mirror of https://github.com/ArduPilot/ardupilot
248 lines
8.7 KiB
C++
248 lines
8.7 KiB
C++
/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
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#pragma once
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/*
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This program is free software: you can redistribute it and/or modify
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it under the terms of the GNU General Public License as published by
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the Free Software Foundation, either version 3 of the License, or
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(at your option) any later version.
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This program is distributed in the hope that it will be useful,
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but WITHOUT ANY WARRANTY; without even the implied warranty of
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MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
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GNU General Public License for more details.
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You should have received a copy of the GNU General Public License
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along with this program. If not, see <http://www.gnu.org/licenses/>.
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*/
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/*
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* NavEKF based AHRS (Attitude Heading Reference System) interface for
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* ArduPilot
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*
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*/
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#include <AP_HAL/AP_HAL.h>
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#include "AP_AHRS.h"
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#if CONFIG_HAL_BOARD == HAL_BOARD_SITL
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#include <SITL/SITL.h>
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#endif
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#if HAL_CPU_CLASS >= HAL_CPU_CLASS_150
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#include <AP_NavEKF/AP_NavEKF.h>
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#include <AP_NavEKF2/AP_NavEKF2.h>
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#include <AP_NavEKF/AP_Nav_Common.h> // definitions shared by inertial and ekf nav filters
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#define AP_AHRS_NAVEKF_AVAILABLE 1
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#define AP_AHRS_NAVEKF_SETTLE_TIME_MS 20000 // time in milliseconds the ekf needs to settle after being started
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class AP_AHRS_NavEKF : public AP_AHRS_DCM
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{
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public:
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enum Flags {
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FLAG_NONE = 0,
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FLAG_ALWAYS_USE_EKF = 0x1,
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};
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// Constructor
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AP_AHRS_NavEKF(AP_InertialSensor &ins, AP_Baro &baro, AP_GPS &gps, RangeFinder &rng,
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NavEKF &_EKF1, NavEKF2 &_EKF2, Flags flags = FLAG_NONE);
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// return the smoothed gyro vector corrected for drift
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const Vector3f &get_gyro(void) const;
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const Matrix3f &get_rotation_body_to_ned(void) const;
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// return the current drift correction integrator value
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const Vector3f &get_gyro_drift(void) const;
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// reset the current gyro drift estimate
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// should be called if gyro offsets are recalculated
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void reset_gyro_drift(void);
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void update(void);
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void reset(bool recover_eulers = false);
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// reset the current attitude, used on new IMU calibration
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void reset_attitude(const float &roll, const float &pitch, const float &yaw);
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// dead-reckoning support
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bool get_position(struct Location &loc) const;
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// get latest altitude estimate above ground level in metres and validity flag
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bool get_hagl(float &hagl) const;
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// status reporting of estimated error
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float get_error_rp(void) const;
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float get_error_yaw(void) const;
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// return a wind estimation vector, in m/s
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Vector3f wind_estimate(void);
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// return an airspeed estimate if available. return true
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// if we have an estimate
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bool airspeed_estimate(float *airspeed_ret) const;
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// true if compass is being used
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bool use_compass(void);
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// we will need to remove these to fully hide which EKF we are using
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NavEKF &get_NavEKF(void) {
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return EKF1;
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}
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const NavEKF &get_NavEKF_const(void) const {
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return EKF1;
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}
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NavEKF2 &get_NavEKF2(void) {
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return EKF2;
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}
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const NavEKF2 &get_NavEKF2_const(void) const {
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return EKF2;
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}
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// return secondary attitude solution if available, as eulers in radians
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bool get_secondary_attitude(Vector3f &eulers);
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// return secondary position solution if available
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bool get_secondary_position(struct Location &loc);
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// EKF has a better ground speed vector estimate
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Vector2f groundspeed_vector(void);
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const Vector3f &get_accel_ef(uint8_t i) const;
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const Vector3f &get_accel_ef() const {
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return get_accel_ef(_ins.get_primary_accel());
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};
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// blended accelerometer values in the earth frame in m/s/s
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const Vector3f &get_accel_ef_blended(void) const;
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// set home location
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void set_home(const Location &loc);
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// returns the inertial navigation origin in lat/lon/alt
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bool get_origin(Location &ret) const;
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bool have_inertial_nav(void) const;
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bool get_velocity_NED(Vector3f &vec) const;
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bool get_relative_position_NED(Vector3f &vec) const;
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// Get a derivative of the vertical position in m/s which is kinematically consistent with the vertical position is required by some control loops.
