Spelling errors (#19935)

src/modules/ekf2/EKF/common.h

@@ -479,7 +479,7 @@ union filter_control_status_u {
 		uint32_t gps                     : 1; ///< 2 - true if GPS measurement fusion is intended
 		uint32_t opt_flow                : 1; ///< 3 - true if optical flow measurements fusion is intended
 		uint32_t mag_hdg                 : 1; ///< 4 - true if a simple magnetic yaw heading fusion is intended
-		uint32_t mag_3D                  : 1; ///< 5 - true if 3-axis magnetometer measurement fusion is inteded
+		uint32_t mag_3D                  : 1; ///< 5 - true if 3-axis magnetometer measurement fusion is intended
 		uint32_t mag_dec                 : 1; ///< 6 - true if synthetic magnetic declination measurements fusion is intended
 		uint32_t in_air                  : 1; ///< 7 - true when the vehicle is airborne
 		uint32_t wind                    : 1; ///< 8 - true when wind velocity is being estimated
@@ -571,7 +571,7 @@ union warning_event_status_u {
 		bool height_sensor_timeout              : 1; ///< 4 - true when the height sensor has not been used to correct the state estimates for a significant time period
 		bool stopping_navigation                : 1; ///< 5 - true when the filter has insufficient data to estimate velocity and position and is falling back to an attitude, height and height rate mode of operation
 		bool invalid_accel_bias_cov_reset       : 1; ///< 6 - true when the filter has detected bad acceerometer bias state estimates and has reset the corresponding covariance matrix elements
-		bool bad_yaw_using_gps_course           : 1; ///< 7 - true when the fiter has detected an invalid yaw esitmate and has reset the yaw angle to the GPS ground course
+		bool bad_yaw_using_gps_course           : 1; ///< 7 - true when the filter has detected an invalid yaw estimate and has reset the yaw angle to the GPS ground course
 		bool stopping_mag_use                   : 1; ///< 8 - true when the filter has detected bad magnetometer data and is stopping further use of the magnetomer data
 		bool vision_data_stopped                : 1; ///< 9 - true when the vision system data has stopped for a significant time period
 		bool emergency_yaw_reset_mag_stopped    : 1; ///< 10 - true when the filter has detected bad magnetometer data, has reset the yaw to anothter source of data and has stopped further use of the magnetomer data

src/modules/ekf2/EKF2.cpp

@@ -1539,7 +1539,7 @@ void EKF2::UpdateAirspeedSample(ekf2_timestamps_s &ekf2_timestamps)
 
 void EKF2::UpdateAuxVelSample(ekf2_timestamps_s &ekf2_timestamps)
 {
-	// EKF auxillary velocity sample
+	// EKF auxiliary velocity sample
 	//  - use the landing target pose estimate as another source of velocity data
 	const unsigned last_generation = _landing_target_pose_sub.get_last_generation();
 	landing_target_pose_s landing_target_pose;

src/modules/ekf2/EKF2.hpp

@@ -358,7 +358,7 @@ private:
 		(ParamExtFloat<px4::params::EKF2_EV_DELAY>)
 		_param_ekf2_ev_delay,	///< off-board vision measurement delay relative to the IMU (mSec)
 		(ParamExtFloat<px4::params::EKF2_AVEL_DELAY>)
-		_param_ekf2_avel_delay,	///< auxillary velocity measurement delay relative to the IMU (mSec)
+		_param_ekf2_avel_delay,	///< auxiliary velocity measurement delay relative to the IMU (mSec)
 
 		(ParamExtFloat<px4::params::EKF2_GYR_NOISE>)
 		_param_ekf2_gyr_noise,	///< IMU angular rate noise used for covariance prediction (rad/sec)

src/modules/ekf2/ekf2_params.c

@@ -139,7 +139,7 @@ PARAM_DEFINE_FLOAT(EKF2_ASP_DELAY, 100);
 PARAM_DEFINE_FLOAT(EKF2_EV_DELAY, 0);
 
 /**
- * Auxillary Velocity Estimate (e.g from a landing target) delay relative to IMU measurements
+ * Auxiliary Velocity Estimate (e.g from a landing target) delay relative to IMU measurements
  *
  * @group EKF2
  * @min 0
@@ -676,7 +676,7 @@ PARAM_DEFINE_INT32(EKF2_NOAID_TOUT, 5000000);
 PARAM_DEFINE_FLOAT(EKF2_RNG_NOISE, 0.1f);
 
 /**
- * Range finder range dependant noise scaler.
+ * Range finder range dependent noise scaler.
  *
  * Specifies the increase in range finder noise with range.
  *
@@ -702,7 +702,7 @@ PARAM_DEFINE_FLOAT(EKF2_RNG_GATE, 5.0f);
 /**
  * Expected range finder reading when on ground.
  *
- * If the vehicle is on ground, is not moving as determined by the motion test and the range finder is returning invalid or no data, then an assumed range value of EKF2_MIN_RNG will be used by the terrain estimator so that a terrain height estimate is avilable at the start of flight in situations where the range finder may be inside its minimum measurements distance when on ground.
+ * If the vehicle is on ground, is not moving as determined by the motion test and the range finder is returning invalid or no data, then an assumed range value of EKF2_MIN_RNG will be used by the terrain estimator so that a terrain height estimate is available at the start of flight in situations where the range finder may be inside its minimum measurements distance when on ground.
  *
  * @group EKF2
  * @min 0.01
@@ -1374,7 +1374,7 @@ PARAM_DEFINE_INT32(EKF2_MAG_CHECK, 1);
  * For magnetic heading fusion the magnetometer Z measurement will be replaced by a synthetic value calculated
  * using the knowledge of the 3D magnetic field vector at the location of the drone. Therefore, this parameter
  * will only have an effect if the global position of the drone is known.
- * For 3D mag fusion the magnetometer Z measurement will simply be ingored instead of fusing the synthetic value.
+ * For 3D mag fusion the magnetometer Z measurement will simply be ignored instead of fusing the synthetic value.
  *
  * @group EKF2
  * @boolean
@@ -1384,7 +1384,7 @@ PARAM_DEFINE_INT32(EKF2_SYNT_MAG_Z, 0);
 /**
  * Default value of true airspeed used in EKF-GSF AHRS calculation.
  *
- * If no airspeed measurements are avalable, the EKF-GSF AHRS calculation will assume this value of true airspeed when compensating for centripetal acceleration during turns. Set to zero to disable centripetal acceleration compensation during fixed wing flight modes.
+ * If no airspeed measurements are available, the EKF-GSF AHRS calculation will assume this value of true airspeed when compensating for centripetal acceleration during turns. Set to zero to disable centripetal acceleration compensation during fixed wing flight modes.
  *
  * @group EKF2
  * @min 0.0