Spelling errors (#19935)

src/drivers/batt_smbus/batt_smbus.cpp

@@ -523,7 +523,7 @@ $ batt_smbus -X write_flash 19069 2 27 0
 
 	PRINT_MODULE_USAGE_COMMAND_DESCR("man_info", "Prints manufacturer info.");
 	PRINT_MODULE_USAGE_COMMAND_DESCR("unseal", "Unseals the devices flash memory to enable write_flash commands.");
-	PRINT_MODULE_USAGE_COMMAND_DESCR("seal", "Seals the devices flash memory to disbale write_flash commands.");
+	PRINT_MODULE_USAGE_COMMAND_DESCR("seal", "Seals the devices flash memory to disable write_flash commands.");
 	PRINT_MODULE_USAGE_COMMAND_DESCR("suspend", "Suspends the driver from rescheduling the cycle.");
 	PRINT_MODULE_USAGE_COMMAND_DESCR("resume", "Resumes the driver from suspension.");
 

src/drivers/camera_trigger/camera_trigger.cpp

@@ -35,7 +35,7 @@
  * @file camera_trigger.cpp
  *
  * External camera-IMU synchronisation and triggering, and support for
- * camera manipulation using PWM signals over FMU auxillary pins.
+ * camera manipulation using PWM signals over FMU auxiliary pins.
  *
  * @author Mohammed Kabir <kabir@uasys.io>
  * @author Kelly Steich <kelly.steich@wingtra.com>

src/drivers/cyphal/parameters.c

@@ -123,7 +123,7 @@ PARAM_DEFINE_INT32(UCAN1_BMS_BS_SUB, -1);
 PARAM_DEFINE_INT32(UCAN1_BMS_BP_SUB, -1);
 
 /**
- * Cyphal leagcy battery port ID.
+ * Cyphal legacy battery port ID.
  *
  * @min -1
  * @max 6143

src/drivers/distance_sensor/broadcom/afbrs50/Inc/platform/argus_print.h

@@ -54,7 +54,7 @@
 #include "api/argus_def.h"
 
 /*!***************************************************************************
- * @brief	A printf-like function to print formated data to an debugging interface.
+ * @brief	A printf-like function to print formatted data to an debugging interface.
  *
  * @details Writes the C string pointed by fmt_t to an output. If format
  * 			includes format specifiers (subsequences beginning with %), the

src/drivers/distance_sensor/pga460/pga460.cpp

@@ -482,10 +482,12 @@ int PGA460::print_usage(const char *reason)
 	PRINT_MODULE_DESCRIPTION(
 		R"DESCR_STR(
 ### Description
+
 Ultrasonic range finder driver that handles the communication with the device and publishes the distance via uORB.
 
 ### Implementation
-This driver is implented as a NuttX task. This Implementation was chosen due to the need for polling on a message
+
+This driver is implemented as a NuttX task. This Implementation was chosen due to the need for polling on a message
 via UART, which is not supported in the work_queue. This driver continuously takes range measurements while it is
 running. A simple algorithm to detect false readings is implemented at the driver levelin an attemptto improve
 the quality of data that is being published. The driver will not publish data at all if it deems the sensor data

src/drivers/distance_sensor/pga460/pga460.h

@@ -286,7 +286,7 @@ public:
 	int read_eeprom();
 
 	/**
-	 * @brief Writes the user defined paramaters to device EEPROM.
+	 * @brief Writes the user defined parameters to device EEPROM.
 	 * @return Returns true if the EEPROM was successfully written to.
 	 */
 	int write_eeprom();
@@ -341,7 +341,7 @@ private:
 	int initialize_device_settings();
 
 	/**
-	 * @brief Writes the user defined paramaters to device register map.
+	 * @brief Writes the user defined parameters to device register map.
 	 * @return Returns true if the thresholds were successfully written.
 	 */
 	int initialize_thresholds();

src/drivers/distance_sensor/ulanding_radar/AerotennaULanding.hpp

@@ -71,7 +71,7 @@ using namespace time_literals;
 
 /**
  * Assume standard deviation to be equal to sensor resolution.
- * Static bench tests have shown that the sensor ouput does
+ * Static bench tests have shown that the sensor output does
  * not vary if the unit is not moved.
  */
 #define SENS_VARIANCE           0.045f * 0.045f

src/drivers/drv_led.h

@@ -44,7 +44,7 @@
 
 #include <board_config.h>
 
-// allow the board to override the number (or maxiumum number) of LED's it has
+// allow the board to override the number (or maximum number) of LED's it has
 #ifndef BOARD_MAX_LEDS
 #define BOARD_MAX_LEDS 4
 #endif

src/drivers/imu/fxas21002c/FXAS21002C.cpp

@@ -39,7 +39,7 @@
 #define FXAS21002C_MAX_RATE              800
 #define FXAS21002C_DEFAULT_RATE          FXAS21002C_MAX_RATE
 #define FXAS21002C_DEFAULT_RANGE_DPS     2000
-#define FXAS21002C_DEFAULT_ONCHIP_FILTER_FREQ 	64 // ODR dependant
+#define FXAS21002C_DEFAULT_ONCHIP_FILTER_FREQ 	64 // ODR dependent
 
 /*
   we set the timer interrupt to run a bit faster than the desired

src/drivers/power_monitor/voxlpm/voxlpm.cpp

@@ -96,7 +96,7 @@ VOXLPM::init()
 		ret = init_ina231();
 
 	} else {
-		PX4_ERR("Unkown device address");
+		PX4_ERR("Unknown device address");
 		ret = PX4_ERROR;
 	}
 

src/drivers/roboclaw/roboclaw_main.cpp

@@ -85,8 +85,8 @@ static void usage()
 This driver communicates over UART with the [Roboclaw motor driver](http://downloads.basicmicro.com/docs/roboclaw_user_manual.pdf).
 It performs two tasks:
 
- - Control the motors based on the `actuator_controls_0` UOrb topic.
- - Read the wheel encoders and publish the raw data in the `wheel_encoders` UOrb topic
+- Control the motors based on the `actuator_controls_0` UOrb topic.
+- Read the wheel encoders and publish the raw data in the `wheel_encoders` UOrb topic
 
 In order to use this driver, the Roboclaw should be put into Packet Serial mode (see the linked documentation), and
 your flight controller's UART port should be connected to the Roboclaw as shown in the documentation. For Pixhawk 4,
@@ -109,16 +109,18 @@ the driver terminates immediately.
 
