# Autotune attitude control status
#
# This message is published by the fw_autotune_attitude_control and mc_autotune_attitude_control modules when the user engages autotune,
# and is subscribed to by the respective attitude controllers to command rate setpoints.
#
# The rate_sp field is consumed by the controllers, while the remaining fields (model coefficients, gains, filters, and autotune state) are used for logging and debugging.

uint64 timestamp  # [us] Time since system start

float32[5] coeff      # [-] Coefficients of the identified discrete-time model
float32[5] coeff_var  # [-] Coefficients' variance of the identified discrete-time model
float32 fitness       # [-] Fitness of the parameter estimate
float32 innov         # [rad/s] Innovation (residual error between model and measured output)
float32 dt_model      # [s] Model sample time used for identification


float32 kc    # [-] Proportional rate-loop gain (ideal form)
float32 ki    # [-] Integral rate-loop gain (ideal form)
float32 kd    # [-] Derivative rate-loop gain (ideal form)
float32 kff   # [-] Feedforward rate-loop gain
float32 att_p # [-] Proportional attitude gain

float32[3] rate_sp # [rad/s] Rate setpoint commanded to the attitude controller.

float32 u_filt  # [-] Filtered input signal (normalized torque setpoint) used in system identification.
float32 y_filt  # [rad/s] Filtered output signal (angular velocity) used in system identification.

uint8 state  # [@enum STATE] Current state of the autotune procedure.
uint8 STATE_IDLE = 0                      # Idle (not running)
uint8 STATE_INIT = 1                      # Initialize filters and setup
uint8 STATE_ROLL_AMPLITUDE_DETECTION = 2  # FW only: determine required excitation amplitude (roll)
uint8 STATE_ROLL = 3                      # Roll-axis excitation and model identification
uint8 STATE_ROLL_PAUSE = 4                # Pause to return to level flight
uint8 STATE_PITCH_AMPLITUDE_DETECTION = 5 # FW only: determine required excitation amplitude (pitch)
uint8 STATE_PITCH = 6                     # Pitch-axis excitation and model identification
uint8 STATE_PITCH_PAUSE = 7               # Pause to return to level flight
uint8 STATE_YAW_AMPLITUDE_DETECTION = 8   # FW only: determine required excitation amplitude (yaw)
uint8 STATE_YAW = 9                       # Yaw-axis excitation and model identification
uint8 STATE_YAW_PAUSE = 10                # Pause to return to level flight
uint8 STATE_VERIFICATION = 11             # Verify model and candidate gains
uint8 STATE_APPLY = 12                    # Apply gains
uint8 STATE_TEST = 13                     # Test gains in closed-loop
uint8 STATE_COMPLETE = 14                 # Tuning completed successfully
uint8 STATE_FAIL = 15                     # Tuning failed (model invalid or controller unstable)
uint8 STATE_WAIT_FOR_DISARM = 16          # Waiting for disarm before finalizing