net->phi = cur_fdm_state->get_Phi();
net->theta = cur_fdm_state->get_Theta();
net->psi = cur_fdm_state->get_Psi();
+ net->alpha = cur_fdm_state->get_Alpha();
+ net->beta = cur_fdm_state->get_Beta();
net->phidot = cur_fdm_state->get_Phi_dot_degps() * SG_DEGREES_TO_RADIANS;
net->thetadot = cur_fdm_state->get_Theta_dot_degps()
* SG_DEGREES_TO_RADIANS;
htonf(net->phi);
htonf(net->theta);
htonf(net->psi);
+ htonf(net->alpha);
+ htonf(net->beta);
htonf(net->phidot);
htonf(net->thetadot);
htonf(net->phi);
htonf(net->theta);
htonf(net->psi);
+ htonf(net->alpha);
+ htonf(net->beta);
htonf(net->phidot);
htonf(net->thetadot);
cur_fdm_state->_set_Euler_Angles( net->phi,
net->theta,
net->psi );
+ cur_fdm_state->_set_Alpha( net->alpha );
+ cur_fdm_state->_set_Beta( net->beta );
cur_fdm_state->_set_Euler_Rates( net->phidot,
net->thetadot,
net->psidot );
#include <time.h> // time_t
-const int FG_NET_FDM_VERSION = 15;
+const int FG_NET_FDM_VERSION = 16;
// Define a structure containing the top level flight dynamics model
float phi; // roll (radians)
float theta; // pitch (radians)
float psi; // yaw or true heading (radians)
+ float alpha; // angle of attack
+ float beta; // side slip angle
// Velocities
float phidot; // roll rate (radians/sec)