Download Aircraft and Rotorcraft System Identification by Mark B. Tischler PDF

By Mark B. Tischler

Offering confirmed equipment, functional guidance, and real-world flight-test effects for quite a lot of cutting-edge flight automobiles, "Aircraft and Rotorcraft method id, moment version" addresses the total strategy of airplane and rotorcraft process identity from instrumentation and flight checking out to version selection, validation, and alertness of the implications. during this hugely expected moment variation, authors Tischler and Remple have further committed in-depth chapters providing prolonged version buildings and identity effects for giant versatile delivery airplane, and the designated technique to boost a continuing complete flight envelope simulation version from person procedure id types and trim try out information. themes mentioned contain: Frequency-response equipment which are specifically compatible for approach id of flight motor vehicle types from flight-test info; particular instructions for flight trying out, information research, and the right kind choice of version constitution complexity; and emphasis at the significance of actual perception in version improvement and functions. specified good points: scholar model of CIFER[registered] with up to date graphical person interface utilizing MATLAB[registered]; a number of flight-test effects for either manned and unmanned cars illustrating the wide-ranging roles of approach identity, together with the research of flight mechanics, suggestions keep watch over, dealing with traits, subsystem dynamics, structural research, higher-order types for airplane and rotorcraft, and simulation; and, broad challenge units on the finish of every bankruptcy, with many workouts in accordance with flight-test info supplied for the XV-15 in hover and cruise giving the reader hands-on real-world adventure with approach identity equipment and interpretation of the implications.

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Extra info for Aircraft and Rotorcraft System Identification

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Instead, a quick frequency-sweep test and system identification can rapidly provide the needed dynamic models for flight mechanics characterization and control law tuning. ,I2 which covers UAV experience at the Ames Research Center during the period 1995-2003. INTRODUCTION AND BRIEF HISTORY Sensor accuracy Ikinematic consistency Drastic time reduction wrt dwell-decay methods Accurate models of all systemslsubsystems Real-time envelope expansion Icontrol optimization Eliminationof hunt and peck solution methods Rapid solution to integrated problems Spec compliance q FCS Software valid Accurate hardware models Dynamic analysis of WT data Integratedsystem perf Idelays Nonlinearities 13 Stab margins for notch filter design Sensor placement Select model-followingdynamics Starting point for 'paper trail' / ICom~lewdistributed model verification1 Linear model determhralid Accurate sim model from prototypes Control system tuning &evaluation Lower-order models Visual Imotion fidelity Math model fidelitv Engineering approach to modeiimprovemant Characterize pilot workload IDetermine hardware bandwidth requirements Validate control law implementation Effects of higher-order dynamics I I Fig.

One role of system identification is to quantify where the actual and predicted motions do not match and to provide information on proper tuning for improved prediction accuracy. In that respect the two procedures, one forward and one inverse, are highly complimentary. Key applications of system-identification results include piloted simulation models, comparison of wind-tunnel vs flight measurements, validation and improvement of physics-based simulation models, flight-control system development and validation, and handling-qualities specification compliance testing.

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.

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