两架商务喷气式飞机的数学模型和六自由度模拟matlab代码.rar

% Supporting Calculations for Geometric, Inertial, and Aerodynamic % Properties of BizJet B % June 12, 2015 % Copyright 2006-2015 by ROBERT F. STENGEL. All rights reserved. clear disp('==============================================') disp('Geometric and Inertial Properties for BizJet B') disp('==============================================') Date = date % Comparable Bizjet Weight Distribution, lb, based on empty weight less engine weight. % (from Stanford AA241 Notes, Ilan Kroo) WingSys = 1020; TailSys = 288; BodySys = 930; GearSys = 425; NacelleSys = 241; PropSys = 340; ControlSys = 196; InstrSys = 76; HydrPneuSys = 94; ElecSys = 361; AvionSys = 321; FurnEquipSys = 794; ACSys = 188; AntiIceSys = 101; LoadHandSys = 2; EmptyStruc = (WingSys+TailSys+BodySys+GearSys+PropSys ... +ControlSys+InstrSys+HydrPneuSys+ElecSys+AvionSys ... +FurnEquipSys+ACSys+AntiIceSys+LoadHandSys); % Less nacelles and engines EngWgt = 1002; EmptyWgt = (EmptyStruc+EngWgt); % Less nacelles EmptyStrucWgt = EmptyStruc/EmptyWgt; WingRatio = (WingSys+GearSys+HydrPneuSys+AntiIceSys)/EmptyStruc; HTRatio = 0.75*(TailSys)/EmptyStruc; VTRatio = 0.25*(TailSys)/EmptyStruc; FusRatio = (BodySys+PropSys+ControlSys+InstrSys+ElecSys ... +AvionSys+FurnEquipSys+ACSys+LoadHandSys)/EmptyStruc; Total = (WingRatio+HTRatio+VTRatio+FusRatio); NacelleRatio = (NacelleSys)/EngWgt; % Related to engine weight rather than empty structure % BizJet B Geometric Properties % x measurements from nose along centerline, negative aft % y & z measurements from centerline, positive right and down S = 19.51 % Reference Area, m^2 taperw = 0.5333 % Wing Taper Ratio cBar = 1.56 % Mean Aerodynamic Chord, m sweep = 11*0.01745329 % Wing L.E. sweep angle, rad xcp = -5.7473 % Wing center of pressure, m GamWing = 3*0.01745329 % Dihedral angle of the wing, rad % BizJet B Mass and Inertial Properties m = 3000 % Total mass for simulation (USER-specified), kg mEmpty = 2522 % Gross empty mass, kg mEng = (1+NacelleRatio)*240 % Mass of engines + nacelles, kg mStruc = mEmpty - mEng % Empty structural mass (less engines + nacelles), kg mWing = WingRatio*mStruc % Wing mass, kg mHT = HTRatio*mStruc % Horizontal tail mass, kg mVT = VTRatio*mStruc % Vertical tail mass, kg mFus = FusRatio*mStruc % Empty fuselage mass, kg mPay = 0.5*(m - mEmpty) % Payload mass, kg mFuel = 0.5*(m - mEmpty) % Fuel mass, kg xcm = xcp - 0.45*cBar % Center of mass from nose (USER-specified), m lWing = xcm - xcp % Horizontal distance between c.m and wing c.p., m zWing = -0.557 % Vertical distance between c.m and wing c.p., m b = 13.16 % Wing Span, m lenFus = 10.72 % Fuselage length, m xcpFus = -0.25*lenFus % Linear-regime fuselage center of pressure, m xcpFusN = -0.5*lenFus % Newtonian-regime fuselage center of pressure, m lFus = xcm - xcpFus; % Linear fuselage lift cp offset,m lFusN = xcm - xcpFusN; % Newtonian fuselage lift cp offset, m dFus = 1.555 % Fuselage diameter, m Sfus = (pi/4)*lenFus*dFus % Plan or side area of fuselage, m Sbase = (pi/4)*dFus^2 % Fuselage cross-sectional area, m^2 bHT = 5.3; % Horizontal