Added possibility to log pid control values

Conflicts:
	apps/multirotor_pos_control/multirotor_pos_control.c
	src/drivers/ardrone_interface/ardrone_interface.c

src/modules/fixedwing_att_control/fixedwing_att_control_att.c

@@ -142,7 +142,7 @@ int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att
 	}
 
 	/* Roll (P) */
-	rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body, att->roll, 0, 0);
+	rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body, att->roll, 0, 0, NULL, NULL, NULL);
 
 
 	/* Pitch (P) */
@@ -152,7 +152,7 @@ int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att
 	/* set pitch plus feedforward roll compensation */
 	rates_sp->pitch = pid_calculate(&pitch_controller,
 					att_sp->pitch_body + pitch_sp_rollcompensation,
-					att->pitch, 0, 0);
+					att->pitch, 0, 0, NULL, NULL, NULL);
 
 	/* Yaw (from coordinated turn constraint or lateral force) */
 	rates_sp->yaw = (att->rollspeed * rates_sp->roll + 9.81f * sinf(att->roll) * cosf(att->pitch) + speed_body[0] * rates_sp->pitch * sinf(att->roll))

src/modules/fixedwing_att_control/fixedwing_att_control_rate.c

@@ -196,11 +196,11 @@ int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
 
 
 	/* roll rate (PI) */
-	actuators->control[0] = pid_calculate(&roll_rate_controller, rate_sp->roll, rates[0], 0.0f, deltaT);
+	actuators->control[0] = pid_calculate(&roll_rate_controller, rate_sp->roll, rates[0], 0.0f, deltaT, NULL, NULL, NULL);
 	/* pitch rate (PI) */
-	actuators->control[1] = -pid_calculate(&pitch_rate_controller, rate_sp->pitch, rates[1], 0.0f, deltaT);
+	actuators->control[1] = -pid_calculate(&pitch_rate_controller, rate_sp->pitch, rates[1], 0.0f, deltaT, NULL, NULL, NULL);
 	/* yaw rate (PI) */
-	actuators->control[2] = pid_calculate(&yaw_rate_controller, rate_sp->yaw, rates[2], 0.0f, deltaT);
+	actuators->control[2] = pid_calculate(&yaw_rate_controller, rate_sp->yaw, rates[2], 0.0f, deltaT, NULL, NULL, NULL);
 
 	counter++;
 

src/modules/fixedwing_pos_control/fixedwing_pos_control_main.c

@@ -319,7 +319,7 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
 					// XXX what is xtrack_err.past_end?
 					if (distance_res == OK /*&& !xtrack_err.past_end*/) {
 
-						float delta_psi_c = pid_calculate(&offtrack_controller, 0, xtrack_err.distance, 0.0f, 0.0f); //p.xtrack_p * xtrack_err.distance
+						float delta_psi_c = pid_calculate(&offtrack_controller, 0, xtrack_err.distance, 0.0f, 0.0f, NULL, NULL, NULL); //p.xtrack_p * xtrack_err.distance
 
 						float psi_c = psi_track + delta_psi_c;
 						float psi_e = psi_c - att.yaw;
@@ -336,7 +336,7 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
 						}
 
 						/* calculate roll setpoint, do this artificially around zero */
-						float delta_psi_rate_c = pid_calculate(&heading_controller, psi_e, 0.0f, 0.0f, 0.0f);
+						float delta_psi_rate_c = pid_calculate(&heading_controller, psi_e, 0.0f, 0.0f, 0.0f, NULL, NULL, NULL);
 						float psi_rate_track = 0; //=V_gr/r_track , this will be needed for implementation of arc following
 						float psi_rate_c = delta_psi_rate_c + psi_rate_track;
 
@@ -359,7 +359,7 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
 
 						float psi_rate_e_scaled = psi_rate_e * ground_speed / 9.81f; //* V_gr / g
 
-						attitude_setpoint.roll_body = pid_calculate(&heading_rate_controller, psi_rate_e_scaled, 0.0f, 0.0f, deltaT);
+						attitude_setpoint.roll_body = pid_calculate(&heading_rate_controller, psi_rate_e_scaled, 0.0f, 0.0f, deltaT, NULL, NULL, NULL);
 
 						if (verbose) {
 							printf("psi_rate_c %.4f ", (double)psi_rate_c);
@@ -379,7 +379,7 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
 					if (pos_updated) {
 
