A Collection Of Nonlinear Aircraft Simulations In Matlab-Books Pdf

A Collection of Nonlinear Aircraft Simulations in MATLAB
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technical findings by NASA sponsored NASA STI Help Desk. contractors and grantees NASA Center for AeroSpace Information. 7121 Standard Drive, Hanover MD 21076 1320, NASA TM 2003 212145. A Collection of Nonlinear Aircraft Simulations,in MATLAB. Frederico R Garza,George Washington University, Joint Institute for the Advancement of Flight Sciences. Langley Research Center Hampton Virginia,Eugene A Morelli. Langley Research Center Hampton Virginia,National Aeronautics and Space Administration.
Langley Research Center,Hampton Virginia 23681 2199. January 2003, The use of trademarks or names of manufacturers in the report is for accurate reporting and does not. constitute an official endorsement either expressed or implied of such products or manufacturers by the. National Aeronautics and Space Administration ,Available from . NASA Center for AeroSpace Information CASI National Technical Information Service NTIS . 7121 Standard Drive 5285 Port Royal Road,Hanover MD 21076 1320 Springfield VA 22161 2171. 301 621 0390 703 605 6000, Table of Contents,TABLES iv.
FIGURES v,ABSTRACT vi,NOMENCLATURE vii, SUPERSCRIPTS x. SUBSCRIPTS x, NON DIMENSIONAL DERIVATIVES xi, Longitudinal xi. Lateral Directional xi,I INTRODUCTION 1,II EQUATIONS OF MOTION 2. ASSUMPTIONS 2, COLLECTED EQUATIONS OF MOTION 2, ENGINE MODEL 6. AERODYNAMIC MODEL 7, ATMOSPHERIC PROPERTIES 7, AIRCRAFT STATES AND CONTROLS 8.
III GENERAL SIMULATION TOOLS 9, TRIM 9, LINEARIZATION 11. Detailed Linearization Example 12, NUMERICAL INTEGRATION 15. Euler s Method 16, Runge Kutta Method of Order Two 16. Runge Kutta Method of Order Four 17, Adams Bashforth Method of Order Three 17. Detailed Numerical Integration Example 17, i, IV AVDS MATLAB INTERFACE 21.
EQUIPMENT REQUIREMENTS 21, SOFTWARE INSTALLATION 21. INTERACTIVE SIMULATION 22, Joystick Control Input 23. Initial States for Interactive Simulation 23, AVDS MATLAB Piloted Simulation Software 24. Stick Gain Modification 26, Control Deflection Exaggeration Factor 27. Integration Routine 27, Starting the AVDS MATLAB Simulation 27.
V SPECIFIC AIRCRAFT SIMULATION DETAILS 29, F 16 SIMULATION 29. Aerodynamic Model and Database 30, Engine Model and Database 31. Mass Properties 33, F 106B SIMULATION 33, Aerodynamic Model and Database 34. Engine Model and Database 35, Mass Properties 35, F 14 SIMULATION 36. Aerodynamic Model and Database 37, Engine Model and Database 39.
Mass Properties 39, F 4 SIMULATION 39, Aerodynamic Model and Database 40. Engine Model and Database 45, Mass Properties 45, FASER SIMULATION 45. Aerodynamic Model and Database 46, Engine Model and Database 48. Mass Properties 49, HL 20 SIMULATION 49, Aerodynamic Model and Database 50. Dynamic Equations 53, Mass Properties 53, ii, X 31 SIMULATION 54.
Aerodynamic Model and Database 55, Engine Model and Database 57. Mass Properties 57, A 7 SIMULATION 58, Aerodynamic Model and Database 59. Engine Model and Database 60, Mass Properties 60,VI GENERATING 3 D MODELS FOR AVDS 62. MODEL CONSTRUCTION REQUIREMENTS 62, MODELING EXAMPLE OF A SIMPLE 3 D AIRCRAFT 62. IMPORTING A COMPLETED 3 D CAD MODEL INTO AVDS 66,VII CONCLUDING REMARKS 68.