 The command to start this driver is:
 
- $ roboclaw start <device> <baud>
+```
+$ roboclaw start <device> <baud>
+```
 
-`<device>` is the name of the UART port. On the Pixhawk 4, this is `/dev/ttyS3`.
-`<baud>` is te baud rate.
+- `<device>` is the name of the UART port. On the Pixhawk 4, this is `/dev/ttyS3`.
+- `<baud>` is the baud rate.
 
 All available commands are:
 
- - `$ roboclaw start <device> <baud>`
- - `$ roboclaw status`
- - `$ roboclaw stop`
+- `$ roboclaw start <device> <baud>`
+- `$ roboclaw status`
+- `$ roboclaw stop`
 	)DESCR_STR");
 }
 

src/drivers/rpm/pcf8583/parameters.c

@@ -60,9 +60,9 @@ PARAM_DEFINE_INT32(PCF8583_POOL, 1000000);
 /**
  * PCF8583 rotorfreq (i2c) pulse reset value
  *
- * Internal device counter is reset to 0 when overun this value,
- * counter is able to store upto 6 digits
- * reset of counter takes some time - measurement with reset has worse accurancy.
+ * Internal device counter is reset to 0 when overrun this value,
+ * counter is able to store up to 6 digits
+ * reset of counter takes some time - measurement with reset has worse accuracy.
  * 0 means reset counter after every measurement.
  *
  * @reboot_required true

src/drivers/tap_esc/TAP_ESC.cpp

@@ -511,17 +511,22 @@ int TAP_ESC::print_usage(const char *reason)
 	PRINT_MODULE_DESCRIPTION(
 		R"DESCR_STR(
 ### Description
+
 This module controls the TAP_ESC hardware via UART. It listens on the
 actuator_controls topics, does the mixing and writes the PWM outputs.
 
 ### Implementation
-Currently the module is implementd as a threaded version only, meaning that it
+
+Currently the module is implemented as a threaded version only, meaning that it
 runs in its own thread instead of on the work queue.
 
 ### Example
-The module is typically started with:
-tap_esc start -d /dev/ttyS2 -n <1-8>
 
+The module is typically started with:
+
+```
+tap_esc start -d /dev/ttyS2 -n <1-8>
+```
 )DESCR_STR");
 
 	PRINT_MODULE_USAGE_NAME("tap_esc", "driver");

src/drivers/tap_esc/drv_tap_esc.h

@@ -107,7 +107,7 @@ typedef struct {
 	uint16_t current; // 0.0 - 200.0 A
 #endif
 #if defined(ESC_HAVE_TEMPERATURE_SENSOR)
-	uint8_t temperature; // 0 - 256 degree celsius
+	uint8_t temperature; // 0 - 256 degrees Celsius
 #endif
 } RunInfoRepsonse;
 /****** Run ***********/
@@ -232,7 +232,7 @@ typedef  struct {
  *
  * speed: -32767 - 32767 rpm
  *
- * temperature: 0 - 256 celsius degree (if available)
+ * temperature: 0 - 256 degrees Celsius (if available)
  * voltage: 0.00 - 100.00 V (if available)
  * current: 0.0 - 200.0 A (if available)
  */

src/drivers/uavcan/sensors/battery.cpp

@@ -115,7 +115,7 @@ UavcanBatteryBridge::battery_sub_cb(const uavcan::ReceivedDataStructure<uavcan::
 
 	_battery_status[instance].remaining = msg.state_of_charge_pct / 100.0f; // between 0 and 1
 	// _battery_status[instance].scale = msg.; // Power scaling factor, >= 1, or -1 if unknown
-	_battery_status[instance].temperature = msg.temperature + CONSTANTS_ABSOLUTE_NULL_CELSIUS; // Kelvin to Celcius
+	_battery_status[instance].temperature = msg.temperature + CONSTANTS_ABSOLUTE_NULL_CELSIUS; // Kelvin to Celsius
 	// _battery_status[instance].cell_count = msg.;
 	_battery_status[instance].connected = true;
 	_battery_status[instance].source = msg.status_flags & uavcan::equipment::power::BatteryInfo::STATUS_FLAG_IN_USE;
@@ -238,7 +238,7 @@ UavcanBatteryBridge::filterData(const uavcan::ReceivedDataStructure<uavcan::equi
 
 	/* Override data that is expected to arrive from UAVCAN msg*/
 	_battery_status[instance] = _battery[instance]->getBatteryStatus();
-	_battery_status[instance].temperature = msg.temperature + CONSTANTS_ABSOLUTE_NULL_CELSIUS; // Kelvin to Celcius
+	_battery_status[instance].temperature = msg.temperature + CONSTANTS_ABSOLUTE_NULL_CELSIUS; // Kelvin to Celsius
 	_battery_status[instance].serial_number = msg.model_instance_id;
 	_battery_status[instance].id = msg.getSrcNodeID().get(); // overwrite zeroed index from _battery
 

src/drivers/uavcan/uavcan_drivers/kinetis/README.md

@@ -18,9 +18,9 @@ and the following commandline defines:
 |UAVCAN_KINETIS_TIMER_NUMBER | - {0..3}  Sets the Periodic Interrupt Timer (PITn) channel |
 
