An Integrated, Modular Simulation System for Education ... - Cal Poly

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ANavionLatB=[0 .07045610 028.73202 2.2942730 0-.2228004 -4.583323]ANavionLatC=[ 1 0 0 0 00 1 0 0 00 0 1 0 00 0 0 1 00 0 0 0 1]ANavionLatD=[0 00 00 00 00 0]%states = {’beta’ ’phi’ ’p’ ’psi’ ’r’};%inputs = {’aileron’ ’rudder’}%output = {’sideslip’ ’bank angle’ ’bank rate’ ’yaw angle’ ’yaw rate’}%sys = ss(ANavionLatA,ANavionLatB,ANavionLatC,ANavionLatD,’statename’,states,...% ’inputname’,inputs,...% ’outpurname’,output)176
Navion Lateral State Space Setup - Nelson%%navion lateral state space setup%FASAND Fundamentals of Aircraft Simulation And Nonlinear Dynamics%% This is a state space model of the Navion example aircraft% used to validate the FASAND code. The A and B matricies were% dimensional derivatives provided in appendix A of "Flight% stability and control" Robert C. Nelson%% This Script is free to copy and distribute for educational purposes as long% as this notice is included.%% Doug Hiranaka%% Created: 8-98% Last Update: 1/25/99 DH Corrected control matrix beta to de%% Copyright (c) 1998-99 by Penguin Aeronautics.NNavionLatA=[ -0.2531035 0 -1.0 0.182-16.02 -8.40 2.19 04.448 -0.350 -0.760 00 1 0 0 ];NNavionLatB=[ 0 0.070456128.73202 2.294273-.2228004 -4.5833230 0 ];%(1,2) WAS 12.3587NNavionLatC=[ 1 0 0 00 1 0 00 0 1 00 0 0 1 ];NNavionLatD=[ 0 00 00 00 0 ];states = {’beta’ ’p’ ’r’ ’phi’};inputs = {’aileron’ ’rudder’};output = {’sideslip’ ’roll rate’ ’yaw rate’ ’roll angle’};nLatSys = ss(NNavionLatA,NNavionLatB,NNavionLatC,NNavionLatD,’statename’,states,...’inputname’,inputs,...’outpurname’,output);177
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Authorization PageI grant permissio
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Table of ContentsLIST OF TABLESXIIL
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Standard Atmosphere 64Input 65Outpu
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RK4 (RUNGE-KUTTA) HELP FILE 91RK4 (
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List of TablesTablePageTable 1. Air
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Figure 27. Kaman SH2-F 72Figure 28.
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has been developing a set of the ba
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Simulink is a graphical user interf
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computers are now fast enough to do
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simulation after the conversion. Th
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then a simple one axis closed loop
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PhEagle IPhEagle Hardware - Sim Cab
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highlight some text on a word proce
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up to perform the less processor in
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the Heads Up Display (HUD). While c
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and monitors and computer code to s
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Existing Simulation ToolsThere are
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great control over the model dynami
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Figure 11 BYOFS Original ScreenFigu
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Basic 6-DOF Nonlinear, Rigid Body,
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0 18 Cmu - Pitch moment due to forw
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each of the linear force terms. The
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PhEagle IIPhEagle II Introduction a
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instructor a graphical interface to
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Simulink block set, however, when m
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existing graphics by creating a TCP
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Simulink environment, and Mathworks
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D/A (output) block is the code for
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Table 9 Cab InputsInput from cab ou
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Key Features of SimulationsStabilit
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subsystem with inputs and outputs.
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viewer has the end of the runway co
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The 6 degree of freedom (3 translat
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difference between the two axes are
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Unit Delay1zelevatorelevElevElevato
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6 DOF Model VerificationThe 6 DOF m
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oth models. The two state space mod
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Impulse ResponseRoll Angle32.5Ampli
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modeled. By feeding back any of the
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R10000 processors an inceptor Flybo
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directly to the Euler block the out
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function and the dynamics were very
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made by handling qualities engineer
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mode. The aircraft was divergent de
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simplified to resemble a spring-dam
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the data and converting to the prop
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ConclusionsConverting existing soft
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Future WorkPhEagle II provides basi
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workstation or PC for function test
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13. Tischler, M. B.; Chen, R. T. N;
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AppendixEuler Help File%***** euler
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k4=dt*(z(index-1)+l3/2.0);l4=dt*(-a
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float K = 10.0;printf("\nEnter wn [
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Snoopy 2nd order RK4 Class//-------
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{private:void CalcPowerDyn();void C
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int opMode;int oldVmode;int checkpt
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}exit_code = 0;}if (opMode != DEBUG
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}opMode = HELP;else if ((*argv[i] =
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Instrument D/A Simulink S-function/
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* Function: mdlInitializeSampleTime
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cdVerIndicator.channelNumber=5;cdVe
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set(&yawForceOut,*uPtrs[26]);set(&r
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Instrument Help Filefunctionallinst
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Stick D/A Simulink S-function/*****
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aToD12.cntCtrl=addr + 3;aToD12.da1L
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* with in an enabled subsystem whic
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#define MDL_DERIVATIVES /* Change t
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Abbreviated Instrument D/A Simulink
Page 140 and 141: {d16.nBits=16;d16.baseAddr=0x340;d1
Page 142 and 143: InputRealPtrsType uPtrs = ssGetInpu
Page 144 and 145: #ifdef MATLAB_MEX_FILE /* Is this f
Page 146 and 147: Abbreviated Stick D/A Simulink S-fu
Page 148 and 149: aToD12.da2Low=addr + 6;aToD12.da2Hi
Page 150 and 151: */static void mdlDerivatives(SimStr
Page 152 and 153: Header file for Stick S-functions//
Page 154 and 155: Abbreviated Stick Help filefunction
Page 156 and 157: #define Deg2Rad 0.01745329#define R
Page 158 and 159: * Parameter Value Description* Name
Page 160 and 161: * y[15]= qDot* y[16]= rDot* y[17]=
Page 162 and 163: ***** Compute the rolling moment ex
Page 164 and 165: xDot=u*CTheta*CPsi+v*(SPhi*STheta*C
Page 166 and 167: SAD file: Navion.tsf2.153 1 Alt1 [f
Page 168 and 169: % | sAcB -sAsB cA | Fzb% Test dataF
Page 170 and 171: Standard Atmosphere Simulink S-func
Page 172 and 173: * in estimate();** Alt=*uPtrs[0]; m
Page 174 and 175: Euler Coordinate Transform and Inte
Page 176 and 177: * Abstract:* Specifiy that we inher
Page 178 and 179: * calulate the trig functions first
Page 180 and 181: Euler Transform Help Filefunction [
Page 182 and 183: Game Joystick Driver Simulink S-fun
Page 184 and 185: */static void mdlInitializeConditio
Page 186 and 187: * This function is called once for
Page 188 and 189: Navion Longitudianal State Space Se
Page 192 and 193: Navion Longitudinal State Space Set
Page 194 and 195: NNavionLatB=[0 0.070456128.73202 2.
Page 196: % create a frequency vectorw=0.1:0.
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An Integrated, Modular Simulation System for Education ... - Cal Poly

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