Classes
struct	AerodynamicCoeff

Functions
float	relAltitude (float pressure, float pressureRef=Constants::MSL_PRESSURE, float temperatureRef=Constants::MSL_TEMPERATURE)
	Returns the altitude given the pressure with respect to a reference pressure and temperature, using International Standard Atmosphere model.

float	relPressure (float altitude, float pressureRef=Constants::MSL_PRESSURE, float temperatureRef=Constants::MSL_TEMPERATURE)
	Returns the pressure given the altitude with respect to a reference pressure and temperature, using International Standard Atmosphere model.

float	relTemperature (float altitude, float temperatureRef=Constants::MSL_TEMPERATURE)
	Returns the temperature at the given altitude with respect to the reference temperature.

float	relDensity (float pressure, float pressureRef=Constants::MSL_PRESSURE, float altitudeRef=0, float temperatureRef=Constants::MSL_TEMPERATURE)
	Returns the air density given the pressure with respect to a reference pressure, altitude and temperature, using the International Standard Atmosphere model.

float	mslPressure (float pressureRef, float temperatureRef, float altitudeRef)
	Returns the expected pressure at mean sea level based on temperature and pressure at a reference altitude, using International Standard Atmosphere model.

float	mslTemperature (float temperatureRef, float altitudeRef)
	Returns the expected temperature at mean sea level based on temperature at a reference altitude, using International Standard Atmosphere model.

float	verticalSpeed (float p, float dpDt, float pRef, float tRef)

Vector2f	geodetic2NED (const Vector2f &target, const Vector2f &origin)

float	computeRho (float d, float t0)
	Computes the rho (air density) of air at the given altitude.

float	computeSoundSpeed (float d, float t0)
	Computes the speed of sound at the given altitude.

float	computeMach (float d, float vtot, float t0)
	Computes the mach relative to the speed at a certain altitude.

float	computePitotMach (float pressureTotal, float pressureStatic)
	Computes the mach from total and static pressure measures from a pitot tube.

float	computePitotAirspeed (float pressureTotal, float pressureStatic, float d, float t0)
	Computes air speed relative to the pitot tube.

float	computeCd (const AerodynamicCoeff &coeff, float mach)
	Computes the CD from aerodynamic coefficients and mach.

Eigen::Vector2f	geodetic2NED (const Eigen::Vector2f &target, const Eigen::Vector2f &origin)
	Converts decimal degrees of latitude and longitude into displacement in meters between two positions the with an ellipsoidal earth model.

Function Documentation

◆ computeCd()

float Boardcore::Aeroutils::computeCd	(	const AerodynamicCoeff &	coeff,
		float	mach )

Computes the CD from aerodynamic coefficients and mach.

Parameters

coeff	Aerodynamic coefficients.
mach	Mach value.

Returns: The computed CD.

Definition at line 122 of file AeroUtils.cpp.

◆ computeMach()

float Boardcore::Aeroutils::computeMach	(	float	d,
		float	vtot,
		float	t0 )

Computes the mach relative to the speed at a certain altitude.

Parameters

d	Altitude agl in NED frame [m].
vtot	Total speed [m/s].
t0	Temperature at ground level [K].

Returns: The mach relative to the speed at a certain altitude.

Definition at line 101 of file AeroUtils.cpp.

◆ computePitotAirspeed()

float Boardcore::Aeroutils::computePitotAirspeed	(	float	pressureTotal,
		float	pressureStatic,
		float	d,
		float	t0 )

Computes air speed relative to the pitot tube.

Parameters

pressureTotal	Total pressure from the pitot tube [Pa].
pressureStatic	Static pressure from the pitot tube [Pa].
d	Altitude agl in NED frame [m].
t0	Temperature at ground level [K].

Returns: Calculated airspeed [m/s].

Definition at line 114 of file AeroUtils.cpp.

◆ computePitotMach()

float Boardcore::Aeroutils::computePitotMach	(	float	pressureTotal,
		float	pressureStatic )

Computes the mach from total and static pressure measures from a pitot tube.