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// This is different to the vertical velocity from the EKF which is not always consistent with the verical position due to the various errors that are being corrected for.
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bool get_vert_pos_rate(float &velocity);
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// write optical flow measurements to EKF
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void writeOptFlowMeas(uint8_t &rawFlowQuality, Vector2f &rawFlowRates, Vector2f &rawGyroRates, uint32_t &msecFlowMeas);
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// inibit GPS useage
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uint8_t setInhibitGPS(void);
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// get speed limit
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void getEkfControlLimits(float &ekfGndSpdLimit, float &ekfNavVelGainScaler);
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void set_ekf_use(bool setting);
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// is the AHRS subsystem healthy?
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bool healthy(void) const;
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// true if the AHRS has completed initialisation
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bool initialised(void) const;
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// get_filter_status - returns filter status as a series of flags
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bool get_filter_status(nav_filter_status &status) const;
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// get compass offset estimates
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// true if offsets are valid
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bool getMagOffsets(Vector3f &magOffsets);
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// report any reason for why the backend is refusing to initialise
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const char *prearm_failure_reason(void) const override;
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// return the amount of yaw angle change due to the last yaw angle reset in radians
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// returns the time of the last yaw angle reset or 0 if no reset has ever occurred
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uint32_t getLastYawResetAngle(float &yawAng) const;
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// return the amount of NE position change in metres due to the last reset
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// returns the time of the last reset or 0 if no reset has ever occurred
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uint32_t getLastPosNorthEastReset(Vector2f &pos) const;
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// return the amount of NE velocity change in metres/sec due to the last reset
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// returns the time of the last reset or 0 if no reset has ever occurred
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uint32_t getLastVelNorthEastReset(Vector2f &vel) const;
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// Resets the baro so that it reads zero at the current height
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// Resets the EKF height to zero
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// Adjusts the EKf origin height so that the EKF height + origin height is the same as before
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// Returns true if the height datum reset has been performed
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// If using a range finder for height no reset is performed and it returns false
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bool resetHeightDatum(void);
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// send a EKF_STATUS_REPORT for current EKF
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void send_ekf_status_report(mavlink_channel_t chan);
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// get_hgt_ctrl_limit - get maximum height to be observed by the control loops in metres and a validity flag
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// this is used to limit height during optical flow navigation
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// it will return invalid when no limiting is required
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bool get_hgt_ctrl_limit(float &limit) const;
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// get_llh - updates the provided location with the latest calculated location including absolute altitude
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// returns true on success (i.e. the EKF knows it's latest position), false on failure
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bool get_location(struct Location &loc) const;
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// get_variances - provides the innovations normalised using the innovation variance where a value of 0
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// indicates prefect consistency between the measurement and the EKF solution and a value of of 1 is the maximum
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// inconsistency that will be accpeted by the filter
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// boolean false is returned if variances are not available
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bool get_variances(float &velVar, float &posVar, float &hgtVar, Vector3f &magVar, float &tasVar, Vector2f &offset) const;
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// returns the expected NED magnetic field
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bool get_mag_field_NED(Vector3f& ret) const;
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// returns the estimated magnetic field offsets in body frame
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bool get_mag_field_correction(Vector3f &ret) const;
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void setTakeoffExpected(bool val);
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void setTouchdownExpected(bool val);
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private:
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enum EKF_TYPE {EKF_TYPE_NONE=0,
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EKF_TYPE1=1,
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EKF_TYPE2=2
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#if CONFIG_HAL_BOARD == HAL_BOARD_SITL
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,EKF_TYPE_SITL=10
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#endif
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};
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EKF_TYPE active_EKF_type(void) const;
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bool always_use_EKF() const {
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return _ekf_flags & FLAG_ALWAYS_USE_EKF;
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}
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NavEKF &EKF1;
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NavEKF2 &EKF2;
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bool ekf1_started = false;
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bool ekf2_started = false;
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Matrix3f _dcm_matrix;
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Vector3f _dcm_attitude;
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Vector3f _gyro_bias;
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Vector3f _gyro_estimate;
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Vector3f _accel_ef_ekf[INS_MAX_INSTANCES];
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Vector3f _accel_ef_ekf_blended;
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const uint16_t startup_delay_ms = 1000;
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uint32_t start_time_ms = 0;
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Flags _ekf_flags;
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uint8_t ekf_type(void) const;
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void update_DCM(void);
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void update_EKF1(void);
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void update_EKF2(void);
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#if CONFIG_HAL_BOARD == HAL_BOARD_SITL
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SITL::SITL *_sitl;
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void update_SITL(void);
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#endif
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};
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#endif
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