An Analytic Investigation Of Accuracy Requirements For Onboard Instrumentation And Film Data For Dynamically Scaled Wind Tunnel Drop Models PDF Download
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| Author | : K. S. Keen |
| Publisher | : |
| Total Pages | : 122 |
| Release | : 1997 |
| Genre | : Equations of motion |
| ISBN | : |
Download An Analytic Investigation of Accuracy Requirements for Onboard Instrumentation and Film Data for Dynamically Scaled Wind Tunnel Drop Models Book in PDF, ePub and Kindle
An analytic study was conducted to evaluate anticipated ranges and required accuracies for onboard linear acceleration and angular rate (or acceleration) measurement equipment to be mounted within dynamically scaled wind tunnel drop models. Generic simulations of the separation motion of a tumbling fuel tank both at full scale and at 1/15th wind tunnel model scale were generated using an analytic trajectory simulation program coupled with a prescribed aerodynamic database. The simulations provide a basis for sizing the required instrumentation for proof of concept demonstrations of telemetry techniques in the wind tunnel. The simulations were also used as test cases to demonstrate extraction of aerodynamic information from drop data positions and orientations as read from film records via an inverse solution of the store equations of motion. The studies also aid identification and evaluation of inaccuracies associated with the basic dynamic scaling laws and standard film based data reduction techniques.
| Author | : |
| Publisher | : |
| Total Pages | : 120 |
| Release | : 1997 |
| Genre | : |
| ISBN | : |
Download An Analytic Investigation of Accuracy Requirements for Onboard Instrumentation and Film Data for Dynamically Scaled Wind Tunnel Drop Models Book in PDF, ePub and Kindle
An analytic study was conducted to evaluate anticipated ranges and required accuracies for onboard linear acceleration and angular rate (or acceleration) measurement equipment to be mounted within dynamically scaled wind tunnel drop models. Generic simulations of the separation motion of a tumbling fuel tank both at full scale and at 1/15th wind tunnel model scale were generated using an analytic trajectory simulation program coupled with a prescribed aerodynamic database. The simulations provide a basis for sizing the required instrumentation for proof of concept demonstrations of telemetry techniques in the wind tunnel. The simulations were also used as test cases to demonstrate extraction of aerodynamic information from drop data positions and orientations as read from film records via an inverse solution of the store equations of motion. The studies also aid identification and evaluation of inaccuracies associated with the basic dynamic scaling laws and standard film based data reduction techniques.
| Author | : Irving C. Statler |
| Publisher | : |
| Total Pages | : 153 |
| Release | : 1967 |
| Genre | : Airplanes |
| ISBN | : |
Download The Development and Evaluation of the CAL/Air Force Dynamic Wind-tunnel Testing System Book in PDF, ePub and Kindle
The Cornell Aeronautical Laboratory (CAL) system provides a unique mounting through which a model can be forced precisely in any desired planar sinusoidal motion. The versatility and overall accuracy of the CAL/Air Force dynamic testing system was demonstrated during a series of wind-tunnel tests. These tests permitted, for the first time, a measurement of the separate components of the rotary damping moment. The moment due to rate of change of angle of attack was measured by oscillating the model in pure plunging motion. The moment due to pitch rate was measured during pitching motion. The sum of these is compared with the total rotary damping moment as measured in rotation. Comparisons of data taken at two frequencies and four Mach numbers indicate that the components are accurate to within plus or minus ten percent of the total rotary damping moment. The results are compared with theory, flight test data, and other wind-tunnel measurements on the same and similar models. Future applications of this equipment are reviewed, particularly with regard to its use as a research tool to support basic investigations for the development of theoretical or semiempirical methods for predicting dynamic stability characteristics of aircraft at transonic speeds. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 782 |
| Release | : 1995 |
| Genre | : Science |
| ISBN | : |
Download Government Reports Announcements & Index Book in PDF, ePub and Kindle
| Author | : |
| Publisher | : |
| Total Pages | : 1162 |
| Release | : 1986 |
| Genre | : Aeronautics |
| ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
| Author | : National Aeronautics and Space Adm Nasa |
| Publisher | : Independently Published |
| Total Pages | : 28 |
| Release | : 2018-12-30 |
| Genre | : |
| ISBN | : 9781792687150 |
Download Modal Correction Method for Dynamically Induced Errors in Wind-Tunnel Model Attitude Measurements Book in PDF, ePub and Kindle
This paper describes a method for correcting the dynamically induced bias errors in wind tunnel model attitude measurements using measured modal properties of the model system. At NASA Langley Research Center, the predominant instrumentation used to measure model attitude is a servo-accelerometer device that senses the model attitude with respect to the local vertical. Under smooth wind tunnel operating conditions, this inertial device can measure the model attitude with an accuracy of 0.01 degree. During wind tunnel tests when the model is responding at high dynamic amplitudes, the inertial device also senses the centrifugal acceleration associated with model vibration. This centrifugal acceleration results in a bias error in the model attitude measurement. A study of the response of a cantilevered model system to a simulated dynamic environment shows significant bias error in the model attitude measurement can occur and is vibration mode and amplitude dependent. For each vibration mode contributing to the bias error, the error is estimated from the measured modal properties and tangential accelerations at the model attitude device. Linear superposition is used to combine the bias estimates for individual modes to determine the overall bias error as a function of time. The modal correction model predicts the bias error to a high degree of accuracy for the vibration modes characterized in the simulated dynamic environment. Buehrle, R. D. and Young, C. P., Jr. Langley Research Center NASA-TM-111560, NAS 1.15:111560 ...
