Port over remaining Point3D usage to the more type and unit safe SG* classes.

[flightgear.git] / src / FDM / YASim / yasim-test.cpp

diff --git a/src/FDM/YASim/yasim-test.cpp b/src/FDM/YASim/yasim-test.cpp
index 4e18b5cdfa3c56e577b68fdeba7cfde46e9039db..2fa6425267f2488eaaf3f5fe0926d8ee7ef36aa0 100644 (file)
--- a/src/FDM/YASim/yasim-test.cpp
+++ b/src/FDM/YASim/yasim-test.cpp
@@ -1,9 +1,13 @@
 #include <stdio.h>
 
+#include <cstring>
+#include <cstdlib>
+
+#include <simgear/props/props.hxx>
 #include <simgear/xml/easyxml.hxx>
-#include <simgear/misc/props.hxx>
 
 #include "FGFDM.hpp"
+#include "Atmosphere.hpp"
 #include "Airplane.hpp"
 
 using namespace yasim;
@@ -12,19 +16,73 @@ using namespace yasim;
 bool fgSetFloat (const char * name, float val) { return false; }
 bool fgSetBool(char const * name, bool val) { return false; }
 bool fgGetBool(char const * name, bool def) { return false; }
+bool fgSetString(char const * name, char const * str) { return false; }
 SGPropertyNode* fgGetNode (const char * path, bool create) { return 0; }
+SGPropertyNode* fgGetNode (const char * path, int i, bool create) { return 0; }
 float fgGetFloat (const char * name, float defaultValue) { return 0; }
+double fgGetDouble (const char * name, double defaultValue = 0.0) { return 0; }
+bool fgSetDouble (const char * name, double defaultValue = 0.0) { return 0; }
 
 static const float RAD2DEG = 57.2957795131;
+static const float DEG2RAD = 0.0174532925199;
+static const float KTS2MPS = 0.514444444444;
+
+
+// Generate a graph of lift, drag and L/D against AoA at the specified
+// speed and altitude.  The result is a space-separated file of
+// numbers: "aoa lift drag LD" (aoa in degrees, lift and drag in
+// G's).  You can use this in gnuplot like so (assuming the output is
+// in a file named "dat":
+//
+// plot "dat" using 1:2 with lines title 'lift', \ 
+//      "dat" using 1:3 with lines title 'drag', \ 
+//      "dat" using 1:4 with lines title 'LD'
+//
+void yasim_graph(Airplane* a, float alt, float kts)
+{
+    Model* m = a->getModel();
+    State s;
+
+    m->setAir(Atmosphere::getStdPressure(alt),
+              Atmosphere::getStdTemperature(alt),
+              Atmosphere::getStdDensity(alt));
+    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);
+
+        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);
+
+        printf("%d %g %g %g\n", deg, lift, drag, lift/drag);
+    }
+}
+
+int usage()
+{
+    fprintf(stderr, "Usage: yasim <ac.xml> [-g [-a alt] [-s kts]]\n");
+    return 1;
+}
 
 int main(int argc, char** argv)
 {
-    FGFDM fdm;
-    Airplane* a = fdm.getAirplane();
+    FGFDM* fdm = new FGFDM();
+    Airplane* a = fdm->getAirplane();
+
+    if(argc < 2) return usage();
 
     // Read
     try {
-        readXML(argv[1], fdm);
+        string file = argv[1];
+        readXML(file, *fdm);
     } catch (const sg_exception &e) {
         printf("XML parse error: %s (%s)\n",
                e.getFormattedMessage().c_str(), e.getOrigin().c_str());
@@ -32,22 +90,40 @@ int main(int argc, char** argv)
 
     // ... and run
     a->compile();
-
-    float aoa = a->getCruiseAoA() * RAD2DEG;
-    float tail = -1 * a->getTailIncidence() * RAD2DEG;
-    float drag = 1000 * a->getDragCoefficient();
-    float cg[3];
-    a->getModel()->getBody()->getCG(cg);
-
-    printf("Solution results:");
-    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: %.3f, %.3f, %.3f\n", cg[0], cg[1], cg[2]);
-
     if(a->getFailureMsg())
         printf("SOLUTION FAILURE: %s\n", a->getFailureMsg());
+
+    if(!a->getFailureMsg() && argc > 2 && strcmp(argv[2], "-g") == 0) {
+        float alt = 5000, kts = 100;
+        for(int i=3; i<argc; i++) {
+            if     (std::strcmp(argv[i], "-a") == 0) alt = std::atof(argv[++i]);
+            else if(std::strcmp(argv[i], "-s") == 0) kts = std::atof(argv[++i]);
+            else return usage();
+        }
+        yasim_graph(a, alt, kts);
+    } else {
+        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);
+        
+        printf("Solution results:");
+        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 : %.3f, %.3f, %.3f\n", SI_inertia[0], SI_inertia[1], SI_inertia[2]);
+        printf("        [kg*m^2]   %.3f, %.3f, %.3f\n", SI_inertia[3], SI_inertia[4], SI_inertia[5]);
+        printf("     Origo at CG   %.3f, %.3f, %.3f\n", SI_inertia[6], SI_inertia[7], SI_inertia[8]);
+    }
+    delete fdm;
+    return 0;
 }