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airspeed: remove duplicated comments from cpp (they should only be in header)

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Signed-off-by: Silvan Fuhrer <silvan@auterion.com>
This commit is contained in:
Silvan Fuhrer
2020-10-05 11:15:55 +02:00
parent f01c4e769f
commit f8d5b09b56
1 changed files with 0 additions and 59 deletions
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src/lib/airspeed/airspeed.cpp
-59
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@@ -45,16 +45,6 @@
#include <px4_platform_common/defines.h>
#include <lib/ecl/geo/geo.h>
/**
* Calculate indicated airspeed.
*
* Note that the indicated airspeed is not the true airspeed because it
* lacks the air density compensation. Use the calc_true_airspeed functions to get
* the true airspeed.
*
* @param differential_pressure total_ pressure - static pressure
* @return indicated airspeed in m/s
*/
float calc_IAS_corrected(enum AIRSPEED_COMPENSATION_MODEL pmodel, enum AIRSPEED_SENSOR_MODEL smodel,
float tube_len, float tube_dia_mm, float differential_pressure, float pressure_ambient, float temperature_celsius)
{
@@ -185,15 +175,6 @@ float calc_IAS_corrected(enum AIRSPEED_COMPENSATION_MODEL pmodel, enum AIRSPEED_
return (differential_pressure > 0.0f) ? airspeed_corrected : -airspeed_corrected;
}
/**
* Calculate indicated airspeed (IAS).
*
* Note that the indicated airspeed is not the true airspeed because it
* lacks the air density and instrument error compensation.
*
* @param differential_pressure total_ pressure - static pressure
* @return IAS in m/s
*/
float calc_IAS(float differential_pressure)
{
if (differential_pressure > 0.0f) {
@@ -205,16 +186,6 @@ float calc_IAS(float differential_pressure)
}
/**
* Calculate true airspeed (TAS) from equivalent airspeed (EAS).
*
* Note that the true airspeed is NOT the groundspeed, because of the effects of wind
*
* @param speed_equivalent current equivalent airspeed
* @param pressure_ambient pressure at the side of the tube/airplane
* @param temperature_celsius air temperature in degrees celcius
* @return TAS in m/s
*/
float calc_TAS_from_EAS(float speed_equivalent, float pressure_ambient, float temperature_celsius)
{
if (!PX4_ISFINITE(temperature_celsius)) {
@@ -225,31 +196,11 @@ float calc_TAS_from_EAS(float speed_equivalent, float pressure_ambient, float te
temperature_celsius));
}
/**
* Calculate equivalent airspeed (EAS) from indicated airspeed (IAS).
* Note that we neglect the conversion from CAS (calibrated airspeed) to EAS.
*
* @param speed_indicated current indicated airspeed
* @param scale scale from IAS to CAS (accounting for instrument and pitot position erros)
* @return EAS in m/s
*/
float calc_EAS_from_IAS(float speed_indicated, float scale)
{
return speed_indicated * scale;
}
/**
* Directly calculate true airspeed (TAS)
*
* Here we assume to have no instrument or pitot position error (IAS = CAS),
* and neglect the CAS to EAS conversion (CAS = EAS).
* Note that the true airspeed is NOT the groundspeed, because of the effects of wind.
*
* @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
* @return true airspeed in m/s
*/
float calc_TAS(float total_pressure, float static_pressure, float temperature_celsius)
{
float density = get_air_density(static_pressure, temperature_celsius);
@@ -277,16 +228,6 @@ float get_air_density(float static_pressure, float temperature_celsius)
return static_pressure / (CONSTANTS_AIR_GAS_CONST * (temperature_celsius - CONSTANTS_ABSOLUTE_NULL_CELSIUS));
}
/**
* Calculate equivalent airspeed (EAS) from true airspeed (TAS).
* It is the inverse function to calc_TAS_from_EAS()
*
*
* @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
* @return EAS in m/s
*/
float calc_EAS_from_TAS(float speed_true, float pressure_ambient, float temperature_celsius)
{
return speed_true * sqrtf(get_air_density(pressure_ambient, temperature_celsius) / CONSTANTS_AIR_DENSITY_SEA_LEVEL_15C);