Fix stall widths for the "auxilliary" (reverse flow) stalls so they

[flightgear.git] / src / FDM / UFO.cxx

diff --git a/src/FDM/UFO.cxx b/src/FDM/UFO.cxx
index 3223e35f9a2b0f6b8af65f07e8495bcc855e849f..60727faf3034b57620b11418bd45e309f6962cf6 100644 (file)
--- a/src/FDM/UFO.cxx
+++ b/src/FDM/UFO.cxx
@@ -3,7 +3,7 @@
 // Written by Curtis Olson, started October 1999.
 // Slightly modified from MagicCarpet.cxx by Jonathan Polley, April 2002
 //
-// Copyright (C) 1999-2002  Curtis L. Olson  - curt@flightgear.org
+// Copyright (C) 1999-2002  Curtis L. Olson  - http://www.flightgear.org/~curt
 //
 // This program is free software; you can redistribute it and/or
 // modify it under the terms of the GNU General Public License as
@@ -21,24 +21,30 @@
 //
 
 
+#ifdef HAVE_CONFIG_H
+#  include <config.h>
+#endif
+
 #include <simgear/math/sg_geodesy.hxx>
 #include <simgear/math/point3d.hxx>
 #include <simgear/math/polar3d.hxx>
 
-#include <Controls/controls.hxx>
+#include <Aircraft/controls.hxx>
 #include <Main/globals.hxx>
 #include <Main/fg_props.hxx>
 
 #include "UFO.hxx"
 
-const double throttle_damp = 0.05;
-const double aileron_damp = 0.01;
-const double elevator_damp = 0.01;
+const double throttle_damp = 0.2;
+const double aileron_damp = 0.05;
+const double elevator_damp = 0.05;
+const double rudder_damp = 0.4;
 
 FGUFO::FGUFO( double dt )
   : Throttle(0.0),
     Aileron(0.0),
-    Elevator(0.0)
+    Elevator(0.0),
+    Rudder(0.0)
 {
 //     set_delta_t( dt );
 }
@@ -62,13 +68,13 @@ void FGUFO::update( double dt ) {
     if (is_suspended())
       return;
 
-    int multiloop = _calc_multiloop(dt);
-
-    double time_step = dt * multiloop;
+    double time_step = dt;
 
     // read the throttle
     double th = globals->get_controls()->get_throttle( 0 );
-    if (globals->get_controls()->get_brake(0)) {
+    if ( globals->get_controls()->get_brake_left() > 0.0 
+         || globals->get_controls()->get_brake_right() > 0.0 )
+    {
         th = -th;
     }
     Throttle = th * throttle_damp + Throttle * (1 - throttle_damp);
@@ -78,6 +84,8 @@ void FGUFO::update( double dt ) {
                + Aileron * (1 - aileron_damp);
     Elevator = globals->get_controls()->get_elevator() * elevator_damp
                + Elevator * (1 - elevator_damp);
+    Rudder = globals->get_controls()->get_rudder() * rudder_damp
+               + Rudder * (1 - rudder_damp);
 
     // the velocity of the aircraft
     double velocity = Throttle * 2000; // meters/sec
@@ -156,6 +164,7 @@ void FGUFO::update( double dt ) {
     // angle of turn
     double turn_rate = sin(roll) * SGD_PI_4; // radians/sec
     double turn = turn_rate * time_step;
+    double yaw = fabs(Rudder) < .2 ? 0.0 : Rudder / (25 + fabs(speed) * .1);
 
     // update (lon/lat) position
     double lat2, lon2, az2;
@@ -179,13 +188,14 @@ void FGUFO::update( double dt ) {
 
     // update euler angles
     _set_Euler_Angles( roll, pitch,
-                       fmod(get_Psi() + turn, SGD_2PI) );
+                       fmod(get_Psi() + turn + yaw, SGD_2PI) );
     _set_Euler_Rates(0,0,0);
 
     _set_Geocentric_Position( lat_geoc, get_Longitude(), 
                             sl_radius + get_Altitude() + climb );
     // cout << "sea level radius (ft) = " << sl_radius << endl;
     // cout << "(setto) sea level radius (ft) = " << get_Sea_level_radius() << endl;
+    _update_ground_elev_at_pos();
     _set_Sea_level_radius( sl_radius * SG_METER_TO_FEET);
     _set_Altitude( get_Altitude() + climb );
 }