weights.c

多学科优化软件isight培训教程初级pdf有很详细的例子讲解

#include <stdio.h>
#include <math.h>

/* w_mpt function */

void w_mpt (FILE *fp, double *rho,double *vel,double *Sw,double *Wfw,double *Nzult,double *Wdg,double *AR,double *L,double
*D,double *Wen,double *Nen,double *Bw,double *Np,double *Wstruct,double *Wlg,double *Wprop,double *Wequip,double *Wempty) {

        /* Local Function Variable Declarations and Initializations */
	/* baseline GA aircraft weights - Raymer(modified)
	simplified estimates for level0 sizing */

	double wsweep=0.;		
	double lambda=1.;
	double toc=0.15;
	double Sht=.2*(*Sw);
	double htsweep=0.;
	double httoc=0.15;
	double htlambda=1.;
	double htAR=.8*(*AR);
	double Svt=.1*(*Sw);
	double vtsweep=0.;
	double vttoc=0.15;
	double vtlambda=1.;
	double vtAR=.8*(*AR);
	double vtplace=0.;
	double Sf=3.14159*(*D)*(*L);
	double Lt=.8*(*L);
	double Nl=*Nzult;
	double Wl=*Wdg;
	double Lm=(*D/2.)*12.;
	double Ln=(*D/2.)*12.;
	double Vt=*Wfw/6.5;
	double Vi=Vt;
	double Nt=1.;
        double Wuav=.02*(*Wdg);
	double M=*vel/1100.;

        /* Local Function Variable Declarations */

	double Q;
	double Wwing;
	double Wht;
	double Wvt;
	double Wfus;
	double Wmaingr;
	double Wnosegr;
	double Wengine;
	double Wfuelsys;
	double Wflightcon;
	double Whydraulics;
	double Wavionics;
	double Welec;
	double Wacai;
	
	/* Calculations */

	Q=.5*(*rho)*pow(*vel,2);
	wsweep=wsweep/57.29;
	htsweep=htsweep/57.29;
	vtsweep=vtsweep/57.29;

	/* wing weight */

	Wwing=.036*\
	      pow(*Sw,.758)*\
	      pow(*Wfw,.0035)*\
	      pow((*AR/pow(cos(wsweep),2)),.6)*\
	      pow(Q,.006)*\
	      pow(lambda,.04)*\
	      pow((100.*toc/cos(wsweep)),(-.3))*\
	      pow((*Nzult*(*Wdg)),.49);
	     
	/* horizontal tail */

	Wht=.016*\
	    pow(Sht,.896)*\
	    pow((htAR/pow(cos(htsweep),2)),0.043)*\
	    pow(Q,.168)*\
	    pow(htlambda,(-.02))*\
	    pow((100.*httoc/cos(htsweep)),(-.12))*\
	    pow((*Nzult*(*Wdg)),.414);

	/* vertical tail */
	

	Wvt=.073*\
	   (1.+.2*vtplace)*\
	   pow(Svt,0.873)*\
	   pow(vtAR/pow(cos(vtsweep),2),0.357)*\
	   pow(Q,.122)*\
	   pow(vtlambda,.039)*\
	   pow(100.*vttoc/cos(vtsweep),-.49)*\
	   pow((*Nzult*(*Wdg)),.376);

	/* fuselage (nonpressurized) */

	Wfus =0.052*\
	      pow(Sf,1.086)*\
	      pow((*Nzult*(*Wdg)),.177)*\
	      pow(Lt,(-.051))*\
	      pow((*L/(*D)),(-.072))*\
	      pow(Q,.241);

	Wmaingr = .095*\
	          pow((Nl*Wl),.768)*\
		  pow((Lm/12.),0.409);

	Wnosegr = .125*\
	          pow((Nl*Wl),.556)*\
		  pow((Ln/12.),0.845);

	Wengine = 2.575*\
	          pow(*Wen,.922)* \
		  *Nen;

	Wfuelsys= 2.49*\
	          pow(Vt,.726)*\
		  pow((1./(1.+Vi/Vt)),.363)* \
		  pow(Nt,.242)* \
		  pow(*Nen,.157);

	Wflightcon = 0.053* \
	             pow(*L,1.536)*\
		     pow(*Bw,0.371)*\
		     pow((*Nzult*(*Wdg)*.0001),.8);

	Whydraulics = 0.001*\
	              *Wdg;

	Wavionics= 2.117*\
	           pow(Wuav,.933);

	Welec= 12.57*\
	       pow((Wfuelsys+Wavionics),.51);

	Wacai = .265*\
	        pow(*Wdg,.52)*\
	        pow(*Np,.68)* \
		pow(Wavionics,.17)* \
		pow(M,0.08);

	*Wstruct= Wwing + Wht + Wvt + Wfus;
	*Wlg = Wmaingr + Wnosegr;
	*Wprop = Wengine + Wfuelsys;
	*Wequip = Wflightcon +Whydraulics +Wavionics + Welec + Wacai;

	*Wempty=*Wstruct+*Wlg+*Wprop+*Wequip;

       
        fprintf(fp,"%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G%13.8G\n",\
              Wwing, Wht, Wvt, Wfus, Wmaingr, Wnosegr, Wengine, Wfuelsys, Wflightcon, Whydraulics, Wavionics,\
	      Welec, Wacai, *Wempty);

};


void main() {
	
/* Input Declarations */

double rho;
double vel;
double Swing;
double Wfuel;
double Nzult;
double AR;
double Length;
double L;
double Diameter;
double D;
double Wen;
double Nen;
double Npass;
double Wpay;

