrow bandwidth PSD or acoustic load history using interpolation method. In this paper, a method of converting the octave bandwidth SPL acoustic load into a narrow bandwidth PSD and reconstructed acoustic load history was investigated. The octave bandwidth SPL was converted to the narrow bandwidth PSD using various interpolation methods such as flat, log and linear scale, and the probabilistic characteristics and fatigue damage results were compared. It was found that average error of fatigue damage index by the log scale interpolation method was relatively small among three methods.
Beauveria bassiana Bb08의 살충성 물질 생산을 위한 배양조건의 통계적 최적화
고은수 ( Go Eun Su ),임영훈 ( Young Hoon Lim ),정형철 ( Hyeong Chul Jeong ),최재필 ( Jae Pil Choi ),박인서 ( In Seo Park ),김정준 ( Jeong Jun Kim ),이동진 ( Dong Jin Lee ),김근 ( Keun Kim ) 한국미생물생명공학회 2013 한국미생물·생명공학회지 Vol.41 No.4
For the maximal production of aphicidal metabolites produced by the Beauveria bassiana Bb08, statistical methods such as the Box-Behnken experimental design and response surface methodology were used. The fungal culture filtrate was sprayed towards 3-star aphids and the mortality was examined. After the statistical analysis of the aphid mortality, the optimal culture conditions were found to be a culture temperature of 26.2oC, medium pH 5.9, flask shaking speed of 209.0 rpm, and culture time of 5.9 days. The expected mortality on days 4, 5, and 6 after spraying the filtrate on to the aphids were 76.8%, 84.9%, and 89.4%, respectively. All 4 factors of the culture conditions significantly affected the production of the aphicidal metabolites, and the order of significance was temperature, pH, culture time and shaking speed.
열음향 피로 시험 장치를 이용한 티타늄 시편의 동적 거동에 관한 실험적 연구
고은수(Eun-Su Go),김문국(Mun-Guk Kim),문영선(Young-Sun Moon),김인걸(In-Gul Kim),박재상(Jae-Sang Park),김민성(Min-Sung Kim) 한국항공우주학회 2020 韓國航空宇宙學會誌 Vol.48 No.2
고초음속 항공기는 초음속 비행 중 공력 가열에 의하여 높은 온도 환경에 노출되기 때문에 동체 및 날개 구조물은 더블 패널 형태의 열 차폐 구조로 설계하여 기체 내부로 높은 온도의 열이 전달되는 것을 막는다. 얇은 두께의 더블 패널 외피는 초음속 항공기의 고출력 엔진 소음과 제트 유동에 의한 음향 하중에 노출되어 음향 피로 손상이 발생할 수 있다. 따라서 열음향 복합 하중을 받는 초음속 항공기 외피 구조의 거동 확인과 피로수명 예측이 필요하다. 본 논문에서는 열음향 복합 하중을 모사할 수 있는 열음향 시험 장치를 설계/제작하여 열음향 하중이 적용되는 티타늄 시편의 열음향 시험을 수행하였다. 열음향 복합 하중에 의한 구조물의 동적 거동을 확인하였으며, 시편 단위 열음향 시험 결과와 유한요소해석 결과를 비교하여 해석 모델을 검증하였다. High supersonic aircraft are exposed to high temperature environments by aerodynamic heating during supersonic flight. Thermal protection system structures such as double-panel structures are used on the skin of the fuselage and wings to prevent the transfer of high heat into the interior of an aircraft. The thin-walled double-panel skin can be exposed to acoustic loads by supersonic aircrafts high power engine noise and jet flow noise, which can cause sonic fatigue damage. Therefore, it is necessary to examine the behavior of supersonic aircraft skin structure under thermal-acoustic load and to predict fatigue life. In this paper, we designed and fabricated thermal-acoustic test equipment to simulate thermal-acoustic load. Thermal-acoustic testing of the titanium specimen under thermal-acoustic load was performed. The analytical model was verified by comparing the thermal-acoustic test results with the finite element analysis results.
PVDF 센서를 이용한 수압램 하중을 받는 복합재 T-Joint의 동적 변형률 측정
고은수 ( Eun-su Go ),김동건 ( Dong-geon Kim ),김인걸 ( In-gul Kim ),우경식 ( Kyeongsik Woo ),김종헌 ( Jong-heon Kim ) 한국복합재료학회 2018 Composites research Vol.31 No.5
수압램 현상은 전투용 항공기의 주요 전투 손상 중 하나이며, 항공기 기체 생존성 평가에 중요한 영향을 미친다. 수압램 효과는 유체-구조물간의 상호관계를 통하여 나타나며, 구조물의 동적 변형률을 측정하여 파손 거동 및 파손 여부를 확인할 수 있다. 본 논문에서는 수압램 현상을 모사할 수 있는 수압램 시험 장치를 이용하여 수압램에 의한 복합재 T-Joint의 파손 시험을 수행하였다. 또한 계측기기의 입력 정전용량과 시간 상수 확인을 위해 PVDF 센서 보정 시험을 수행하였다. 복합재 T-Joint에 스트레인 게이지와 전하증폭기를 사용하지 않은 PVDF 센서를 부착하여 수압램 현상에 의한 복합재 T-Joint의 동적 변형률을 측정하였다. PVDF 센서와 스트레인 게이지의 동적 변형률을 이용하여 복합재 T-Joint의 파손 거동 및 파손 여부를 확인하였다. The hydrodynamic ram (HRAM) phenomenon is one of the main types of ballistic battle damages of a military aircraft and has great importance to airframe survivability design. The HRAM effect occurs due to the interaction between the fluid and structure, and damage can be investigated by measuring the pressure of the fluid and the dynamic strains on the structure. In this paper, HRAM test of a composite T-Joint was performed using a ram simulator which can generate HRAM pressure. In addition, calibration tests of PVDF sensor were performed to determine the circuit capacitance and time constant of the measurement system. The failure behavior of the composite T-Joint due to HRAM pressure was examined using the strain gauges and a PVDF sensor which were attached to the surface of the composite T-Joint.