 Things that could be improved:
-1. Build time command line configuartion of Mailbox/FIFO and filters
-2. Build time command line configuartion clock source
-    - Curently the driver use `const uavcan::uint8_t CLOCKSEL  = 0;` To Select OSCERCLK
+1. Build time command line configuration of Mailbox/FIFO and filters
+2. Build time command line configuration clock source
+    - Currently the driver use `const uavcan::uint8_t CLOCKSEL  = 0;` To Select OSCERCLK
 3. Dynamic filter disable. There are no filter enable bits on the FlexCAN, just the number of Filters
    can be set. But this changes the memory map. So the configuration show below has been chosen.
 

src/drivers/uavcan/uavcan_params.c

@@ -318,7 +318,7 @@ PARAM_DEFINE_INT32(UAVCAN_SUB_HYGRO, 0);
 /**
  * subscription ICE
  *
- * Enable UAVCAN internal combusion engine (ICE) subscription.
+ * Enable UAVCAN internal combustion engine (ICE) subscription.
  *  uavcan::equipment::ice::reciprocating::Status
  *
  * @boolean

src/drivers/uwb/uwb_sr150/module.yaml

@@ -13,7 +13,7 @@ parameters:
         UWB_INIT_OFF_X:
           description:
             short: UWB sensor X offset in body frame
-            long: UWB sensor positioning in relation to Drone in NED. X offset. A Positiv offset results in a Position o
+            long: UWB sensor positioning in relation to Drone in NED. X offset. A Positive offset results in a Position o
           type: float
           unit: m
           decimal: 2

src/drivers/uwb/uwb_sr150/uwb_sr150.cpp

@@ -394,7 +394,7 @@ int UWB_SR150::distance()
 					break;
 
 				case UWB_LIN_DEP_FOR_THREE:
-					PX4_INFO("UWB localization: linear dependant with 3 Anchors");
+					PX4_INFO("UWB localization: linear dependent with 3 Anchors");
 					break;
 
 				case UWB_ANC_ON_ONE_LEVEL:
@@ -402,7 +402,7 @@ int UWB_SR150::distance()
 					break;
 
 				case UWB_LIN_DEP_FOR_FOUR:
-					PX4_INFO("UWB localization: linear dependant with four or more Anchors");
+					PX4_INFO("UWB localization: linear dependent with four or more Anchors");
 					break;
 
 				case UWB_RANK_ZERO:

src/lib/airspeed/airspeed.cpp

@@ -49,7 +49,7 @@ float calc_IAS_corrected(enum AIRSPEED_COMPENSATION_MODEL pmodel, enum AIRSPEED_
 			 float tube_len, float tube_dia_mm, float differential_pressure, float pressure_ambient, float temperature_celsius)
 {
 	if (!PX4_ISFINITE(temperature_celsius)) {
-		temperature_celsius = 15.f; // ICAO Standard Atmosphere 15 degrees celcius
+		temperature_celsius = 15.f; // ICAO Standard Atmosphere 15 degrees Celsius
 	}
 
 	// air density in kg/m3
@@ -189,7 +189,7 @@ float calc_IAS(float differential_pressure)
 float calc_TAS_from_CAS(float speed_calibrated, float pressure_ambient, float temperature_celsius)
 {
 	if (!PX4_ISFINITE(temperature_celsius)) {
-		temperature_celsius = 15.f; // ICAO Standard Atmosphere 15 degrees celcius
+		temperature_celsius = 15.f; // ICAO Standard Atmosphere 15 degrees Celsius
 	}
 
 	return speed_calibrated * sqrtf(CONSTANTS_AIR_DENSITY_SEA_LEVEL_15C / get_air_density(pressure_ambient,
@@ -222,7 +222,7 @@ float calc_TAS(float total_pressure, float static_pressure, float temperature_ce
 float get_air_density(float static_pressure, float temperature_celsius)
 {
 	if (!PX4_ISFINITE(temperature_celsius)) {
-		temperature_celsius = 15.f; // ICAO Standard Atmosphere 15 degrees celcius
+		temperature_celsius = 15.f; // ICAO Standard Atmosphere 15 degrees Celsius
 	}
 
 	return static_pressure / (CONSTANTS_AIR_GAS_CONST * (temperature_celsius - CONSTANTS_ABSOLUTE_NULL_CELSIUS));

src/lib/airspeed/airspeed.h

@@ -92,7 +92,7 @@ __EXPORT float calc_IAS(float differential_pressure);
  *
  * @param speed_equivalent current calibrated airspeed
  * @param pressure_ambient pressure at the side of the tube/airplane
- * @param temperature_celsius air temperature in degrees celcius
+ * @param temperature_celsius air temperature in degrees Celsius
  * @return TAS in m/s
  */
 __EXPORT float calc_TAS_from_CAS(float speed_indicated, float pressure_ambient,
@@ -116,7 +116,7 @@ __EXPORT float calc_CAS_from_IAS(float speed_indicated, float scale);
  *
  * @param total_pressure pressure inside the pitot/prandtl tube
  * @param static_pressure pressure at the side of the tube/airplane
- * @param temperature_celsius air temperature in degrees celcius
+ * @param temperature_celsius air temperature in degrees Celsius
  * @return true airspeed in m/s
  */
 __EXPORT float calc_TAS(float total_pressure, float static_pressure, float temperature_celsius);
@@ -125,7 +125,7 @@ __EXPORT float calc_TAS(float total_pressure, float static_pressure, float tempe
 * Calculates air density.
 *
 * @param static_pressure ambient pressure in millibar
-* @param temperature_celcius air / ambient temperature in celcius
+* @param temperature_celcius air / ambient temperature in Celsius
 */
 __EXPORT float get_air_density(float static_pressure, float temperature_celsius);
 
