AeroUtils.h

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/* Copyright (c) 2019-2023 Skyward Experimental Rocketry
 * Authors: Luca Erbetta, Emilio Corigliano
 *
 * Permission is hereby granted, free of charge, to any person obtaining a copy
 * of this software and associated documentation files (the "Software"), to deal
 * in the Software without restriction, including without limitation the rights
 * to use, copy, modify, merge, publish, distribute, sublicense, and/or sell
 * copies of the Software, and to permit persons to whom the Software is
 * furnished to do so, subject to the following conditions:
 *
 * The above copyright notice and this permission notice shall be included in
 * all copies or substantial portions of the Software.
 *
 * THE SOFTWARE IS PROVIDED "AS IS", WITHOUT WARRANTY OF ANY KIND, EXPRESS OR
 * IMPLIED, INCLUDING BUT NOT LIMITED TO THE WARRANTIES OF MERCHANTABILITY,
 * FITNESS FOR A PARTICULAR PURPOSE AND NONINFRINGEMENT. IN NO EVENT SHALL THE
 * AUTHORS OR COPYRIGHT HOLDERS BE LIABLE FOR ANY CLAIM, DAMAGES OR OTHER
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 * THE SOFTWARE.
 */
 
#pragma once
 
#include <utils/Constants.h>
 
#include <Eigen/Core>
#include <cmath>
 
namespace Boardcore
{
 
namespace Aeroutils
{
 
float relAltitude(float pressure, float pressureRef = Constants::MSL_PRESSURE,
                  float temperatureRef = Constants::MSL_TEMPERATURE);
 
float relPressure(float altitude, float pressureRef = Constants::MSL_PRESSURE,
                  float temperatureRef = Constants::MSL_TEMPERATURE);
 
float relTemperature(float altitude,
                     float temperatureRef = Constants::MSL_TEMPERATURE);
 
float relDensity(float pressure, float pressureRef = Constants::MSL_PRESSURE,
                 float altitudeRef    = 0,
                 float temperatureRef = Constants::MSL_TEMPERATURE);
 
float mslPressure(float pressureRef, float temperatureRef, float altitudeRef);
 
float mslTemperature(float temperatureRef, float altitudeRef);
 
float verticalSpeed(float p, float dpDt, float pRef, float tRef);
 
Eigen::Vector2f geodetic2NED(const Eigen::Vector2f& target,
                             const Eigen::Vector2f& origin);
 
float computeRho(float d, float t0);
 
float computeSoundSpeed(float d, float t0);
 
float computeMach(float d, float vtot, float t0);
 
float computePitotMach(float pressureTotal, float pressureStatic);
 
float computePitotAirspeed(float pressureTotal, float pressureStatic, float d,
                           float t0);
 
struct AerodynamicCoeff
{
    float n000, n100, n200, n300, n400, n500, n600;
};
 
float computeCd(const AerodynamicCoeff& coeff, float mach);
 
}  // namespace Aeroutils
 
}  // namespace Boardcore