VIII ACKNOWLEDGEMENTS 69,IX APPENDIX 70,X REFERENCES 75. iii, Tables,TABLE 1 MASS PROPERTIES OF THE SIMULATED F 16 33. TABLE 2 MASS PROPERTIES OF THE SIMULATED F 106B 36. TABLE 3 MASS PROPERTIES OF THE SIMULATED F 14 39,TABLE 4 MASS PROPERTIES OF THE SIMULATED F 4 45. TABLE 5 MASS PROPERTIES OF THE SIMULATED FASER 49,TABLE 6 MASS PROPERTIES OF THE SIMULATED HL 20 54. TABLE 7 MASS PROPERTIES OF THE SIMULATED X 31 58,TABLE 8 MASS PROPERTIES OF THE SIMULATED A 7 61.
TABLE A 1 F 16 SIMULATION PACKAGE DIRECTORY NAME F 16 70. TABLE A 2 F 106B SIMULATION PACKAGE DIRECTORY NAME F 106B 71. TABLE A 3 F 14 SIMULATION PACKAGE DIRECTORY NAME F 14 72. TABLE A 4 F 4 SIMULATION PACKAGE DIRECTORY NAME F 4 72. TABLE A 5 FASER SIMULATION PACKAGE DIRECTORY NAME FASER 73. TABLE A 6 HL 20 SIMULATION PACKAGE DIRECTORY NAME HL 20 73. TABLE A 7 X 31 SIMULATION PACKAGE DIRECTORY NAME X 31 74. TABLE A 8 A 7 SIMULATION PACKAGE DIRECTORY NAME A 7 74. iv, Figures,FIGURE 1 FLOWCHART FOR NUMERICAL LINEARIZATION 12. FIGURE 2 FLOWCHART FOR NONLINEAR SIMULATION 16,FIGURE 3 ELEVATOR PERTURBATION 18. FIGURE 4 AVDS AIRCRAFT STATE INITIALIZATION WINDOW 24. FIGURE 5 INTERACTIVE SIMULATION FLOWCHART 25, FIGURE 6 SCREEN SHOT OF THE F 16 AVDS MATLAB INTERACTIVE SIMULATION 26. FIGURE 7 THREE VIEW OF THE F 16 30,FIGURE 8 THREE VIEW OF THE F 106B 34. FIGURE 9 THREE VIEW OF THE F 14 37,FIGURE 10 THREE VIEW OF THE F 4 40.
FIGURE 11 THREE VIEW OF THE FASER 46,FIGURE 12 THREE VIEW OF THE HL 20 50. FIGURE 13 THREE VIEW OF THE X 31 55,FIGURE 14 THREE VIEW OF THE A 7 59. FIGURE 15 THREE VIEW OF THE MIG 15 AIRCRAFT 63,FIGURE 16 FRONT AND REAR FUSELAGE OPENINGS 64. FIGURE 17 MODELED MIG 15 FUSELAGE SECTION 64, FIGURE 18 3 D MODEL WITH WING TAIL AND CONTROL SURFACES 65. FIGURE 19 MODEL WITH WIRE FRAME CANOPY 65,FIGURE 20 COMPLETED 3 D MIG 15 MODEL 66.
FIGURE 21 INPUT SCREEN FOR ACNAME SIM INI 67, v, ABSTRACT. Nonlinear six degree of freedom simulations for a variety of aircraft were created. using MATLAB Data for aircraft geometry aerodynamic characteristics mass inertia. properties and engine characteristics were obtained from open literature publications. documenting wind tunnel experiments and flight tests Each nonlinear simulation was. implemented within a common framework in MATLAB and includes an interface with. another commercially available program to read pilot inputs and produce a three . dimensional 3 D display of the simulated airplane motion Aircraft simulations include. the General Dynamics F 16 Fighting Falcon Convair F 106B Delta Dart Grumman F 14. Tomcat McDonnell Douglas F 4 Phantom NASA Langley Free Flying Aircraft for Sub . scale Experimental Research FASER NASA HL 20 Lifting Body NASA DARPA X . 31 Enhanced Fighter Maneuverability Demonstrator and the Vought A 7 Corsair II All. nonlinear simulations and 3 D displays run in real time in response to pilot inputs using. contemporary desktop personal computer hardware The simulations can also be run in. batch mode Each nonlinear simulation includes the full nonlinear dynamics of the bare. airframe with a scaled direct connection from pilot inputs to control surface deflections. to provide adequate pilot control Since all the nonlinear simulations are implemented. entirely in MATLAB user defined control laws can be added in a straightforward. fashion and the simulations are portable across various computing platforms Routines. for trim linearization and numerical integration are included The general nonlinear. simulation framework and the specifics for each particular aircraft are documented . vi, NOMENCLATURE, angle of attack deg or rad, angle of sideslip deg or rad. t numerical integration time step s, a left left aileron control surface deflection deg. a right right aileron control surface deflection deg. a , aileron control surface deflection a right a left 2 deg. c canard control surface deflection deg, df differential flap deflection deg.
