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Analysis and Prediction of the Rigid, Coaxial Rotor System's Blade-crossover Interaction Events
Analysis and Prediction of the Rigid, Coaxial Rotor System's Blade-crossover Interaction Events
상세정보
- 자료유형
- 학위논문 서양
- 최종처리일시
- 20260202105320
- ISBN
- 9798297671645
- DDC
- 330
- 저자명
- Sharma, Kalki.
- 서명/저자
- Analysis and Prediction of the Rigid, Coaxial Rotor Systems Blade-crossover Interaction Events
- 발행사항
- [Sl] : The Pennsylvania State University, 2025
- 발행사항
- Ann Arbor : ProQuest Dissertations & Theses, 2025
- 형태사항
- 289 p
- 주기사항
- Source: Dissertations Abstracts International, Volume: 87-04, Section: B.
- 주기사항
- Advisor: Brentner, Kenneth S.
- 학위논문주기
- Thesis (Ph.D.)--The Pennsylvania State University, 2025.
- 초록/해제
- 요약The modern compound coaxial helicopter, such as the Raider and Defiant, has been developed to overcome the speed limitations of the conventional single main and tail rotor helicopter. Although there are advantages to this configuration, the proximity of the rotors results in aerodynamic interactions between the rotors that cause impulsive loading events, and this results in potential problems with vibrations and acoustics. One of the primary impulsive loading event is the blade-crossover interaction (BCI).This work focuses on understanding, isolating, and predicting BCI events in rigid coaxial rotor systems. BCI events are significant aerodynamic interactions that occur when the blades of the upper and lower rotors cross each other, leading to impulsive loading and increased noise levels. The impact of BCI events is demonstrated through acoustic measurements, with predictions computed using rotor performance data extracted from various analysis tools and fed into acoustic prediction software (PSU-WOPWOP). It is determined that mid-fidelity rotorcraft analysis tools do not adequately account for BCI events, necessitating the use of Computational Fluid Dynamics (CFD). The interaction is also studied in isolation by simulating the crossing of airfoils using approaches of varying fidelity, confirming that lower-order methods fail to capture the physics accounted for in CFD. To compute the BCI events in milliseconds, the data generated from the CFD analysis is used to develop a surrogate model using the Gaussian Process Regression (GPR) model approach. The BCI events are shown to increase sound pressure levels (SPL) by up to 10 dB, effectively doubling noise below the rotor system at high speed forward flight, with the key factors governing the interaction being the speed and vertical separation distance of the rotor blades upon crossover. The key contributions of this work are: 1) demonstrated the importance of BCI events in rotor acoustics, showing that they can add up to 10 dB in SPL; 2) isolated and quantified the impact of BCI events on noise, revealing noise directivity most dominant below and 5° aft of the shaft axis as well as below and parallel to the direction of the BCI events; 3) compared models of varying fidelity, showing that lower-fidelity models over-predict BCI intensity by 2-3 times compared to CFD; 4) developed a surrogate model using 2D CFD data to predict BCI events, providing accurate results at significantly faster computational speeds; 5) showed that appending BCI events to mid-fidelity results improves noise prediction accuracy, bringing it closer to CFD results.
- 일반주제명
- Aircraft
- 일반주제명
- Vortices
- 일반주제명
- Acoustics
- 일반주제명
- Reynolds number
- 일반주제명
- Geometry
- 일반주제명
- Radiation
- 일반주제명
- Aerodynamics
- 일반주제명
- Aerospace engineering
- 일반주제명
- Fluid mechanics
- 기본자료저록
- Dissertations Abstracts International. 87-04B.
- 전자적 위치 및 접속
- 로그인 후 원문을 볼 수 있습니다.
MARC
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■020 ▼a9798297671645
■035 ▼a(MiAaPQ)AAI32289486
■035 ▼a(MiAaPQ)PennState35441kys5232
■040 ▼aMiAaPQ▼cMiAaPQ
■0820 ▼a330
■1001 ▼aSharma, Kalki.
■24510▼aAnalysis and Prediction of the Rigid, Coaxial Rotor System's Blade-crossover Interaction Events
■260 ▼a[Sl]▼bThe Pennsylvania State University▼c2025
■260 1▼aAnn Arbor▼bProQuest Dissertations & Theses▼c2025
■300 ▼a289 p
■500 ▼aSource: Dissertations Abstracts International, Volume: 87-04, Section: B.
■500 ▼aAdvisor: Brentner, Kenneth S.
■5021 ▼aThesis (Ph.D.)--The Pennsylvania State University, 2025.
■520 ▼aThe modern compound coaxial helicopter, such as the Raider and Defiant, has been developed to overcome the speed limitations of the conventional single main and tail rotor helicopter. Although there are advantages to this configuration, the proximity of the rotors results in aerodynamic interactions between the rotors that cause impulsive loading events, and this results in potential problems with vibrations and acoustics. One of the primary impulsive loading event is the blade-crossover interaction (BCI).This work focuses on understanding, isolating, and predicting BCI events in rigid coaxial rotor systems. BCI events are significant aerodynamic interactions that occur when the blades of the upper and lower rotors cross each other, leading to impulsive loading and increased noise levels. The impact of BCI events is demonstrated through acoustic measurements, with predictions computed using rotor performance data extracted from various analysis tools and fed into acoustic prediction software (PSU-WOPWOP). It is determined that mid-fidelity rotorcraft analysis tools do not adequately account for BCI events, necessitating the use of Computational Fluid Dynamics (CFD). The interaction is also studied in isolation by simulating the crossing of airfoils using approaches of varying fidelity, confirming that lower-order methods fail to capture the physics accounted for in CFD. To compute the BCI events in milliseconds, the data generated from the CFD analysis is used to develop a surrogate model using the Gaussian Process Regression (GPR) model approach. The BCI events are shown to increase sound pressure levels (SPL) by up to 10 dB, effectively doubling noise below the rotor system at high speed forward flight, with the key factors governing the interaction being the speed and vertical separation distance of the rotor blades upon crossover. The key contributions of this work are: 1) demonstrated the importance of BCI events in rotor acoustics, showing that they can add up to 10 dB in SPL; 2) isolated and quantified the impact of BCI events on noise, revealing noise directivity most dominant below and 5° aft of the shaft axis as well as below and parallel to the direction of the BCI events; 3) compared models of varying fidelity, showing that lower-fidelity models over-predict BCI intensity by 2-3 times compared to CFD; 4) developed a surrogate model using 2D CFD data to predict BCI events, providing accurate results at significantly faster computational speeds; 5) showed that appending BCI events to mid-fidelity results improves noise prediction accuracy, bringing it closer to CFD results.
■590 ▼aSchool code: 0176.
■650 4▼aAircraft
■650 4▼aVortices
■650 4▼aAcoustics
■650 4▼aReynolds number
■650 4▼aGeometry
■650 4▼aRadiation
■650 4▼aAerodynamics
■650 4▼aAerospace engineering
■650 4▼aFluid mechanics
■690 ▼a0986
■690 ▼a0538
■690 ▼a0800
■690 ▼a0204
■71020▼aThe Pennsylvania State University.
■7730 ▼tDissertations Abstracts International▼g87-04B.
■790 ▼a0176
■791 ▼aPh.D.
■792 ▼a2025
■793 ▼aEnglish
■85640▼uhttp://www.riss.kr/pdu/ddodLink.do?id=T17360194▼nKERIS▼z이 자료의 원문은 한국교육학술정보원에서 제공합니다.


