ardupilot/libraries/AP_NavEKF3/AP_NavEKF3_Measurements.cpp

#include <AP_HAL/AP_HAL.h>

#if HAL_CPU_CLASS >= HAL_CPU_CLASS_150
#include "AP_NavEKF3.h"
#include "AP_NavEKF3_core.h"
#include <AP_AHRS/AP_AHRS.h>
#include <AP_Vehicle/AP_Vehicle.h>
#include <GCS_MAVLink/GCS.h>

extern const AP_HAL::HAL& hal;


/********************************************************
*              OPT FLOW AND RANGE FINDER                *
********************************************************/

// Read the range finder and take new measurements if available
// Apply a median filter
void NavEKF3_core::readRangeFinder(void)
{
    uint8_t midIndex;
    uint8_t maxIndex;
    uint8_t minIndex;
    // get theoretical correct range when the vehicle is on the ground
    // don't allow range to go below 5cm becasue this can cause problems with optical flow processing
    rngOnGnd = MAX(frontend->_rng.ground_clearance_cm() * 0.01f, 0.05f);

    // limit update rate to maximum allowed by data buffers
    if ((imuSampleTime_ms - lastRngMeasTime_ms) > frontend->sensorIntervalMin_ms) {

        // reset the timer used to control the measurement rate
        lastRngMeasTime_ms =  imuSampleTime_ms;

        // store samples and sample time into a ring buffer if valid
        // use data from two range finders if available

        for (uint8_t sensorIndex = 0; sensorIndex <= 1; sensorIndex++) {
            if (frontend->_rng.status(sensorIndex) == RangeFinder::RangeFinder_Good) {
                rngMeasIndex[sensorIndex] ++;
                if (rngMeasIndex[sensorIndex] > 2) {
                    rngMeasIndex[sensorIndex] = 0;
                }
                storedRngMeasTime_ms[sensorIndex][rngMeasIndex[sensorIndex]] = imuSampleTime_ms - 25;
                storedRngMeas[sensorIndex][rngMeasIndex[sensorIndex]] = frontend->_rng.distance_cm(sensorIndex) * 0.01f;
            }

            // check for three fresh samples
            bool sampleFresh[2][3] = {};
            for (uint8_t index = 0; index <= 2; index++) {
                sampleFresh[sensorIndex][index] = (imuSampleTime_ms - storedRngMeasTime_ms[sensorIndex][index]) < 500;
            }

            // find the median value if we have three fresh samples
            if (sampleFresh[sensorIndex][0] && sampleFresh[sensorIndex][1] && sampleFresh[sensorIndex][2]) {
                if (storedRngMeas[sensorIndex][0] > storedRngMeas[sensorIndex][1]) {
                    minIndex = 1;
                    maxIndex = 0;
                } else {
                    minIndex = 0;
                    maxIndex = 1;
                }
                if (storedRngMeas[sensorIndex][2] > storedRngMeas[sensorIndex][maxIndex]) {
                    midIndex = maxIndex;
                } else if (storedRngMeas[sensorIndex][2] < storedRngMeas[sensorIndex][minIndex]) {
                    midIndex = minIndex;
                } else {
                    midIndex = 2;
                }

                // don't allow time to go backwards
                if (storedRngMeasTime_ms[sensorIndex][midIndex] > rangeDataNew.time_ms) {
                    rangeDataNew.time_ms = storedRngMeasTime_ms[sensorIndex][midIndex];
                }

                // limit the measured range to be no less than the on-ground range
                rangeDataNew.rng = MAX(storedRngMeas[sensorIndex][midIndex],rngOnGnd);

                // get position in body frame for the current sensor
                rangeDataNew.sensor_idx = sensorIndex;

                // write data to buffer with time stamp to be fused when the fusion time horizon catches up with it
                storedRange.push(rangeDataNew);

                // indicate we have updated the measurement
                rngValidMeaTime_ms = imuSampleTime_ms;

            } else if (!takeOffDetected && ((imuSampleTime_ms - rngValidMeaTime_ms) > 200)) {
                // before takeoff we assume on-ground range value if there is no data
                rangeDataNew.time_ms = imuSampleTime_ms;
                rangeDataNew.rng = rngOnGnd;
                rangeDataNew.time_ms = imuSampleTime_ms;

                // don't allow time to go backwards
                if (imuSampleTime_ms > rangeDataNew.time_ms) {
                    rangeDataNew.time_ms = imuSampleTime_ms;
                }

