/*
   This program is free software: you can redistribute it and/or modify
   it under the terms of the GNU General Public License as published by
   the Free Software Foundation, either version 3 of the License, or
   (at your option) any later version.

   This program is distributed in the hope that it will be useful,
   but WITHOUT ANY WARRANTY; without even the implied warranty of
   MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
   GNU General Public License for more details.

   You should have received a copy of the GNU General Public License
   along with this program.  If not, see <http://www.gnu.org/licenses/>.
 */
/*
  parent class for aircraft simulators
*/

#include "SIM_Aircraft.h"

#include <stdio.h>
#include <sys/time.h>
#include <unistd.h>


#if defined(__CYGWIN__) || defined(__CYGWIN64__)
#include <windows.h>
#include <time.h>
#include <mmsystem.h>
#endif

#include <GCS_MAVLink/GCS.h>
#include <AP_Logger/AP_Logger.h>
#include <AP_Param/AP_Param.h>
#include <AP_Declination/AP_Declination.h>

using namespace SITL;

/*
  parent class for all simulator types
 */

Aircraft::Aircraft(const char *frame_str) :
    ground_level(0.0f),
    frame_height(0.0f),
    dcm(),
    gyro(),
    gyro_prev(),
    ang_accel(),
    velocity_ef(),
    mass(0.0f),
    accel_body(0.0f, 0.0f, -GRAVITY_MSS),
    time_now_us(0),
    gyro_noise(radians(0.1f)),
    accel_noise(0.3f),
    rate_hz(1200.0f),
    autotest_dir(nullptr),
    frame(frame_str),
    num_motors(1),
#if defined(__CYGWIN__) || defined(__CYGWIN64__)
    min_sleep_time(20000)
#else
    min_sleep_time(5000)
#endif
{
    // make the SIM_* variables available to simulator backends
    sitl = AP::sitl();

    set_speedup(1.0f);

    last_wall_time_us = get_wall_time_us();
    frame_counter = 0;

    // allow for orientation settings, such as with tailsitters
    enum ap_var_type ptype;
    ahrs_orientation = (AP_Int8 *)AP_Param::find("AHRS_ORIENTATION", &ptype);

    // ahrs_orientation->get() returns ROTATION_NONE here, regardless of the actual value
    enum Rotation imu_rotation = ahrs_orientation?(enum Rotation)ahrs_orientation->get():ROTATION_NONE;
    sitl->ahrs_rotation.from_rotation(imu_rotation);
    sitl->ahrs_rotation_inv = sitl->ahrs_rotation.transposed();
    last_imu_rotation = imu_rotation;

    terrain = reinterpret_cast<AP_Terrain *>(AP_Param::find_object("TERRAIN_"));
}

void Aircraft::set_start_location(const Location &start_loc, const float start_yaw)
{
    home = start_loc;
    home_yaw = start_yaw;
    home_is_set = true;

    ::printf("Home: %f %f alt=%fm hdg=%f\n",
             home.lat*1e-7,
             home.lng*1e-7,
             home.alt*0.01,
             home_yaw);

    location = home;
    ground_level = home.alt * 0.01f;

    dcm.from_euler(0.0f, 0.0f, radians(home_yaw));
}

/*
   return difference in altitude between home position and current loc
*/
float Aircraft::ground_height_difference() const
{
    float h1, h2;
    if (sitl &&
        sitl->terrain_enable && terrain &&
        terrain->height_amsl(home, h1, false) &&
        terrain->height_amsl(location, h2, false)) {
        return h2 - h1;
    }
    return 0.0f;
}

void Aircraft::set_precland(SIM_Precland *_precland) {
    precland = _precland;
    precland->set_default_location(home.lat * 1.0e-7f, home.lng * 1.0e-7f, static_cast<int16_t>(get_home_yaw()));
}

/*
   return current height above ground level (metres)
*/
float Aircraft::hagl() const
{
    return (-position.z) + home.alt * 0.01f - ground_level - frame_height - ground_height_difference();
}
/*
   return true if we are on the ground
*/
bool Aircraft::on_ground() const
{
    return hagl() <= 0.001f;  // prevent bouncing around ground
}