 						//TODO: take care of relative vs. ab. altitude
-						attitude_setpoint.pitch_body = pid_calculate(&altitude_controller, global_setpoint.altitude, global_pos.alt, 0.0f, 0.0f);
+						attitude_setpoint.pitch_body = pid_calculate(&altitude_controller, global_setpoint.altitude, global_pos.alt, 0.0f, 0.0f, NULL, NULL, NULL);
 
 					}
 

src/modules/multirotor_att_control/multirotor_attitude_control.c

@@ -182,11 +182,11 @@ void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_s
 
 	/* control pitch (forward) output */
 	rates_sp->pitch = pid_calculate(&pitch_controller, att_sp->pitch_body ,
-					att->pitch, att->pitchspeed, deltaT);
+					att->pitch, att->pitchspeed, deltaT, NULL, NULL, NULL);
 
 	/* control roll (left/right) output */
 	rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body ,
-				       att->roll, att->rollspeed, deltaT);
+				       att->roll, att->rollspeed, deltaT, NULL, NULL, NULL);
 
 	// printf("rates_sp: %4.4f, att setpoint: %4.4f\n, pitch: %4.4f, pitchspeed: %4.4f, dT: %4.4f", rates_sp->pitch, att_sp->pitch_body, att->pitch, att->pitchspeed, deltaT);
 

src/modules/multirotor_att_control/multirotor_rate_control.c

@@ -197,11 +197,11 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
 
 	/* control pitch (forward) output */
 	float pitch_control = pid_calculate(&pitch_rate_controller, rate_sp->pitch ,
-			rates[1], 0.0f, deltaT);
+			rates[1], 0.0f, deltaT, NULL, NULL, NULL);
 
 	/* control roll (left/right) output */
 	float roll_control = pid_calculate(&roll_rate_controller, rate_sp->roll ,
-			rates[0], 0.0f, deltaT);
+			rates[0], 0.0f, deltaT, NULL, NULL, NULL);
 
 	/* increase resilience to faulty control inputs */
 	if (isfinite(pitch_control)) {

src/modules/systemlib/pid/pid.c

@@ -124,7 +124,7 @@ __EXPORT int pid_set_parameters(PID_t *pid, float kp, float ki, float kd, float
  * @param dt
  * @return
  */
-__EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, float dt)
+__EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, float dt, float *ctrl_p, float *ctrl_i, float *ctrl_d)
 {
 	/*  error = setpoint - actual_position
 	 integral = integral + (error*dt)
@@ -152,7 +152,7 @@ __EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, flo
 	if (pid->mode == PID_MODE_DERIVATIV_CALC) {
 
 //		d = (error_filtered - pid->error_previous_filtered) / dt;
-		d = pid->error_previous_filtered - error_filtered;
+		d = error_filtered - pid->error_previous_filtered ;
 		pid->error_previous_filtered = error_filtered;
 	} else if (pid->mode == PID_MODE_DERIVATIV_SET) {
 		d = -val_dot;
@@ -194,6 +194,10 @@ __EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, flo
 	// 	pid->error_previous = error;
 	// }
 
+	*ctrl_p = (error * pid->kp);
+	*ctrl_i = (i * pid->ki);
+	*ctrl_d = (d * pid->kd);
+
 	return pid->last_output;
 }
 

src/modules/systemlib/pid/pid.h

@@ -72,7 +72,7 @@ typedef struct {
 __EXPORT void pid_init(PID_t *pid, float kp, float ki, float kd, float intmax, float limit, float diff_filter_factor, uint8_t mode);
 __EXPORT int pid_set_parameters(PID_t *pid, float kp, float ki, float kd, float intmax, float limit, float diff_filter_factor);
 //void pid_set(PID_t *pid, float sp);
-__EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, float dt);
+__EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, float dt, float *ctrl_p, float *ctrl_i, float *ctrl_d);
 
 __EXPORT void pid_reset_integral(PID_t *pid);