                // write data to buffer with time stamp to be fused when the fusion time horizon catches up with it
                storedRange.push(rangeDataNew);

                // indicate we have updated the measurement
                rngValidMeaTime_ms = imuSampleTime_ms;

            }
        }
    }
}

// write the raw optical flow measurements
// this needs to be called externally.
void NavEKF3_core::writeOptFlowMeas(uint8_t &rawFlowQuality, Vector2f &rawFlowRates, Vector2f &rawGyroRates, uint32_t &msecFlowMeas, const Vector3f &posOffset)
{
    // limit update rate to maximum allowed by sensor buffers
    if ((imuSampleTime_ms - flowMeaTime_ms) < frontend->sensorIntervalMin_ms) {
        return;
    }

    // The raw measurements need to be optical flow rates in radians/second averaged across the time since the last update
    // The PX4Flow sensor outputs flow rates with the following axis and sign conventions:
    // A positive X rate is produced by a positive sensor rotation about the X axis
    // A positive Y rate is produced by a positive sensor rotation about the Y axis
    // This filter uses a different definition of optical flow rates to the sensor with a positive optical flow rate produced by a
    // negative rotation about that axis. For example a positive rotation of the flight vehicle about its X (roll) axis would produce a negative X flow rate
    flowMeaTime_ms = imuSampleTime_ms;
    // calculate bias errors on flow sensor gyro rates, but protect against spikes in data
    // reset the accumulated body delta angle and time
    // don't do the calculation if not enough time lapsed for a reliable body rate measurement
    if (delTimeOF > 0.01f) {
        flowGyroBias.x = 0.99f * flowGyroBias.x + 0.01f * constrain_float((rawGyroRates.x - delAngBodyOF.x/delTimeOF),-0.1f,0.1f);
        flowGyroBias.y = 0.99f * flowGyroBias.y + 0.01f * constrain_float((rawGyroRates.y - delAngBodyOF.y/delTimeOF),-0.1f,0.1f);
        delAngBodyOF.zero();
        delTimeOF = 0.0f;
    }
    // by definition if this function is called, then flow measurements have been provided so we
    // need to run the optical flow takeoff detection
    detectOptFlowTakeoff();

    // calculate rotation matrices at mid sample time for flow observations
    stateStruct.quat.rotation_matrix(Tbn_flow);
    // don't use data with a low quality indicator or extreme rates (helps catch corrupt sensor data)
    if ((rawFlowQuality > 0) && rawFlowRates.length() < 4.2f && rawGyroRates.length() < 4.2f) {
        // correct flow sensor body rates for bias and write
        ofDataNew.bodyRadXYZ.x = rawGyroRates.x - flowGyroBias.x;
        ofDataNew.bodyRadXYZ.y = rawGyroRates.y - flowGyroBias.y;
        // the sensor interface doesn't provide a z axis rate so use the rate from the nav sensor instead
        if (delTimeOF > 0.001f) {
            // first preference is to use the rate averaged over the same sampling period as the flow sensor
            ofDataNew.bodyRadXYZ.z = delAngBodyOF.z / delTimeOF;
        } else if (imuDataNew.delAngDT > 0.001f){
            // second preference is to use most recent IMU data
            ofDataNew.bodyRadXYZ.z = imuDataNew.delAng.z / imuDataNew.delAngDT;
        } else {
            // third preference is use zero
            ofDataNew.bodyRadXYZ.z =  0.0f;
        }
        // write uncorrected flow rate measurements
        // note correction for different axis and sign conventions used by the px4flow sensor
        ofDataNew.flowRadXY = - rawFlowRates; // raw (non motion compensated) optical flow angular rate about the X axis (rad/sec)
        // write the flow sensor position in body frame
        ofDataNew.body_offset = &posOffset;
        // write flow rate measurements corrected for body rates
        ofDataNew.flowRadXYcomp.x = ofDataNew.flowRadXY.x + ofDataNew.bodyRadXYZ.x;
        ofDataNew.flowRadXYcomp.y = ofDataNew.flowRadXY.y + ofDataNew.bodyRadXYZ.y;
        // record time last observation was received so we can detect loss of data elsewhere
        flowValidMeaTime_ms = imuSampleTime_ms;
        // estimate sample time of the measurement
        ofDataNew.time_ms = imuSampleTime_ms - frontend->_flowDelay_ms - frontend->flowTimeDeltaAvg_ms/2;
        // Correct for the average intersampling delay due to the filter updaterate
        ofDataNew.time_ms -= localFilterTimeStep_ms/2;
        // Prevent time delay exceeding age of oldest IMU data in the buffer
        ofDataNew.time_ms = MAX(ofDataNew.time_ms,imuDataDelayed.time_ms);
        // Save data to buffer
        storedOF.push(ofDataNew);
    }
}


