CIFERÂ®-MATLAB Interfaces: Development and ... - Cal Poly

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Nomenclature ax Longitudinal Acceleration φ Roll Attitude ay az b e f G k L Lateral Acceleration Vertical Acceleration Damping Coefficient Error Channel Feedback Channel Autospectrum Spring Coefficient Length φ γ θ τ τ p ω 180 ψ Phase Angle Coherence Pitch Attitude Time Constant Phase Delay 180-Degree Frequency Yaw Attitude M Mass N Scale Factor p Roll Body Rate q Pitch Body Rate r Yaw Body Rate s U 0 Frequency Domain Variable Longitudinal Velocity Subscripts u V 0 v W 0 w Y X α β δ Longitudinal Body Acceleration Lateral Velocity Lateral Body Acceleration Vertical Velocity Vertical Body Acceleration Output Input Angle of Attack Sideslip Command Channel a ail dot ele m rud whl xx xy yy Actual Vehicle Aileron Time Derivative Elevator Model Vehicle Rudder Wheel Input Cross Output x
Chapter 1: Introduction The focus of this thesis is directed towards tools that aid in system identification. System identification is the process of taking measured data from a physical system and analyzing it to develop a mathematical model of that system. This is an important aspect of control system design as it allows for the validation of simulated system models, optimization of existing control systems, and handling qualities specification compliance. Figure 1.1 shows how system identification fits into a design cycle. Assumptions Model Simulation Predicted Aircraft Motion Physical Understanding Model System Identification Measured Aircraft Motion Figure 1.1: The Role of System Id Starting at the top left of Figure 1.1, assumptions are made that result in some form of mathematical model, which describes an aircraft. The model can then be applied to a simulation that will predict the motion of the aircraft. Once a physical model of the aircraft is constructed, physical measurements can be made of its actual motion and responses to input. System identification can then be used to extract a new mathematical model of the aircraft. The new model can be compared to the old model and the assumptions used to create it for greater physical understanding of the aircraft’s motion. The mathematical model created through system identification can either be nonparametric or parametric. Nonparametric models do not assume an order or structure. They can exist either in the time-domain as an impulse response or in the frequency-domain as a frequency response. 1
Page 1 and 2: CIFER ® -MATLAB Interfaces: Develo
Page 3 and 4: Approval Page TITLE: AUTHOR: CIFER
Page 5 and 6: Acknowledgements The author would l
Page 7 and 8: 4.4 ANALYSIS ON SHADOW 200 TUAV....
Page 9: Figure 4.21: Comparisons with Exact
Page 13 and 14: 1.1.1 What CIFER ® Encompasses CIF
Page 15 and 16: Figure 1.3: Doublet Example (UAV Fl
Page 17 and 18: One almost universal concern with t
Page 19 and 20: involving handling qualities analys
Page 21 and 22: One key feature of frequency respon
Page 23 and 24: and high-frequency content is captu
Page 25 and 26: Thus the low-frequency content of l
Page 27 and 28: consistency by reconstructing respo
Page 29 and 30: Chapter 3: Programming and Code Dev
Page 31 and 32: interpret it, how to condition it,
Page 33 and 34: Figure 3.1: Name-value Pairs and St
Page 35 and 36: Figure 3.2: Percent Error Compariso
Page 37 and 38: command-line-based interface that r
Page 39 and 40: 3.2.1 Development Process The most
Page 41 and 42: The third screen is used to match w
Page 43 and 44: Chapter 4: Validation and Applicati
Page 45 and 46: Figure 4.2: SISO Mass-Spring-Damper
Page 47 and 48: 4.3 UH-60 Simulation The first in-d
Page 49 and 50: The differences between the two cal
Page 51 and 52: Table 4.3: Cutoff Frequency Results
Page 53 and 54: Two sets of data were used: one was
Page 55 and 56: Figure 4.14: Roll Angle to Rate Com
Page 57 and 58: The same checks were run on the fli
Page 59 and 60: Figure 4.20: Vertical Velocity Pert
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Figure 4.22: Aileron - Roll Rate Re
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CIFER ® offers a utility for analy
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La Length: Lm = [4.14] N τ a Time
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UAV might conceivably achieve bandw
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FRESPID and MISOSA have been create
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Bibliography Works Cited: 1.) Hamel
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Appendix A: Screen Layout Compariso
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New GUI Interface: Figure A6: MATLA
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Figure A10: MATLAB GUI: Final Scree
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CIFER ® main programs The three ma
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out_f = frespid('XVLATSWP',1); >> o
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The variables that support screen 8
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as input and up to five outputs to
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All the information is displayed to
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to either the linearized phase and
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CIFER ® support utilities: Three f
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Appendix C: Online Help for Main Pr
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id.maxfft SCREEN 9 id.plotopt id.pl
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[out] = composite('TEST',2,'casenam
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misosa Structure fields are: casena
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Function: cifhq Description: This f
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the results will be displayed in th
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in.source SCREEN 2 in.pminfrq in.pm
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cifarith Structure fields are: name
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and magnitude must be included. Oth
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c_in.outputs(1) c_in.frcalc(1,1) c_
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% Set up blank composite case c_in
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