@@ -135,7 +135,7 @@ __EXPORT float get_air_density(float static_pressure, float temperature_celsius)
  *
  * @param speed_true current true airspeed
  * @param pressure_ambient pressure at the side of the tube/airplane
- * @param temperature_celsius air temperature in degrees celcius
+ * @param temperature_celsius air temperature in degrees Celsius
  * @return CAS in m/s
  */
 __EXPORT float calc_CAS_from_TAS(float speed_true, float pressure_ambient,

src/lib/battery/module.yaml

@@ -43,7 +43,7 @@ parameters:
             description:
                 short: Voltage drop per cell on full throttle
                 long: |
-                    This implicitely defines the internal resistance
+                    This implicitly defines the internal resistance
                     to maximum current ratio for battery 1 and assumes linearity.
                     A good value to use is the difference between the
                     5C and 20-25C load. Not used if BAT${i}_R_INTERNAL is

src/lib/drivers/smbus_sbs/SBS.hpp

@@ -69,7 +69,7 @@ public:
 
 	int populate_smbus_data(battery_status_s &msg);
 
-	virtual void RunImpl(); // Can be overriden by derived implimentation
+	virtual void RunImpl(); // Can be overridden by derived implimentation
 
 	virtual void custom_method(const BusCLIArguments &cli) = 0; //Has be overriden by derived implimentation
 
@@ -81,7 +81,7 @@ public:
 
 	/**
 	* @brief Read info from battery on startup.
-	* @return Returns PX4_OK on success, PX4_ERROR on failure. Can be overriden by derived implimentation
+	* @return Returns PX4_OK on success, PX4_ERROR on failure. Can be overridden by derived implimentation
 	*/
 	virtual int get_startup_info();
 

src/lib/led/led.h

@@ -76,7 +76,7 @@ public:
 	}
 
 	/**
-	 * get maxium time between two consecutive calls to update() in us.
+	 * get maximum time between two consecutive calls to update() in us.
 	 */
 	int maximum_update_interval() const
 	{

src/lib/parameters/flashparams/flashfs.c

@@ -1048,7 +1048,7 @@ int parameter_flashfs_init(sector_descriptor_t *fconfig, uint8_t *buffer, uint16
 
 	flash_entry_header_t *pf = find_entry(parameters_token);
 
-	/*  No paramaters */
+	/*  No parameters */
 
 	if (pf == NULL) {
 		size_t total_size = size + sizeof(flash_entry_header_t);

src/lib/parameters/px_process_params.py

@@ -33,7 +33,7 @@
 ############################################################################
 
 #
-# PX4 paramaters processor (main executable file)
+# PX4 parameters processor (main executable file)
 #
 # This tool scans the PX4 source code for declarations of tunable parameters
 # and outputs the list in various formats.

src/lib/systemlib/system_params.c

@@ -146,7 +146,7 @@ PARAM_DEFINE_INT32(SYS_CAL_BARO, 0);
  * Required temperature rise during thermal calibration
  *
  * A temperature increase greater than this value is required during calibration.
- * Calibration will complete for each sensor when the temperature increase above the starting temeprature exceeds the value set by SYS_CAL_TDEL.
+ * Calibration will complete for each sensor when the temperature increase above the starting temperature exceeds the value set by SYS_CAL_TDEL.
  * If the temperature rise is insufficient, the calibration will continue indefinitely and the board will need to be repowered to exit.
  *
  * @unit celcius
@@ -223,7 +223,7 @@ PARAM_DEFINE_INT32(SYS_HAS_BARO, 1);
  *
  * If set to the number of distance sensors, the preflight check will check
  * for their presence and valid data publication. Disable with 0 if no distance
- * sensor present or to disbale the preflight check.
+ * sensor present or to disable the preflight check.
  *
  * @reboot_required true
  *

src/lib/tunes/tune_definition.desc

@@ -83,8 +83,8 @@
  */
 
 
-//           ordinal name                  tune                                        interruptable*     hint
-//  * Repeated tunes should always be defined as interruptable, if not an explict 'tone_control stop' is needed
+//           ordinal name                  tune                                        interruptible*     hint
+//  * Repeated tunes should always be defined as interruptible, if not an explicit 'tone_control stop' is needed
 PX4_DEFINE_TUNE(0,  CUSTOM,                "",                                              true  /*  empty to align with the index */)
 PX4_DEFINE_TUNE(1,  STARTUP,               "MFT240L8 O4aO5dc O4aO5dc O4aO5dc L16dcdcdcdc",  true  /*  startup tune */)
 PX4_DEFINE_TUNE(2,  ERROR_TUNE,            "MBT200a8a8a8PaaaP",                             true  /*  ERROR tone */)

src/lib/tunes/tunes.h

@@ -92,7 +92,7 @@ public:
 	 * or the tune being already played is a repeated tune.
 	 * @param  tune_control struct containig the uORB message
 	 * @return              return ControlResult::InvalidTune if the default tune does not exist,
-	 * 			ControlResult::WouldInterrupt if tune was already playing and not interruptable,
+	 * 			ControlResult::WouldInterrupt if tune was already playing and not interruptible,
 	 * 			ControlResult::AlreadyPlaying if same tune was already playing,
 	 * 			ControlResult::Success if new tune was set.
 	 */

src/modules/commander/commander_params.c

@@ -1063,7 +1063,7 @@ PARAM_DEFINE_FLOAT(COM_WIND_WARN, -1.f);
  * the time since takeoff is above this value. It is not possible to resume the
  * mission or switch to any mode other than RTL or Land.
  *
- * Set a nagative value to disable.
+ * Set a negative value to disable.
  *
  *
  * @unit s

