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RocketWorkbench
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Based on the original Rocket Workbench on SourceForge in CVS at: https://sourceforge.net/projects/rocketworkbench
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RocketWorkbench/rocketworkbench/source/executables/profiler/src/profiler.c

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#include <stdlib.h>
#include <string.h>
#include <math.h>
#include "gpcp.h"
#include "libcompat/include/getopt.h"
#include "profiler.h"
#define M_PI2 9.869604401
Options rocket_options[] = {
{"global", PARENT, NULL},
{"length_units", STRING, "global"},
{"mass_units", STRING, "global"},
{"rocket", PARENT, NULL},
{"name", STRING, "rocket"},
{"cg", FLOAT, "rocket"},
{"body", PARENT, "rocket"},
{"type", STRING, "body"},
{"length", FLOAT, "body"},
{"diameter", FLOAT, "body"},
{"density", FLOAT, "body"},
{"mass", FLOAT, "body"},
{"fin", PARENT, "rocket"},
{"num", INTEGER, "fin"},
{"pos", FLOAT, "fin"},
{"root_chord", FLOAT, "fin"},
{"tip_chord", FLOAT, "fin"},
{"root_tip_d", FLOAT, "fin"},
{"semispan", FLOAT, "fin"},
{"body_radius", FLOAT, "fin"},
{"mass", FLOAT, "fin"},
{"motor", PARENT, "rocket"},
{"zpos", FLOAT, "motor"},
{"rpos", FLOAT, "motor"},
{"diameter", FLOAT, "motor"},
{"length", FLOAT, "motor"},
{"empty_mass", FLOAT, "motor"},
{"full_mass", FLOAT, "motor"},
{"tank", PARENT, "rocket"},
{"zpos", FLOAT, "tank"},
{"rpos", FLOAT, "tank"},
{"diameter", FLOAT, "tank"},
{"length", FLOAT, "tank"},
{"empty_mass", FLOAT, "tank"},
{"full_mass", FLOAT, "tank"},
{"other", PARENT, "rocket"},
{"shape", STRING, "other"},
{"zpos", FLOAT, "other"},
{"rpos", FLOAT, "other"},
{"Ix", FLOAT, "other"},
{"Iy", FLOAT, "other"},
{"mass", FLOAT, "other"},
{NULL, 0, NULL}
};
int read_value(Data *d, rocket_t *r);
int profile_rocket(rocket_t *r);
int profile_fins(rocket_t *r);
int profile_body(rocket_t *r);
void usage(void);
int main(int argc, char *argv[])
{
int c;
Data *data;
rocket_t rocket;
char filename[FILENAME_MAX] = "";
rocket.body.n_body_parts = 0;
rocket.body.body_parts = NULL;
rocket.n_fin_set = 0;
rocket.fin_set = NULL;
rocket.Lr = 0;
rocket.Ar = 0;
while (1)
{
c = getopt(argc, argv, "f:");
if (c == EOF)
break;
switch (c)
{
case 'f':
if (strlen(optarg) > FILENAME_MAX)
{
printf("Filename too long!\n");
return -1;
break;
}
strncpy (filename, optarg, FILENAME_MAX);
break;
case 'h':
usage();
break;
}
}
if (strcmp(filename, "") == 0)
{
printf("A rocket description file must be provide.\n");
usage();
return -1;
}
GPCP_RegisterOptions(rocket_options);
if (GPCP_ReadFile(filename, &data))
{
printf("Error parsing configuration file.\n");
return -1;
}
read_value(data, &rocket);
/* GPCP_PrintData(data); */
GPCP_FreeData(&data);
profile_rocket(&rocket);
free (rocket.fin_set);
free (rocket.body.body_parts);
return 0;
};
void usage(void)
{
printf("Usage:");