/********************************************************
*                      MAGNETOMETER                     *
********************************************************/

// check for new magnetometer data and update store measurements if available
void NavEKF3_core::readMagData()
{
    if (!_ahrs->get_compass()) {
        allMagSensorsFailed = true;
        return;        
    }
    // If we are a vehicle with a sideslip constraint to aid yaw estimation and we have timed out on our last avialable
    // magnetometer, then declare the magnetometers as failed for this flight
    uint8_t maxCount = _ahrs->get_compass()->get_count();
    if (allMagSensorsFailed || (magTimeout && assume_zero_sideslip() && magSelectIndex >= maxCount-1 && inFlight)) {
        allMagSensorsFailed = true;
        return;
    }

    // limit compass update rate to prevent high processor loading because magnetometer fusion is an expensive step and we could overflow the FIFO buffer
    if (use_compass() && ((_ahrs->get_compass()->last_update_usec() - lastMagUpdate_us) > 1000 * frontend->sensorIntervalMin_ms)) {
        frontend->logging.log_compass = true;

        // If the magnetometer has timed out (been rejected too long) we find another magnetometer to use if available
        // Don't do this if we are on the ground because there can be magnetic interference and we need to know if there is a problem
        // before taking off. Don't do this within the first 30 seconds from startup because the yaw error could be due to large yaw gyro bias affsets
        if (magTimeout && (maxCount > 1) && !onGround && imuSampleTime_ms - ekfStartTime_ms > 30000) {

            // search through the list of magnetometers
            for (uint8_t i=1; i<maxCount; i++) {
                uint8_t tempIndex = magSelectIndex + i;
                // loop back to the start index if we have exceeded the bounds
                if (tempIndex >= maxCount) {
                    tempIndex -= maxCount;
                }
                // if the magnetometer is allowed to be used for yaw and has a different index, we start using it
                if (_ahrs->get_compass()->use_for_yaw(tempIndex) && tempIndex != magSelectIndex) {
                    magSelectIndex = tempIndex;
                    GCS_MAVLINK::send_statustext_all(MAV_SEVERITY_INFO, "EKF3 IMU%u switching to compass %u",(unsigned)imu_index,magSelectIndex);
                    // reset the timeout flag and timer
                    magTimeout = false;
                    lastHealthyMagTime_ms = imuSampleTime_ms;
                    // zero the learned magnetometer bias states
                    stateStruct.body_magfield.zero();
                    // clear the measurement buffer
                    storedMag.reset();
                    // clear the data waiting flag so that we do not use any data pending from the previous sensor
                    magDataToFuse = false;
                    // request a reset of the magnetic field states
                    magStateResetRequest = true;
                    // declare the field unlearned so that the reset request will be obeyed
                    magFieldLearned = false;
                }
            }
        }

        // detect changes to magnetometer offset parameters and reset states
        Vector3f nowMagOffsets = _ahrs->get_compass()->get_offsets(magSelectIndex);
        bool changeDetected = lastMagOffsetsValid && (nowMagOffsets != lastMagOffsets);
        if (changeDetected) {
            // zero the learned magnetometer bias states
            stateStruct.body_magfield.zero();
            // clear the measurement buffer
            storedMag.reset();
        }
        lastMagOffsets = nowMagOffsets;
        lastMagOffsetsValid = true;

        // store time of last measurement update
        lastMagUpdate_us = _ahrs->get_compass()->last_update_usec(magSelectIndex);

        // estimate of time magnetometer measurement was taken, allowing for delays
        magDataNew.time_ms = imuSampleTime_ms - frontend->magDelay_ms;

        // Correct for the average intersampling delay due to the filter updaterate
        magDataNew.time_ms -= localFilterTimeStep_ms/2;

        // read compass data and scale to improve numerical conditioning
        magDataNew.mag = _ahrs->get_compass()->get_field(magSelectIndex) * 0.001f;

        // check for consistent data between magnetometers
        consistentMagData = _ahrs->get_compass()->consistent();

        // save magnetometer measurement to buffer to be fused later
        storedMag.push(magDataNew);
    }
}

/********************************************************
*                Inertial Measurements                  *
********************************************************/