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

src/modules/flight_mode_manager/FlightModeManager.cpp

@@ -385,7 +385,7 @@ void FlightModeManager::handleCommand()
 		// check what command it is
 		FlightTaskIndex desired_task = switchVehicleCommand(command.command);
 
-		// ignore all unkown commands
+		// ignore all unknown commands
 		if (desired_task != FlightTaskIndex::None
 		    && _vehicle_status_sub.get().vehicle_type == vehicle_status_s::VEHICLE_TYPE_ROTARY_WING) {
 			// switch to the commanded task

src/modules/flight_mode_manager/Templates/FlightTasks_generated.cpp.em

@@ -91,7 +91,7 @@ upperCase = lambda s: s[:].upper() if s else ''
 
 @[end for]@
 @[end if]@
-	// ignore all unkown commands
+	// ignore all unknown commands
 	default : return FlightTaskIndex::None;
 	}
 }

src/modules/flight_mode_manager/tasks/Auto/FlightTaskAuto.hpp

@@ -197,7 +197,7 @@ private:
 	_triplet_next_wp; /**< next triplet from navigator which may differ from the intenal one (_next_wp) depending on the vehicle state.*/
 	matrix::Vector3f _closest_pt; /**< closest point to the vehicle position on the line previous - target */
 
-	hrt_abstime _time_last_cruise_speed_override{0}; ///< timestamp the cruise speed was last time overriden using DO_CHANGE_SPEED
+	hrt_abstime _time_last_cruise_speed_override{0}; ///< timestamp the cruise speed was last time overridden using DO_CHANGE_SPEED
 
 	MapProjection _reference_position{}; /**< Class used to project lat/lon setpoint into local frame. */
 	float _reference_altitude{NAN}; /**< Altitude relative to ground. */

src/modules/flight_mode_manager/tasks/AutoFollowTarget/follow_target_params.c

@@ -99,7 +99,7 @@ PARAM_DEFINE_FLOAT(FLW_TGT_FA, 180.0f);
  * to prevent terrain collisions due to GPS inaccuracies of the target.
  *
  * @value 0 2D Tracking: Maintain constant altitude relative to home and track XY position only
- * @value 1 2D + Terrain: Mantain constant altitude relative to terrain below and track XY position
+ * @value 1 2D + Terrain: Maintain constant altitude relative to terrain below and track XY position
  * @value 2 3D Tracking: Track target's altitude (be aware that GPS altitude bias usually makes this useless)
  * @group Follow target
  */

src/modules/flight_mode_manager/tasks/ManualAltitude/FlightTaskManualAltitude.hpp

@@ -85,7 +85,7 @@ protected:
 					(ParamFloat<px4::params::MPC_MAN_Y_TAU>) _param_mpc_man_y_tau,
 					(ParamFloat<px4::params::MPC_MAN_TILT_MAX>) _param_mpc_man_tilt_max, /**< maximum tilt allowed for manual flight */
 					(ParamFloat<px4::params::MPC_LAND_ALT1>) _param_mpc_land_alt1, /**< altitude at which to start downwards slowdown */
-					(ParamFloat<px4::params::MPC_LAND_ALT2>) _param_mpc_land_alt2, /**< altitude below wich to land with land speed */
+					(ParamFloat<px4::params::MPC_LAND_ALT2>) _param_mpc_land_alt2, /**< altitude below which to land with land speed */
 					(ParamFloat<px4::params::MPC_LAND_SPEED>)
 					_param_mpc_land_speed, /**< desired downwards speed when approaching the ground */
 					(ParamFloat<px4::params::MPC_TKO_SPEED>)

src/modules/flight_mode_manager/tasks/Orbit/FlightTaskOrbit.cpp

@@ -52,7 +52,7 @@ FlightTaskOrbit::FlightTaskOrbit()
 bool FlightTaskOrbit::applyCommandParameters(const vehicle_command_s &command)
 {
 	bool ret = true;
-	// save previous velocity and roatation direction
+	// save previous velocity and rotation direction
 	bool new_is_clockwise = _orbit_velocity > 0;
 	float new_radius = _orbit_radius;
 	float new_absolute_velocity = fabsf(_orbit_velocity);

src/modules/fw_autotune_attitude_control/fw_autotune_attitude_control_params.c

@@ -46,7 +46,7 @@
  * and can be dangerous. Only activate if you know what you
  * are doing, and in a safe environment.
  *
- * Any motion of the remote stick will abord the signal
+ * Any motion of the remote stick will abort the signal
  * injection and reset this parameter
  * Best is to perform the identification in position or
  * hold mode.

src/modules/fw_pos_control_l1/fw_pos_control_l1_params.c

@@ -76,7 +76,7 @@ PARAM_DEFINE_FLOAT(FW_L1_DAMPING, 0.75f);
 /**
  * L1 controller roll slew rate limit.
  *
- * The maxium change in roll angle setpoint per second.
+ * The maximum change in roll angle setpoint per second.
  *
  * @unit deg/s
  * @min 0
@@ -826,7 +826,7 @@ PARAM_DEFINE_FLOAT(FW_T_TAS_TC, 5.0f);
 PARAM_DEFINE_FLOAT(FW_GND_SPD_MIN, 5.0f);
 
