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  • 1
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    MEMS/NEMS : Handbook Techniques and Applications (2006)
    Boston, MA : Springer
    Details
    Keywords: Electronics ; Engineering design ; Mechanical engineering ; Nanotechnology ; Optical materials
    ISBN: 9780387257860
    URL: https://doi.org/10.1007/b136111
    Language: English
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    E-BOOK
  • 2
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    Inertial Navigation for Aircraft (1970)
    Springer Nature
    Details
    Publication Date: 1970-03-01
    Print ISSN: 0036-8733
    Electronic ISSN: 1946-7087
    Topics: Biology , Natural Sciences in General , Physics
    Published by Springer Nature
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    PAPER CURRENT
  • 3
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    An optimization approach to the design of frequency sampling filters implemented with finite word length architectures (1993)
    Elsevier
    Details
    Publication Date: 1993-05-01
    Print ISSN: 0016-0032
    Electronic ISSN: 1879-2693
    Topics: Mathematics , Technology
    Published by Elsevier
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    PAPER CURRENT
  • 4
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    Development of a pneumatic high-angle-of-attack Flush Airdata Sensing (HI-FADS) system (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The HI-FADS system design is an evolution of the FADS systems (e.g., Larson et al., 1980, 1987), which emphasizes the entire airdata system development. This paper describes the HI-FADS measurement system, with particular consideration given to the basic measurement hardware and the development of the HI-FADS aerodynamic model and the basic nonlinear regression algorithm. Algorithm initialization techniques are developed, and potential algorithm divergence problems are discussed. Data derived from HI-FADS flight tests are used to demonstrate the system accuracies and to illustrate the developed concepts and methods.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: In: Control and dynamic systems. Vol. 52 - Integrated technology methods and applications in aerospace systems design (A94-12611 02-01); p. 453-511.
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Pneumatic distortion compensation for aircraft surface pressure sensing devices (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: In this paper a technique of compensating for pneumatic distortion in aircraft surface pressure sensing devices is developed. The compensation allows conventional pressure sensing technology to obtain improved unsteady pressure measurements. Pressure distortion caused by frictional attenuation and pneumatic resonance within the sensing system makes obtaining unsteady pressure measurements by conventional sensors difficult. Typically, most of the distortion occurs within the pneumatic tubing used to transmit pressure impulses from the surface of the aircraft to the measurement transducer. This paper develops a second-order distortion model that accurately describes the behavior of the primary wave harmonic of the pneumatic tubing. The model is expressed in state-variable form and is coupled with standard results from minimum-variance estimation theory to develop an algorithm to compensate for the effects of pneumatic distortion. Both postflight and real-time algorithms are developed and evaluated using simulated and flight data. Covariance selection and filter-tuning examples are presented. Results presented verify that, given appropriate covariance magnitudes, the algorithms accurately reconstruct surface pressure values from remotely sensed pressure measurements.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Aircraft (ISSN 0021-8669); 28; 828-836
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Failure detection and fault management techniques for flush airdata sensing systems (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Methods based on chi-squared analysis are presented for detecting system and individual-port failures in the high-angle-of-attack flush airdata sensing system on the NASA F-18 High Alpha Research Vehicle. The HI-FADS hardware is introduced, and the aerodynamic model describes measured pressure in terms of dynamic pressure, angle of attack, angle of sideslip, and static pressure. Chi-squared analysis is described in the presentation of the concept for failure detection and fault management which includes nominal, iteration, and fault-management modes. A matrix of pressure orifices arranged in concentric circles on the nose of the aircraft indicate the parameters which are applied to the regression algorithms. The sensing techniques are applied to the F-18 flight data, and two examples are given of the computed angle-of-attack time histories. The failure-detection and fault-management techniques permit the matrix to be multiply redundant, and the chi-squared analysis is shown to be useful in the detection of failures.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AIAA PAPER 92-0263
    Format: text
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  • 7
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    Compensating for pneumatic distortion in pressure sensing devices (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A general numerical technique for obtaining unsteady pressure measurements using conventional pressure sensing technology has been developed. A pneumatic distortion model, based on the Navier-Stokes equations of momentum and continuity, was reduced to a low-order, state-variable model retaining most of the dynamic characteristics of the full model. The reduced-order model is coupled with results from minimum variance estimation theory to develop an algorithm to compensate the effects of pneumatic distortion. Both postflight and real-time algorithms were developed and evaluated using simulated and flight data.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 90-0631
    Format: text
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  • 8
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    Failure detection and fault management techniques for flush airdata sensing systems (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A high-angle-of-attack flush airdata sensing system was installed and flight tested on the F-18 High Alpha Research Vehicle at NASA-Dryden. This system uses a matrix of pressure orifices arranged in concentric circles on the nose of the vehicle to determine angles of attack, angles of sideslip, dynamic pressure, and static pressure as well as other airdata parameters. Results presented use an arrangement of 11 symmetrically distributed ports on the aircraft nose. Experience with this sensing system data indicates that the primary concern for real-time implementation is the detection and management of overall system and individual pressure sensor failures. The multiple port sensing system is more tolerant to small disturbances in the measured pressure data than conventional probe-based intrusive airdata systems. However, under adverse circumstances, large undetected failures in individual pressure ports can result in algorithm divergence and catastrophic failure of the entire system. How system and individual port failures may be detected using chi sq. analysis is shown. Once identified, the effects of failures are eliminated using weighted least squares.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: NASA-TM-4335 , H-1780 , NAS 1.15:4335 , Aerospace Sciences Meeting; Jan 06, 1992 - Jan 09, 1992; Reno, NV; United States
    Format: application/pdf
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  • 9
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    Compensating for pneumatic distortion in pressure sensing devices (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A technique of compensating for pneumatic distortion in pressure sensing devices was developed and verified. This compensation allows conventional pressure sensing technology to obtain improved unsteady pressure measurements. Pressure distortion caused by frictional attenuation and pneumatic resonance within the sensing system makes obtaining unsteady pressure measurements by conventional sensors difficult. Most distortion occurs within the pneumatic tubing which transmits pressure impulses from the aircraft's surface to the measurement transducer. To avoid pneumatic distortion, experiment designers mount the pressure sensor at the surface of the aircraft, (called in-situ mounting). In-situ transducers cannot always fit in the available space and sometimes pneumatic tubing must be run from the aircraft's surface to the pressure transducer. A technique to measure unsteady pressure data using conventional pressure sensing technology was developed. A pneumatic distortion model is reduced to a low-order, state-variable model retaining most of the dynamic characteristics of the full model. The reduced-order model is coupled with results from minimum variance estimation theory to develop an algorithm to compensate for the effects of pneumatic distortion. Both postflight and real-time algorithms are developed and evaluated using simulated and flight data.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-101716 , H-1586 , NAS 1.15:101716 , AIAA 28th Aerospace Sciences Meeting; Jan 08, 1990 - Jan 11, 1990; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Estimating Fluctuating Pressures From Distorted Measurements (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Two algorithms extract estimates of time-dependent input (upstream) pressures from outputs of pressure sensors located at downstream ends of pneumatic tubes. Effect deconvolutions that account for distoring effects of tube upon pressure signal. Distortion of pressure measurements by pneumatic tubes also discussed in "Distortion of Pressure Signals in Pneumatic Tubes," (ARC-12868). Varying input pressure estimated from measured time-varying output pressure by one of two deconvolution algorithms that take account of measurement noise. Algorithms based on minimum-covariance (Kalman filtering) theory.
    Keywords: MECHANICS
    Type: ARC-12844 , NASA Tech Briefs (ISSN 0145-319X); 18; 2; P. 75
    Format: text
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