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

More documents

Recommendations

Info

* Parameter Value Description* Name*---------- ----- -----------* Dimensionless stability derivatives (logitudinal) */CL = dp[12]; /* Lift */CD = dp[13]; /* Drag */CLAlpha = dp[24]; /* Lift curve slope (per radian) */CDAlpha = dp[27]; /* Drag curve slope */CmAlpha = dp[18]; /* Pitching moment curve slope*/CLAlphaDot = dp[25];CmAlphaDot = dp[19]; /* Pitching moment to angle of attack rate */CLq = dp[26]; /* Change in lift to pitch rate */Cmq = dp[20]; /* Pitch damping */CLm = 0.0;CDM = 0.0;CmM = 0.0;CLDelE = dp[30]; /* heave to elevator */CmDelE = dp[32]; /* Pitch control to elevator (Note sign - -> up) *//* Cm0 = dp[15]; *//* Dimensionless stability derivatives (lateral) */CyBeta = dp[43]; /* Sway */ClBeta = dp[33]; /* roll rate to beta dihedral */CnBeta = dp[38]; /* yaw rate to beta */Clp = dp[34]; /* roll damping */Cnp = dp[39];/* yaw moment to roll rate */Clr = dp[35]; /* roll moment to yaw rate */Cnr = dp[40]; /* yaw damping */ClDelA = dp[36]; /* roll control */CnDelA = dp[41];/* yaw due to aileron - adverse yaw */CyDelR = dp[47]; /* sway to rudder */ClDelR = dp[37]; /* roll rate due to rudder */CnDelR = dp[42]; /* yaw due to rudder */Beta = 0.0; /***** Beta is the Side slip angle *****/Alpha = 0.0;u = u0*cos(Beta)*cos(Alpha);v = u0*sin(Beta);w = -u0*sin(Alpha);Thrust = CD*.5*Rho*Area*u0*u0;/***** trim thrust = drag *****/Deflect_Rudder = 0.0; /***** initialize *****/Deflect_Aileron = 0.0;Deflect_Elevator = 0.0;Alpha = 0.0;Beta = 0.0;/***** pre-calculate the trig functions *****//***** theta - pitch angle, psi - yaw angle, phi - roll angle *****/Theta=0;Psi=0;Phi=0;STheta=sin(Theta);SPhi=sin(Phi);SPsi=sin(Psi);CTheta=cos(Theta);CPhi=cos(Phi);144
CPsi=cos(Psi);TTheta=tan(Theta);SecTheta=1.0;if (CTheta > 1e-6)SecTheta = 1.0/CTheta;/* u_Trim = u0;UpdateState();*/}#endif /* MDL_INITIALIZE_CONDITIONS *//* ENTRY POINT FOR FLIGHT MODEL LOOP* This function takes as parameters references to a state_vect structure* containing the control input from the current pass, as well as the* values <strong>for</strong> all other aircraft data from the previous pass. *//* Function: mdlOutputs =======================================================* Abstract:**/static void mdlOutputs(SimStruct *S, int_T tid){/* Function: mdlOutputs ======================================================* Abstract:* This function is called once <strong>for</strong> every major integration time step.** Control vector:* Deflect_Elevator = uPtrs[0]* Deflect_Aileron = uPtrs[1]* Deflect_Rudder = uPtrs[2]* Rho = uPtrs[3]* Fx = uPtrs[4]* Fy = uPtrs[5]* Fz = uPtrs[6]* PitchingMoment = uPtrs[7]* RollingMoment = uPtrs[8]* YawingMoment = uPtrs[9]** Output vector values:* y[0] = xx* y[1] = yy* y[2] = zz* y[3] = Psi* y[4] = Theta* y[5] = Phi* y[6] = u* y[7] = v* y[8] = w* y[9] = p* y[10]= q* y[11]= r* y[12]= Alpha* y[13]= Beta* y[14]= pDot145
Page 2:
Authorization PageI grant permissio
Page 6 and 7:
Table of ContentsLIST OF TABLESXIIL
Page 8 and 9:
Standard Atmosphere 64Input 65Outpu
Page 10 and 11:
RK4 (RUNGE-KUTTA) HELP FILE 91RK4 (
Page 12 and 13:
List of TablesTablePageTable 1. Air
Page 14 and 15:
Figure 27. Kaman SH2-F 72Figure 28.
Page 16 and 17:
has been developing a set of the ba
Page 18 and 19:
Simulink is a graphical user interf
Page 20 and 21:
computers are now fast enough to do
