airspeed.h

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/**
 * @file airspeed.h
 * Airspeed estimation declarations
 *
 * @author Lorenz Meier <lorenz@px4.io>
 *
 */

#ifndef AIRSPEED_H_
#define AIRSPEED_H_

#include "math.h"

__BEGIN_DECLS

enum AIRSPEED_SENSOR_MODEL {
    AIRSPEED_SENSOR_MODEL_MEMBRANE = 0,
    AIRSPEED_SENSOR_MODEL_SDP3X,
};

enum AIRSPEED_COMPENSATION_MODEL {
    AIRSPEED_COMPENSATION_MODEL_PITOT = 0,
    AIRSPEED_COMPENSATION_MODEL_NO_PITOT = 1,
    AIRSPEED_COMPENSATION_TUBE_PRESSURE_LOSS = 2
};

/**
 * Calculate indicated airspeed (IAS).
 *
 * 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 total_pressure pressure inside the pitot/prandtl tube
 * @param static_pressure pressure at the side of the tube/airplane
 * @return indicated airspeed in m/s
 */
__EXPORT 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);

/**
 * Calculate indicated airspeed (IAS).
 *
 * 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 total_pressure pressure inside the pitot/prandtl tube
 * @param static_pressure pressure at the side of the tube/airplane
 * @return indicated airspeed in m/s
 */
__EXPORT 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
 */
__EXPORT float calc_TAS_from_EAS(float speed_indicated, float pressure_ambient,
                 float 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
 */
__EXPORT float calc_EAS_from_IAS(float speed_indicated, float 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
 */
__EXPORT float calc_TAS(float total_pressure, float static_pressure, float temperature_celsius);

/**
* Calculates air density.
*
* @param static_pressure ambient pressure in millibar
* @param temperature_celcius air / ambient temperature in celcius
*/
__EXPORT float get_air_density(float static_pressure, float temperature_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
 */
__EXPORT float calc_EAS_from_TAS(float speed_true, float pressure_ambient,
                 float temperature_celsius);

__END_DECLS

#endif