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ardupilot/libraries/AP_AHRS/AP_AHRS.cpp

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/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
/*
APM_AHRS.cpp
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/>.
*/
#include "AP_AHRS.h"
#include <AP_HAL/AP_HAL.h>
extern const AP_HAL::HAL& hal;
// table of user settable parameters
const AP_Param::GroupInfo AP_AHRS::var_info[] = {
// index 0 and 1 are for old parameters that are no longer not used
// @Param: GPS_GAIN
// @DisplayName: AHRS GPS gain
// @Description: This controls how how much to use the GPS to correct the attitude. This should never be set to zero for a plane as it would result in the plane losing control in turns. For a plane please use the default value of 1.0.
// @Range: 0.0 1.0
// @Increment: .01
AP_GROUPINFO("GPS_GAIN", 2, AP_AHRS, gps_gain, 1.0f),
// @Param: GPS_USE
// @DisplayName: AHRS use GPS for navigation
// @Description: This controls whether to use dead-reckoning or GPS based navigation. If set to 0 then the GPS won't be used for navigation, and only dead reckoning will be used. A value of zero should never be used for normal flight.
// @Values: 0:Disabled,1:Enabled
// @User: Advanced
AP_GROUPINFO("GPS_USE", 3, AP_AHRS, _gps_use, 1),
// @Param: YAW_P
// @DisplayName: Yaw P
// @Description: This controls the weight the compass or GPS has on the heading. A higher value means the heading will track the yaw source (GPS or compass) more rapidly.
// @Range: 0.1 0.4
// @Increment: .01
AP_GROUPINFO("YAW_P", 4, AP_AHRS, _kp_yaw, 0.2f),
// @Param: RP_P
// @DisplayName: AHRS RP_P
// @Description: This controls how fast the accelerometers correct the attitude
// @Range: 0.1 0.4
// @Increment: .01
AP_GROUPINFO("RP_P", 5, AP_AHRS, _kp, 0.2f),
// @Param: WIND_MAX
// @DisplayName: Maximum wind
// @Description: This sets the maximum allowable difference between ground speed and airspeed. This allows the plane to cope with a failing airspeed sensor. A value of zero means to use the airspeed as is.
// @Range: 0 127
// @Units: m/s
// @Increment: 1
AP_GROUPINFO("WIND_MAX", 6, AP_AHRS, _wind_max, 0.0f),
// NOTE: 7 was BARO_USE
// @Param: TRIM_X
// @DisplayName: AHRS Trim Roll
// @Description: Compensates for the roll angle difference between the control board and the frame. Positive values make the vehicle roll right.
// @Units: Radians
// @Range: -0.1745 +0.1745
// @Increment: 0.01
// @User: User
// @Param: TRIM_Y
// @DisplayName: AHRS Trim Pitch
// @Description: Compensates for the pitch angle difference between the control board and the frame. Positive values make the vehicle pitch up/back.
// @Units: Radians
// @Range: -0.1745 +0.1745
// @Increment: 0.01
// @User: User
// @Param: TRIM_Z
// @DisplayName: AHRS Trim Yaw
// @Description: Not Used
// @Units: Radians
// @Range: -0.1745 +0.1745
// @Increment: 0.01
// @User: Advanced
AP_GROUPINFO("TRIM", 8, AP_AHRS, _trim, 0),
// @Param: ORIENTATION
// @DisplayName: Board Orientation
// @Description: Overall board orientation relative to the standard orientation for the board type. This rotates the IMU and compass readings to allow the board to be oriented in your vehicle at any 90 or 45 degree angle. This option takes affect on next boot. After changing you will need to re-level your vehicle.
