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By Mark B. Tischler

ISBN-10: 1563478374

ISBN-13: 9781563478376

Offering confirmed tools, useful guidance, and real-world flight-test effects for a variety of state of the art flight autos, "Aircraft and Rotorcraft approach identity, moment variation" addresses the full strategy of plane and rotorcraft approach id from instrumentation and flight trying out to version selection, validation, and alertness of the implications. during this hugely expected moment variation, authors Tischler and Remple have extra devoted in-depth chapters providing prolonged version constructions and id effects for giant versatile shipping airplane, and the specified method to boost a continuing complete flight envelope simulation version from person procedure identity types and trim try out facts. issues mentioned contain: Frequency-response equipment which are particularly compatible for approach identity of flight car versions from flight-test facts; particular directions for flight checking out, info research, and the correct choice of version constitution complexity; and emphasis at the value of actual perception in version improvement and functions. distinctive beneficial properties: scholar model of CIFER[registered] with up to date graphical person interface utilizing MATLAB[registered]; a variety of flight-test effects for either manned and unmanned cars illustrating the wide-ranging roles of method id, together with the research of flight mechanics, suggestions keep an eye on, dealing with traits, subsystem dynamics, structural research, higher-order versions for airplane and rotorcraft, and simulation; and, wide challenge units on the finish of every bankruptcy, with many routines in accordance with flight-test info supplied for the XV-15 in hover and cruise giving the reader hands-on real-world event with method id tools and interpretation of the implications.

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Additional resources for Aircraft and Rotorcraft System Identification

Sample text

There is a wealth of useful information in this report for further study on rotorcraft applications of system identification. More About the Role of Nonparametric vs Parametric Models in Flight-Vehicle System Identification As we introduced in Sec. 1, there are two types of models to consider when discussing system identification: nonparametric and parametric models. 3. In the case of nonparametric models, we are concerned with characterizing only the measured input-to-output behavior of the aircraft dynamics, not the nature of the aircraft equations of motion.

Noise models must be identified. If the presence of noise is ignored (either output error or equation error formulation), it will introduce biases in the identification results. Independent measure provided Coherence function provides a direct and independent measure of system excitation, data quality, and system response linearity. No independent metric to assess system excitation and linearity. Responses Response pairs are fit only in the frequency range over which the data are accurate. 4 Characteristic (continued) Frequency-responsemethods Time-response methods Number of points Small number of points are included in iterative identification criterion, which improves computational efficiency.

2 aerodynamic angles, a, P INTRODUCTION AND BRIEF HISTORY t I I 0 20 40 I 60 Time (sec) 3 I I 80 100 Fig. 3 Typical frequency-sweepinput. effective format, used exclusively herein for presenting identification results in the frequency domain, is the Bode plot of the frequency-response function H, which displays log-magnitude (20 log,,(HI, dB) and phase (LH, deg) vs log-frequency (o, radls herein) on a semilog scale. A typical example is the Bode plot for aircraft sideslip response to rudder p/6, obtained from flight-test data shown injhe solid curve of Fig.

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Aircraft and Rotorcraft System Identification by Mark B. Tischler


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