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https://bitbucket.org/librepilot/librepilot.git
synced 2025-03-21 13:28:58 +01:00
Brought out several air parameter functions from IL2 simulator and added them to the global simulator.cpp file.
This commit is contained in:
Laura Sebesta
parent
5e785d4524
commit
b84b8f656c
@ -42,7 +42,7 @@
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* can be found shipped with IL2 in the file DeviceLink.txt
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*
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* id's used in this file:
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* 30: IAS in km/h (float)
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* 30: CAS in km/h (float)
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* 32: vario in m/s (float)
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* 38: angular speed °/s (float) (which direction? azimuth?)
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* 40: barometric alt in m (float)
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@ -68,25 +68,20 @@
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#include <math.h>
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#include <qxtlogger.h>
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const float IL2Simulator::FT2M = 0.3048;
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const float IL2Simulator::FT2M = 12*.254;
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const float IL2Simulator::KT2MPS = 0.514444444;
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const float IL2Simulator::MPS2KMH = 3.6;
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const float IL2Simulator::KMH2MPS = (1.0/3.6);
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const float IL2Simulator::INHG2KPA = 3.386;
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const float IL2Simulator::RAD2DEG = (180.0/M_PI);
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const float IL2Simulator::DEG2RAD = (M_PI/180.0);
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const float IL2Simulator::M2DEG = 60.*1852.; // 60 miles per degree times 1852 meters per mile
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const float IL2Simulator::DEG2M = (1.0/(60.*1852.));
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const float IL2Simulator::AIR_CONST = 287.058; // J/(kg*K)
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const float IL2Simulator::GROUNDDENSITY = 1.225; // kg/m³ ;)
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const float IL2Simulator::TEMP_GROUND = (15.0 + 273.0); // 15°C in Kelvin
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const float IL2Simulator::TEMP_LAPSE_RATE = -0.0065; //degrees per meter
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const float IL2Simulator::AIR_CONST_FACTOR = -0.0341631947363104; //several nature constants calculated into one
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const float IL2Simulator::NM2DEG = 60.*1852.; // 60 miles per degree times 1852 meters per mile
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const float IL2Simulator::DEG2NM = (1.0/(60.*1852.));
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IL2Simulator::IL2Simulator(const SimulatorSettings& params) :
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Simulator(params)
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{
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airParameters=getAirParameters();
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}
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@ -125,31 +120,6 @@ void IL2Simulator::transmitUpdate()
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}
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/**
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* calculate air density from altitude
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*/
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float IL2Simulator::DENSITY(float alt) {
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return (GROUNDDENSITY * pow(
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((TEMP_GROUND+(TEMP_LAPSE_RATE*alt))/TEMP_GROUND),
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((AIR_CONST_FACTOR/TEMP_LAPSE_RATE)-1) )
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);
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}
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/**
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* calculate air pressure from altitude
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*/
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float IL2Simulator::PRESSURE(float alt) {
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return DENSITY(alt)*(TEMP_GROUND+(alt*TEMP_LAPSE_RATE))*AIR_CONST;
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}
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/**
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* calculate TAS from IAS and altitude
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*/
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float IL2Simulator::TAS(float IAS, float alt) {
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return (IAS*sqrt(GROUNDDENSITY/DENSITY(alt)));
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}
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/**
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* process data string from flight simulator
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*/
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@ -171,7 +141,7 @@ void IL2Simulator::processUpdate(const QByteArray& inp)
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float value = values[1].toFloat();
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switch (id) {
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case 30:
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current.ias=value * KMH2MPS;
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current.cas=value * KMH2MPS;
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break;
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case 32:
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current.dZ=value;
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@ -206,8 +176,9 @@ void IL2Simulator::processUpdate(const QByteArray& inp)
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old.ddX=0;
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}
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// calculate TAS from alt and IAS
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current.tas = TAS(current.ias,current.Z);
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// calculate TAS from alt and CAS
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float gravity =9.805;
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current.tas = cas2tas(current.cas, current.Z, airParameters, gravity);
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// assume the plane actually flies straight and no wind
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// groundspeed is horizontal vector of TAS
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@ -269,7 +240,8 @@ void IL2Simulator::processUpdate(const QByteArray& inp)
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out.longitude = LLA[1] * 1e7;
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out.groundspeed = current.groundspeed;
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out.calibratedAirspeed = current.ias;
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out.calibratedAirspeed = current.cas;