/*
 *  Read IMU delta angle and delta velocity measurements and downsample to 100Hz
 *  for storage in the data buffers used by the EKF. If the IMU data arrives at
 *  lower rate than 100Hz, then no downsampling or upsampling will be performed.
 *  Downsampling is done using a method that does not introduce coning or sculling
 *  errors.
 */
void NavEKF3_core::readIMUData()
{
    const AP_InertialSensor &ins = _ahrs->get_ins();

    // average IMU sampling rate
    dtIMUavg = ins.get_loop_delta_t();

    // the imu sample time is used as a common time reference throughout the filter
    imuSampleTime_ms = frontend->imuSampleTime_us / 1000;

    // use the nominated imu or primary if not available
    if (ins.use_accel(imu_index)) {
        readDeltaVelocity(imu_index, imuDataNew.delVel, imuDataNew.delVelDT);
        accelPosOffset = ins.get_imu_pos_offset(imu_index);
    } else {
        readDeltaVelocity(ins.get_primary_accel(), imuDataNew.delVel, imuDataNew.delVelDT);
        accelPosOffset = ins.get_imu_pos_offset(ins.get_primary_accel());
    }

    // Get delta angle data from primary gyro or primary if not available
    if (ins.use_gyro(imu_index)) {
        readDeltaAngle(imu_index, imuDataNew.delAng);
    } else {
        readDeltaAngle(ins.get_primary_gyro(), imuDataNew.delAng);
    }
    imuDataNew.delAngDT = MAX(ins.get_delta_angle_dt(imu_index),1.0e-4f);

    // Get current time stamp
    imuDataNew.time_ms = imuSampleTime_ms;

    // Accumulate the measurement time interval for the delta velocity and angle data
    imuDataDownSampledNew.delAngDT += imuDataNew.delAngDT;
    imuDataDownSampledNew.delVelDT += imuDataNew.delVelDT;

    // Rotate quaternon atitude from previous to new and normalise.
    // Accumulation using quaternions prevents introduction of coning errors due to downsampling
    imuQuatDownSampleNew.rotate(imuDataNew.delAng);
    imuQuatDownSampleNew.normalize();

    // Rotate the latest delta velocity into body frame at the start of accumulation
    Matrix3f deltaRotMat;
    imuQuatDownSampleNew.rotation_matrix(deltaRotMat);

    // Apply the delta velocity to the delta velocity accumulator
    imuDataDownSampledNew.delVel += deltaRotMat*imuDataNew.delVel;

    // Keep track of the number of IMU frames since the last state prediction
    framesSincePredict++;

    // If 10msec has elapsed, and the frontend has allowed us to start a new predict cycle, then store the accumulated IMU data
    // to be used by the state prediction, ignoring the frontend permission if more than 20msec has lapsed
    if ((dtIMUavg*(float)framesSincePredict >= EKF_TARGET_DT && startPredictEnabled) || (dtIMUavg*(float)framesSincePredict >= 2.0f*EKF_TARGET_DT)) {

        // convert the accumulated quaternion to an equivalent delta angle
        imuQuatDownSampleNew.to_axis_angle(imuDataDownSampledNew.delAng);

        // Time stamp the data
        imuDataDownSampledNew.time_ms = imuSampleTime_ms;

        // Write data to the FIFO IMU buffer
        storedIMU.push_youngest_element(imuDataDownSampledNew);

        // calculate the achieved average time step rate for the EKF
        float dtNow = constrain_float(0.5f*(imuDataDownSampledNew.delAngDT+imuDataDownSampledNew.delVelDT),0.0f,10.0f*EKF_TARGET_DT);
        dtEkfAvg = 0.98f * dtEkfAvg + 0.02f * dtNow;

        // zero the accumulated IMU data and quaternion
        imuDataDownSampledNew.delAng.zero();
        imuDataDownSampledNew.delVel.zero();
        imuDataDownSampledNew.delAngDT = 0.0f;
        imuDataDownSampledNew.delVelDT = 0.0f;
        imuQuatDownSampleNew[0] = 1.0f;
        imuQuatDownSampleNew[3] = imuQuatDownSampleNew[2] = imuQuatDownSampleNew[1] = 0.0f;

        // reset the counter used to let the frontend know how many frames have elapsed since we started a new update cycle
        framesSincePredict = 0;

        // set the flag to let the filter know it has new IMU data nad needs to run
        runUpdates = true;

