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a5cc4bcd08
Update the model for the standard configuration based on the model from Sensirion and add also an option to do the tube pressure loss correction from Sensirion for other configurations.
125 lines
4.4 KiB
C
125 lines
4.4 KiB
C
/****************************************************************************
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*
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* Copyright (c) 2012-2013, 2017 PX4 Development Team. All rights reserved.
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*
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* Redistribution and use in source and binary forms, with or without
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* modification, are permitted provided that the following conditions
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* are met:
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*
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* 1. Redistributions of source code must retain the above copyright
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* notice, this list of conditions and the following disclaimer.
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* 2. Redistributions in binary form must reproduce the above copyright
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* notice, this list of conditions and the following disclaimer in
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* the documentation and/or other materials provided with the
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* distribution.
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* 3. Neither the name PX4 nor the names of its contributors may be
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* used to endorse or promote products derived from this software
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* without specific prior written permission.
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*
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* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
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* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
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* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
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* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
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* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
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* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
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* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
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* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
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* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
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* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
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* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
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* POSSIBILITY OF SUCH DAMAGE.
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*
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****************************************************************************/
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/**
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* @file airspeed.h
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* Airspeed estimation declarations
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*
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* @author Lorenz Meier <lorenz@px4.io>
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*
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*/
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#ifndef AIRSPEED_H_
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#define AIRSPEED_H_
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#include "math.h"
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#include "conversions.h"
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__BEGIN_DECLS
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enum AIRSPEED_SENSOR_MODEL {
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AIRSPEED_SENSOR_MODEL_MEMBRANE = 0,
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AIRSPEED_SENSOR_MODEL_SDP3X,
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};
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enum AIRSPEED_COMPENSATION_MODEL {
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AIRSPEED_COMPENSATION_MODEL_PITOT = 0,
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AIRSPEED_COMPENSATION_MODEL_NO_PITOT = 1,
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AIRSPEED_COMPENSATION_TUBE_PRESSURE_LOSS = 2
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};
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/**
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* Calculate indicated airspeed.
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*
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* Note that the indicated airspeed is not the true airspeed because it
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* lacks the air density compensation. Use the calc_true_airspeed functions to get
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* the true airspeed.
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*
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* @param total_pressure pressure inside the pitot/prandtl tube
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* @param static_pressure pressure at the side of the tube/airplane
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* @return indicated airspeed in m/s
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*/
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__EXPORT float calc_indicated_airspeed_corrected(enum AIRSPEED_COMPENSATION_MODEL pmodel,
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enum AIRSPEED_SENSOR_MODEL smodel,
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float tube_len, float tube_dia_mm, float differential_pressure, float pressure_ambient, float temperature_celsius);
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/**
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* Calculate indicated airspeed.
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*
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* Note that the indicated airspeed is not the true airspeed because it
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* lacks the air density compensation. Use the calc_true_airspeed functions to get
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* the true airspeed.
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*
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* @param total_pressure pressure inside the pitot/prandtl tube
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* @param static_pressure pressure at the side of the tube/airplane
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* @return indicated airspeed in m/s
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*/
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__EXPORT float calc_indicated_airspeed(float differential_pressure);
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/**
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* Calculate true airspeed from indicated airspeed.
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*
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* Note that the true airspeed is NOT the groundspeed, because of the effects of wind
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*
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* @param speed_indicated current indicated airspeed
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* @param pressure_ambient pressure at the side of the tube/airplane
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* @param temperature_celsius air temperature in degrees celcius
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* @return true airspeed in m/s
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*/
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__EXPORT float calc_true_airspeed_from_indicated(float speed_indicated, float pressure_ambient,
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float temperature_celsius);
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/**
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* Directly calculate true airspeed
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*
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* Note that the true airspeed is NOT the groundspeed, because of the effects of wind
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*
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* @param total_pressure pressure inside the pitot/prandtl tube
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* @param static_pressure pressure at the side of the tube/airplane
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* @param temperature_celsius air temperature in degrees celcius
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* @return true airspeed in m/s
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*/
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__EXPORT float calc_true_airspeed(float total_pressure, float static_pressure, float temperature_celsius);
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/**
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* Calculates air density.
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*
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* @param static_pressure ambient pressure in millibar
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* @param temperature_celcius air / ambient temperature in celcius
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*/
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__EXPORT float get_air_density(float static_pressure, float temperature_celsius);
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__END_DECLS
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#endif
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