printf("\n\tprofiler -f infile");
printf("\n\nArguments:\n");
printf("-f file \t Perform an analysis of the specified rocket.\n");
printf("-h \t Print usage.\n");
}
int profile_rocket(rocket_t *r)
{
int i, n;
fin_t *f;
r->m = 0;
/* reference area of the rocket */
r->Ar = M_PI * pow(r->Lr, 2)/4;
r->n_mach = 20;
r->mach = (double *) malloc(sizeof(double) * r->n_mach);
/* fill the table of the mach number */
for (i = 0; i < r->n_mach; i++)
{
r->mach[i] = (1.0/r->n_mach) * i;
}
profile_fins(r);
profile_body(r);
/* tables in function of the mach number */
r->X = (double *) malloc(sizeof(double) * r->n_mach);
r->C_N_alpha = (double *) malloc(sizeof(double) * r->n_mach);
r->C_mq = (double *) malloc(sizeof(double) * r->n_mach);
r->C_m_alpha = (double *) malloc(sizeof(double) * r->n_mach);
for (i = 0; i < r->n_mach; i++)
{
r->C_N_alpha[i] = r->body.C_N_alpha_b;
/* formula 3-106 */
for (n = 0; n < r->n_fin_set; n++)
{
f = r->fin_set + n;
r->C_N_alpha[i] += f->C_N_alpha_tb_m * f->C_N_alpha_1[i];
r->C_N_alpha[i] += f->C_N_alpha_bt_m * f->C_N_alpha_1[i];
}
/* rocket center of pressure location */
r->X[i] = r->body.Xb * r->body.C_N_alpha_b;
/* formula 3-107 */
for (n = 0; n < r->n_fin_set; n++)
{
f = r->fin_set + n;
r->X[i] += f->Xt * f->C_N_alpha_tb_m * f->C_N_alpha_1[i];
r->X[i] += f->Xbt * f->C_N_alpha_bt_m * f->C_N_alpha_1[i];
}
r->X[i] = r->X[i] / r->C_N_alpha[i];
/* formula 3-115 CHECKME, formula was badly print,
i redevelop it myself */
r->C_mq[i] = 0;
for (n = 0; n < r->n_fin_set; n++)
{
f = r->fin_set + n;
r->C_mq[i] += 2 * f->C_N_alpha_tb_m * f->C_N_alpha_1[i] *
pow((f->Xt - r->Xcg)/r->Lr, 2);
}
r->C_m_alpha[i] = 0;
for (n = 0; n < r->n_fin_set; n++)
{
f = r->fin_set + n;
r->C_m_alpha[i] += f->C_N_alpha_tb_m * f->C_N_alpha_1[i] *
(r->X[i] - r->Xcg) / r->Lr;
}
/*
printf("Aerodynamic properties of the entire rocket.\n"
"--------------------------------------------\n");
printf("Reference area (Ar) = % f m2\n", r->Ar);
printf("C_N_alpha = % f\n", r->C_N_alpha);
printf("X = % f\n", r->X);
printf("Cmq = % f\n", r->C_mq);
*/
}
for (i = 0; i < r->n_mach; i++)
{
printf("M = %.2f -> C_N_alpha = %.3f, Cmq = %.3f, Cm_alpha = %.3f,"
" X = %.2f\n",
r->mach[i], r->C_N_alpha[i], r->C_mq[i], r->C_m_alpha[i], r->X[i]);
}
return 0;
}
int profile_fins(rocket_t *r)
{
int i, n;
float cr, ct, rt, lt, xt, s;
float beta;
float lambda;
float sac; /* midchord sweep angle cosine */
float tau; /* (s + rt)/rt */
float tau2; /* tau^2 */
float tau3;
fin_t *f;
/* fin treatment */
for (n = 0; n < r->n_fin_set; n++)
{
f = r->fin_set + n;
f->C_N_alpha_1 = (double *) malloc(sizeof(double) * r->n_mach);
cr = f->cr;
ct = f->ct;
rt = f->rt;
lt = f->lt;
xt = f->xt;
s = f->s;
/* add fin mass to the rocket mass */
r->m += f->N * f->m;
/* inertial properties */
f->Xcg = 0;
f->Ixx = 0;
f->Iyy = 0;
/* center of pressure of the fins */
/* formula 3-27 */