e elevator control surface deflection deg, lf leading edge flap deflection deg. lg landing gear deflection deg, nf negative flap deflection deg. pf positive flap deflection deg, r rudder control surface deflection deg. sb speed brake deflection deg, sp symmetric wing spoiler deflection deg. tf trailing edge flap deflection deg, th throttle deflection.
th left left engine throttle deflection, th right right engine throttle deflection. tv outboard thrust vectoring paddle deflection deg. Euler roll angle rad, vii, flight path angle rad, Euler pitch angle rad. atmospheric density slug ft3, eng engine power level time constant s. Euler yaw angle rad, eng angular velocity of the engine rotating mass about the X body axis rad s. aX linear acceleration along X body axis g,aY linear acceleration along Y body axis g.
aZ linear acceleration along Z body axis g,A system matrix. b wing span ft,B input matrix,c mean aerodynamic chord ft. C output matrix,c vector of mass inertia properties. c1 c9 inertia constants, CA non dimensional axial force coefficient C A C X. CD drag coefficient,CD minimum drag coefficient, min.
Cl non dimensional rolling moment coefficient,CL lift coefficient. CL lift curve slope, ,Cm non dimensional pitching moment coefficient. CN non dimensional normal force coefficient C N CZ. Cn non dimensional yawing moment coefficient,CX non dimensional X body axis force coefficient. CY non dimensional Y body axis force coefficient, viii. CZ non dimensional Z body axis force coefficient,D feed through matrix.
g earth gravitational acceleration 32 174 ft s2,h altitude above mean sea level ft. heng engine angular momentum about X body axis slug ft2 s. I eng X body axis moment of inertia for the engine rotating mass slug ft2. IX X body axis moment of inertia slug ft2,IXZ X Z body axis product of inertia slug ft2. IY Y body axis moment of inertia slug ft2,IZ Z body axis moment of inertia slug ft2. m aircraft mass slugs,M Mach number,O order,p X body axis angular velocity component rad s. Pc commanded engine power level percent,Pa actual engine power level percent.
q Y body axis angular velocity component rad s,q dynamic pressure lb ft2. r Z body axis angular velocity component rad s,S wing reference area ft2. T engine thrust lb,T temperature factor,Tidle idle engine thrust lb. Tl rolling moment about X body axis generated by thrust ft lb. Tm pitching moment about Y body axis generated by thrust ft lb. Tmax maximum engine thrust lb,Tmax ab engine thrust with maximum afterburner lb. ix, Tmil military engine thrust lb,Tmin ab engine thrust with minimum afterburner lb.
Tn yawing moment about Z body axis generated by thrust ft lb. TX X body axis thrust component lb,TY Y body axis thrust component lb. TZ Z body axis thrust component lb, u X body axis translational velocity component ft s. u control vector, v Y body axis translational velocity component ft s. Vt airspeed ft s, w Z body axis translational velocity component ft s. x state vector, xc g longitudinal center of gravity location fraction of c.
xc g ref reference longitudinal center of gravity location fraction of c. xE X earth axis position ft, y output vector,yE Y earth axis position ft. SUPERSCRIPTS , time derivative,SUBSCRIPTS ,0 basic or trim value. left left,right right,S stability axes,E earth axes. x, NON DIMENSIONAL DERIVATIVES ,Longitudinal, C X C X. CL CL , i i q qc, , 2Vt, C X C X, CX CX , i i q qc.
, 2Vt, CZ CZ, CZ CZ , i i q qc, , 2Vt, Cm Cm, Cm Cm . i i q qc, , 2Vt,where i Vt e and or other controls. Lateral Directional, CY CY, CY CY , j j k kb, , 2Vt. Cl Cl, Cl Cl , j j k kb, , 2Vt, Cn Cn, Cn Cn , j j k kb. , 2Vt,where j a r and or other controls and k p r pS rS.

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