 /**
- * RC stick configuraton fixed-wing.
+ * RC stick configuration fixed-wing.
  *
  * Set RC/joystick configuration for fixed-wing manual position and altitude controlled flight.
  *

src/modules/gyro_fft/CMSIS_5/CMSIS/DSP/Include/arm_math.h

@@ -7916,7 +7916,7 @@ typedef struct
   const float32_t *dualCoefficients;      /**< Dual coefficients */
   const float32_t *supportVectors;        /**< Support vectors */
   const int32_t   *classes;               /**< The two SVM classes */
-  float32_t       coef0;                  /**< Independant constant */
+  float32_t       coef0;                  /**< Independent constant */
   float32_t       gamma;                  /**< Gamma factor */
 } arm_svm_sigmoid_instance_f32;
 

src/modules/local_position_estimator/sensors/gps.cpp

@@ -210,7 +210,7 @@ void BlockLocalPositionEstimator::gpsCorrect()
 	// fault detection
 	float beta = (r.transpose() * (S_I * r))(0, 0);
 
-	// artifically increase beta threshhold to prevent fault during landing
+	// artificially increase beta threshhold to prevent fault during landing
 	float beta_thresh = 1e2f;
 
 	if (beta / BETA_TABLE[n_y_gps] > beta_thresh) {

src/modules/local_position_estimator/sensors/land.cpp

@@ -67,7 +67,7 @@ void BlockLocalPositionEstimator::landCorrect()
 	// fault detection
 	float beta = (r.transpose() * (S_I * r))(0, 0);
 
-	// artifically increase beta threshhold to prevent fault during landing
+	// artificially increase beta threshhold to prevent fault during landing
 	float beta_thresh = 1e2f;
 
 	if (beta / BETA_TABLE[n_y_land] > beta_thresh) {

src/modules/mavlink/mavlink_stream.h

@@ -129,7 +129,7 @@ protected:
 	virtual bool send() = 0;
 
 	/**
-	 * Function to collect/update data for the streams at a high rate independant of
+	 * Function to collect/update data for the streams at a high rate independent of
 	 * actual stream rate.
 	 *
 	 * This function is called at every iteration of the mavlink module.

src/modules/mavlink/module.yaml

@@ -167,7 +167,7 @@ parameters:
                 short: Enable serial flow control for instance ${i}
                 long: |
                     This is used to force flow control on or off for the the mavlink
-                    instance. By default it is auto detected. Use when auto detction fails.
+                    instance. By default it is auto detected. Use when auto detection fails.
 
             type: enum
             values:

src/modules/mc_att_control/mc_att_control_params.c

@@ -86,7 +86,7 @@ PARAM_DEFINE_FLOAT(MC_YAW_P, 2.8f);
  * in yaw compared to the other axes and it makes sense because yaw is not critical for
  * stable hovering or 3D navigation.
  *
- * For yaw control tuning use MC_YAW_P. This ratio has no inpact on the yaw gain.
+ * For yaw control tuning use MC_YAW_P. This ratio has no impact on the yaw gain.
  *
  * @min 0.0
  * @max 1.0

src/modules/mc_autotune_attitude_control/mc_autotune_attitude_control_params.c

@@ -54,7 +54,7 @@ PARAM_DEFINE_INT32(MC_AT_EN, 0);
  * and can be dangerous. Only activate if you know what you
  * are doing, and in a safe environment.
  *
- * Any motion of the remote stick will abord the signal
+ * Any motion of the remote stick will abort the signal
  * injection and reset this parameter
  * Best is to perform the identification in position or
  * hold mode.

src/modules/mc_pos_control/PositionControl/ControlMath.hpp

@@ -98,7 +98,7 @@ bool cross_sphere_line(const matrix::Vector3f &sphere_c, const float sphere_r, c
 
 /**
  * Adds e.g. feed-forward to the setpoint making sure existing or added NANs have no influence on control.
- * This function is udeful to support all the different setpoint combinations of position, velocity, acceleration with NAN representing an uncommited value.
+ * This function is udeful to support all the different setpoint combinations of position, velocity, acceleration with NAN representing an uncommitted value.
  * @param setpoint existing possibly NAN setpoint to add to
  * @param addition value/NAN to add to the setpoint
  */

src/modules/mc_pos_control/mc_pos_control_params.c

@@ -848,7 +848,7 @@ PARAM_DEFINE_INT32(MPC_YAW_MODE, 0);
 PARAM_DEFINE_FLOAT(SYS_VEHICLE_RESP, -0.4f);
 
 /**
- * Overall Horizonal Velocity Limit
+ * Overall Horizontal Velocity Limit
  *
  * If set to a value greater than zero, other parameters are automatically set (such as
  * MPC_XY_VEL_MAX or MPC_VEL_MANUAL).

src/modules/mc_rate_control/mc_rate_control_params.c

@@ -359,7 +359,7 @@ PARAM_DEFINE_FLOAT(MC_ACRO_EXPO_Y, 0.69f);
  * SuperExpo factor for refining the input curve shape tuned using MC_ACRO_EXPO.
  *
  * 0 Pure Expo function
- * 0.7 resonable shape enhancement for intuitive stick feel
+ * 0.7 reasonable shape enhancement for intuitive stick feel
  * 0.95 very strong bent input curve only near maxima have effect
  *
  * @min 0
@@ -375,7 +375,7 @@ PARAM_DEFINE_FLOAT(MC_ACRO_SUPEXPO, 0.7f);
  * SuperExpo factor for refining the input curve shape tuned using MC_ACRO_EXPO_Y.
  *
  * 0 Pure Expo function
- * 0.7 resonable shape enhancement for intuitive stick feel
+ * 0.7 reasonable shape enhancement for intuitive stick feel
  * 0.95 very strong bent input curve only near maxima have effect
  *
  * @min 0