/*
   update location from position
*/
void Aircraft::update_position(void)
{
    location = home;
    location.offset(position.x, position.y);

    location.alt  = static_cast<int32_t>(home.alt - position.z * 100.0f);

#if 0
    // logging of raw sitl data
    Vector3f accel_ef = dcm * accel_body;
// @LoggerMessage: SITL
// @Description: Simulation data
// @Field: TimeUS: Time since system startup
// @Field: VN: Velocity - North component
// @Field: VE: Velocity - East component
// @Field: VD: Velocity - Down component
// @Field: AN: Acceleration - North component
// @Field: AE: Acceleration - East component
// @Field: AD: Acceleration - Down component
// @Field: PN: Position - North component
// @Field: PE: Position - East component
// @Field: PD: Position - Down component
    AP::logger().Write("SITL", "TimeUS,VN,VE,VD,AN,AE,AD,PN,PE,PD", "Qfffffffff",
                                           AP_HAL::micros64(),
                                           velocity_ef.x, velocity_ef.y, velocity_ef.z,
                                           accel_ef.x, accel_ef.y, accel_ef.z,
                                           position.x, position.y, position.z);
#endif
}

/*
   update body magnetic field from position and rotation
*/
void Aircraft::update_mag_field_bf()
{
    // get the magnetic field intensity and orientation
    float intensity;
    float declination;
    float inclination;
    AP_Declination::get_mag_field_ef(location.lat * 1e-7f, location.lng * 1e-7f, intensity, declination, inclination);

    // create a field vector and rotate to the required orientation
    Vector3f mag_ef(1e3f * intensity, 0.0f, 0.0f);
    Matrix3f R;
    R.from_euler(0.0f, -ToRad(inclination), ToRad(declination));
    mag_ef = R * mag_ef;

    // calculate frame height above ground
    const float frame_height_agl = fmaxf((-position.z) + home.alt * 0.01f - ground_level, 0.0f);

    if (!sitl) {
        // running example program
        return;
    }

    // calculate scaling factor that varies from 1 at ground level to 1/8 at sitl->mag_anomaly_hgt
    // Assume magnetic anomaly strength scales with 1/R**3
    float anomaly_scaler = (sitl->mag_anomaly_hgt / (frame_height_agl + sitl->mag_anomaly_hgt));
    anomaly_scaler = anomaly_scaler * anomaly_scaler * anomaly_scaler;

    // add scaled anomaly to earth field
    mag_ef += sitl->mag_anomaly_ned.get() * anomaly_scaler;

    // Rotate into body frame
    mag_bf = dcm.transposed() * mag_ef;

    // add motor interference
    mag_bf += sitl->mag_mot.get() * battery_current;
}

/* advance time by deltat in seconds */
void Aircraft::time_advance()
{
    // we only advance time if it hasn't been advanced already by the
    // backend
    if (last_time_us == time_now_us) {
        time_now_us += frame_time_us;
    }
    last_time_us = time_now_us;
    if (use_time_sync) {
        sync_frame_time();
    }
}

/* setup the frame step time */
void Aircraft::setup_frame_time(float new_rate, float new_speedup)
{
    rate_hz = new_rate;
    target_speedup = new_speedup;
    frame_time_us = static_cast<uint64_t>(1.0e6f/rate_hz);

    scaled_frame_time_us = frame_time_us/target_speedup;
    last_wall_time_us = get_wall_time_us();
    achieved_rate_hz = rate_hz;
}

/* adjust frame_time calculation */
void Aircraft::adjust_frame_time(float new_rate)
{
    if (!is_equal(rate_hz, new_rate)) {
        rate_hz = new_rate;
        frame_time_us = static_cast<uint64_t>(1.0e6f/rate_hz);
        scaled_frame_time_us = frame_time_us/target_speedup;
    }
}