        // extract the oldest available data from the FIFO buffer
        imuDataDelayed = storedIMU.pop_oldest_element();

        // protect against delta time going to zero
        // TODO - check if calculations can tolerate 0
        float minDT = 0.1f*dtEkfAvg;
        imuDataDelayed.delAngDT = MAX(imuDataDelayed.delAngDT,minDT);
        imuDataDelayed.delVelDT = MAX(imuDataDelayed.delVelDT,minDT);

        // correct the extracted IMU data for sensor errors
        delAngCorrected = imuDataDelayed.delAng;
        delVelCorrected = imuDataDelayed.delVel;
        correctDeltaAngle(delAngCorrected, imuDataDelayed.delAngDT);
        correctDeltaVelocity(delVelCorrected, imuDataDelayed.delVelDT);

    } else {
        // we don't have new IMU data in the buffer so don't run filter updates on this time step
        runUpdates = false;
    }
}

// read the delta velocity and corresponding time interval from the IMU
// return false if data is not available
bool NavEKF3_core::readDeltaVelocity(uint8_t ins_index, Vector3f &dVel, float &dVel_dt) {
    const AP_InertialSensor &ins = _ahrs->get_ins();

    if (ins_index < ins.get_accel_count()) {
        ins.get_delta_velocity(ins_index,dVel);
        dVel_dt = MAX(ins.get_delta_velocity_dt(ins_index),1.0e-4f);
        return true;
    }
    return false;
}

/********************************************************
*             Global Position Measurement               *
********************************************************/

// check for new valid GPS data and update stored measurement if available
void NavEKF3_core::readGpsData()
{
    // check for new GPS data
    // limit update rate to avoid overflowing the FIFO buffer
    if (_ahrs->get_gps().last_message_time_ms() - lastTimeGpsReceived_ms > frontend->sensorIntervalMin_ms) {
        if (_ahrs->get_gps().status() >= AP_GPS::GPS_OK_FIX_3D) {
            // report GPS fix status
            gpsCheckStatus.bad_fix = false;

            // store fix time from previous read
            secondLastGpsTime_ms = lastTimeGpsReceived_ms;

            // get current fix time
            lastTimeGpsReceived_ms = _ahrs->get_gps().last_message_time_ms();

            // estimate when the GPS fix was valid, allowing for GPS processing and other delays
            // ideally we should be using a timing signal from the GPS receiver to set this time
            // Use the driver specified delay
            gpsDataNew.time_ms = lastTimeGpsReceived_ms - (uint32_t)(_ahrs->get_gps().get_lag() * 1000.0f);

            // Correct for the average intersampling delay due to the filter updaterate
            gpsDataNew.time_ms -= localFilterTimeStep_ms/2;

            // Prevent the time stamp falling outside the oldest and newest IMU data in the buffer
            gpsDataNew.time_ms = MIN(MAX(gpsDataNew.time_ms,imuDataDelayed.time_ms),imuDataDownSampledNew.time_ms);

            // Get which GPS we are using for position information
            gpsDataNew.sensor_idx = _ahrs->get_gps().primary_sensor();

            // read the NED velocity from the GPS
            gpsDataNew.vel = _ahrs->get_gps().velocity();

            // Use the speed and position accuracy from the GPS if available, otherwise set it to zero.
            // Apply a decaying envelope filter with a 5 second time constant to the raw accuracy data
            float alpha = constrain_float(0.0002f * (lastTimeGpsReceived_ms - secondLastGpsTime_ms),0.0f,1.0f);
            gpsSpdAccuracy *= (1.0f - alpha);
            float gpsSpdAccRaw;
            if (!_ahrs->get_gps().speed_accuracy(gpsSpdAccRaw)) {
                gpsSpdAccuracy = 0.0f;
            } else {
                gpsSpdAccuracy = MAX(gpsSpdAccuracy,gpsSpdAccRaw);
                gpsSpdAccuracy = MIN(gpsSpdAccuracy,50.0f);
            }
            gpsPosAccuracy *= (1.0f - alpha);
            float gpsPosAccRaw;
            if (!_ahrs->get_gps().horizontal_accuracy(gpsPosAccRaw)) {
                gpsPosAccuracy = 0.0f;
            } else {
                gpsPosAccuracy = MAX(gpsPosAccuracy,gpsPosAccRaw);
                gpsPosAccuracy = MIN(gpsPosAccuracy,100.0f);
            }
            gpsHgtAccuracy *= (1.0f - alpha);
            float gpsHgtAccRaw;
            if (!_ahrs->get_gps().vertical_accuracy(gpsHgtAccRaw)) {
                gpsHgtAccuracy = 0.0f;
            } else {
                gpsHgtAccuracy = MAX(gpsHgtAccuracy,gpsHgtAccRaw);
                gpsHgtAccuracy = MIN(gpsHgtAccuracy,100.0f);
            }