Parameters

pressureTotal	Total pressure from the pitot tube [Pa].
pressureStatic	Static pressure from the pitot tube [Pa].

Returns: Calculated mach.

Definition at line 106 of file AeroUtils.cpp.

◆ computeRho()

float Boardcore::Aeroutils::computeRho	(	float	d,
		float	t0 )

Computes the rho (air density) of air at the given altitude.

Parameters

d	Altitude agl in NED frame [m].
t0	Temperature at ground level [K].

Returns: The air density at the given altitude [kg/m^3].

Definition at line 86 of file AeroUtils.cpp.

◆ computeSoundSpeed()

float Boardcore::Aeroutils::computeSoundSpeed	(	float	d,
		float	t0 )

Computes the speed of sound at the given altitude.

Parameters

d	Altitude agl in NED frame [m].
t0	Temperature at ground level [K].

Returns: The speed of sound at the given altitude [m/s].

Definition at line 94 of file AeroUtils.cpp.

◆ geodetic2NED() [1/2]

Eigen::Vector2f Boardcore::Aeroutils::geodetic2NED	(	const Eigen::Vector2f &	target,
		const Eigen::Vector2f &	origin )

Converts decimal degrees of latitude and longitude into displacement in meters between two positions the with an ellipsoidal earth model.

Parameters

target	Coordinates of target position [lat lon][deg]
origin	Coordinates of the Initial position used as the origin of the NED frame [lat lon][deg]

Returns: Target NED position with respect to the origin coordinates [n e][m]

◆ geodetic2NED() [2/2]

Vector2f Boardcore::Aeroutils::geodetic2NED	(	const Vector2f &	target,
		const Vector2f &	origin )

Definition at line 74 of file AeroUtils.cpp.

◆ mslPressure()

float Boardcore::Aeroutils::mslPressure	(	float	pressureRef,
		float	temperatureRef,
		float	altitudeRef )

Returns the expected pressure at mean sea level based on temperature and pressure at a reference altitude, using International Standard Atmosphere model.

Warning: This function is valid for altitudes below 11000 meters above sea level

Parameters

pressureRef	Pressure at reference altitude [Pa]
temperatureRef	Temperature at reference altitude. Must be > 0 [K]
altitudeRef	Reference altitude [m]

Returns: Pressure at mean sea level [Pa]

Definition at line 58 of file AeroUtils.cpp.

◆ mslTemperature()

float Boardcore::Aeroutils::mslTemperature	(	float	temperatureRef,
		float	altitudeRef )

Returns the expected temperature at mean sea level based on temperature at a reference altitude, using International Standard Atmosphere model.

Warning: This function is valid for altitudes below 11000 meters above sea level.

Parameters

temperatureRef	Temperature at reference altitude [K]
altitudeRef	Reference altitude [m]

Returns: Temperature at mean sea level [K]

Definition at line 64 of file AeroUtils.cpp.

◆ relAltitude()

float Boardcore::Aeroutils::relAltitude	(	float	pressure,
		float	pressureRef = Constants::MSL_PRESSURE,
		float	temperatureRef = Constants::MSL_TEMPERATURE )

Returns the altitude given the pressure with respect to a reference pressure and temperature, using International Standard Atmosphere model.

Warning: This function is valid for altitudes below 11000 meters above sea level.; This function provides a relative altitude from the altitude where the reference pressure and temperature were measured. It does not provide altitude above mean sea level unless the reference is, in fact, the sea level.

This means that if the reference pressure and temperature are those at mean sea level, then the returned altitude is from mean sea level. Otherwise if the reference pressure and temperature are those form the launchpad, then the returned altitude is from above ground level.

Parameters

pressure	Current absolute pressure [Pa]
pressureRef	Pressure at reference altitude (must be > 0) [Pa]
temperatureRef	Temperature at reference altitude [K]

Returns: Current altitude with respect to the reference altitude [m]

Definition at line 36 of file AeroUtils.cpp.