// @Values: 0:None,1:Yaw45,2:Yaw90,3:Yaw135,4:Yaw180,5:Yaw225,6:Yaw270,7:Yaw315,8:Roll180,9:Roll180Yaw45,10:Roll180Yaw90,11:Roll180Yaw135,12:Pitch180,13:Roll180Yaw225,14:Roll180Yaw270,15:Roll180Yaw315,16:Roll90,17:Roll90Yaw45,18:Roll90Yaw90,19:Roll90Yaw135,20:Roll270,21:Roll270Yaw45,22:Roll270Yaw90,23:Roll270Yaw136,24:Pitch90,25:Pitch270,26:Pitch180Yaw90,27:Pitch180Yaw270,28:Roll90Pitch90,29:Roll180Pitch90,30:Roll270Pitch90,31:Roll90Pitch180,32:Roll270Pitch180,33:Roll90Pitch270,34:Roll180Pitch270,35:Roll270Pitch270,36:Roll90Pitch180Yaw90,37:Roll90Yaw270
// @User: Advanced
AP_GROUPINFO("ORIENTATION", 9, AP_AHRS, _board_orientation, 0),
// @Param: COMP_BETA
// @DisplayName: AHRS Velocity Complementary Filter Beta Coefficient
// @Description: This controls the time constant for the cross-over frequency used to fuse AHRS (airspeed and heading) and GPS data to estimate ground velocity. Time constant is 0.1/beta. A larger time constant will use GPS data less and a small time constant will use air data less.
// @Range: 0.001 0.5
// @Increment: .01
// @User: Advanced
AP_GROUPINFO("COMP_BETA", 10, AP_AHRS, beta, 0.1f),
// @Param: GPS_MINSATS
// @DisplayName: AHRS GPS Minimum satellites
// @Description: Minimum number of satellites visible to use GPS for velocity based corrections attitude correction. This defaults to 6, which is about the point at which the velocity numbers from a GPS become too unreliable for accurate correction of the accelerometers.
// @Range: 0 10
// @Increment: 1
// @User: Advanced
AP_GROUPINFO("GPS_MINSATS", 11, AP_AHRS, _gps_minsats, 6),
// NOTE: index 12 was for GPS_DELAY, but now removed, fixed delay
// of 1 was found to be the best choice
// 13 was the old EKF_USE
#if AP_AHRS_NAVEKF_AVAILABLE
// @Param: EKF_TYPE
// @DisplayName: Use NavEKF Kalman filter for attitude and position estimation
// @Description: This controls whether the NavEKF Kalman filter is used for attitude and position estimation and whether fallback to the DCM algorithm is allowed. Note that on copters "disabled" is not available, and will be the same as "enabled - no fallback"
// @Values: 0:Disabled,1:Enabled,2:Enable EKF2
// @User: Advanced
AP_GROUPINFO("EKF_TYPE", 14, AP_AHRS, _ekf_type, 1),
#endif
AP_GROUPEND
};
// return airspeed estimate if available
bool AP_AHRS::airspeed_estimate(float *airspeed_ret) const
{
if (airspeed_sensor_enabled()) {
*airspeed_ret = _airspeed->get_airspeed();
if (_wind_max > 0 && _gps.status() >= AP_GPS::GPS_OK_FIX_2D) {
// constrain the airspeed by the ground speed
// and AHRS_WIND_MAX
float gnd_speed = _gps.ground_speed();
float true_airspeed = *airspeed_ret * get_EAS2TAS();
true_airspeed = constrain_float(true_airspeed,
gnd_speed - _wind_max,
gnd_speed + _wind_max);
*airspeed_ret = true_airspeed / get_EAS2TAS();
}
return true;
}
return false;
}
// set_trim
void AP_AHRS::set_trim(Vector3f new_trim)
{
Vector3f trim;
trim.x = constrain_float(new_trim.x, ToRad(-AP_AHRS_TRIM_LIMIT), ToRad(AP_AHRS_TRIM_LIMIT));
trim.y = constrain_float(new_trim.y, ToRad(-AP_AHRS_TRIM_LIMIT), ToRad(AP_AHRS_TRIM_LIMIT));
_trim.set_and_save(trim);
}
// add_trim - adjust the roll and pitch trim up to a total of 10 degrees
void AP_AHRS::add_trim(float roll_in_radians, float pitch_in_radians, bool save_to_eeprom)
{
Vector3f trim = _trim.get();
// add new trim
trim.x = constrain_float(trim.x + roll_in_radians, ToRad(-AP_AHRS_TRIM_LIMIT), ToRad(AP_AHRS_TRIM_LIMIT));