src/modules/rc_update/params.c

@@ -1858,7 +1858,7 @@ PARAM_DEFINE_INT32(RC_MAP_PARAM3, 0);
 /**
  * Failsafe channel PWM threshold.
  *
- * Use RC_MAP_FAILSAFE to specify which channel is used to indicate RC loss via this theshold.
+ * Use RC_MAP_FAILSAFE to specify which channel is used to indicate RC loss via this threshold.
  * By default this is the throttle channel.
  *
  * Set to a PWM value slightly above the PWM value for the channel (e.g. throttle) in a failsafe event,

src/modules/sensors/sensor_params_flow.c

@@ -100,7 +100,7 @@ PARAM_DEFINE_FLOAT(SENS_FLOW_MAXR, 8.f);
  * Optical flow max rate.
  *
  * Optical flow data maximum publication rate. This is an upper bound,
- * actual optical flow data rate is still dependant on the sensor.
+ * actual optical flow data rate is still dependent on the sensor.
  *
  * @min 1
  * @max 200

src/modules/sensors/sensor_params_mag.c

@@ -82,7 +82,7 @@ PARAM_DEFINE_INT32(CAL_MAG_ROT_AUTO, 1);
  * Magnetometer max rate.
  *
  * Magnetometer data maximum publication rate. This is an upper bound,
- * actual magnetometer data rate is still dependant on the sensor.
+ * actual magnetometer data rate is still dependent on the sensor.
  *
  * @min 1
  * @max 200

src/modules/sensors/vehicle_air_data/params.c

@@ -45,7 +45,7 @@ PARAM_DEFINE_FLOAT(SENS_BARO_QNH, 1013.25f);
  * Baro max rate.
  *
  * Barometric air data maximum publication rate. This is an upper bound,
- * actual barometric data rate is still dependant on the sensor.
+ * actual barometric data rate is still dependent on the sensor.
  *
  * @min 1
  * @max 200

src/modules/sih/sih.cpp

@@ -562,7 +562,7 @@ void Sih::reconstruct_sensors_signals()
 	float altitude = (_H0 - _p_I(2)) + _baro_offset_m + generate_wgn() * 0.14f; // altitude with noise
 	_baro_p_mBar = CONSTANTS_STD_PRESSURE_MBAR *        // reconstructed pressure in mBar
 		       powf((1.0f + altitude * TEMP_GRADIENT / T1_K), -CONSTANTS_ONE_G / (TEMP_GRADIENT * CONSTANTS_AIR_GAS_CONST));
-	_baro_temp_c = T1_K + CONSTANTS_ABSOLUTE_NULL_CELSIUS + TEMP_GRADIENT * altitude; // reconstructed temperture in celcius
+	_baro_temp_c = T1_K + CONSTANTS_ABSOLUTE_NULL_CELSIUS + TEMP_GRADIENT * altitude; // reconstructed temperture in Celsius
 
 	// GPS
 	_gps_lat_noiseless = _LAT0 + degrees((double)_p_I(0) / CONSTANTS_RADIUS_OF_EARTH);

src/modules/sih/sih.hpp

@@ -159,7 +159,7 @@ private:
 
 	// hard constants
 	static constexpr uint16_t NB_MOTORS = 6;
-	static constexpr float T1_C = 15.0f;                        // ground temperature in celcius
+	static constexpr float T1_C = 15.0f;                        // ground temperature in Celsius
 	static constexpr float T1_K = T1_C - CONSTANTS_ABSOLUTE_NULL_CELSIUS;   // ground temperature in Kelvin
 	static constexpr float TEMP_GRADIENT  = -6.5f / 1000.0f;    // temperature gradient in degrees per metre
 	// Aerodynamic coefficients
@@ -281,14 +281,14 @@ private:
 	double      _gps_lon, _gps_lon_noiseless;
 	float       _gps_alt, _gps_alt_noiseless;
 	float       _baro_p_mBar;   // reconstructed (simulated) pressure in mBar
-	float       _baro_temp_c;   // reconstructed (simulated) barometer temperature in celcius
+	float       _baro_temp_c;   // reconstructed (simulated) barometer temperature in degrees Celsius
 
 	// parameters
 	float _MASS, _T_MAX, _Q_MAX, _L_ROLL, _L_PITCH, _KDV, _KDW, _H0, _T_TAU;
 	double _LAT0, _LON0, _COS_LAT0;
 	matrix::Vector3f _W_I;  // weight of the vehicle in inertial frame [N]
 	matrix::Matrix3f _I;    // vehicle inertia matrix
-	matrix::Matrix3f _Im1;  // inverse of the intertia matrix
+	matrix::Matrix3f _Im1;  // inverse of the inertia matrix
 	matrix::Vector3f _mu_I; // NED magnetic field in inertial frame [G]
 
 	int _gps_used;