            // check if we have enough GPS satellites and increase the gps noise scaler if we don't
            if (_ahrs->get_gps().num_sats() >= 6 && (PV_AidingMode == AID_ABSOLUTE)) {
                gpsNoiseScaler = 1.0f;
            } else if (_ahrs->get_gps().num_sats() == 5 && (PV_AidingMode == AID_ABSOLUTE)) {
                gpsNoiseScaler = 1.4f;
            } else { // <= 4 satellites or in constant position mode
                gpsNoiseScaler = 2.0f;
            }

            // Check if GPS can output vertical velocity and set GPS fusion mode accordingly
            if (_ahrs->get_gps().have_vertical_velocity() && frontend->_fusionModeGPS == 0) {
                useGpsVertVel = true;
            } else {
                useGpsVertVel = false;
            }

            // Monitor quality of the GPS velocity data before and after alignment using separate checks
            if (PV_AidingMode != AID_ABSOLUTE) {
                // Pre-alignment checks
                gpsGoodToAlign = calcGpsGoodToAlign();
            } else {
                gpsGoodToAlign = false;
            }

            // Post-alignment checks
            calcGpsGoodForFlight();

            // Read the GPS locaton in WGS-84 lat,long,height coordinates
            const struct Location &gpsloc = _ahrs->get_gps().location();

            // Set the EKF origin and magnetic field declination if not previously set  and GPS checks have passed
            if (gpsGoodToAlign && !validOrigin) {
                setOrigin();

                // set the NE earth magnetic field states using the published declination
                // and set the corresponding variances and covariances
                alignMagStateDeclination();

                // Set the height of the NED origin to ‘height of baro height datum relative to GPS height datum'
                EKF_origin.alt = gpsloc.alt - baroDataNew.hgt;

                // Set the uncertinty of the GPS origin height
                ekfOriginHgtVar = sq(gpsHgtAccuracy);

            }

            // convert GPS measurements to local NED and save to buffer to be fused later if we have a valid origin
            if (validOrigin) {
                gpsDataNew.pos = location_diff(EKF_origin, gpsloc);
                gpsDataNew.hgt = 0.01f * (gpsloc.alt - EKF_origin.alt);
                storedGPS.push(gpsDataNew);
                // declare GPS available for use
                gpsNotAvailable = false;
            }

            frontend->logging.log_gps = true;

        } else {
            // report GPS fix status
            gpsCheckStatus.bad_fix = true;
        }
    }
}

// read the delta angle and corresponding time interval from the IMU
// return false if data is not available
bool NavEKF3_core::readDeltaAngle(uint8_t ins_index, Vector3f &dAng) {
    const AP_InertialSensor &ins = _ahrs->get_ins();

    if (ins_index < ins.get_gyro_count()) {
        ins.get_delta_angle(ins_index,dAng);
        frontend->logging.log_imu = true;
        return true;
    }
    return false;
}


/********************************************************
*                  Height Measurements                  *
********************************************************/

// check for new pressure altitude measurement data and update stored measurement if available
void NavEKF3_core::readBaroData()
{
    // check to see if baro measurement has changed so we know if a new measurement has arrived
    // limit update rate to avoid overflowing the FIFO buffer
    if (frontend->_baro.get_last_update() - lastBaroReceived_ms > frontend->sensorIntervalMin_ms) {
        frontend->logging.log_baro = true;

        baroDataNew.hgt = frontend->_baro.get_altitude();

        // If we are in takeoff mode, the height measurement is limited to be no less than the measurement at start of takeoff
        // This prevents negative baro disturbances due to copter downwash corrupting the EKF altitude during initial ascent
        if (getTakeoffExpected()) {
            baroDataNew.hgt = MAX(baroDataNew.hgt, meaHgtAtTakeOff);
        }

        // time stamp used to check for new measurement
        lastBaroReceived_ms = frontend->_baro.get_last_update();

        // estimate of time height measurement was taken, allowing for delays
        baroDataNew.time_ms = lastBaroReceived_ms - frontend->_hgtDelay_ms;