/*
   try to synchronise simulation time with wall clock time, taking
   into account desired speedup
   This tries to take account of possible granularity of
   get_wall_time_us() so it works reasonably well on windows
*/
void Aircraft::sync_frame_time(void)
{
    frame_counter++;
    uint64_t now = get_wall_time_us();
    if (frame_counter >= 40 &&
        now > last_wall_time_us) {
        const float rate = frame_counter * 1.0e6f/(now - last_wall_time_us);
        achieved_rate_hz = (0.99f*achieved_rate_hz) + (0.01f * rate);
        if (achieved_rate_hz < rate_hz * target_speedup) {
            scaled_frame_time_us *= 0.999f;
        } else {
            scaled_frame_time_us /= 0.999f;
        }
#if 0
        ::printf("achieved_rate_hz=%.3f rate=%.2f rate_hz=%.3f sft=%.1f\n",
                 static_cast<double>(achieved_rate_hz),
                 static_cast<double>(rate),
                 static_cast<double>(rate_hz),
                 static_cast<double>(scaled_frame_time_us));
#endif
        const uint32_t sleep_time = static_cast<uint32_t>(scaled_frame_time_us * frame_counter);
        if (sleep_time > min_sleep_time) {
            usleep(sleep_time);
        }
        last_wall_time_us = now;
        frame_counter = 0;
    }
}

/* add noise based on throttle level (from 0..1) */
void Aircraft::add_noise(float throttle)
{
    gyro += Vector3f(rand_normal(0, 1),
                     rand_normal(0, 1),
                     rand_normal(0, 1)) * gyro_noise * fabsf(throttle);
    accel_body += Vector3f(rand_normal(0, 1),
                           rand_normal(0, 1),
                           rand_normal(0, 1)) * accel_noise * fabsf(throttle);
}

/*
  normal distribution random numbers
  See
  http://en.literateprograms.org/index.php?title=Special:DownloadCode/Box-Muller_transform_%28C%29&oldid=7011
*/
double Aircraft::rand_normal(double mean, double stddev)
{
    static double n2 = 0.0;
    static int n2_cached = 0;
    if (!n2_cached) {
        double x, y, r;
        do
        {
            x = 2.0 * rand()/RAND_MAX - 1;
            y = 2.0 * rand()/RAND_MAX - 1;
            r = x*x + y*y;
        } while (is_zero(r) || r > 1.0);
        const double d = sqrt(-2.0 * log(r)/r);
        const double n1 = x * d;
        n2 = y * d;
        const double result = n1 * stddev + mean;
        n2_cached = 1;
        return result;
    } else {
        n2_cached = 0;
        return n2 * stddev + mean;
    }
}




/*
   fill a sitl_fdm structure from the simulator state
*/
void Aircraft::fill_fdm(struct sitl_fdm &fdm)
{
    if (use_smoothing) {
        smooth_sensors();
    }
    fdm.timestamp_us = time_now_us;
    if (fdm.home.lat == 0 && fdm.home.lng == 0) {
        // initialise home
        fdm.home = home;
    }
    fdm.latitude  = location.lat * 1.0e-7;
    fdm.longitude = location.lng * 1.0e-7;
    fdm.altitude  = location.alt * 1.0e-2;
    fdm.heading   = degrees(atan2f(velocity_ef.y, velocity_ef.x));
    fdm.speedN    = velocity_ef.x;
    fdm.speedE    = velocity_ef.y;
    fdm.speedD    = velocity_ef.z;
    fdm.xAccel    = accel_body.x;
    fdm.yAccel    = accel_body.y;
    fdm.zAccel    = accel_body.z;
    fdm.rollRate  = degrees(gyro.x);
    fdm.pitchRate = degrees(gyro.y);
    fdm.yawRate   = degrees(gyro.z);
    fdm.angAccel.x = degrees(ang_accel.x);
    fdm.angAccel.y = degrees(ang_accel.y);
    fdm.angAccel.z = degrees(ang_accel.z);
    float r, p, y;
    dcm.to_euler(&r, &p, &y);
    fdm.rollDeg  = degrees(r);
    fdm.pitchDeg = degrees(p);
    fdm.yawDeg   = degrees(y);
    fdm.quaternion.from_rotation_matrix(dcm);
    fdm.airspeed = airspeed_pitot;
    fdm.battery_voltage = battery_voltage;
    fdm.battery_current = battery_current;
    fdm.num_motors = num_motors;
    memcpy(fdm.rpm, rpm, num_motors * sizeof(float));
    fdm.rcin_chan_count = rcin_chan_count;
    fdm.range = range;
    memcpy(fdm.rcin, rcin, rcin_chan_count * sizeof(float));
    fdm.bodyMagField = mag_bf;

