Effects of vibration on inertial wind-tunnel model attitude measurement devices

Publisher: National Aeronautics and Space Administration, Langley Research Center, Publisher: National Technical Information Service, distributor in Hampton, Va, [Springfield, Va

Written in English
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  • Accelerometers.,
  • Angle of attack.,
  • Correction.,
  • Instrument errors.,
  • Vibration effects.,
  • Wind tunnel models.

Edition Notes

StatementClarence P. Young, Jr. ... [et al.].
SeriesNASA technical memorandum -- 109083.
ContributionsYoung, Clarence P., Langley Research Center.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL15403912M

[36] A. Hood and D.J. Pines, "A Multi-functional Sensor for Simulataneous Measurement of Structure-borne Sound and Vibration", 13th U.S. National Congress of Applied Mechanics, June 22 [37] D.J. Pines, "Damage Detection in Civil Structures Using Wave Propagation. Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats. The present book focus on uses and developments of wind tunnels. It consists on nine chapters presenting different studies on the design, uses and developments of the wind tunnel in different applications like wind turbines, building and aircraft models. An impediment to the use of seismic protection devices has been the difficulty for practicing engineers to design buildings with isolation system or damping devices. ASCE/SEI task committees charged with development of new generation of codes for seismic design and retrofit of buildings have updated the relevant code sections with one goal.

Experimental Determination of Measurement-System Parameters. Loading Effects under Dynamic Conditions. Probl Bibliography Measuring Devices 4 4 42 43 Motion and Dimensional Measurement Introduction Fundamental Standards Relative Displacement, Translational and Rotational Calibration. Resistive Potentiometers.4/5(15). MDA Modeling of the Attenuation Effects of the Atmosphere for IR/VIS Application; MDA High Performance Actuators for Solid Propulsion Control Systems; MDA Radiation Hardened Interceptor Seeker Sensor Technologies; MDA Software Enhancements to Improve Inertial Measurement Unit Performance. the wind tunnel walls are modeled as flat panels. The analysis captures the influence of the LRTA and the wind tunnel walls quite well down to µ ~ or , when the wake-induced flows on the wind tunnel walls probably separated, a feature not . The SPAW ARC further cited specific simulator improvements that the FAA should consider in developing improved standards for ice accretion models, such as the aerodynamic effects of lift, drag, and rotational moments (e.g. pitch, roll, and yaw effects) through means other than weight; the effects of icing on control feel, airframe buffeting.

Main Low Speed Wind Tunnel Testing. Low Speed Wind Tunnel Testing J. B. Barlow, W. H. Rae, Jr, A. Pope continues to be a cornerstone in the development for a wide range of vehicles and other devices that must perform their functions in the face of forces imposed You can write a book review and share your experiences. Other readers will. Library of Congress Cataloging-in-Publication Data (Revised for vol. 8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C. Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes.   Effects of High Humidity on PIDs. Like many sensors and measurement instrumentation, traditional PIDs can be affected by the environmental conditions such as those found in outdoor environments, in particular dirt and humidity. Humidity is a naturally occurring phenomenon and is present in the atmosphere and gasses. PDF; PDF; Print; Help NASA SBIR/STTR Program Support For questions about the NASA SBIR/STTR solicitations, the proposal preparation and electronic submission process, and other program related areas, please contact the NASA SBIR/STTR Program Support Office. Phone: Email: [email protected] NASA SBIR/STTR Program Support is available .

Effects of vibration on inertial wind-tunnel model attitude measurement devices Download PDF EPUB FB2

Effects of Vibration on Inertial Wind-Tunnel Model Attitude Measurement Devices Clarence P. Young, Jr. North Carolina State University, Raleigh, North Carolina Ralph D.

Buehrle Langley Research Center, Hampton, Virginia S. Balakrishna and W. Allen Kilgore Vigyan, Inc., Hampton, Virginia (NASA-TM-I) EFFECTS OF VIBRATION ON INERTIAL WIND-TUNNEL.

