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Add missing const qualifier

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kamilritz
2020-01-08 09:00:31 +01:00
committed by Mathieu Bresciani
parent 066392ef02
commit 9e6d27fafb
14 changed files with 225 additions and 245 deletions
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EKF/ekf_helper.cpp
+26 -27
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@@ -391,25 +391,26 @@ void Ekf::alignOutputFilter()
// It is used to align the yaw angle after launch or takeoff for fixed wing vehicle only.
bool Ekf::realignYawGPS()
{
// Need at least 5 m/s of GPS horizontal speed and ratio of velocity error to velocity < 0.15 for a reliable alignment
float gpsSpeed = sqrtf(sq(_gps_sample_delayed.vel(0)) + sq(_gps_sample_delayed.vel(1)));
const float gpsSpeed = sqrtf(sq(_gps_sample_delayed.vel(0)) + sq(_gps_sample_delayed.vel(1)));
// Need at least 5 m/s of GPS horizontal speed and
// ratio of velocity error to velocity < 0.15 for a reliable alignment
if ((gpsSpeed > 5.0f) && (_gps_sample_delayed.sacc < (0.15f * gpsSpeed))) {
// check for excessive horizontal GPS velocity innovations
bool badVelInnov = (_gps_vel_test_ratio(0) > 1.0f) && _control_status.flags.gps;
const bool badVelInnov = (_gps_vel_test_ratio(0) > 1.0f) && _control_status.flags.gps;
// calculate GPS course over ground angle
float gpsCOG = atan2f(_gps_sample_delayed.vel(1), _gps_sample_delayed.vel(0));
const float gpsCOG = atan2f(_gps_sample_delayed.vel(1), _gps_sample_delayed.vel(0));
// calculate course yaw angle
float ekfGOG = atan2f(_state.vel(1), _state.vel(0));
const float ekfGOG = atan2f(_state.vel(1), _state.vel(0));
// Check the EKF and GPS course over ground for consistency
float courseYawError = gpsCOG - ekfGOG;
const float courseYawError = gpsCOG - ekfGOG;
// If the angles disagree and horizontal GPS velocity innovations are large or no previous yaw alignment, we declare the magnetic yaw as bad
bool badYawErr = fabsf(courseYawError) > 0.5f;
bool badMagYaw = (badYawErr && badVelInnov);
const bool badYawErr = fabsf(courseYawError) > 0.5f;
const bool badMagYaw = (badYawErr && badVelInnov);
if (badMagYaw) {
_num_bad_flight_yaw_events ++;
@@ -426,7 +427,7 @@ bool Ekf::realignYawGPS()
}
// save a copy of the quaternion state for later use in calculating the amount of reset change
Quatf quat_before_reset = _state.quat_nominal;
const Quatf quat_before_reset = _state.quat_nominal;
// update transformation matrix from body to world frame using the current state estimate
_R_to_earth = Dcmf(_state.quat_nominal);
@@ -455,14 +456,12 @@ bool Ekf::realignYawGPS()
// calculate new filter quaternion states using corrected yaw angle
_state.quat_nominal = Quatf(euler321);
_R_to_earth = Dcmf(_state.quat_nominal);
uncorrelateQuatStates();
// If heading was bad, then we also need to reset the velocity and position states
_velpos_reset_request = badMagYaw;
// update transformation matrix from body to world frame using the current state estimate
_R_to_earth = Dcmf(_state.quat_nominal);
// Use the last magnetometer measurements to reset the field states
_state.mag_B.zero();
_state.mag_I = _R_to_earth * _mag_sample_delayed.mag;
@@ -551,7 +550,7 @@ bool Ekf::resetMagHeading(const Vector3f &mag_init, bool increase_yaw_var, bool
}
// save a copy of the quaternion state for later use in calculating the amount of reset change
Quatf quat_before_reset = _state.quat_nominal;
const Quatf quat_before_reset = _state.quat_nominal;
Quatf quat_after_reset = _state.quat_nominal;
// update transformation matrix from body to world frame using the current estimate
@@ -572,13 +571,13 @@ bool Ekf::resetMagHeading(const Vector3f &mag_init, bool increase_yaw_var, bool
// calculate the observed yaw angle
if (_control_status.flags.ev_yaw) {
// convert the observed quaternion to a rotation matrix
Dcmf R_to_earth_ev(_ev_sample_delayed.quat); // transformation matrix from body to world frame
const Dcmf R_to_earth_ev(_ev_sample_delayed.quat); // transformation matrix from body to world frame