    // copy laser scanner results
    fdm.scanner.points = scanner.points;
    fdm.scanner.ranges = scanner.ranges;

    if (smoothing.enabled) {
        fdm.xAccel = smoothing.accel_body.x;
        fdm.yAccel = smoothing.accel_body.y;
        fdm.zAccel = smoothing.accel_body.z;
        fdm.rollRate  = degrees(smoothing.gyro.x);
        fdm.pitchRate = degrees(smoothing.gyro.y);
        fdm.yawRate   = degrees(smoothing.gyro.z);
        fdm.speedN    = smoothing.velocity_ef.x;
        fdm.speedE    = smoothing.velocity_ef.y;
        fdm.speedD    = smoothing.velocity_ef.z;
        fdm.latitude  = smoothing.location.lat * 1.0e-7;
        fdm.longitude = smoothing.location.lng * 1.0e-7;
        fdm.altitude  = smoothing.location.alt * 1.0e-2;
    }

    if (ahrs_orientation != nullptr) {
        enum Rotation imu_rotation = (enum Rotation)ahrs_orientation->get();
        if (imu_rotation != last_imu_rotation) {
            // Surprisingly, Matrix3<T>::from_rotation(ROTATION_CUSTOM) is the identity matrix
            // so we must deal with that here
            if (imu_rotation == ROTATION_CUSTOM) {
                if ((custom_roll == nullptr) || (custom_pitch == nullptr) || (custom_yaw == nullptr)) {
                    enum ap_var_type ptype;
                    custom_roll = (AP_Float *)AP_Param::find("AHRS_CUSTOM_ROLL", &ptype);
                    custom_pitch = (AP_Float *)AP_Param::find("AHRS_CUSTOM_PIT", &ptype);
                    custom_yaw = (AP_Float *)AP_Param::find("AHRS_CUSTOM_YAW", &ptype);
                }
                if ((custom_roll != nullptr) && (custom_pitch != nullptr) && (custom_yaw != nullptr)) {
                    sitl->ahrs_rotation.from_euler(radians(*custom_roll), radians(*custom_pitch), radians(*custom_yaw));
                    sitl->ahrs_rotation_inv = sitl->ahrs_rotation.transposed();
                } else {
                    AP_HAL::panic("could not find one or more of parameters AHRS_CUSTOM_ROLL/PITCH/YAW");
                }
            } else {
                sitl->ahrs_rotation.from_rotation(imu_rotation);
                sitl->ahrs_rotation_inv = sitl->ahrs_rotation.transposed();
                last_imu_rotation = imu_rotation;
            }
        }
        if (imu_rotation != ROTATION_NONE) {
            Matrix3f m = dcm;
            m = m * sitl->ahrs_rotation_inv;

            m.to_euler(&r, &p, &y);
            fdm.rollDeg  = degrees(r);
            fdm.pitchDeg = degrees(p);
            fdm.yawDeg   = degrees(y);
            fdm.quaternion.from_rotation_matrix(m);
        }
    }
    
    if (!is_equal(last_speedup, float(sitl->speedup)) && sitl->speedup > 0) {
        set_speedup(sitl->speedup);
        last_speedup = sitl->speedup;
    }
}

uint64_t Aircraft::get_wall_time_us() const
{
#if defined(__CYGWIN__) || defined(__CYGWIN64__)
    static DWORD tPrev;
    static uint64_t last_ret_us;
    if (tPrev == 0) {
        tPrev = timeGetTime();
        return 0;
    }
    DWORD now = timeGetTime();
    last_ret_us += (uint64_t)((now - tPrev)*1000UL);
    tPrev = now;
    return last_ret_us;
#else
    struct timeval tp;
    gettimeofday(&tp, nullptr);
    return static_cast<uint64_t>(tp.tv_sec * 1.0e6 + tp.tv_usec);
#endif
}

/*
  set simulation speedup
 */
void Aircraft::set_speedup(float speedup)
{
    setup_frame_time(rate_hz, speedup);
}

void Aircraft::update_model(const struct sitl_input &input)
{
    if (!home_is_set) {
        if (sitl == nullptr) {
            return;
        }
        Location loc;
        loc.lat = sitl->opos.lat.get() * 1.0e7;
        loc.lng = sitl->opos.lng.get() * 1.0e7;
        loc.alt = sitl->opos.alt.get() * 1.0e2;
        set_start_location(loc, sitl->opos.hdg.get());
    }
    update(input);
}

