A Measurement Of The Static Aeroelastic Deformation And Loading Of A Wing In Supersonic Flow
DOWNLOAD
Download A Measurement Of The Static Aeroelastic Deformation And Loading Of A Wing In Supersonic Flow PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get A Measurement Of The Static Aeroelastic Deformation And Loading Of A Wing In Supersonic Flow book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page
A Measurement Of The Static Aeroelastic Deformation And Loading Of A Wing In Supersonic Flow
DOWNLOAD
Author : Frank Herman Durgin
language : en
Publisher:
Release Date : 1963
A Measurement Of The Static Aeroelastic Deformation And Loading Of A Wing In Supersonic Flow written by Frank Herman Durgin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1963 with Aerodynamics categories.
The aeroelastic analysis of Zisfein, Donato and Farrell (AD-155739) uses an aerodynamic matrix, a structural matrix and the initial angle of attack to predict the equilibrium pressures and shape of a wing. To test the accuracy of their methods, a flexible wing was built and instrumented with pressure taps and mirrors. The wing was tested at Mach numbers of 2 and 3, and both the pressure distribution and the deflected shape were measured. An aerodynamic matrix computed on the basis of the semiempirical procedures of the above authors was used to predict pressure distributions, and an experimentally determined structural matrix was used to find equilibrium angles of attack. Finally, these two matrices were used in the aeroelastic equations to compute pressures and angles of attack from the undeflected shape of the wing. Comparisons between theory and experiment are presented for eight different free stream conditions. -- page iii.
U S Government Research Reports
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1964
U S Government Research Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Science categories.
Proceedings Of Symposium On Aeroelastic Dynamic Modeling Technology 23 24 25 September 1963 Dayton Ohio
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1964
Proceedings Of Symposium On Aeroelastic Dynamic Modeling Technology 23 24 25 September 1963 Dayton Ohio written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Aeroelasticity categories.
Index Of Nasa Technical Publications
DOWNLOAD
Author : United States. National Aeronautics and Space Administration
language : en
Publisher:
Release Date : 1960
Index Of Nasa Technical Publications written by United States. National Aeronautics and Space Administration and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aeronautics categories.
Measurement Of Aeroelastic Wing Deflections On A Remotely Piloted Aircraft Using Modal Strain Shapes
DOWNLOAD
Author : Stephen Daniel Wilfred Warwick
language : en
Publisher:
Release Date : 2020
Measurement Of Aeroelastic Wing Deflections On A Remotely Piloted Aircraft Using Modal Strain Shapes written by Stephen Daniel Wilfred Warwick and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2020 with categories.
The aerospace industry endeavours to improve modern aircraft capabilities in efficiency, endurance, and comfort. One means of achieving these goals is through new enhancements in aerodynamics. Increased wing aspect ratio is an example of further improving efficiency. However, this comes with new challenges including possibly adverse aero-elastic and aero-servo-elastic (ASE) phenomena. New computational methods and tools are emerging and there is a need for experimental data for validation. University of Victoria's Centre for Aerospace Research (UVic CfAR) set out to design a 20kg ASE demonstrator using a remotely piloted aircraft (RPA). This aircraft was designed with the intent of exploring coupling between aero-elastic modes including coupling between the short period aerodynamic mode and the first out-of-plane elastic mode of the wing. This thesis discuses the implementation of instrumentation designed and integrated into the ASE RPA demonstrator to monitor the deformation of the elastic wing in-flight. A strain based measurement technique was selected for integration into the ASE aircraft. This choice was made for several reasons including its reliability regardless of outdoor lighting, relatively lightweight processing requirements for real time applications, and suitable sampling bandwidth. To compute the wing deformation from strain, a method, sometimes referred to as strain pattern analysis (SPA), utilizing linear combinations of reference modal shapes fit against the measured strain, was used. Although this method is not new, to the author's knowledge, it is the first practical application to a reduced scale RPA demonstrator. The deformation measurement system was validated against a series of distributed static load tests on the ground. Distributed load cases along the wing demonstrated good out-of-plane measurement performance. A