Correlation of Test and Analysis for the 1/5‐Scale V‐22 Aeroelastic Model

Popelka, David; Sheffler, M.; Bilger, J. M.

doi:10.4050/jahs.32.21

Cited by 33 publications

(7 citation statements)

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“…Ref. [16] contains results of stability tests and correlation with analysis for the 115 Scale V-22 aeroelastic model. Some experimental data for the XV-15 for rotor loads and stability are available in References [14] and [17].…”

Section: Validationmentioning

confidence: 99%

Aeroelastic analysis of advanced geometry tiltrotor aircraft

Srinivas¹,

Chopra²,

Nixon³

1995

36th Structures, Structural Dynamics and Materials Conference

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A tiltrotor model is formulated to predict the dynamics and aeroelastic stability of composite-coupled advanced geometry rotors. Advanced geometry rotor blades are modeled with arbitrary sweep, anhedral, pretwist and planform taper variation with span. The effect of advanced geometry blades on the tiltrotor response and whirl flutter stability in airplane mode is studied. Blade tip sweep and tip droop increase the flutter speed while forward tip sweep, tip anhedral and planform taper decrease it. Predicted wing beam mode damping correlates satisfactorily with test data.

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Section: Validationmentioning

confidence: 99%

Aeroelastic analysis of advanced geometry tiltrotor aircraft

Srinivas¹,

Chopra²,

Nixon³

1995

36th Structures, Structural Dynamics and Materials Conference

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“…Historically the rotorcraft industry relied on custom in-house-designed-per-aircraft analysis methods. Several computer codes, DYN4-DYN5 [23], PASTA [38] and CAMRAD [35,36], were used by Popelka [51] to correlate analysis and test data for 1/5 scale V22 aeroelastic model. These codes are based on simplifying assumptions to reduce analytical complexity and computational cost.…”

Section: Multibody Dynamics Modeling For Rotorcraft Applicationsmentioning

confidence: 99%

Extension-Twist Coupling Optimization in Composite Rotor Blades

Ozbay

2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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This work could not have been completed without the help of many people to whom I would like to give my thanks. I would like to express my deepest gratitude to Dr. Erian Armanios for his patient guidance throughout my life at Georgia Tech. This work would have never been possible without his immeasurable professional and emotional support, encouragement and above all his trust. I am also grateful to Dr. D. Stefan Dancila for his support in this work. His valuable critiques and guidance helped me improve my work. I also would like to acknowledge Dr. Olivier A. Bauchau. I am thankful to him for providing the DYMORE and VABS programs. I would like to thank Dr. Dewey H. Hodges and Dr. Abdul-Hamid Zureick for their willingness to serve on my thesis committee. This work has been completed under a grant from the National Rotorcraft Technology Center. I am sincerely thankful for their support. Additionally I would like to thank my officemates, true friends, Samer Tawfik, Xinyuan Tan and Dr. Roxana Vasilescu for their technical and emotional support. I sincerely thank my parents Nedime and Engin Ozbay. Without their love, support and sacrifices, I would not be who I am now. Thank you for your belief in what I could achieve eventually. Finally I would like to express my great gratitude to my lovely wife Tuba, for her unconditional love, support and confidence. It is a huge understatement to say that I could achieve this without her. I love her. The rest of my days are special because of her. v TABLE OF CONTENTS

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“…These analyses were included in the widely-used code, CAMRAD (Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics) (Johnson 1980(Johnson , 1981, where in addition to dynamic stability, performance and loads of tilting proprotor aircraft can be also calculated. Bell Helicopter (Popelka et al 1985) developed inhouse their own code, called DYN4, to predict the dynamics of a tilt-rotor aircraft. Johnson (1984,1985) made an assessment of analytical capability for tilt-rotor aircraft in relation to the XV-15 tilt rotor research aircraft.…”

Section: Tilt-rotorsmentioning

confidence: 99%

Design and analysis trends of helicopter rotor systems

Chopra

1994

Sadhana

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To overcome many of the problems associated with conventional articulated rotor systems, new rotor systems are being contemplated. In this paper, the state-of-art technology of advanced rotor systems is assessed. Advanced rotors include hingeless, bearing, less, composite, circulation control, tilt and advanced geometry rotors. The paper reviews mathematical modelling, analysis methods, past and recent developments, potential limitations and future research needs in each system. Also, the potential of incorporation of structural optimization methodology and smart structures technology in rotors to improve the efficiency and capabilities of rotorcraft is discussed.

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Correlation of Test and Analysis for the 1/5‐Scale V‐22 Aeroelastic Model

Cited by 33 publications

References 0 publications

Aeroelastic analysis of advanced geometry tiltrotor aircraft

Aeroelastic analysis of advanced geometry tiltrotor aircraft

Extension-Twist Coupling Optimization in Composite Rotor Blades

Design and analysis trends of helicopter rotor systems

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