/* Output Declarations */

double Wfuelcruise;
double R;
double Range;
double Vstall;
double rhosea;
double PassWt;
double con_tol;
double Wtot;
double Wpass;
double diff;
double wtot0;
double Wempty;
double Bw;
double Wstruct;
double Wlg;
double Wprop;
double Wequip;
FILE *fpinput;
FILE *fpoutput;
FILE *fptable;
FILE *fptemp;
int i=1;

/* Get Inputs */

if ((fpinput = fopen("WeightsIn.txt","r"))==NULL) {
        printf("\n");
        printf("*** ERROR ***\n");
        printf("Cannot open input file WeightsIn.txt. \n");
        printf("\n");
        exit (1);
    }

fscanf(fpinput,"\n");
fscanf(fpinput," ==== Weights Analysis Input File ====\n");
fscanf(fpinput,"\n");
fscanf(fpinput,"rho = %lf\n", &rho);
fscanf(fpinput,"vel = %lf\n", &vel);
fscanf(fpinput,"Swing = %lf\n", &Swing);
fscanf(fpinput,"Nzult = %lf\n", &Nzult);
fscanf(fpinput,"AR = %lf\n", &AR);
fscanf(fpinput,"Length = %lf\n", &Length);
fscanf(fpinput,"Diameter = %lf\n", &Diameter);
fscanf(fpinput,"Wfuel = %lf\n", &Wfuel);
fscanf(fpinput,"Wen = %lf\n", &Wen);
fscanf(fpinput,"Nen = %lf\n", &Nen);
fscanf(fpinput,"Npass = %lf\n", &Npass);
fscanf(fpinput,"Wpay = %lf\n", &Wpay);
fclose(fpinput);

/* Calculations */

L=Length;
D=Diameter;
PassWt=175.0;
con_tol = 0.001;
Wtot = 0.0;
Wpass = PassWt*Npass;
diff = 500.0;

/* Write Weight Convergence Information */

if ((fptable = fopen("WeightsTable.txt","w"))==NULL) {
        printf("\n");
        printf("*** ERROR ***\n");
        printf("Cannot open convergence file WeightsTable.txt. \n");
        printf("\n");
        exit (1);
    }

fprintf(fptable,"    Iteration and Convergence of Individual Aircraft Component Weights\n");
fprintf(fptable,"%13s%13s%13s%13s%13s%13s%13s%13s%13s%13s%13s%13s%13s%13s\n",\
   "Wing","H. Tail","V. Tail","Fuselage","Main Gear","Nose Gear","Engines","FuelSys",\
   "Controls","Hydraulics","Avionics","Electrical","A/C&Anti-Ice","Total Empty");

/* Write Output File */

if ((fpoutput = fopen("WeightsOut.txt","w"))==NULL) {
        printf("\n");
        printf("*** ERROR ***\n");
        printf("Cannot open output file WeightsOut.txt. \n");
        printf("\n");
        exit(1);
}

fprintf(fpoutput,"\n");
fprintf(fpoutput," ==== Weights Analysis Output File ====\n");
fprintf(fpoutput,"\n");
fprintf(fpoutput," ===========  Convergence Data ============ \n");
fprintf(fpoutput,"\n");


while (diff > con_tol) {

   wtot0 = Wtot;

   /* weights calculations */

   Wtot=Wpay+Wfuel+Wpass+Wempty;

   /*	empty weight estimation */

   Bw=sqrt(AR*Swing);

  
   w_mpt(fptable,&rho,&vel,&Swing,&Wfuel,&Nzult,&Wtot,&AR,&L,&D,&Wen,&Nen,&Bw,&Npass,&Wstruct,&Wlg,&Wprop,&Wequip,&Wempty);

   diff = sqrt(pow(wtot0 - Wtot,2));

   fprintf(fpoutput,"Convergence Difference: %13.8G \n", diff);

};

/* Close Convergence Information Table */

fclose(fptable);

/* Finish Generating Output File */

fprintf(fpoutput,"\n");
fprintf(fpoutput,"   === Weight Analysis === \n");
fprintf(fpoutput,"\n");
fprintf(fpoutput," Weight of Payload (lbs.)                 = %15.6G \n", Wpay);
fprintf(fpoutput," Weight of Fuel (lbs.)                    = %15.6G \n", Wfuel);
fprintf(fpoutput," Number of Passengers                     = %15.6G \n", Npass);
fprintf(fpoutput," Weight of Passengers @ %5.1f (lbs.) each = %15.6G \n", PassWt, Wpass);
fprintf(fpoutput,"\n");
fprintf(fpoutput,"   === Weight of Aircraft Components === \n");
fprintf(fpoutput,"\n");
fprintf(fpoutput,"Weight of Aircraft Structure (lbs.)          = %15.6G \n", Wstruct);
fprintf(fpoutput,"Weight of Aircraft Landing Gear (lbs.)       = %15.6G \n", Wlg);
fprintf(fpoutput,"Weight of Aircraft Propulsion System (lbs.)  = %15.6G \n", Wprop);
fprintf(fpoutput,"Weight of Aircraft Internal Equipment(lbs.)  = %15.6G \n", Wequip);
fprintf(fpoutput,"Total Weight of Empty Aircraft (lbs.)        = %15.6G \n", Wempty);
fprintf(fpoutput,"Total Weight of Loaded Aircraft (lbs.)       = %15.6G \n", Wtot);
fclose(fpoutput);

/* Lines to Slow Down the Code to Demo Parallel Feature in iSIGHT */

/*while (i < 3000) {

    if ((fptemp = fopen("WeightsLoop.txt","w"))==NULL) {
        printf("\n");
        printf("*** ERROR ***\n");
        printf("Cannot open temporary file WeightsLoop.txt. \n");
        printf("\n");
        exit (1);
    }
    fprintf(fptemp,"%d",i);
    fclose(fptemp);
    i++;
  
};*/

exit (0);

};