◆ relDensity()

float Boardcore::Aeroutils::relDensity	(	float	pressure,
		float	pressureRef = Constants::MSL_PRESSURE,
		float	altitudeRef = 0,
		float	temperatureRef = Constants::MSL_TEMPERATURE )

Returns the air density given the pressure with respect to a reference pressure, altitude and temperature, using the International Standard Atmosphere model.

Warning: This function is valid for altitudes below 11000 meters above sea level.

Parameters

pressure	Current atmospheric pressure [Pa]
pressureRef	Pressure at reference altitude (must be > 0) [Pa]
altitudeRef	Reference altitude [m]
temperatureRef	Temperature at reference altitude [K]

Returns: Current air density [Kg/m^3]

Definition at line 51 of file AeroUtils.cpp.

◆ relPressure()

float Boardcore::Aeroutils::relPressure	(	float	altitude,
		float	pressureRef = Constants::MSL_PRESSURE,
		float	temperatureRef = Constants::MSL_TEMPERATURE )

Returns the pressure given the altitude with respect to a reference pressure and temperature, using International Standard Atmosphere model.

Warning: This function is valid for altitudes below 11000 meters above sea level.; This function provides a relative pressure at the given altitude relative to the altitude where the reference pressure and temperature were measured. It does not provide altitude above mean sea level unless the reference is, in fact, the sea level.

This means that if the reference pressure and temperature are those at mean sea level, then the returned pressure is from mean sea level. Otherwise if the reference pressure and temperature are those form the launchpad, then the returned pressure is from above ground level.

Parameters

altitude	Current relative altitude wrt the altitude of the reference pressure and temperature [m]
pressureRef	Pressure at reference altitude (must be > 0) [Pa]
temperatureRef	Temperature at reference altitude [K]

Returns: Current pressure at the given altitude wrt the reference altitude [m]

Definition at line 41 of file AeroUtils.cpp.

◆ relTemperature()

float Boardcore::Aeroutils::relTemperature	(	float	altitude,
		float	temperatureRef = Constants::MSL_TEMPERATURE )

Returns the temperature at the given altitude with respect to the reference temperature.

Warning: This function is valid for altitudes below 11000 meters above sea level.; This function provides a relative temperature from the altitude where the reference temperature is measured. It does not provide temperature above mean sea level unless the reference is, in fact, measured at the sea level.

This means that if the reference temperature is that at mean sea level, then the returned temperature is that at the given altitude from mean sea level. Otherwise if the reference temperature is that form the launchpad, then the returned temperature is that at the given altitude from above ground level.

Parameters

altitude	Current relative altitude wrt the altitude of the reference pressure [m]
temperatureRef	Temperature at reference altitude [K]

Returns: Current temperature at the given altitude wrt the reference altitude [m]

Definition at line 46 of file AeroUtils.cpp.

◆ verticalSpeed()

float Boardcore::Aeroutils::verticalSpeed	(	float	p,
		float	dpDt,
		float	pRef,
		float	tRef )

Returns the vertical speed (or rate of climb) of the rocket, assuming an International Standard Atmosphere model.

Warning: This function is valid for altitudes below 11000 meters above sea level

Parameters

p	Current pressure (must be > 0) [Pa]
dpDt	Rate of change of pressure [Pa/s]
pRef	Reference pressure (must be > 0) [Pa]
tRef	Reference temperature [K]

Returns: Vertical speed, positive upwards [m/s]

Definition at line 69 of file AeroUtils.cpp.

Classes

Functions

Function Documentation

◆ computeCd()

◆ computeMach()

◆ computePitotAirspeed()

◆ computePitotMach()

◆ computeRho()

◆ computeSoundSpeed()

◆ geodetic2NED() [1/2]

◆ geodetic2NED() [2/2]

◆ mslPressure()

◆ mslTemperature()

◆ relAltitude()

◆ relDensity()

◆ relPressure()

◆ relTemperature()

◆ verticalSpeed()