        // Correct for the average intersampling delay due to the filter updaterate
        baroDataNew.time_ms -= localFilterTimeStep_ms/2;

        // Prevent time delay exceeding age of oldest IMU data in the buffer
        baroDataNew.time_ms = MAX(baroDataNew.time_ms,imuDataDelayed.time_ms);

        // save baro measurement to buffer to be fused later
        storedBaro.push(baroDataNew);
    }
}

// calculate filtered offset between baro height measurement and EKF height estimate
// offset should be subtracted from baro measurement to match filter estimate
// offset is used to enable reversion to baro from alternate height data source
void NavEKF3_core::calcFiltBaroOffset()
{
    // Apply a first order LPF with spike protection
    baroHgtOffset += 0.1f * constrain_float(baroDataDelayed.hgt + stateStruct.position.z - baroHgtOffset, -5.0f, 5.0f);
}

// calculate filtered offset between GPS height measurement and EKF height estimate
// offset should be subtracted from GPS measurement to match filter estimate
// offset is used to switch reversion to GPS from alternate height data source
void NavEKF3_core::calcFiltGpsHgtOffset()
{
    // Estimate the WGS-84 height of the EKF's origin using a Bayes filter

    // calculate the variance of our a-priori estimate of the ekf origin height
    float deltaTime = constrain_float(0.001f * (imuDataDelayed.time_ms - lastOriginHgtTime_ms), 0.0f, 1.0f);
    if (activeHgtSource == HGT_SOURCE_BARO) {
        // Use the baro drift rate
        const float baroDriftRate = 0.05f;
        ekfOriginHgtVar += sq(baroDriftRate * deltaTime);
    } else if (activeHgtSource == HGT_SOURCE_RNG) {
        // use the worse case expected terrain gradient and vehicle horizontal speed
        const float maxTerrGrad = 0.25f;
        ekfOriginHgtVar += sq(maxTerrGrad * norm(stateStruct.velocity.x , stateStruct.velocity.y) * deltaTime);
    } else if (activeHgtSource == HGT_SOURCE_GPS) {
        // by definition we are using GPS height as the EKF datum in this mode
        // so cannot run this filter
        return;
    }
    lastOriginHgtTime_ms = imuDataDelayed.time_ms;

    // calculate the observation variance assuming EKF error relative to datum is independant of GPS observation error
    // when not using GPS as height source
    float originHgtObsVar = sq(gpsHgtAccuracy) + P[8][8];

    // calculate the correction gain
    float gain = ekfOriginHgtVar / (ekfOriginHgtVar + originHgtObsVar);

    // calculate the innovation
    float innovation = - stateStruct.position.z - gpsDataDelayed.hgt;

    // check the innovation variance ratio
    float ratio = sq(innovation) / (ekfOriginHgtVar + originHgtObsVar);

    // correct the EKF origin and variance estimate if the innovation variance ratio is < 5-sigma
    if (ratio < 5.0f) {
        EKF_origin.alt -= (int)(100.0f * gain * innovation);
        ekfOriginHgtVar -= MAX(gain * ekfOriginHgtVar , 0.0f);
    }
}

/********************************************************
*                Air Speed Measurements                 *
********************************************************/

// check for new airspeed data and update stored measurements if available
void NavEKF3_core::readAirSpdData()
{
    // if airspeed reading is valid and is set by the user to be used and has been updated then
    // we take a new reading, convert from EAS to TAS and set the flag letting other functions
    // know a new measurement is available
    const AP_Airspeed *aspeed = _ahrs->get_airspeed();
    if (aspeed &&
            aspeed->use() &&
            (aspeed->last_update_ms() - timeTasReceived_ms) > frontend->sensorIntervalMin_ms) {
        tasDataNew.tas = aspeed->get_raw_airspeed() * aspeed->get_EAS2TAS();
        timeTasReceived_ms = aspeed->last_update_ms();
        tasDataNew.time_ms = timeTasReceived_ms - frontend->tasDelay_ms;

        // Correct for the average intersampling delay due to the filter update rate
        tasDataNew.time_ms -= localFilterTimeStep_ms/2;

        // Save data into the buffer to be fused when the fusion time horizon catches up with it
        storedTAS.push(tasDataNew);
    }
    // Check the buffer for measurements that have been overtaken by the fusion time horizon and need to be fused
    tasDataToFuse = storedTAS.recall(tasDataDelayed,imuDataDelayed.time_ms);
}

/********************************************************
*              Range Beacon Measurements                *
********************************************************/

