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Spelling errors (#19935)

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This commit is contained in:
Hamish Willee
2022-07-27 14:33:16 +10:00
committed by GitHub
parent 97f632a408
commit e6eed43648
97 changed files with 170 additions and 158 deletions
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src/lib/airspeed/airspeed.cpp
+3 -3
View File
@@ -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
+4 -4
View File
@@ -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,