/*
  update the simulation attitude and relative position
 */
void Aircraft::update_dynamics(const Vector3f &rot_accel)
{
    const float delta_time = frame_time_us * 1.0e-6f;

    // update rotational rates in body frame
    gyro += rot_accel * delta_time;

    gyro.x = constrain_float(gyro.x, -radians(2000.0f), radians(2000.0f));
    gyro.y = constrain_float(gyro.y, -radians(2000.0f), radians(2000.0f));
    gyro.z = constrain_float(gyro.z, -radians(2000.0f), radians(2000.0f));

    // estimate angular acceleration using a first order difference calculation
    // TODO the simulator interface should provide the angular acceleration
    ang_accel = (gyro - gyro_prev) / delta_time;
    gyro_prev = gyro;

    // update attitude
    dcm.rotate(gyro * delta_time);
    dcm.normalize();

    Vector3f accel_earth = dcm * accel_body;
    accel_earth += Vector3f(0.0f, 0.0f, GRAVITY_MSS);

    // if we're on the ground, then our vertical acceleration is limited
    // to zero. This effectively adds the force of the ground on the aircraft
    if (on_ground() && accel_earth.z > 0) {
        accel_earth.z = 0;
    }

    // work out acceleration as seen by the accelerometers. It sees the kinematic
    // acceleration (ie. real movement), plus gravity
    accel_body = dcm.transposed() * (accel_earth + Vector3f(0.0f, 0.0f, -GRAVITY_MSS));

    // new velocity vector
    velocity_ef += accel_earth * delta_time;

    const bool was_on_ground = on_ground();
    // new position vector
    position += velocity_ef * delta_time;

    // velocity relative to air mass, in earth frame
    velocity_air_ef = velocity_ef + wind_ef;

    // velocity relative to airmass in body frame
    velocity_air_bf = dcm.transposed() * velocity_air_ef;

    // airspeed
    airspeed = velocity_air_ef.length();

    // airspeed as seen by a fwd pitot tube (limited to 120m/s)
    airspeed_pitot = constrain_float(velocity_air_bf * Vector3f(1.0f, 0.0f, 0.0f), 0.0f, 120.0f);

    // constrain height to the ground
    if (on_ground()) {
        if (!was_on_ground && AP_HAL::millis() - last_ground_contact_ms > 1000) {
            gcs().send_text(MAV_SEVERITY_INFO, "SIM Hit ground at %f m/s", velocity_ef.z);
            last_ground_contact_ms = AP_HAL::millis();
        }
        position.z = -(ground_level + frame_height - home.alt * 0.01f + ground_height_difference());

        switch (ground_behavior) {
        case GROUND_BEHAVIOR_NONE:
            break;
        case GROUND_BEHAVIOR_NO_MOVEMENT: {
            // zero roll/pitch, but keep yaw
            float r, p, y;
            dcm.to_euler(&r, &p, &y);
            dcm.from_euler(0.0f, 0.0f, y);
            // no X or Y movement
            velocity_ef.x = 0.0f;
            velocity_ef.y = 0.0f;
            if (velocity_ef.z > 0.0f) {
                velocity_ef.z = 0.0f;
            }
            gyro.zero();
            use_smoothing = true;
            break;
        }
        case GROUND_BEHAVIOR_FWD_ONLY: {
            // zero roll/pitch, but keep yaw
            float r, p, y;
            dcm.to_euler(&r, &p, &y);
            if (velocity_ef.length() < 5) {
                // at high speeds don't constrain pitch, otherwise we
                // can get stuck in takeoff
                p = 0;
            } else {
                p = MAX(p, 0);
            }
            dcm.from_euler(0.0f, p, y);
            // only fwd movement
            Vector3f v_bf = dcm.transposed() * velocity_ef;
            v_bf.y = 0.0f;
            if (v_bf.x < 0.0f) {
                v_bf.x = 0.0f;
            }
            velocity_ef = dcm * v_bf;
            if (velocity_ef.z > 0.0f) {
                velocity_ef.z = 0.0f;
            }
            gyro.zero();
            use_smoothing = true;
            break;
        }
        case GROUND_BEHAVIOR_TAILSITTER: {
            // point straight up
            float r, p, y;
            dcm.to_euler(&r, &p, &y);
            dcm.from_euler(0.0f, radians(90), y);
            // no movement
            if (accel_earth.z > -1.1*GRAVITY_MSS) {
                velocity_ef.zero();
            }
            gyro.zero();
            use_smoothing = true;
            break;
        }
        }
    }
}