trim.y = constrain_float(trim.y + pitch_in_radians, ToRad(-AP_AHRS_TRIM_LIMIT), ToRad(AP_AHRS_TRIM_LIMIT));
// set new trim values
_trim.set(trim);
// save to eeprom
if( save_to_eeprom ) {
_trim.save();
}
}
// return a ground speed estimate in m/s
Vector2f AP_AHRS::groundspeed_vector(void)
{
// Generate estimate of ground speed vector using air data system
Vector2f gndVelADS;
Vector2f gndVelGPS;
float airspeed;
bool gotAirspeed = airspeed_estimate_true(&airspeed);
bool gotGPS = (_gps.status() >= AP_GPS::GPS_OK_FIX_2D);
if (gotAirspeed) {
Vector3f wind = wind_estimate();
Vector2f wind2d = Vector2f(wind.x, wind.y);
Vector2f airspeed_vector = Vector2f(cosf(yaw), sinf(yaw)) * airspeed;
gndVelADS = airspeed_vector - wind2d;
}
// Generate estimate of ground speed vector using GPS
if (gotGPS) {
float cog = radians(_gps.ground_course_cd()*0.01f);
gndVelGPS = Vector2f(cosf(cog), sinf(cog)) * _gps.ground_speed();
}
// If both ADS and GPS data is available, apply a complementary filter
if (gotAirspeed && gotGPS) {
// The LPF is applied to the GPS and the HPF is applied to the air data estimate
// before the two are summed
//Define filter coefficients
// alpha and beta must sum to one
// beta = dt/Tau, where
// dt = filter time step (0.1 sec if called by nav loop)
// Tau = cross-over time constant (nominal 2 seconds)
// More lag on GPS requires Tau to be bigger, less lag allows it to be smaller
// To-Do - set Tau as a function of GPS lag.
const float alpha = 1.0f - beta;
// Run LP filters
_lp = gndVelGPS * beta + _lp * alpha;
// Run HP filters
_hp = (gndVelADS - _lastGndVelADS) + _hp * alpha;
// Save the current ADS ground vector for the next time step
_lastGndVelADS = gndVelADS;
// Sum the HP and LP filter outputs
return _hp + _lp;
}
// Only ADS data is available return ADS estimate
if (gotAirspeed && !gotGPS) {
return gndVelADS;
}
// Only GPS data is available so return GPS estimate
if (!gotAirspeed && gotGPS) {
return gndVelGPS;
}
return Vector2f(0.0f, 0.0f);
}
// update_trig - recalculates _cos_roll, _cos_pitch, etc based on latest attitude
// should be called after _dcm_matrix is updated
void AP_AHRS::update_trig(void)
{
Vector2f yaw_vector;
const Matrix3f &temp = get_rotation_body_to_ned();
// sin_yaw, cos_yaw
yaw_vector.x = temp.a.x;
yaw_vector.y = temp.b.x;
yaw_vector.normalize();
_sin_yaw = constrain_float(yaw_vector.y, -1.0, 1.0);
_cos_yaw = constrain_float(yaw_vector.x, -1.0, 1.0);
// cos_roll, cos_pitch
float cx2 = temp.c.x * temp.c.x;
if (cx2 >= 1.0f) {
_cos_pitch = 0;
_cos_roll = 1.0f;
} else {
_cos_pitch = safe_sqrt(1 - cx2);
_cos_roll = temp.c.z / _cos_pitch;
}
_cos_pitch = constrain_float(_cos_pitch, 0, 1.0);
_cos_roll = constrain_float(_cos_roll, -1.0, 1.0); // this relies on constrain_float() of infinity doing the right thing
// sin_roll, sin_pitch
_sin_pitch = -temp.c.x;
if (is_zero(_cos_pitch)) {
_sin_roll = sinf(roll);
} else {
_sin_roll = temp.c.y / _cos_pitch;
}
// sanity checks
if (yaw_vector.is_inf() || yaw_vector.is_nan()) {
yaw_vector.x = 0.0f;
yaw_vector.y = 0.0f;
_sin_yaw = 0.0f;
_cos_yaw = 1.0f;
}
if (isinf(_cos_roll) || isnan(_cos_roll)) {
_cos_roll = cosf(roll);
}
if (isinf(_sin_roll) || isnan(_sin_roll)) {
_sin_roll = sinf(roll);
}
}
/*
update the centi-degree values
*/
void AP_AHRS::update_cd_values(void)
{
roll_sensor = degrees(roll) * 100;
pitch_sensor = degrees(pitch) * 100;
yaw_sensor = degrees(yaw) * 100;
if (yaw_sensor < 0)
yaw_sensor += 36000;
}
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