f->Yt = rt + (s/3)*(cr + 2*ct)/(cr + ct);
/* formula 3-30 */
f->Xt = lt + (xt/3)*(cr + 2*ct)/(cr + ct) +
(cr + ct - cr*ct/(cr+ct))/6;
/* formula 3-101 */
f->Xbt = lt + cr/4 +
((sqrt(s*s - rt*rt)*acosh(s/rt) - s + M_PI*rt/2)/
(rt*acosh(s/rt)/sqrt(s*s - rt*rt) + s/rt - M_PI/2) - rt) *
(xt + 0.25*(ct-cr))/s; /* check this part (tan(sweepback)) */
/* fin area */
f->Af = cr*s - xt*s/2 + (xt + ct - cr)*s/2;
/* fin aspect ratio */
f->AR = pow(s,2)/f->Af;
/* cosine of the midchord sweep angle */
sac = s/sqrt(pow(xt + ct - cr/2 - ct/2, 2) + pow(s, 2));
for (i = 0; i < r->n_mach; i++)
{
/* M is the mach number */
beta = sqrt(1 - pow(r->mach[i], 2));
/* formula 3-6 */
f->C_N_alpha_1[i] = 2 * M_PI * f->AR *
(f->Af/r->Ar) / (2 + sqrt(4 + pow(beta*f->AR/sac, 2) ));
}
/* formula 3-35 */
f->C_l_delta_m = f->N * f->Yt / r->Lr; /* *f->C_N_alpha_1 */
lambda = ct / cr;
/* formula 3-51 */
f->C_l_p_m = -(f->N * cr * s / (6*pow(r->Lr, 2)))*
((1+3*lambda)*pow(s, 2) + 4*(1+2*lambda)*s*rt + 6*(1+lambda)*pow(rt, 2));
/* * f->C_N_alpha_1;*/
tau = (s + rt)/rt;
tau2 = pow(tau, 2);
tau3 = pow(tau, 3);
/* formula 3-96 */
f->Ktb_alpha = 2*((1 + pow(tau, -4))*(0.5*atan(0.5*(tau-1/tau))) -
pow(tau, -2)*((tau-1/tau) + 2*atan(1/tau)))/
(M_PI * pow(1-1/tau, 2));
/*formula 3-98 */
f->Kbt = pow((1 - 1/tau2)/(1 - 1/tau), 2) - f->Ktb_alpha;
/* formula 3-105 */
/* CHECK THIS : when optimize with -O2 or -O3 in gcc, the value is nan
but is good with -O ???? */
f->Ktb_delta =
(M_PI2 * pow(1+1/tau, 2)/4 +
M_PI * pow( (tau2 + 1)/(tau2-tau), 2)*asin((tau2-1)/(tau2+1)) -
2*M_PI*(tau+1)/(tau2 - tau) +
pow((tau2+1)/(tau2-tau), 2)*pow(asin((tau2-1)/(tau2+1)), 2) -
4*(tau+1)*asin((tau2-1)/(tau2+1))/(tau2-tau) +
8*log((tau2+1)/(2*tau))/pow(tau-1,2))/M_PI2;
/* formula 3-122 */
f->Krb = 1 + ((tau-lambda)/tau - (1-lambda)*log(tau)/(tau-1))/
((tau+1)*(tau-lambda)/2 - (1-lambda)*(tau3-1)/(3*(tau-1)));
f->C_N_alpha_tb_m = f->N * f->Ktb_alpha / 2; /* * f->C_N_alpha_1 */
f->C_N_alpha_bt_m = f->N * f->Kbt / 2; /* * f->C_N_alpha_1 */
f->C_l_delta_tb_m = f->C_l_delta_m * f->Ktb_delta;
f->C_l_p_tb_m = f->C_l_p_m * f->Krb;
printf("Aerodynamic properties of the fin set number %d\n"
"-----------------------------------------------\n", n+1);
printf("Fin area (Af) = % f m2\n", f->Af);
printf("Aspect ratio (AR) = % f\n", f->AR);
printf("\n");
printf("Interference factors.\n");
printf("Ktb_alpha = % f\n", f->Ktb_alpha);
printf("Kbt = % f\n", f->Kbt);
printf("Ktb_delta = % f\n", f->Ktb_delta);
printf("Krb = % f\n", f->Krb);
printf("\n");
printf("Fin center of pressure location.\n");
printf("Yt = % .3f m\n", f->Yt);
printf("Xt = % .3f m\n", f->Xt);
printf("Xbt = % .3f m\n", f->Xbt);
printf("\n");
printf("Fin stability coefficients.\n");
for (i = 0; i < r->n_mach; i++)
{
printf("M = % .2f -> C_N_alpha_1 = % .4f\n",
r->mach[i], f->C_N_alpha_1[i]);
}
printf("C_l_delta_m = % f\n", f->C_l_delta_m);
printf("C_l_p_m = % f\n", f->C_l_p_m);