/*
  update wind vector
*/
void Aircraft::update_wind(const struct sitl_input &input)
{
    // wind vector in earth frame
    wind_ef = Vector3f(cosf(radians(input.wind.direction))*cosf(radians(input.wind.dir_z)), 
                       sinf(radians(input.wind.direction))*cosf(radians(input.wind.dir_z)), 
                       sinf(radians(input.wind.dir_z))) * input.wind.speed;

    wind_ef.z += get_local_updraft(position);

    const float wind_turb = input.wind.turbulence * 10.0f;  // scale input.wind.turbulence to match standard deviation when using iir_coef=0.98
    const float iir_coef = 0.98f;  // filtering high frequencies from turbulence

    if (wind_turb > 0 && !on_ground()) {

        turbulence_azimuth = turbulence_azimuth + (2 * rand());

        turbulence_horizontal_speed =
                static_cast<float>(turbulence_horizontal_speed * iir_coef+wind_turb * rand_normal(0, 1) * (1 - iir_coef));

        turbulence_vertical_speed = static_cast<float>((turbulence_vertical_speed * iir_coef) + (wind_turb * rand_normal(0, 1) * (1 - iir_coef)));

        wind_ef += Vector3f(
            cosf(radians(turbulence_azimuth)) * turbulence_horizontal_speed,
            sinf(radians(turbulence_azimuth)) * turbulence_horizontal_speed,
            turbulence_vertical_speed);
    }
}

/*
  smooth sensors for kinematic consistancy when we interact with the ground
 */
void Aircraft::smooth_sensors(void)
{
    uint64_t now = time_now_us;
    Vector3f delta_pos = position - smoothing.position;
    if (smoothing.last_update_us == 0 || delta_pos.length() > 10) {
        smoothing.position = position;
        smoothing.rotation_b2e = dcm;
        smoothing.accel_body = accel_body;
        smoothing.velocity_ef = velocity_ef;
        smoothing.gyro = gyro;
        smoothing.last_update_us = now;
        smoothing.location = location;
        printf("Smoothing reset at %.3f\n", now * 1.0e-6f);
        return;
    }
    const float delta_time = (now - smoothing.last_update_us) * 1.0e-6f;
    if (delta_time < 0 || delta_time > 0.1) {
        return;
    }

    // calculate required accel to get us to desired position and velocity in the time_constant
    const float time_constant = 0.1f;
    Vector3f dvel = (velocity_ef - smoothing.velocity_ef) + (delta_pos / time_constant);
    Vector3f accel_e = dvel / time_constant + (dcm * accel_body + Vector3f(0.0f, 0.0f, GRAVITY_MSS));
    const float accel_limit = 14 * GRAVITY_MSS;
    accel_e.x = constrain_float(accel_e.x, -accel_limit, accel_limit);
    accel_e.y = constrain_float(accel_e.y, -accel_limit, accel_limit);
    accel_e.z = constrain_float(accel_e.z, -accel_limit, accel_limit);
    smoothing.accel_body = smoothing.rotation_b2e.transposed() * (accel_e + Vector3f(0.0f, 0.0f, -GRAVITY_MSS));

    // calculate rotational rate to get us to desired attitude in time constant
    Quaternion desired_q, current_q, error_q;
    desired_q.from_rotation_matrix(dcm);
    desired_q.normalize();
    current_q.from_rotation_matrix(smoothing.rotation_b2e);
    current_q.normalize();
    error_q = desired_q / current_q;
    error_q.normalize();

    Vector3f angle_differential;
    error_q.to_axis_angle(angle_differential);
    smoothing.gyro = gyro + angle_differential / time_constant;

    float R, P, Y;
    smoothing.rotation_b2e.to_euler(&R, &P, &Y);
    float R2, P2, Y2;
    dcm.to_euler(&R2, &P2, &Y2);