case where only load is applied near the root of the wing resulted in the largest error in part as the mode shapes generated are less suited to approximate the resulting shape. In general errors in out-of-plane displacement at the end of the flexible wing portion can be expected to be less than 5%. The displacement at the tip of the wing can be as great as 11% for the left wing whereas the right wing is 4.7%. This suggest an asymmetry between the left and right wings requiring specifically tuned FE models for each to achieve best results. Twist angles presented in tests were relatively small for accurate comparison against the reference measurement, which was relatively noisy. Generally, the deformation measurement by SPA technique followed the same twist behaviours as the reference. A twist case, unlikely to be seen in flight, provided some insight into twist measurement robustness. The work presented is merely a small step forward with many opportunities for further research. There is room for improvement of the FE model used to generate the mode shapes in the strain pattern analysis. Initial efforts focused on the flexible spar portion of the wing. With more work improvements could be achieved for the estimation of the rigid wing. Additionally, there was some asymmetry between each wing semi-span, and with some focus on the left wing its results could be improved to at least match that of the right wing. A real-time implementation was not completed and would be particularly interesting for use as feedback for flight control. Study of load alleviation techniques may benefit. Another topic of study is the combination of this method with other measurements, such as accelerometers, to provide improved performance state estimation through sensor fusion.
Comparison Of Experimental And Theoretical Static Aeroelastic Loads And Deflections Of A Thin 45 Wing In Supersonic Flow
DOWNLOAD
Author : Floyd V. Bennett
language : en
Publisher:
Release Date : 1961
Comparison Of Experimental And Theoretical Static Aeroelastic Loads And Deflections Of A Thin 45 Wing In Supersonic Flow written by Floyd V. Bennett and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1961 with Aerodynamic load categories.
Wind tunnel tests showing the effects of static aeroelasticity for a thin 45° delta wing in supersonic flow are presented and compared with theory in the Mach number range 1.30 t o 4.00. Calculated deformations, normal-force coefficients, and pitching-moment coefficients based on a linearized potential theory for subsonic leading edges at a Mach number of 1.30 and a linearized potential theory for supersonic leading edges at Mach numbers of 1.64, 3.00, and 4.00 are shown to compare favorably with the wind-tunnel results.
A Selected Listing Of Nasa Scientific And Technical Reports For
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1960
A Selected Listing Of Nasa Scientific And Technical Reports For written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1960 with Aeronautics categories.
Reports And Memoranda Aeronautical Research Council
DOWNLOAD
Author : Aeronautical Research Council (Great Britain)
language : en
Publisher:
Release Date : 1972
Reports And Memoranda Aeronautical Research Council written by Aeronautical Research Council (Great Britain) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1972 with Aeronautics categories.
Nonlinear Thermoelastic Effects On Hypersonic Stability And Control
DOWNLOAD
Author : James R. Batt
language : en
Publisher:
Release Date : 1964
Nonlinear Thermoelastic Effects On Hypersonic Stability And Control written by James R. Batt and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1964 with Aerodynamics, Hypersonic categories.
Strain Gage Loads Calibration Testing Of The Active Aeroelastic Wing F A 18 Aircraft
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 2002
Strain Gage Loads Calibration Testing Of The Active Aeroelastic Wing F A 18 Aircraft written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with Airplanes categories.
This report describes strain-gage calibration loading through the application of known loads of the Active Aeroelastic Wing F/A-18 airplane. The primary goal of this test is to produce a database suitable for deriving load equations for left and right wing root and fold shear; bending moment; torque; and all eight wing control-surface hinge moments. A secondary goal is to produce a database of wing deflections mesured by string potentiometers and the onboard flight deflection measurement system. Another goal is to produce strain-gage data through both the laboratory data acquisition system and the onboard aircraft data system as a check of the aircraft system. Thirty-two hydraulic jacks have applied loads through whiffletrees to 104 tension-compression load pads bonded to the lower wing surfaces. The load pads covered approximately 60 percent of the lower wing surface.