Comprehensive System Identification of Ducted Fan UAVs - Cal Poly

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Figure 1.4 – Trek Aerospace Solotrek Ducted Fan – 2001Figure 1.5 – Allied Aerospace i-Star MAV 9” Vehicle – 2003Figure 1.2 depicts the Hiller flying platform. This vehicle underwent some testingof the pitching moment characteristics of ducted fans back in 1958 3 . For this purpose itwas included in the study. Figure 1.3 shows the Aerovironment/Honeywell teamed efforttechnology demonstrator for DARPA. This vehicle was used for flight testing andparametric modeling as well as for the identification of sensor packages. Figure 1.4shows the Trek Aerospace Solotrek. This unique design underwent comprehensive wind- 4 -
tunnel testing to study the characteristics of the ducted fan at varying propeller speeds.Finally, Figure 1.5 shows the Allied Aerospace i-Star MAV vehicle. Pictured is the 9”diameter vehicle. There is also a bigger cousin with a 29” diameter. Both of thesevehicles were used for actuator identification, flight testing, and simulation as part ofwork for DARPA. Figure 1.6 shows a detailed view of the MAV.Figure 1.6 – Detailed view of 9” MAV DesignThe basic design of the ducted fan UAV incorporates a small COTS power plantthat is centered inside a duct. The flow of air in the duct is passed over stators for flowstraightening and over vanes which allow actuation to generate moments. Figure 1.7shows the vanes and stators on the bottom of the 9” MAV design.- 5 -
Page 1 and 2: Comprehensive System Identification
Page 3 and 4: APROVAL PAGETITLE:AUTHOR:Comprehens
Page 5 and 6: ACKNOWLEDGMENTSThe author would lik
Page 7 and 8: 3.4.4 Magnetometer Identification..
Page 9 and 10: LIST OF FIGURESFigure 1.1 - Land Wa
Page 11 and 12: Figure 3.48 - Magnetometer Depictio
Page 13 and 14: CHAPTER 1 - INTRODUCTION AND MOTIVA
Page 15: The vehicles examined within the sc
Page 19 and 20: Figure 1.8 - Helicopter Body Axes S
Page 21 and 22: GPSRate GyrosAccelerometersIMUInner
Page 23 and 24: CHAPTER 2 - METHODS AND TECHNIQUES2
Page 25 and 26: 2.2.1 Flight Test TechniquesThere a
Page 27 and 28: manufacturer specifications are mod
Page 29 and 30: 3.2 Bare-Airframe IDThe bare-airfra
Page 31 and 32: Table 3.2 - OAV Frequency Range of
Page 33 and 34: ⎧ p⎫⎪ ⎪y = ⎨q⎬⎪ r ⎪
Page 35 and 36: Table 3.4 - OAV DERIVID Identified
Page 37 and 38: The identified state-space model yi
Page 39 and 40: Better sensors, at higher sampling
Page 41 and 42: Figure 3.3 - Yaw response frequency
Page 43 and 44: Figure 3.4 shows that even though t
Page 45 and 46: It can be seen that the Aerovironme
Page 47 and 48: 3.2.2 Allied Aerospace MAVFlight te
Page 49 and 50: 30MAGNITUDE(DB)-10-50250PHASE(DEG)5
Page 51 and 52: A 0th/2nd order transfer function i
Page 53 and 54: Figure 3.12 shows the same for the
Page 55 and 56: Techsburg) the pitching moment resp
Page 57 and 58: Table 3.11 shows that all of the di
Page 59 and 60: Figure 3.14 shows how increasing th
Page 61 and 62: the duct, the effects of the man ne
Page 63 and 64: ft-lbMu PLATFORM= 5.11ftsecThis dim
Page 65 and 66: apparent that the size of the duct
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adequate way to characterize the di
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actuators varied in size, weight, c
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It is noticeable from the figure th
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Table 3.17 - Actuator Calibration F
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Figure 2.1 shows an example frequen
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The test matrix is provided as Tabl
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frequency response curves shown in
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Table 3.22 shows that for the first
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The time delays all seemed to be ar
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400035003000250020001500y = -13429x
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higher data rates, and tighter tole
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esponse and the response obtained f
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The time histories show that the ou
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Figure 3.31 - Magnitude Comparison
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Performing the frequency response a
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Results from STI utilizing the exac
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The fact that the rate saturated du
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Table 3.23 for the maximum rates an
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Verification of the identified mode
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from testing (3.22), it was found t
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3.4.1 Accelerometer IdentificationM
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Figure 3.43 shows that gyros were m
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5 meter circle centered about the t
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Figure 3.46 shows the modeled fluct
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Figure 3.49 - Pressure Altimeter Mo
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Figure 4.1 - Simulink MAV ModelFigu
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Figure 4.3 - Simulink Sweep Generat
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cause a pitching moment to be exert
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Figure 4.6 - Cross Control Decoupli
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⎡ Lp Lq Lr Lu Lv Lw0 0 0⎤⎢MpM
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It can be seen right away that the
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Figure 4.8 shows that the coherence
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CHAPTER 5 - CONCLUSIONSThe need for
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6. Mettler, B., Tischler, M. B., an
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Appendix AOAV Proposal VehicleIdent
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DS8417 - 5V- 125 -
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HS512MG - 5V- 127 -
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DS368 - 5V- 129 -
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94091 - 5V- 131 -
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CS-10BB - 5V- 133 -
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Appendix CActuator Generated Transf
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DS8417 - 100% - 5V- 137 -
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DS8417 - 100% - 6V- 139 -
Page 153 and 154:
HS512MG - 100% - 5V- 141 -
Page 155 and 156:
HS512MG - 100% - 6V- 143 -
Page 157 and 158:
DS368 - 100% - 5V- 145 -
Page 159 and 160:
DS368 - 100% - 6V- 147 -
Page 161 and 162:
94091 - 80% - 5V- 149 -
Page 163 and 164:
94091 - 80% - 6V- 151 -
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CS-10BB - 100% - 5V- 153 -
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CS-10BB - 100% - 6V- 155 -
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Appendix DActuator Time Domain Veri
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94091 5V94091 6V- 159 -
Page 173 and 174:
DS368 5VDS368 6V- 161 -
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Comprehensive System Identification of Ducted Fan UAVs - Cal Poly

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