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out.trueAirspeed=cas2tas(current.cas, current.Z, airParameters, gravity);
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out.dstN=current.Y;
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out.dstE=current.X;
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@ -44,29 +44,20 @@ private slots:
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void transmitUpdate();
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private:
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static const float FT2M;
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static const float KT2MPS;
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static const float MPS2KMH;
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static const float KMH2MPS;
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static const float INHG2KPA;
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static const float RAD2DEG;
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static const float DEG2RAD;
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static const float M2DEG;
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static const float DEG2M;
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static const float AIR_CONST;
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static const float GROUNDDENSITY;
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static const float TEMP_GROUND;
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static const float TEMP_LAPSE_RATE;
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static const float AIR_CONST_FACTOR;
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float DENSITY(float pressure);
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float PRESSURE(float alt);
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float TAS(float ias,float alt);
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static const float FT2M;
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static const float KT2MPS;
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static const float MPS2KMH;
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static const float KMH2MPS;
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static const float INHG2KPA;
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static const float RAD2DEG;
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static const float DEG2RAD;
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static const float NM2DEG;
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static const float DEG2NM;
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void processUpdate(const QByteArray& data);
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float angleDifference(float a,float b);
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AirParameters airParameters;
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};
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class IL2SimulatorCreator : public SimulatorCreator
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@ -71,6 +71,15 @@ Simulator::Simulator(const SimulatorSettings& params) :
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baroAltTime = currentTime;
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airspeedActualTime=currentTime;
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//Define standard atmospheric constants
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airParameters.univGasConstant=8.31447; //[J/(mol·K)]
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airParameters.dryAirConstant=287.058; //[J/(kg*K)]
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airParameters.groundDensity=1.225; //[kg/m^3]
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airParameters.groundTemp=15+273.15; //[K]
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airParameters.tempLapseRate=0.0065; //[deg/m]
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airParameters.M=0.0289644; //[kg/mol]
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airParameters.relativeHumidity=20; //[%]
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airParameters.seaLevelPress=101.325; //[kPa]
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}
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Simulator::~Simulator()
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@ -408,10 +417,7 @@ void Simulator::updateUAVOs(Output2Hardware out){
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LLA[0]=out.latitude;
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LLA[1]=out.longitude;
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LLA[2]=out.altitude;
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double ECEF[3];
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double RNE[9];
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Utils::CoordinateConversions().RneFromLLA(LLA,(double (*)[3])RNE);
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Utils::CoordinateConversions().LLA2ECEF(LLA,ECEF);
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homeData.Be[0]=0;
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homeData.Be[1]=0;
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homeData.Be[2]=0;
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@ -727,6 +733,9 @@ void Simulator::updateUAVOs(Output2Hardware out){
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AirspeedActual::DataFields airspeedActualData;
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memset(&airspeedActualData, 0, sizeof(AirspeedActual::DataFields));
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airspeedActualData.CalibratedAirspeed = out.calibratedAirspeed + noise.airspeedActual.CalibratedAirspeed;
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airspeedActualData.TrueAirspeed = out.trueAirspeed + noise.airspeedActual.TrueAirspeed;
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airspeedActualData.alpha=out.angleOfAttack;
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airspeedActualData.beta=out.angleOfSlip;
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airspeedActual->setData(airspeedActualData);
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airspeedActualTime=airspeedActualTime.addMSecs(settings.airspeedActualRate);
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@ -757,3 +766,68 @@ void Simulator::updateUAVOs(Output2Hardware out){
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}
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}
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}
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/**
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* calculate air density from altitude. http://en.wikipedia.org/wiki/Density_of_air
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*/
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float Simulator::airDensityFromAltitude(float alt, AirParameters air, float gravity) {
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float p= airPressureFromAltitude(alt, air, gravity);
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float rho=p*air.M/(air.univGasConstant*(air.groundTemp-air.tempLapseRate*alt));
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return rho;
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}
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/**
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* @brief Simulator::airPressureFromAltitude Get air pressure from altitude and atmospheric conditions.
