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  • 1
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    Status of wind tunnel magnetic suspension research (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper reports the status of the NASA Langley Research Center program aimed at the development of the technology required for large-scale Magnetic Suspension and Balance Systems. The use of magnetic suspension of the model in a wind tunnel is seen to be the only viable method to eliminate aerodynamic interference problems arising with mechanical model-supports. The two small-scale magnetic suspension systems in operation at Langley are the only ones now active in the U.S. The general features and capabilities of these two systems and all of the ongoing research in the use of magnetic suspension are described.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: SAE PAPER 851898
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Dynamic response tests of inertial and optical wind-tunnel model attitude measurement devices (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-109182 , NAS 1.15:109182
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Electrical Properties and Power Considerations of a Piezoelectric Actuator (1999)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: This paper assesses the electrical characteristics of piezoelectric wafers for use in aeronautical applications such as active noise control in aircraft. Determination of capacitive behavior and power consumption is necessary to optimize the system configuration and to design efficient driving electronics. Empirical relations are developed from experimental data to predict the capacitance and loss tangent of a PZT5A ceramic as nonlinear functions of both applied peak voltage and driving frequency. Power consumed by the PZT is the rate of energy required to excite the piezoelectric system along with power dissipated due to dielectric loss and mechanical and structural damping. Overall power consumption is thus quantified as a function of peak applied voltage and driving frequency. It was demonstrated that by incorporating the variation of capacitance and power loss with voltage and frequency, satisfactory estimates of power requirements can be obtained. These relations allow general guidelines in selection and application of piezoelectric actuators and driving electronics for active control applications.
    Keywords: Electronics and Electrical Engineering
    Format: application/pdf
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  • 4
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    Determining Calibration Constants for Attitude Measurements (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Algorithm based on method of least squares determines calibration constants of seismic instruments for precise attitude measurements. Algorithm programed and run successfully on commercially available desk-top computer. Simplifies determinations of accelerometer calibration constants, and used in field to verify accelerometer stability.
    Keywords: PHYSICAL SCIENCES
    Type: LAR-13214 , NASA Tech Briefs (ISSN 0145-319X); 9; 4; P. 95
    Format: text
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  • 5
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    Two-Axis, Self-Nulling Skin-Friction Balance (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Two-dimensional aerodynamic skin-friction force measured directly. Disk-shaped prototype design has overall dimensions of 1.25 (3.18 centimeters) diameter and 0.5 inch (1.27 centimeters) height. Unique mechanism consisting of two flexural pivoted arms connected in tandem but at right angle with each other designed to impart plane motion needed to sense two-axis flow over sensing element of balance. Sensing element, 0.370 inch (0.940 centimeter) in diameter, attached to end of second arm is servoed by two restoring-force motors orthogonally mounted in plane of airflow. Mechanism allows free plane motion of sensing element with no friction, and balance self-nulled to provide direct plane skin-friction force measurements continuously.
    Keywords: MECHANICS
    Type: LAR-13294 , NASA Tech Briefs (ISSN 0145-319X); 10; 3 P; P. 97
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Measurement of forces and moments from a thrust vector controlled rocket on a five component test stand. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Test stand for measurement of forces and moments from thrust vector controlled rocket, analyzing dynamic characteristics of hydrostatic supports
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: GUIDANCE AND CONTROL IN SPACE, INTERNATIONAL FEDERATION OF AUTOMATIC CONTROL, CONGRESS; Jun 16, 1969 - Jun 21, 1969; WARSAW; POLAND
    Format: text
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  • 7
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    The dynamic characteristics of a five component oscillating balance (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Frequency response of five component strain gage oscillating balance for dynamic wind tunnel stability testing
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: INTERNATIONAL AEROSPACE INSTRUMENTATION SYMPOSIUM; May 10, 1971 - May 12, 1971; LAS VEGAS, NV
    Format: text
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  • 8
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    The design, analysis and application of a practical vibrational platform (1977)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The design, analysis and application of a unique vibrational platform employing flexural pivots is described. A Lagrangian equation for the slightly-damped second-order system was derived and verified experimentally. Platform frequencies from 0.7 to 20 Hz with an extremely low damping coefficient were observed. Various educational and instrumentation applications of this simple mechanical system are included.
    Keywords: QUALITY ASSURANCE AND RELIABILITY
    Type: Spring Meeting of Society for Experimental Stress Analysis; May 15, 1977 - May 20, 1977; Dallas, TX
    Format: text
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  • 9
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    Experiment and analysis on the flow process dynamics of the NASA-Langley eight foot transonic pressure tunnel (1977)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A dynamic response test performed in a eight foot transonic pressure tunnel is described. The dynamics of the flow process of the wind tunnel at transonic conditions were obtained. Descriptions of the test conditions, instrumentation, presentation of raw data, analysis of data, and finally, based on experimental evidences, an attempt to construct an input output relationship of the flow process from the viewpoints of control engineering are included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-154806
    Format: application/pdf
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  • 10
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    Transient response characteristics of test chamber Mach number (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The transient dynamic characteristics of a test chamber Mach number was established for a disturbance initiated in the test chamber. An approximate linear expression was given, showing that the change in the Mach number is linearly proportional to the algebraic sum of the static pressure change in the test chamber and the stagnation pressure change. The static pressure change is the dominating factor. The two pressure changes were also calculated for small Mach number variations, and these results were applied to instrumentation requirements.
    Keywords: AERODYNAMICS
    Type: NASA-CR-147919 , TR-76-T9
    Format: application/pdf
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