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new library for atmosphere calculations

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Signed-off-by: RomanBapst <bapstroman@gmail.com>
This commit is contained in:
Roman Bapst
2023-10-21 19:25:45 +02:00
committed by GitHub
parent f120ebcdc0
commit ecb78ca207
10 changed files with 341 additions and 57 deletions
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src/lib/airspeed/airspeed.cpp
+6 -24
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@@ -44,6 +44,9 @@
#include <px4_platform_common/defines.h>
#include <lib/geo/geo.h>
#include <lib/atmosphere/atmosphere.h>
using atmosphere::getDensityFromPressureAndTemp;
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)
@@ -53,7 +56,7 @@ float calc_IAS_corrected(enum AIRSPEED_COMPENSATION_MODEL pmodel, enum AIRSPEED_
}
// air density in kg/m3
const float rho_air = get_air_density(pressure_ambient, temperature_celsius);
const float rho_air = getDensityFromPressureAndTemp(pressure_ambient, temperature_celsius);
const float dp = fabsf(differential_pressure);
float dp_tot = dp;
@@ -153,18 +156,6 @@ float calc_IAS_corrected(enum AIRSPEED_COMPENSATION_MODEL pmodel, enum AIRSPEED_
break;
}
// if (!PX4_ISFINITE(dp_tube)) {
// dp_tube = 0.0f;
// }
// if (!PX4_ISFINITE(dp_pitot)) {
// dp_pitot = 0.0f;
// }
// if (!PX4_ISFINITE(dv)) {
// dv = 0.0f;
// }
// computed airspeed without correction for inflow-speed at tip of pitot-tube
const float airspeed_uncorrected = sqrtf(2.0f * dp_tot / CONSTANTS_AIR_DENSITY_SEA_LEVEL_15C);
@@ -192,7 +183,7 @@ float calc_TAS_from_CAS(float speed_calibrated, float pressure_ambient, float te
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,
return speed_calibrated * sqrtf(CONSTANTS_AIR_DENSITY_SEA_LEVEL_15C / getDensityFromPressureAndTemp(pressure_ambient,
temperature_celsius));
}
@@ -203,7 +194,7 @@ float calc_CAS_from_IAS(float speed_indicated, float scale)
float calc_TAS(float total_pressure, float static_pressure, float temperature_celsius)
{
float density = get_air_density(static_pressure, temperature_celsius);
float density = getDensityFromPressureAndTemp(static_pressure, temperature_celsius);
if (density < 0.0001f || !PX4_ISFINITE(density)) {
density = CONSTANTS_AIR_DENSITY_SEA_LEVEL_15C;
@@ -219,15 +210,6 @@ 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 Celsius
}
return static_pressure / (CONSTANTS_AIR_GAS_CONST * (temperature_celsius - CONSTANTS_ABSOLUTE_NULL_CELSIUS));
}
float calc_calibrated_from_true_airspeed(float speed_true, float air_density)
{
return speed_true * sqrtf(air_density / CONSTANTS_AIR_DENSITY_SEA_LEVEL_15C);