Sub: Change M_PI to match Copter.

ArduSub/Attitude.cpp

@@ -33,7 +33,7 @@ void Sub::get_pilot_desired_lean_angles(float roll_in, float pitch_in, float &ro
     }
 
     // do lateral tilt to euler roll conversion
-    roll_in = (18000/M_PI_F) * atanf(cosf(pitch_in*(M_PI_F/18000))*tanf(roll_in*(M_PI_F/18000)));
+    roll_in = (18000/M_PI) * atanf(cosf(pitch_in*(M_PI/18000))*tanf(roll_in*(M_PI/18000)));
 
     // return
     roll_out = roll_in;

ArduSub/commands_logic.cpp

@@ -666,7 +666,7 @@ bool Sub::verify_circle(const AP_Mission::Mission_Command& cmd)
     }
 
     // check if we have completed circling
-    return fabsf(circle_nav.get_angle_total()/M_2PI_F) >= LOWBYTE(cmd.p1);
+    return fabsf(circle_nav.get_angle_total()/M_2PI) >= LOWBYTE(cmd.p1);
 }
 
 // verify_RTL - handles any state changes required to implement RTL

ArduSub/control_poshold.cpp

@@ -625,8 +625,8 @@ void Copter::poshold_get_wind_comp_lean_angles(int16_t &roll_angle, int16_t &pit
     poshold.wind_comp_timer = 0;
 
     // convert earth frame desired accelerations to body frame roll and pitch lean angles
-    roll_angle = atanf((-poshold.wind_comp_ef.x*ahrs.sin_yaw() + poshold.wind_comp_ef.y*ahrs.cos_yaw())/981)*(18000/M_PI_F);
-    pitch_angle = atanf(-(poshold.wind_comp_ef.x*ahrs.cos_yaw() + poshold.wind_comp_ef.y*ahrs.sin_yaw())/981)*(18000/M_PI_F);
+    roll_angle = atanf((-poshold.wind_comp_ef.x*ahrs.sin_yaw() + poshold.wind_comp_ef.y*ahrs.cos_yaw())/981)*(18000/M_PI);
+    pitch_angle = atanf(-(poshold.wind_comp_ef.x*ahrs.cos_yaw() + poshold.wind_comp_ef.y*ahrs.sin_yaw())/981)*(18000/M_PI);
 }
 
 // poshold_roll_controller_to_pilot_override - initialises transition from a controller submode (brake or loiter) to a pilot override on roll axis