#if 0
// @LoggerMessage: SMOO
// @Description: Smoothed sensor data fed to EKF to avoid inconsistencies
// @Field: TimeUS: Time since system startup
// @Field: AEx: Angular Velocity (around x-axis)
// @Field: AEy: Angular Velocity (around y-axis)
// @Field: AEz: Angular Velocity (around z-axis)
// @Field: DPx: Velocity (along x-axis)
// @Field: DPy: Velocity (along y-axis)
// @Field: DPz: Velocity (along z-axis)
// @Field: R: Roll
// @Field: P: Pitch
// @Field: Y: Yaw
// @Field: R2: DCM Roll
// @Field: P2: DCM Pitch
// @Field: Y2: DCM Yaw
    AP::logger().Write("SMOO", "TimeUS,AEx,AEy,AEz,DPx,DPy,DPz,R,P,Y,R2,P2,Y2",
                                           "Qffffffffffff",
                                           AP_HAL::micros64(),
                                           degrees(angle_differential.x),
                                           degrees(angle_differential.y),
                                           degrees(angle_differential.z),
                                           delta_pos.x, delta_pos.y, delta_pos.z,
                                           degrees(R), degrees(P), degrees(Y),
                                           degrees(R2), degrees(P2), degrees(Y2));
#endif


    // integrate to get new attitude
    smoothing.rotation_b2e.rotate(smoothing.gyro * delta_time);
    smoothing.rotation_b2e.normalize();

    // integrate to get new position
    smoothing.velocity_ef += accel_e * delta_time;
    smoothing.position += smoothing.velocity_ef * delta_time;

    smoothing.location = home;
    smoothing.location.offset(smoothing.position.x, smoothing.position.y);
    smoothing.location.alt  = static_cast<int32_t>(home.alt - smoothing.position.z * 100.0f);

    smoothing.last_update_us = now;
    smoothing.enabled = true;
}

/*
  return a filtered servo input as a value from -1 to 1
  servo is assumed to be 1000 to 2000, trim at 1500
 */
float Aircraft::filtered_idx(float v, uint8_t idx)
{
    if (sitl->servo_speed <= 0) {
        return v;
    }
    const float cutoff = 1.0f / (2 * M_PI * sitl->servo_speed);
    servo_filter[idx].set_cutoff_frequency(cutoff);
    return servo_filter[idx].apply(v, frame_time_us * 1.0e-6f);
}


/*
  return a filtered servo input as a value from -1 to 1
  servo is assumed to be 1000 to 2000, trim at 1500
 */
float Aircraft::filtered_servo_angle(const struct sitl_input &input, uint8_t idx)
{
    const float v = (input.servos[idx] - 1500)/500.0f;
    return filtered_idx(v, idx);
}

/*
  return a filtered servo input as a value from 0 to 1
  servo is assumed to be 1000 to 2000
 */
float Aircraft::filtered_servo_range(const struct sitl_input &input, uint8_t idx)
{
    const float v = (input.servos[idx] - 1000)/1000.0f;
    return filtered_idx(v, idx);
}

// extrapolate sensors by a given delta time in seconds
void Aircraft::extrapolate_sensors(float delta_time)
{
    Vector3f accel_earth = dcm * accel_body;
    accel_earth.z += GRAVITY_MSS;

    dcm.rotate(gyro * delta_time);
    dcm.normalize();

    // work out acceleration as seen by the accelerometers. It sees the kinematic
    // acceleration (ie. real movement), plus gravity
    accel_body = dcm.transposed() * (accel_earth + Vector3f(0,0,-GRAVITY_MSS));

    // new velocity and position vectors
    velocity_ef += accel_earth * delta_time;
    position += velocity_ef * delta_time;
    velocity_air_ef = velocity_ef + wind_ef;
    velocity_air_bf = dcm.transposed() * velocity_air_ef;
}

void Aircraft::update_external_payload(const struct sitl_input &input)
{
    external_payload_mass = 0;

    // update sprayer
    if (sprayer && sprayer->is_enabled()) {
        sprayer->update(input);
        external_payload_mass += sprayer->payload_mass();
    }

    // update buzzer
    if (buzzer && buzzer->is_enabled()) {
        buzzer->update(input);
    }

