Files
PX4-Autopilot/src/lib/atmosphere/atmosphere.cpp
T
Roman Bapst ecb78ca207 new library for atmosphere calculations
Signed-off-by: RomanBapst <bapstroman@gmail.com>
2023-10-21 12:25:45 -05:00

81 lines
3.2 KiB
C++

/****************************************************************************
*
* Copyright (C) 2023 PX4 Development Team. All rights reserved.
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
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* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
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****************************************************************************/
/**
* @file atmosphere.cpp
*
*/
#include <geo/geo.h>
#include "atmosphere.h"
namespace atmosphere
{
static constexpr float kTempRefKelvin = 15.f - CONSTANTS_ABSOLUTE_NULL_CELSIUS; // temperature at base height in Kelvin
static constexpr float kTempGradient = -6.5f / 1000.f; // temperature gradient in degrees per meter
static constexpr float kPressRefSeaLevelPa = 101325.f; // pressure at sea level in Pa
float getDensityFromPressureAndTemp(const float pressure_pa, const float temperature_celsius)
{
return (pressure_pa / (CONSTANTS_AIR_GAS_CONST * (temperature_celsius - CONSTANTS_ABSOLUTE_NULL_CELSIUS)));
}
float getPressureFromAltitude(const float altitude_m)
{
return kPressRefSeaLevelPa * powf((altitude_m * kTempGradient + kTempRefKelvin) / kTempRefKelvin,
-CONSTANTS_ONE_G / (kTempGradient * CONSTANTS_AIR_GAS_CONST));
}
float getAltitudeFromPressure(float pressure_pa, float pressure_sealevel_pa)
{
// calculate altitude using the hypsometric equation
const float pressure_ratio = pressure_pa / pressure_sealevel_pa;
/*
* Solve:
*
* / -(aR / g) \
* | (p / p1) . T1 | - T1
* \ /
* h = ------------------------------- + h1
* a
*/
return (((powf(pressure_ratio, (-(kTempGradient * CONSTANTS_AIR_GAS_CONST) / CONSTANTS_ONE_G))) * kTempRefKelvin) -
kTempRefKelvin) / kTempGradient;
}
float getStandardTemperatureAtAltitude(float altitude_m)
{
return 15.0f + kTempGradient * altitude_m;
}
}