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* @param alt altitude
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* @param air atmospheric conditions
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* @param gravity
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* @return
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*/
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float Simulator::airPressureFromAltitude(float alt, AirParameters air, float gravity) {
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return air.seaLevelPress* pow(1 - air.tempLapseRate * alt /air.groundTemp, gravity * air.M/(air.univGasConstant*air.tempLapseRate));
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}
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/**
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* @brief Simulator::cas2tas calculate TAS from CAS and altitude. http://en.wikipedia.org/wiki/Airspeed
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* @param CAS Calibrated airspeed
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* @param alt altitude
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* @param air atmospheric conditions
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* @param gravity
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* @return True airspeed
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*/
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float Simulator::cas2tas(float CAS, float alt, AirParameters air, float gravity) {
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float rho=airDensityFromAltitude(alt, air, gravity);
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return (CAS * sqrt(air.groundDensity/rho));
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}
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/**
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* @brief Simulator::tas2cas calculate CAS from TAS and altitude. http://en.wikipedia.org/wiki/Airspeed
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* @param TAS True airspeed
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* @param alt altitude
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* @param air atmospheric conditions
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* @param gravity
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* @return Calibrated airspeed
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*/
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float Simulator::tas2cas(float TAS, float alt, AirParameters air, float gravity) {
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float rho=airDensityFromAltitude(alt, air, gravity);
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return (TAS / sqrt(air.groundDensity/rho));
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}
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/**
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* @brief Simulator::getAirParameters get air parameters
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* @return airParameters
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*/
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AirParameters Simulator::getAirParameters(){
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return airParameters;
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}
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/**
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* @brief Simulator::setAirParameters set air parameters
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* @param airParameters
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*/
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void Simulator::setAirParameters(AirParameters airParameters){
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this->airParameters=airParameters;
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}
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@ -41,9 +41,9 @@
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#include "accels.h"
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#include "actuatorcommand.h"
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#include "actuatordesired.h"
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#include "airspeedactual.h"
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#include "attitudeactual.h"
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#include "attitudesettings.h"
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#include "airspeedactual.h"
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#include "baroaltitude.h"
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#include "flightstatus.h"
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#include "gcsreceiver.h"
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@ -70,10 +70,9 @@ typedef struct _FLIGHT_PARAM {
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float dT;
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unsigned int i;
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// speed (relative)
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float ias;
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float cas;
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float tas;
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// speeds
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float cas; //Calibrated airspeed
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float tas; //True airspeed
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float groundspeed;
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// position (absolute)
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@ -103,6 +102,18 @@ typedef struct _FLIGHT_PARAM {
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} FLIGHT_PARAM;
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struct AirParameters
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{
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float groundDensity;
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float groundTemp;
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float seaLevelPress;
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float tempLapseRate;
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float univGasConstant;
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float dryAirConstant;
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float relativeHumidity; //[%]
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float M; //Molar mass
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};
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typedef struct _CONNECTION
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{
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QString simulatorId;
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@ -213,6 +224,10 @@ public:
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QString SimulatorId() const { return simulatorId; }
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void setSimulatorId(QString str) { simulatorId = str; }
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float airDensityFromAltitude(float alt, AirParameters air, float gravity);
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float airPressureFromAltitude(float alt, AirParameters air, float gravity);
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float cas2tas(float CAS, float alt, AirParameters air, float gravity);
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float tas2cas(float TAS, float alt, AirParameters air, float gravity);
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static bool IsStarted() { return isStarted; }
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@ -226,6 +241,9 @@ public:
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void resetInitialHomePosition();
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void updateUAVOs(Output2Hardware out);
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AirParameters getAirParameters();
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void setAirParameters(AirParameters airParameters);
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signals:
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void autopilotConnected();
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void autopilotDisconnected();
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@ -317,6 +335,8 @@ private:
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void setupInputObject(UAVObject* obj, quint32 updatePeriod);
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void setupWatchedObject(UAVObject *obj, quint32 updatePeriod);
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void setupObjects();
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AirParameters airParameters;
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};
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