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 42 |
| Release | : 2018-05-22 |
| Genre | : |
| ISBN | : 9781719395175 |
Download Dependence of Dynamic Modeling Accuracy on Sensor Measurements, Mass Properties, and Aircraft Geometry Book in PDF, ePub and Kindle
The NASA Generic Transport Model (GTM) nonlinear simulation was used to investigate the effects of errors in sensor measurements, mass properties, and aircraft geometry on the accuracy of identified parameters in mathematical models describing the flight dynamics and determined from flight data. Measurements from a typical flight condition and system identification maneuver were systematically and progressively deteriorated by introducing noise, resolution errors, and bias errors. The data were then used to estimate nondimensional stability and control derivatives within a Monte Carlo simulation. Based on these results, recommendations are provided for maximum allowable errors in sensor measurements, mass properties, and aircraft geometry to achieve desired levels of dynamic modeling accuracy. Results using additional flight conditions and parameter estimation methods, as well as a nonlinear flight simulation of the General Dynamics F-16 aircraft, were compared with these recommendations Grauer, Jared A. and Morelli, Eugene A. Langley Research Center DYNAMIC MODELS; MATHEMATICAL MODELS; FLIGHT SIMULATION; ERRORS; AIRCRAFT INSTRUMENTS; MEASURING INSTRUMENTS; SYSTEM IDENTIFICATION; COMPUTER AIDED DESIGN; MONTE CARLO METHOD; AIRCRAFT STABILITY
| Author | : National Aeronautics and Space Administration (NASA) |
| Publisher | : Createspace Independent Publishing Platform |
| Total Pages | : 46 |
| Release | : 2018-07-02 |
| Genre | : |
| ISBN | : 9781722186227 |
Download Dynamic Response Tests of Inertial and Optical Wind-Tunnel Model Attitude Measurement Devices Book in PDF, ePub and Kindle
Results are presented for an experimental study of the response of inertial and optical wind-tunnel model attitude measurement systems in a wind-off simulated dynamic environment. This study is part of an ongoing activity at the NASA Langley Research Center to develop high accuracy, advanced model attitude measurement systems that can be used in a dynamic wind-tunnel environment. This activity was prompted by the inertial model attitude sensor response observed during high levels of model vibration which results in a model attitude measurement bias error. Significant bias errors in model attitude measurement were found for the measurement using the inertial device during wind-off dynamic testing of a model system. The amount of bias present during wind-tunnel tests will depend on the amplitudes of the model dynamic response and the modal characteristics of the model system. Correction models are presented that predict the vibration-induced bias errors to a high degree of accuracy for the vibration modes characterized in the simulated dynamic environment. The optical system results were uncorrupted by model vibration in the laboratory setup. Buehrle, R. D. and Young, C. P., Jr. and Burner, A. W. and Tripp, J. S. and Tcheng, P. and Finley, T. D. and Popernack, T. G., Jr. Langley Research Center RTOP 505-59-54-01...
| Author | : Emanuel Rind |
| Publisher | : |
| Total Pages | : 68 |
| Release | : 1979 |
| Genre | : Aeronautical instruments |
| ISBN | : |
Download Instrument Error Analysis as it Applies to Wind-tunnel Testing Book in PDF, ePub and Kindle
| Author | : |
| Publisher | : |
| Total Pages | : 128 |
| Release | : 2007-08 |
| Genre | : |
| ISBN | : |
Download Popular Science Book in PDF, ePub and Kindle
Popular Science gives our readers the information and tools to improve their technology and their world. The core belief that Popular Science and our readers share: The future is going to be better, and science and technology are the driving forces that will help make it better.