Get this from a library. Effects of vibration on inertial wind-tunnel model attitude measurement devices. [Clarence P Young; Langley Research Center.;]. 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.

The inertial device cannot distinguish between the gravity vector and the centrifugal accelerations associated with wind tunnel model vibration, this situation results in a model attitude.

for Vibration Sensitive Inertial Angle of Attack Measurement Devices Bradley L. Crawford and Tom D. Finley wind tunnel test results on a High Speed Research techniques usually require some vibration analysis once the model is mounted in the tunnel. These techniques.

An example is presented for the case of a laser diode mounted on a flexible post undergoing vibration. Using a single three-axis accelerometer, combined with a priori knowledge of the system's structural dynamics, pitch angle fluctuations on the order of deg were successfully estimated within deg : Robert R.

Long, Edward B. White, Nathan R. Tichenor, Kevin Kremeyer. There have been significant improvements in the sensors for estimating the basic meteorological parameters.

For determining the three-dimensional wind vector in high temporal and high spatial resolution, a miniaturized multi-hole probe (MHP) along with the Global Navigation Satellite System (GNSS) and inertial measurement unit (IMU) has been implemented [8,9,10].Cited by: Therefore, to mitigate these vibration effects, Brake designed an active inertial dampening to take care of frequencies of less than 5 Hz and the gimbal system mechanical design provides a good passive inertial dampening for frequencies on the order of 5–20 Hz.

For higher frequencies, the gimbal mounting system is responsible for dampening Author: Christopher Dahlin Rodin, Fabio Augusto de Alcantara Andrade, Anthony Reinier Hovenburg, Tor Arne Jo.

This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. This book documents the history of the Pioneer Venus program and the exploration of the Venusian atmosphere and surface.

The mission is reviewed from its initial planning in the late s to a history of the Pioneer spacecraft series leading up to Pioneer Venus, the launch of Pioneers 12 and the Orbiter and Multiprobe missions, including instrument. Air unsteady flow in wind tunnel test usually results in vibration of model support system, and large vibration can influence the accuracy and reliability of wind tunnel test.

To solve the vibration problem, piezoelectric structure with control program is applied to model support system to achieve active vibration control. A test rig is designed, fabricated and the parameters of the physical airfoil model and the connected ADVA are identified.

The feasibility of the ADVA for flutter suppression is assessed via a wind tunnel testing. The experimental results show that applying the closed-loop ADVA increases the airfoil flutter speed by %.

@article{osti_, title = {Investigation of Dynamic Aerodynamics and Control of Wind Turbine Sections Under Relevant Inflow/Blade Attitude Conditions}, author = {Naughton, Jonathan W.}, abstractNote = {The growth of wind turbines has led to highly variable loading on the blades. Coupled with the relative reduced stiffness of longer blades, the need to control.

On Janua Gemini spacecraft dynamics stability model also completed its test program providing dynamic stability coefficients for the spacecraft reentry at mach numbers to These tests completed all the originally scheduled wind tunnel testing for Project Gemini; however, three additional test programs had been initiated.

Li et al. studied the effects of sudden changes of wind loads as the train passing through a bridge tower or two trains passing each other by using the wind tunnel test rig with moving train models. Han et al. [ ] developed an experimental setup for measuring the aerodynamic characteristics of vehicles and the bridge in wind tunnel and then Cited by: 1.

CEAS European air and space conference. --On sub-pixel displacement estimation used for particle image velocimetry --On results' accuracy at two-dimensional wind tunnel testing in-orbit demonstration space platform --The development of a redundant inertial measurement unit --Creating aero-databases by adaptive.

In this work: (1) the ground effect on vehicle dynamics is studied using a new model and experimental validation of the model is performed, (2) a nonlinear-disturbance observer (NDO) is designed and implemented for motion control, and finally, and (3) an IGE model-based feed-forward controller is developed for motion by: 2.

