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This commit is contained in:
Henning Stahlke 2017-02-19 12:57:39 +01:00
parent d4688d206a
commit 5f78545961

View file

@ -33,9 +33,9 @@ static const float KTS2MPS = 0.514444444444;
enum Config
{
CONFIG_NONE,
CONFIG_APPROACH,
CONFIG_CRUISE,
CONFIG_NONE,
CONFIG_APPROACH,
CONFIG_CRUISE,
};
// Generate a graph of lift, drag and L/D against AoA at the specified
@ -50,70 +50,70 @@ enum Config
*/
void yasim_graph(Airplane* a, float alt, float kts, int cfg = CONFIG_NONE)
{
Model* m = a->getModel();
State s;
Model* m = a->getModel();
State s;
m->setAir(Atmosphere::getStdPressure(alt),
Atmosphere::getStdTemperature(alt),
Atmosphere::getStdDensity(alt));
m->setAir(Atmosphere::getStdPressure(alt),
Atmosphere::getStdTemperature(alt),
Atmosphere::getStdDensity(alt));
switch (cfg) {
case CONFIG_APPROACH:
a->loadApproachControls();
break;
case CONFIG_CRUISE:
a->loadCruiseControls();
break;
case CONFIG_NONE:
break;
}
//if we fake the properties we could also use FGFDM::getExternalInput()
switch (cfg) {
case CONFIG_APPROACH:
a->loadApproachControls();
break;
case CONFIG_CRUISE:
a->loadCruiseControls();
break;
case CONFIG_NONE:
break;
}
//if we fake the properties we could also use FGFDM::getExternalInput()
m->getBody()->recalc();
m->getBody()->recalc();
for(int deg=-179; deg<=179; deg++) {
float aoa = deg * DEG2RAD;
Airplane::setupState(aoa, kts * KTS2MPS, 0 ,&s);
m->getBody()->reset();
m->initIteration();
m->calcForces(&s);
for(int deg=-179; deg<=179; deg++) {
float aoa = deg * DEG2RAD;
Airplane::setupState(aoa, kts * KTS2MPS, 0 ,&s);
m->getBody()->reset();
m->initIteration();
m->calcForces(&s);
float acc[3];
m->getBody()->getAccel(acc);
Math::tmul33(s.orient, acc, acc);
float acc[3];
m->getBody()->getAccel(acc);
Math::tmul33(s.orient, acc, acc);
float drag = acc[0] * (-1/9.8);
float lift = 1 + acc[2] * (1/9.8);
float drag = acc[0] * (-1/9.8);
float lift = 1 + acc[2] * (1/9.8);
printf("%d %g %g %g\n", deg, lift, drag, lift/drag);
}
printf("%d %g %g %g\n", deg, lift, drag, lift/drag);
}
}
void yasim_masses(Airplane* a)
{
RigidBody* body = a->getModel()->getBody();
int i, N = body->numMasses();
float pos[3];
float m, mass = 0;
printf("id posx posy posz mass\n");
for (i = 0; i < N; i++)
{
body->getMassPosition(i, pos);
m = body->getMass(i);
printf("%d %.3f %.3f %.3f %.3f\n", i, pos[0], pos[1], pos[2], m);
mass += m;
}
printf("Total mass: %g", mass);
RigidBody* body = a->getModel()->getBody();
int i, N = body->numMasses();
float pos[3];
float m, mass = 0;
printf("id posx posy posz mass\n");
for (i = 0; i < N; i++)
{
body->getMassPosition(i, pos);
m = body->getMass(i);
printf("%d %.3f %.3f %.3f %.3f\n", i, pos[0], pos[1], pos[2], m);
mass += m;
}
printf("Total mass: %g", mass);
}
int usage()
{
fprintf(stderr, "Usage: yasim <ac.xml> [-g [-a alt] [-s kts] [-approach | -cruise] ]\n");
fprintf(stderr, " yasim <ac.xml> [-m]\n");
fprintf(stderr, " -g print lift/drag table: aoa, lift, drag, lift/drag \n");
fprintf(stderr, " -m print mass distribution table: id, x, y, z, mass \n");
return 1;
fprintf(stderr, "Usage: yasim <ac.xml> [-g [-a alt] [-s kts] [-approach | -cruise] ]\n");
fprintf(stderr, " yasim <ac.xml> [-m]\n");
fprintf(stderr, " -g print lift/drag table: aoa, lift, drag, lift/drag \n");