src/modules/sih/sih_params.c

@@ -55,7 +55,7 @@ PARAM_DEFINE_FLOAT(SIH_MASS, 1.0f);
 /**
  * Vehicle inertia about X axis
  *
- * The intertia is a 3 by 3 symmetric matrix.
+ * The inertia is a 3 by 3 symmetric matrix.
  * It represents the difficulty of the vehicle to modify its angular rate.
  *
  * @unit kg m^2
@@ -69,7 +69,7 @@ PARAM_DEFINE_FLOAT(SIH_IXX, 0.025f);
 /**
  * Vehicle inertia about Y axis
  *
- * The intertia is a 3 by 3 symmetric matrix.
+ * The inertia is a 3 by 3 symmetric matrix.
  * It represents the difficulty of the vehicle to modify its angular rate.
  *
  * @unit kg m^2
@@ -83,7 +83,7 @@ PARAM_DEFINE_FLOAT(SIH_IYY, 0.025f);
 /**
  * Vehicle inertia about Z axis
  *
- * The intertia is a 3 by 3 symmetric matrix.
+ * The inertia is a 3 by 3 symmetric matrix.
  * It represents the difficulty of the vehicle to modify its angular rate.
  *
  * @unit kg m^2
@@ -97,7 +97,7 @@ PARAM_DEFINE_FLOAT(SIH_IZZ, 0.030f);
 /**
  * Vehicle cross term inertia xy
  *
- * The intertia is a 3 by 3 symmetric matrix.
+ * The inertia is a 3 by 3 symmetric matrix.
  * This value can be set to 0 for a quad symmetric about its center of mass.
  *
  * @unit kg m^2
@@ -110,7 +110,7 @@ PARAM_DEFINE_FLOAT(SIH_IXY, 0.0f);
 /**
  * Vehicle cross term inertia xz
  *
- * The intertia is a 3 by 3 symmetric matrix.
+ * The inertia is a 3 by 3 symmetric matrix.
  * This value can be set to 0 for a quad symmetric about its center of mass.
  *
  * @unit kg m^2
@@ -123,7 +123,7 @@ PARAM_DEFINE_FLOAT(SIH_IXZ, 0.0f);
 /**
  * Vehicle cross term inertia yz
  *
- * The intertia is a 3 by 3 symmetric matrix.
+ * The inertia is a 3 by 3 symmetric matrix.
  * This value can be set to 0 for a quad symmetric about its center of mass.
  *
  * @unit kg m^2
@@ -393,7 +393,7 @@ PARAM_DEFINE_FLOAT(SIH_MAG_OFFSET_Y,  0.0f);
 PARAM_DEFINE_FLOAT(SIH_MAG_OFFSET_Z,  0.0f);
 
 /**
- * distance sensor minimun range
+ * distance sensor minimum range
  *
  * @unit m
  * @min 0.0
@@ -405,7 +405,7 @@ PARAM_DEFINE_FLOAT(SIH_MAG_OFFSET_Z,  0.0f);
 PARAM_DEFINE_FLOAT(SIH_DISTSNSR_MIN, 0.0f);
 
 /**
- * distance sensor maximun range
+ * distance sensor maximum range
  *
  * @unit m
  * @min 0.0
@@ -417,7 +417,7 @@ PARAM_DEFINE_FLOAT(SIH_DISTSNSR_MIN, 0.0f);
 PARAM_DEFINE_FLOAT(SIH_DISTSNSR_MAX, 100.0f);
 
 /**
- * if >= 0 the distance sensor measures will be overrided by this value
+ * if >= 0 the distance sensor measures will be overridden by this value
  *
  * Absolute value superior to 10000 will disable distance sensor
  *

src/modules/temperature_compensation/temperature_calibration/polyfit.hpp

@@ -39,8 +39,8 @@ equation of the following form:
 yi = a0 + a1.xi + a2.xi^2 + a3.xi^3 + .... + an.xi^n + ei , where:
 
 i = [0,m]
-xi is the x coordinate (independant variable) of the i'th measurement
-yi is the y coordinate (dependant variable) of the i'th measurement
+xi is the x coordinate (independent variable) of the i'th measurement
+yi is the y coordinate (dependent variable) of the i'th measurement
 ei is a random fit error being the difference between the i'th y coordinate
    and the value predicted by the polynomial.
 

src/modules/vtol_att_control/standard_params.c

@@ -89,8 +89,8 @@ PARAM_DEFINE_FLOAT(VT_B_TRANS_RAMP, 3.0f);
 /**
  * Output on airbrakes channel during back transition
  *
- * Used for airbrakes or with ESCs that have reverse thrust enabled on a seperate channel
- * Airbrakes need to be enables for your selected model/mixer
+ * Used for airbrakes or with ESCs that have reverse thrust enabled on a separate channel.
+ * Airbrakes need to be enabled for your selected model/mixer.
  *
  * @min 0
  * @max 1

src/systemcmds/hardfault_log/hardfault_log.c

@@ -1214,16 +1214,16 @@ static void print_usage(void)
 
 
 	PRINT_MODULE_USAGE_NAME("hardfault_log", "command");
-	PRINT_MODULE_USAGE_COMMAND_DESCR("check", "Check if there's an uncommited hardfault");
-	PRINT_MODULE_USAGE_COMMAND_DESCR("rearm", "Drop an uncommited hardfault");
+	PRINT_MODULE_USAGE_COMMAND_DESCR("check", "Check if there's an uncommitted hardfault");
+	PRINT_MODULE_USAGE_COMMAND_DESCR("rearm", "Drop an uncommitted hardfault");
 
 	PRINT_MODULE_USAGE_COMMAND_DESCR("fault", "Generate a hardfault (this command crashes the system :)");
 	PRINT_MODULE_USAGE_ARG("0|1", "Hardfault type: 0=divide by 0, 1=Assertion (default=0)", true);
 
 	PRINT_MODULE_USAGE_COMMAND_DESCR("commit",
-					 "Write uncommited hardfault to /fs/microsd/fault_%i.txt (and rearm, but don't reset)");
+					 "Write uncommitted hardfault to /fs/microsd/fault_%i.txt (and rearm, but don't reset)");
 	PRINT_MODULE_USAGE_COMMAND_DESCR("count",
-					 "Read the reboot counter, counts the number of reboots of an uncommited hardfault (returned as the exit code of the program)");
+					 "Read the reboot counter, counts the number of reboots of an uncommitted hardfault (returned as the exit code of the program)");
 	PRINT_MODULE_USAGE_COMMAND_DESCR("reset", "Reset the reboot counter");
 }