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Attenuation Errors in Airborne Pressure Sensing Devices,” NASA TM, May Moes, Timothy R. and Whitmore, Stephen A., “A Preliminary Look at Techniques Used to Obtain Airdata From Flight at High Angles of Attack,” NASA TM, Dec.

Gracey, William, “Wind-Tunnel Investigation of a Number of Total-Pressure Tubes. But they also concede that these devices have a part to play in the management of HAVS exposure when used as a ‘tool timer’ linked to properly measured tool vibration levels.

And by proper that means to the relevant part of standards like ANSI S (or BS EN ISO in the UK) using instrumentation conforming to ISO and undertaken by. Hybrid Fault Detection and Isolation Techniques for Aircraft Inertial Measurement Sensors.

Seungkeun Kim, Insung Jung, Wind Tunnel Test of an RPV with Shape-Change Effector and Sensor Arrays. David Raney, Randolph Cabell, Spacecraft Attitude and Orbit Control • Tuesday, 17 August • hrs. After a long time I have come across this book.

It deals with first principles and has included many case studies. It will be helpful for researchers, designers & applied engineers.

26 March () Post a Review You can write a book review and share your experiences. Other readers will always be interested in your opinion of the books you.

Wind tunnel balances, elements of computer-based instrumentation, measurements and analyses methods. Elements of high speed wind tunnel testing: design aspects to supersonic and hypersonic wind-tunnels, other high speed facilities like shock tube shock tunnels, free piston tunnels, ballistic ranges and low density tunnels, special aspects of.

This book provides an authoritative and practical presentation of the determination of gust loads on airplanes, especially continuous turbulence gust loads. The text emphasizes the basic concepts involved in gust load determination and enriches the material with discussion of important relationships, definitions of terminology and nomenclature.

Structural landing test model (SLTM). A 3/8, geometrically scaled model of the lander, dropped at various velocities and attitudes to determine landing stability boundaries. The 3/8 scale was chosen because the Martian gravity was 3/8 that of Earth's.

Thermal-effects test model (TETM). A full-scale model incorporating developmental thermal. Data may be acquired through the use of an inertial measurement system and a synchronized video of calibrated airplane instruments; a temporary, high resolution bank angle scale affixed to the attitude indicator; and a wheel and column force measurement indication 2.c Handling qualities.

Longitudinal control tests. Longitudinal static T(P0): ±10% of P0. Low-speed wind-tunnel investigation of forward-located spoilers and trailing splines as trailing-vortex hazard-alleviation devices on an aspect-ratio-8 wing model / (Washington, D.C.: National Aeronautics and Space Administration ; [Springfield, Va.

The attitude control of fixed-wing MAVS in turbulent environments. Thus if one were to make a 1/th scale model of a C with a m wingspan, one would expect the time constant to be on the order of s (versus 1 s for the C, under the assumption that the C has acceptable roll time constants).

Stack J. Tests in the Cited by:. Large-Scale Wind-Tunnel Tests of An Airplane Model With Two Propellers and Rotating Cylinder Flaps: James A Weilberg and Berl Gamse: NASA: TN D NASA TN: Langford, Mark: UAH: Large-Scale Wind-tunnel Investigation of An Airplane Model with A Tilt Wing of Aspect Ratioand Four Propellers, in the Presence of A Ground Plane.AF Effects of sustained vibration and high temperature environments on polymer bonded composite materials AF Chip-scale Inertial Measurement System AF Missile Motor Cutting Technology.Scott D.

Holland, Wind-Tunnel Blockage and Actuation Systems Test of a Two-Dimensional Scramjet Inlet Unstart Model at Mach 6, NASA TM, Novemberpp.

Michael L. Nelson, Gretchen L. Gottlich and David J. Bianco, World Wide Web Implementation of the Langley Technical Report Server, NASA TM, Septemberpp.