fprintf(stderr, " -m print mass distribution table: id, x, y, z, mass \n");
return 1;
}
@ -137,50 +137,50 @@ int main(int argc, char** argv)
if(a->getFailureMsg())
printf("SOLUTION FAILURE: %s\n", a->getFailureMsg());
if(!a->getFailureMsg() && argc > 2 ) {
if(strcmp(argv[2], "-g") == 0) {
float alt = 5000, kts = 100;
int cfg = CONFIG_NONE;
for(int i=3; i<argc; i++) {
if (std::strcmp(argv[i], "-a") == 0) {
if(strcmp(argv[2], "-g") == 0) {
float alt = 5000, kts = 100;
int cfg = CONFIG_NONE;
for(int i=3; i<argc; i++) {
if (std::strcmp(argv[i], "-a") == 0) {
if (i+1 < argc) alt = std::atof(argv[++i]);
}
else if(std::strcmp(argv[i], "-s") == 0) {
else if(std::strcmp(argv[i], "-s") == 0) {
if(i+1 < argc) kts = std::atof(argv[++i]);
}
else if(std::strcmp(argv[i], "-approach") == 0) cfg = CONFIG_APPROACH;
else if(std::strcmp(argv[i], "-cruise") == 0) cfg = CONFIG_CRUISE;
else return usage();
}
yasim_graph(a, alt, kts, cfg);
}
else if(strcmp(argv[2], "-m") == 0) {
yasim_masses(a);
}
}
else {
printf("Solution results:");
float aoa = a->getCruiseAoA() * RAD2DEG;
float tail = -1 * a->getTailIncidence() * RAD2DEG;
float drag = 1000 * a->getDragCoefficient();
float cg[3];
a->getModel()->getBody()->getCG(cg);
a->getModel()->getBody()->recalc();
else if(std::strcmp(argv[i], "-approach") == 0) cfg = CONFIG_APPROACH;
else if(std::strcmp(argv[i], "-cruise") == 0) cfg = CONFIG_CRUISE;
else return usage();
}
yasim_graph(a, alt, kts, cfg);
}
else if(strcmp(argv[2], "-m") == 0) {
yasim_masses(a);
}
}
else {
printf("Solution results:");
float aoa = a->getCruiseAoA() * RAD2DEG;
float tail = -1 * a->getTailIncidence() * RAD2DEG;
float drag = 1000 * a->getDragCoefficient();
float cg[3];
a->getModel()->getBody()->getCG(cg);
a->getModel()->getBody()->recalc();
float SI_inertia[9];
a->getModel()->getBody()->getInertiaMatrix(SI_inertia);
float SI_inertia[9];
a->getModel()->getBody()->getInertiaMatrix(SI_inertia);
printf(" Iterations: %d\n", a->getSolutionIterations());
printf(" Drag Coefficient: %f\n", drag);
printf(" Lift Ratio: %f\n", a->getLiftRatio());
printf(" Cruise AoA: %f\n", aoa);
printf(" Tail Incidence: %f\n", tail);
printf("Approach Elevator: %f\n", a->getApproachElevator());
printf(" CG: x:%.3f, y:%.3f, z:%.3f\n\n", cg[0], cg[1], cg[2]);
printf("Inertia tensor [kg*m^2], origo at CG:\n");
printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[0], SI_inertia[1], SI_inertia[2]);
printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[3], SI_inertia[4], SI_inertia[5]);
printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[6], SI_inertia[7], SI_inertia[8]);
}
printf(" Iterations: %d\n", a->getSolutionIterations());
printf(" Drag Coefficient: %f\n", drag);
printf(" Lift Ratio: %f\n", a->getLiftRatio());
printf(" Cruise AoA: %f\n", aoa);
printf(" Tail Incidence: %f\n", tail);
printf("Approach Elevator: %f\n", a->getApproachElevator());
printf(" CG: x:%.3f, y:%.3f, z:%.3f\n\n", cg[0], cg[1], cg[2]);
printf("Inertia tensor [kg*m^2], origo at CG:\n");
printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[0], SI_inertia[1], SI_inertia[2]);
printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[3], SI_inertia[4], SI_inertia[5]);
printf(" %7.3f, %7.3f, %7.3f\n", SI_inertia[6], SI_inertia[7], SI_inertia[8]);
}
delete fdm;
return 0;
}