// check for new airspeed data and update stored measurements if available
void NavEKF3_core::readRngBcnData()
{
    // get the location of the beacon data
    const AP_Beacon *beacon = _ahrs->get_beacon();

    // exit immediately if no beacon object
    if (beacon == nullptr) {
        return;
    }

    // get the number of beacons in use
    N_beacons = beacon->count();

    // search through all the beacons for new data and if we find it stop searching and push the data into the observation buffer
    bool newDataToPush = false;
    uint8_t numRngBcnsChecked = 0;
    // start the search one index up from where we left it last time
    uint8_t index = lastRngBcnChecked;
    while (!newDataToPush && numRngBcnsChecked < N_beacons) {
        // track the number of beacons checked
        numRngBcnsChecked++;

        // move to next beacon, wrap index if necessary
        index++;
        if (index >= N_beacons) {
            index = 0;
        }

        // check that the beacon is healthy and has new data
        if (beacon->beacon_healthy(index) &&
                beacon->beacon_last_update_ms(index) != lastTimeRngBcn_ms[index])
        {
            // set the timestamp, correcting for measurement delay and average intersampling delay due to the filter update rate
            lastTimeRngBcn_ms[index] = beacon->beacon_last_update_ms(index);
            rngBcnDataNew.time_ms = lastTimeRngBcn_ms[index] - frontend->_rngBcnDelay_ms - localFilterTimeStep_ms/2;

            // set the range noise
            // TODO the range library should provide the noise/accuracy estimate for each beacon
            rngBcnDataNew.rngErr = frontend->_rngBcnNoise;

            // set the range measurement
            rngBcnDataNew.rng = beacon->beacon_distance(index);

            // set the beacon position
            rngBcnDataNew.beacon_posNED = beacon->beacon_position(index);

            // identify the beacon identifier
            rngBcnDataNew.beacon_ID = index;

            // indicate we have new data to push to the buffer
            newDataToPush = true;

            // update the last checked index
            lastRngBcnChecked = index;
        }
    }

    // Check if the beacon system has returned a 3D fix
    if (beacon->get_vehicle_position_ned(beaconVehiclePosNED, beaconVehiclePosErr)) {
        rngBcnLast3DmeasTime_ms = imuSampleTime_ms;
    }

    // Check if the range beacon data can be used to align the vehicle position
    if (imuSampleTime_ms - rngBcnLast3DmeasTime_ms < 250 && beaconVehiclePosErr < 1.0f && rngBcnAlignmentCompleted) {
        // check for consistency between the position reported by the beacon and the position from the 3-State alignment filter
        float posDiffSq = sq(receiverPos.x - beaconVehiclePosNED.x) + sq(receiverPos.y - beaconVehiclePosNED.y);
        float posDiffVar = sq(beaconVehiclePosErr) + receiverPosCov[0][0] + receiverPosCov[1][1];
        if (posDiffSq < 9.0f*posDiffVar) {
            rngBcnGoodToAlign = true;
            // Set the EKF origin and magnetic field declination if not previously set
            if (!validOrigin && PV_AidingMode != AID_ABSOLUTE) {
                // get origin from beacon system
                Location origin_loc;
                if (beacon->get_origin(origin_loc)) {
                    setOriginLLH(origin_loc);

                    // set the NE earth magnetic field states using the published declination
                    // and set the corresponding variances and covariances
                    alignMagStateDeclination();

                    // Set the height of the NED origin to ‘height of baro height datum relative to GPS height datum'
                    EKF_origin.alt = origin_loc.alt - baroDataNew.hgt;

                    // Set the uncertainty of the origin height
                    ekfOriginHgtVar = sq(beaconVehiclePosErr);
                }
            }
        } else {
            rngBcnGoodToAlign = false;
        }
    } else {
        rngBcnGoodToAlign = false;
    }

    // Save data into the buffer to be fused when the fusion time horizon catches up with it
    if (newDataToPush) {
        storedRangeBeacon.push(rngBcnDataNew);
    }

    // Check the buffer for measurements that have been overtaken by the fusion time horizon and need to be fused
    rngBcnDataToFuse = storedRangeBeacon.recall(rngBcnDataDelayed,imuDataDelayed.time_ms);

    // Correct the range beacon earth frame origin for estimated offset relative to the EKF earth frame origin
    if (rngBcnDataToFuse) {
        rngBcnDataDelayed.beacon_posNED += bcnPosOffsetNED;
    }

}

#endif // HAL_CPU_CLASS