tail span, m cHT = 1.1; % Mean horizontal tail chord, m swpHT = 38*0.0174533; % Horizontal tail sweep, rad SHT = bHT*cHT % Horizontal tail area, m^2 xHT = -11.3426; % Linear xcp of horizontal tail lHT = xcm - xHT; % Horizontal tail length, m zHT = 1.5; % zcp of horizontal tail, m xVT = -10.044; % Linear xcp of vertical tail, m lVT = xcm - xVT; % Vertical tail length, m bVT = 2.409; % Vertical tail span, m cVT = 1.88; % Mean vertical tail chord, m swpVT = 50*0.0174533; % Vertical tail sweep, rad SVT = bVT*cVT; % Vertical tail area, m^2 zVT = 1.5; % zcp of vertical tail, m xEng = -7.735; % xcm of engine, m lEng = xcm - xEng; % Engine length, m yEng = 1.1325; % ycm of engine, m zEng = 0.4038; % zcm of engine, m xNac = -7.7252; % xcp of engine, m lNac = xcm - xNac; % Nacelle length, m bNac = 2.5; % Nacelle span, m cNac = 1.82; % Nacellechord, m dNac = 0.73; % Nacelle diameter, m SbaseNac = 0.25*pi*dNac^2; % Nacelle base area, m^2 Snac = bNac*cNac; % Nacelle plan area, m^2 xVent = -9.94; % xcp of ventral fin, m lVent = xcm - xVent; % Ventral fin length, m zVent = 0; % zcp of ventral fin, m bVent = 1; % Ventral fin span, m cVent = 0.85; % Ventral fin chord, m Svent = bVent*cVent; % Ventral fin area, m^2 swpVent = 60*0.0174533; % Ventral sweep angle, rad Splan = S + Sfus + Snac + SHT + Svent % Plan area of airplane Swet = 2*(Splan + Sfus + SVT) % Wetted area of airplane ARwing = (b^2) / S % Wing aspect ratio ARHT = (bHT^2) / SHT % Horizontal tail aspect ratio ARnac = (bNac^2) / Snac % Engine nacelle aspect ratio ARvent = (bVent^2)/ Svent % Ventral fin aspect ratio ARVT = (bVT^2) / SVT % Vertical tail aspect ratio % Moments and Product of Inertia Ixx = (1/12)*((mWing+mFuel)*b^2 + mHT*bHT^2 + mVT*bVT^2) + (0.25*(mFus+mPay)*dFus^2 + mEng*yEng^2 + mVT*zVT^2) Iyy = (1/12)*((mFus+mPay)*lenFus^2 + (mWing+mFuel)*cBar^2 + mVT*cHT^2) + (mEng*lEng^2 + mHT*lHT^2 + mVT*lHT^2) Izz = (1/12)*((mFus+mPay)*lenFus^2 + (mWing+mFuel)*b^2 + mHT*bHT^2) + (mEng*lEng^2 + mHT*lHT^2 + mVT*lVT^2) Ixz = mHT*lHT*zHT + mVT*lVT*zVT + mEng*lEng*zEng dEmax = 20 * 0.01745329 % Maximum Elevator Deflection is �20 deg dAmax = 35 * 0.01745329 % Maximum Aileron Deflection is �35 deg dRmax = 35 * 0.01745329 % Maximum Rudder Deflection is �35 deg save('InerGeo.mat','m','xcm','Ixx','Iyy','Izz','Ixz','cBar','b','S', ... 'Splan','taperw','ARwing','sweep','xcp','lWing','GamWing','lHT','lVT') disp('===================================') disp('Aerodynamic Properties for BizJet B') disp('===================================') % BizJet B Aero Properties AlphaTable = [-10 -8 -6 -4 -2 0 2 4 6 8 10 11 12 13 14 15 16 17 18 19 20 ... 21 22 23 24 25 30 35 40 45 50 55 60 65 70 75 80 85 90]; Points = length(AlphaTable); AlphaRad = 0.0174533*AlphaTable; SinAlpha = sin(AlphaRad); CosAlpha = cos(AlphaRad); % Newtonian Coefficients CN = 2*(Splan/S)*SinAlpha.*SinAlpha; CN = CN.*sign(AlphaRad); CDNewt = 2*(Splan/S)*abs(SinAlpha.*SinAlpha.*SinAlpha); CLNewt = CN.*CosAlpha; cpNewt = (S*lWing + Sfus*lFusN + SHT*lHT + Svent*lVent + Snac*lNac)... / (S + Sfus + SHT + Svent + Snac); % Longitudinal Aerodynamics %