printf("\n");
printf("Fin stability coefficients with interference factors.\n");
printf("C_N_alpha_tb_m = % f\n", f->C_N_alpha_tb_m);
printf("C_N_alpha_bt_m = % f\n", f->C_N_alpha_bt_m);
printf("C_N_delta_tb_m = % f\n", f->C_l_delta_tb_m);
printf("C_l_p_tb_m = % f\n", f->C_l_p_tb_m);
}
return 0;
}
int profile_body(rocket_t *r)
{
int i, n;
float fn;
float dp; /* diameter of the previous part */
body_part_t *previous_part = NULL;
body_part_t *part = NULL;
/* body parts treatment */
for (n = 0; n < r->body.n_body_parts; n++)
{
part = r->body.body_parts + n;
if (n != 0)
previous_part = r->body.body_parts + n - 1;
r->m += part->m;
switch (part->type)
{
case OGIVE_NOSE:
fn = part->l / part->d;
part->A = 0;
part->V = 0;
part->Xof = 0;
part->Xcg = 0.466 * part->l;
part->Ix = 0;
part->Iy = 0;
break;
case ELLIPTIC_NOSE:
break;
case CONIC_NOSE:
part->A = M_PI * part->d *
sqrt(pow(part->d/2, 2) + pow(part->l, 2)) / 2;
part->V = M_PI * pow(part->d/2, 2) * part->l / 3;
part->Xof = 0;
part->Xcg = 2 * part->l / 3;
part->Ix = part->m * pow(part->d, 2) / 8;
/* moment of inertia about the axis passing at the tip of the cone */
part->Iy = part->m * (pow(part->d, 2)/16 + pow(part->l, 2)/2);
break;
case PARABOLIC_NOSE:
break;
case TUBE:
part->A = M_PI * part->d * part->l;
part->V = M_PI * pow(part->d, 2) * part->l / 4;
if (previous_part == NULL)
return -1;
part->Xof = previous_part->Xof + previous_part->l;
part->Xcg = part->Xof + part->l / 2;
part->Ix = part->m * pow(part->d, 2) / 4;
part->Iy = part->m * (pow(part->d, 2)/8 + pow(part->l, 2)/12);
break;
case TRANSITION:
dp = r->body.body_parts[n - 1].d;
part->A = M_PI*(part->d*sqrt(pow(part->d/2, 2) +
pow(part->l/(1 - part->d/dp), 2))/2 -
dp*sqrt(pow(dp/2, 2) +
pow(part->l*part->d/(dp*(1-part->d/dp)), 2))/2);
part->V = M_PI * part->l *
(pow(part->d/2, 2) - pow(dp/2, 2)*dp/part->d)/(3*(1 - dp/part->d));
/*part->Ix = ;*/
break;
default:
printf("Unknown type : %d\n", part->type);
break;
}
}
r->body.V = 0;
r->body.lo = 0;
r->body.Ab = 0;
for (i = 0; i < r->body.n_body_parts; i++)
{
part = r->body.body_parts + i;
r->body.V += part->V;
r->body.lo += part->l;
/* compute it only for the last part */
r->body.Ab = M_PI * pow(part->d, 2) / 4;
printf("Part geometric characteristics.\n");
printf("Volume = %e m3\n", part->V);
printf("Area = %e m2\n", part->A);
printf("Mass = %e kg\n", part->m);
printf("Ixx = %e kg-m2\n", part->Ix);
printf("Iyy = %e kg-m2\n", part->Iy);
printf("Xof = %e m\n", part->Xof);
printf("Xcg = %e m\n", part->Xcg);
}
/* formula 3-66 */
r->body.C_N_alpha_b = 2 * r->body.Ab / r->Ar;
r->body.Xb = r->body.lo - r->body.V/r->body.Ab;
printf("\n");
printf("Aerodynamic properties of the body.\n"
"-----------------------------------\n");
printf("Ab = % f\n", r->body.Ab);
printf("lo = % f\n", r->body.lo);
printf("C_N_alpha_b = % f\n", r->body.C_N_alpha_b);
printf("Xb = % f\n", r->body.Xb);
return 0;
}