From f8d5b09b5666ad5ffdbf411eddbe5a21453cc938 Mon Sep 17 00:00:00 2001
From: Silvan Fuhrer <silvan@auterion.com>
Date: Mon, 5 Oct 2020 11:15:55 +0200
Subject: [PATCH] airspeed: remove duplicated comments from cpp (they should
 only be in header)

Signed-off-by: Silvan Fuhrer <silvan@auterion.com>
---
 src/lib/airspeed/airspeed.cpp | 59 -----------------------------------
 1 file changed, 59 deletions(-)

diff --git a/src/lib/airspeed/airspeed.cpp b/src/lib/airspeed/airspeed.cpp
index 3d15233a87..5a10c6e4fb 100644
--- a/src/lib/airspeed/airspeed.cpp
+++ b/src/lib/airspeed/airspeed.cpp
@@ -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);