// calculate the yaw angle for a 312 sequence
euler321(2) = atan2f(R_to_earth_ev(1, 0), R_to_earth_ev(0, 0));
} else if (_params.mag_fusion_type <= MAG_FUSE_TYPE_3D) {
// rotate the magnetometer measurements into earth frame using a zero yaw angle
Vector3f mag_earth_pred = R_to_earth * mag_init;
const Vector3f mag_earth_pred = R_to_earth * mag_init;
// the angle of the projection onto the horizontal gives the yaw angle
euler321(2) = -atan2f(mag_earth_pred(1), mag_earth_pred(0)) + getMagDeclination();
@@ -630,13 +629,13 @@ bool Ekf::resetMagHeading(const Vector3f &mag_init, bool increase_yaw_var, bool
// calculate the observed yaw angle
if (_control_status.flags.ev_yaw) {
// convert the observed quaternion to a rotation matrix
Dcmf R_to_earth_ev(_ev_sample_delayed.quat); // transformation matrix from body to world frame
const Dcmf R_to_earth_ev(_ev_sample_delayed.quat); // transformation matrix from body to world frame
// calculate the yaw angle for a 312 sequence
euler312(0) = atan2f(-R_to_earth_ev(0, 1), R_to_earth_ev(1, 1));
} else if (_params.mag_fusion_type <= MAG_FUSE_TYPE_3D) {
// rotate the magnetometer measurements into earth frame using a zero yaw angle
Vector3f mag_earth_pred = R_to_earth * mag_init;
const Vector3f mag_earth_pred = R_to_earth * mag_init;
// the angle of the projection onto the horizontal gives the yaw angle
euler312(0) = -atan2f(mag_earth_pred(1), mag_earth_pred(0)) + getMagDeclination();
@@ -668,7 +667,7 @@ bool Ekf::resetMagHeading(const Vector3f &mag_init, bool increase_yaw_var, bool
}
// set the earth magnetic field states using the updated rotation
Dcmf R_to_earth_after(quat_after_reset);
const Dcmf R_to_earth_after(quat_after_reset);
_state.mag_I = R_to_earth_after * mag_init;
// reset the corresponding rows and columns in the covariance matrix and set the variances on the magnetic field states to the measurement variance
@@ -1198,21 +1197,21 @@ hagl_max : Maximum height above ground (meters). NaN when limiting is not needed
void Ekf::get_ekf_ctrl_limits(float *vxy_max, float *vz_max, float *hagl_min, float *hagl_max)
{
// Calculate range finder limits
float rangefinder_hagl_min = _rng_valid_min_val;
const float rangefinder_hagl_min = _rng_valid_min_val;
// Allow use of 75% of rangefinder maximum range to allow for angular motion
float rangefinder_hagl_max = 0.75f * _rng_valid_max_val;
const float rangefinder_hagl_max = 0.75f * _rng_valid_max_val;
// Calculate optical flow limits
// Allow ground relative velocity to use 50% of available flow sensor range to allow for angular motion
float flow_vxy_max = fmaxf(0.5f * _flow_max_rate * (_terrain_vpos - _state.pos(2)), 0.0f);
float flow_hagl_min = _flow_min_distance;
float flow_hagl_max = _flow_max_distance;
const float flow_vxy_max = fmaxf(0.5f * _flow_max_rate * (_terrain_vpos - _state.pos(2)), 0.0f);
const float flow_hagl_min = _flow_min_distance;
const float flow_hagl_max = _flow_max_distance;
// TODO : calculate visual odometry limits
bool relying_on_rangefinder = _control_status.flags.rng_hgt && !_params.range_aid;
const bool relying_on_rangefinder = _control_status.flags.rng_hgt && !_params.range_aid;
bool relying_on_optical_flow = _control_status.flags.opt_flow && !(_control_status.flags.gps || _control_status.flags.ev_pos || _control_status.flags.ev_vel);
const bool relying_on_optical_flow = _control_status.flags.opt_flow && !(_control_status.flags.gps || _control_status.flags.ev_pos || _control_status.flags.ev_vel);
// Do not require limiting by default
*vxy_max = NAN;
@@ -1649,8 +1648,8 @@ void Ekf::calcExtVisRotMat()
if (rot_vec_norm > 1e-6f) {
// apply an input limiter to protect from spikes
Vector3f _input_delta_vec = rot_vec - _ev_rot_vec_filt;
float input_delta_len = _input_delta_vec.norm();
const Vector3f _input_delta_vec = rot_vec - _ev_rot_vec_filt;
const float input_delta_len = _input_delta_vec.norm();
if (input_delta_len > 0.1f) {
rot_vec = _ev_rot_vec_filt + _input_delta_vec * (0.1f / input_delta_len);