    // update grippers
    if (gripper && gripper->is_enabled()) {
        gripper->set_alt(hagl());
        gripper->update(input);
        external_payload_mass += gripper->payload_mass();
    }
    if (gripper_epm && gripper_epm->is_enabled()) {
        gripper_epm->update(input);
        external_payload_mass += gripper_epm->payload_mass();
    }

    // update parachute
    if (parachute && parachute->is_enabled()) {
        parachute->update(input);
        // TODO: add drag to vehicle, presumably proportional to velocity
    }

    if (precland && precland->is_enabled()) {
        precland->update(get_location(), get_position());
    }
}

void Aircraft::add_shove_forces(Vector3f &rot_accel, Vector3f &body_accel)
{
    const uint32_t now = AP_HAL::millis();
    if (sitl == nullptr) {
        return;
    }
    if (sitl->shove.t == 0) {
        return;
    }
    if (sitl->shove.start_ms == 0) {
        sitl->shove.start_ms = now;
    }
    if (now - sitl->shove.start_ms < uint32_t(sitl->shove.t)) {
        // FIXME: can we get a vector operation here instead?
        body_accel.x += sitl->shove.x;
        body_accel.y += sitl->shove.y;
        body_accel.z += sitl->shove.z;
    } else {
        sitl->shove.start_ms = 0;
        sitl->shove.t = 0;
    }
}

float Aircraft::get_local_updraft(Vector3f currentPos)
{
    int scenario = sitl->thermal_scenario;

    #define MAX_THERMALS 10

    float thermals_w[MAX_THERMALS];
    float thermals_r[MAX_THERMALS];
    float thermals_x[MAX_THERMALS];
    float thermals_y[MAX_THERMALS];

    int n_thermals = 0;

    switch (scenario) {
        case 1:
            n_thermals = 1;
            thermals_w[0] =  2.0;
            thermals_r[0] =  80.0;
            thermals_x[0] = -180.0;
            thermals_y[0] = -260.0;
            break;
        case 2:
            n_thermals = 1;
            thermals_w[0] =  4.0;
            thermals_r[0] =  30.0;
            thermals_x[0] = -180.0;
            thermals_y[0] = -260.0;
            break;
        case 3:
            n_thermals = 1;
            thermals_w[0] =  2.0;
            thermals_r[0] =  30.0;
            thermals_x[0] = -180.0;
            thermals_y[0] = -260.0;
            break;
    }

    // Wind drift at this altitude
    float driftX = sitl->wind_speed * (currentPos.z+100) * cosf(sitl->wind_direction * DEG_TO_RAD);
    float driftY = sitl->wind_speed * (currentPos.z+100) * sinf(sitl->wind_direction * DEG_TO_RAD);

    int iThermal;
    float w = 0.0f;
    float r2;
    for (iThermal=0;iThermal<n_thermals;iThermal++) {
        Vector3f thermalPos(thermals_x[iThermal] + driftX/thermals_w[iThermal],
                            thermals_y[iThermal] + driftY/thermals_w[iThermal],
                            0);
        Vector3f relVec = currentPos - thermalPos;
        r2 = relVec.x*relVec.x + relVec.y*relVec.y;
        w += thermals_w[iThermal]*exp(-r2/(thermals_r[iThermal]*thermals_r[iThermal]));
    }

    return w;
}

void Aircraft::add_twist_forces(Vector3f &rot_accel)
{
    if (sitl == nullptr) {
        return;
    }
    if (sitl->gnd_behav != -1) {
        ground_behavior = (GroundBehaviour)sitl->gnd_behav.get();
    }
    const uint32_t now = AP_HAL::millis();
    if (sitl == nullptr) {
        return;
    }
    if (sitl->twist.t == 0) {
        return;
    }
    if (sitl->twist.start_ms == 0) {
        sitl->twist.start_ms = now;
    }
    if (now - sitl->twist.start_ms < uint32_t(sitl->twist.t)) {
        // FIXME: can we get a vector operation here instead?
        rot_accel.x += sitl->twist.x;
        rot_accel.y += sitl->twist.y;
        rot_accel.z += sitl->twist.z;
    } else {
        sitl->twist.start_ms = 0;
        sitl->twist.t = 0;
    }
}