/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
#include "Sub.h"


/*
 * control_althold.pde - init and run calls for althold, flight mode
 */

// althold_init - initialise althold controller
bool Sub::althold_init(bool ignore_checks)
{
#if FRAME_CONFIG == HELI_FRAME
    // do not allow helis to enter Alt Hold if the Rotor Runup is not complete
    if (!ignore_checks && !motors.rotor_runup_complete()){
        return false;
    }
#endif

    // initialize vertical speeds and leash lengths
    // sets the maximum speed up and down returned by position controller
    pos_control.set_speed_z(-g.pilot_velocity_z_max, g.pilot_velocity_z_max);
    pos_control.set_accel_z(g.pilot_accel_z);

    // initialise position and desired velocity
    pos_control.set_alt_target(inertial_nav.get_altitude());
    pos_control.set_desired_velocity_z(inertial_nav.get_velocity_z());

    // stop takeoff if running
    takeoff_stop();

    return true;
}

// althold_run - runs the althold controller
// should be called at 100hz or more
void Sub::althold_run()
{
    AltHoldModeState althold_state;
    float takeoff_climb_rate = 0.0f;

    // initialize vertical speeds and acceleration
    pos_control.set_speed_z(-g.pilot_velocity_z_max, g.pilot_velocity_z_max);
    pos_control.set_accel_z(g.pilot_accel_z);

    // apply SIMPLE mode transform to pilot inputs
    update_simple_mode();

    // get pilot desired lean angles
    float target_roll, target_pitch;
    get_pilot_desired_lean_angles(channel_roll->control_in, channel_pitch->control_in, target_roll, target_pitch, attitude_control.get_althold_lean_angle_max());

    // get pilot's desired yaw rate
    float target_yaw_rate = get_pilot_desired_yaw_rate(channel_yaw->control_in);

    // get pilot desired climb rate
    float target_climb_rate = get_pilot_desired_climb_rate(channel_throttle->control_in);
    target_climb_rate = constrain_float(target_climb_rate, -g.pilot_velocity_z_max, g.pilot_velocity_z_max);

#if FRAME_CONFIG == HELI_FRAME
    // helicopters are held on the ground until rotor speed runup has finished
    bool takeoff_triggered = (ap.land_complete && (channel_throttle->control_in > get_takeoff_trigger_throttle()) && motors.rotor_runup_complete());
#else
    bool takeoff_triggered = (ap.land_complete && (channel_throttle->control_in > get_takeoff_trigger_throttle()));
#endif

//    // Alt Hold State Machine Determination
//    if(!ap.auto_armed) {
//        althold_state = AltHold_Disarmed;
//    } else if (!motors.get_interlock()){
//        althold_state = AltHold_MotorStop;
//    } else if (takeoff_state.running || takeoff_triggered){
//        althold_state = AltHold_Takeoff;
//    } else if (ap.land_complete){
//        althold_state = AltHold_Landed;
//    } else {
        althold_state = AltHold_Flying;
//    }

    // Alt Hold State Machine
    switch (althold_state) {

    case AltHold_Disarmed:

#if FRAME_CONFIG == HELI_FRAME  // Helicopters always stabilize roll/pitch/yaw
        attitude_control.set_yaw_target_to_current_heading();
        // call attitude controller
        attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw_smooth(target_roll, target_pitch, target_yaw_rate, get_smoothing_gain());
        attitude_control.set_throttle_out(0,false,g.throttle_filt);
#else   // Multicopter do not stabilize roll/pitch/yaw when disarmed
        attitude_control.set_throttle_out_unstabilized(0,true,g.throttle_filt);
#endif  // HELI_FRAME
        pos_control.relax_alt_hold_controllers(get_throttle_pre_takeoff(channel_throttle->control_in)-throttle_average);
        break;

    case AltHold_MotorStop:

#if FRAME_CONFIG == HELI_FRAME    
        // helicopters are capable of flying even with the motor stopped, therefore we will attempt to keep flying
        // call attitude controller
        attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw_smooth(target_roll, target_pitch, target_yaw_rate, get_smoothing_gain());

        // force descent rate and call position controller
        pos_control.set_alt_target_from_climb_rate(-abs(g.land_speed), G_Dt, false);
        pos_control.update_z_controller();
#else   // Multicopter do not stabilize roll/pitch/yaw when motor are stopped
        attitude_control.set_throttle_out_unstabilized(0,true,g.throttle_filt);
        pos_control.relax_alt_hold_controllers(get_throttle_pre_takeoff(channel_throttle->control_in)-throttle_average);
#endif  // HELI_FRAME
        break;

    case AltHold_Takeoff:

        // initiate take-off
        if (!takeoff_state.running) {
            takeoff_timer_start(constrain_float(g.pilot_takeoff_alt,0.0f,1000.0f));
            // indicate we are taking off
            set_land_complete(false);
            // clear i terms
            set_throttle_takeoff();
        }

        // get take-off adjusted pilot and takeoff climb rates
        takeoff_get_climb_rates(target_climb_rate, takeoff_climb_rate);

        // call attitude controller
        attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw_smooth(target_roll, target_pitch, target_yaw_rate, get_smoothing_gain());

        // call position controller
        pos_control.set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
        pos_control.add_takeoff_climb_rate(takeoff_climb_rate, G_Dt);
        pos_control.update_z_controller();
        break;

    case AltHold_Landed:

#if FRAME_CONFIG == HELI_FRAME  // Helicopters always stabilize roll/pitch/yaw
        attitude_control.set_yaw_target_to_current_heading();
        // call attitude controller
        attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw_smooth(target_roll, target_pitch, target_yaw_rate, get_smoothing_gain());
        attitude_control.set_throttle_out(get_throttle_pre_takeoff(channel_throttle->control_in),false,g.throttle_filt);
#else   // Multicopter do not stabilize roll/pitch/yaw when disarmed
        attitude_control.set_throttle_out_unstabilized(get_throttle_pre_takeoff(channel_throttle->control_in),true,g.throttle_filt);
#endif
        pos_control.relax_alt_hold_controllers(get_throttle_pre_takeoff(channel_throttle->control_in)-throttle_average);
        break;

    case AltHold_Flying:
        // call attitude controller
        attitude_control.input_euler_angle_roll_pitch_euler_rate_yaw_smooth(target_roll, target_pitch, target_yaw_rate, get_smoothing_gain());

        // call throttle controller
        if (sonar_enabled && (sonar_alt_health >= SONAR_ALT_HEALTH_MAX)) {
            // if sonar is ok, use surface tracking
            target_climb_rate = get_surface_tracking_climb_rate(target_climb_rate, pos_control.get_alt_target(), G_Dt);
        }

        // call position controller
        pos_control.set_alt_target_from_climb_rate_ff(target_climb_rate, G_Dt, false);
        pos_control.update_z_controller();
        break;
    }

    //control_in is range 0-1000
    //radio_in is raw pwm value
    motors.set_forward(channel_forward->radio_in);
    motors.set_strafe(channel_strafe->radio_in);
}