Page 22 and 23:
simulation after the conversion. Th
Page 24 and 25:
then a simple one axis closed loop
Page 26 and 27:
PhEagle IPhEagle Hardware - Sim Cab
Page 28 and 29:
highlight some text on a word proce
Page 30 and 31:
up to perform the less processor in
Page 32 and 33:
the Heads Up Display (HUD). While c
Page 34 and 35:
and monitors and computer code to s
Page 36 and 37:
Existing Simulation ToolsThere are
Page 38 and 39:
great control over the model dynami
Page 40 and 41:
Figure 11 BYOFS Original ScreenFigu
Page 42 and 43:
Basic 6-DOF Nonlinear, Rigid Body,
Page 44 and 45:
0 18 Cmu - Pitch moment due to forw
Page 46 and 47:
each of the linear force terms. The
Page 48 and 49:
PhEagle IIPhEagle II Introduction a
Page 50 and 51:
instructor a graphical interface to
Page 52 and 53:
Simulink block set, however, when m
Page 54 and 55:
existing graphics by creating a TCP
Page 56 and 57:
Simulink environment, and Mathworks
Page 58 and 59:
D/A (output) block is the code for
Page 60 and 61:
Table 9 Cab InputsInput from cab ou
Page 62 and 63:
Key Features of SimulationsStabilit
Page 64 and 65:
subsystem with inputs and outputs.
Page 66 and 67:
viewer has the end of the runway co
Page 68 and 69:
The 6 degree of freedom (3 translat
Page 70 and 71:
difference between the two axes are
Page 72 and 73:
Unit Delay1zelevatorelevElevElevato
Page 74 and 75:
6 DOF Model VerificationThe 6 DOF m
Page 76 and 77:
oth models. The two state space mod
Page 78 and 79:
Impulse ResponseRoll Angle32.5Ampli
Page 80 and 81:
modeled. By feeding back any of the
Page 82 and 83:
R10000 processors an inceptor Flybo
Page 84 and 85:
directly to the Euler block the out
Page 86 and 87:
function and the dynamics were very
Page 88 and 89:
made by handling qualities engineer
Page 90 and 91:
mode. The aircraft was divergent de
Page 92 and 93:
simplified to resemble a spring-dam
Page 94 and 95:
the data and converting to the prop
Page 96 and 97:
ConclusionsConverting existing soft
Page 98 and 99:
Future WorkPhEagle II provides basi
Page 100 and 101:
workstation or PC for function test
Page 102 and 103:
13. Tischler, M. B.; Chen, R. T. N;
Page 104 and 105:
AppendixEuler Help File%***** euler
Page 106 and 107:
k4=dt*(z(index-1)+l3/2.0);l4=dt*(-a
Page 108 and 109: float K = 10.0;printf("\nEnter wn [
Page 110 and 111: Snoopy 2nd order RK4 Class//-------
Page 112 and 113: {private:void CalcPowerDyn();void C
Page 114 and 115: int opMode;int oldVmode;int checkpt
Page 116 and 117: }exit_code = 0;}if (opMode != DEBUG
Page 118 and 119: }opMode = HELP;else if ((*argv[i] =
Page 120 and 121: Instrument D/A Simulink S-function/
Page 122 and 123: * Function: mdlInitializeSampleTime
Page 124 and 125: cdVerIndicator.channelNumber=5;cdVe
Page 126 and 127: set(&yawForceOut,*uPtrs[26]);set(&r
Page 128 and 129: Instrument Help Filefunctionallinst
Page 130 and 131: Stick D/A Simulink S-function/*****
Page 132 and 133: aToD12.cntCtrl=addr + 3;aToD12.da1L
Page 134 and 135: * with in an enabled subsystem whic
Page 136 and 137: #define MDL_DERIVATIVES /* Change t
Page 138 and 139: 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 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 190 and 191: ANavionLatB=[0 .07045610 028.73202
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.
show all

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

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?