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test_round_
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@RivaAlkahal
RivaAlkahal committed Dec 19, 2023
1 parent 998a466 commit 3e27b0d
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Showing 2 changed files with 20 additions and 23 deletions.
31 changes: 13 additions & 18 deletions src/astro/aerodynamics/marsDtmAtmosphereModel.cpp
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Original file line number Diff line number Diff line change
Expand Up @@ -97,8 +97,8 @@ namespace aerodynamics
coefficients_ = loadCoefficients( filename );
currentLegendrePolynomials_.resize( 6 );
currentLegendrePolynomials_[ 0 ] = 0.0;
std::cout << "Loaded Matrix values:" << std::endl;
std::cout << coefficients_[0][3] << "\t";
//std::cout << "Loaded Matrix values:" << std::endl;
//std::cout << coefficients_[0][3] << "\t";
}

// function to compute the local true solar time
Expand Down Expand Up @@ -135,7 +135,7 @@ namespace aerodynamics
//Areocentric Solar Longitude
double Ls1 = omegaFMS + EoC;
Ls = basic_mathematics::computeModulo( Ls1,360.0);
std::cout << "Ls: " << Ls << std::endl;
//std::cout << "Ls: " << Ls << std::endl;
//Equation of Time
double EoT = 2.861 * sin( unit_conversions::convertDegreesToRadians(2*Ls))
- 0.071 * sin( unit_conversions::convertDegreesToRadians(4*Ls))
Expand All @@ -145,12 +145,12 @@ namespace aerodynamics
double MST = 24*((basic_astrodynamics::convertCalendarDateToJulianDay(year,month,day,hours,minutes,0.0) - 2451549.5)/1.0274912517 + 44796.0 - 0.0009626); //double MST
//std::cout << "MST1: " << MST << std::endl;
MST = basic_mathematics::computeModulo( MST,24.0);// Modulo MST
std::cout << "MST: " << MST << std::endl;
//std::cout << "MST: " << MST << std::endl;
//Local Mean Solar Time
double LMST = basic_mathematics::computeModulo( MST-longitude*(24.0/360.0),24.0);
//Local True Solar Time
double LTST = basic_mathematics::computeModulo(LMST + EoT*(24.0/360.0),24.0);
std::cout << "LTST: " << LTST << std::endl;
//std::cout << "LTST: " << LTST << std::endl;
//Subsolar Longitude
double subSolarLongitude = MST*(360.0/24.0) + EoT + 180.0;
// return LTST in seconds.
Expand Down Expand Up @@ -232,10 +232,10 @@ namespace aerodynamics
using basic_mathematics::computeLegendrePolynomialExplicit;
marsDate date2 = marsDate(year_, month_, day_, hours_ , minutes_, 0.0);
double doy = date2.marsDayofYear(date2); //day of year
std::cout << "doy: " << doy << std::endl;
//std::cout << "doy: " << doy << std::endl;
double t = computeLocalSolarTime(longitude, day_, month_, year_, hours_, minutes_); //seconds
int F = 0.0; // flux parameter is set to 0 for now.
std::cout<<"coefficients_[14][indexg]" << coefficients_[14][indexg] << std::endl;
//std::cout<<"coefficients_[14][indexg]" << coefficients_[14][indexg] << std::endl;
// Non-periodic term
double NP = (coefficients_[1][indexg] * F) + coefficients_[30][indexg] * currentLegendrePolynomials_[1]
+ coefficients_[31][indexg] * currentLegendrePolynomials_[ 2 ]
Expand Down Expand Up @@ -316,10 +316,6 @@ namespace aerodynamics
double da41 = computeDustStorm( Ls );
double fpds = coefficients_[40][indexg]*da41 + coefficients_[69][indexg]*taus[3];
double Gl = fpds + f0 + PA + PSA + PD;
std::cout << "f0: " << f0 << std::endl;
std::cout << "PA: " << PA << std::endl;
std::cout << "PSA: " << PSA << std::endl;
std::cout << "PD: " << PD << std::endl;
return Gl;
}

Expand All @@ -334,7 +330,7 @@ namespace aerodynamics
{
double T0 = coefficients_[0][indexg];
double Ti;
double Gl = computeGl(latitude, longitude, minutes_, hours_, day_ , month_, year_, indexg);
double Gl = computeGl_Subr(latitude, longitude, minutes_, hours_, day_ , month_, year_, indexg);
Ti = T0*(1.0 + Gl);
return Ti;
}
Expand Down Expand Up @@ -386,15 +382,14 @@ namespace aerodynamics
rho0 = coefficients_[0][col]*mmass_[indexm]/avogadroConstant_; //g/cm3
//std::cout << "coefficients_[0][col]: " << coefficients_[0][col] << std::endl;
double fi = heightDistributionFunction(altitude, latitude, longitude, minutes_, hours_, day_ , month_, year_, indexm);
if (col == 7)
std::cout << "fi CO2: " << fi << std::endl;
//if (col == 7)
// std::cout << "fi CO2: " << fi << std::endl;

double gl = computeGl_Subr(latitude, longitude, minutes_, hours_, day_ , month_, year_, col);

double gl = computeGl(latitude, longitude, minutes_, hours_, day_ , month_, year_, col);
std::cout << "gl: " << gl << std::endl;
std::cout << "col" << col << std::endl;
rho += rho0*fi*exp(gl);
indexm +=1;
std::cout << "rho: " << indexm << " " << rho << std::endl;
//std::cout << "rho: " << indexm << " " << rho << std::endl;
}
return rho;
}
Expand Down
12 changes: 7 additions & 5 deletions tests/src/astro/aerodynamics/unitTestMarsDtmAtmosphere.cpp
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Original file line number Diff line number Diff line change
Expand Up @@ -52,7 +52,8 @@ int main( )
// Create Earth object
BodyListSettings defaultBodySettings =
getDefaultBodySettings( { "Mars" } );
defaultBodySettings.at( "Mars" )->atmosphereSettings = marsDtmAtmosphereSettings( TODO );
std::string filename = "/Users/ralkahal/Documents/PhD/Programs/atmodensitydtm/dtm_mars";
defaultBodySettings.at( "Mars" )->atmosphereSettings = marsDtmAtmosphereSettings( filename, 3378.0E3);
SystemOfBodies bodies = createSystemOfBodies( defaultBodySettings );

// Create vehicle object.
Expand Down Expand Up @@ -80,7 +81,8 @@ int main( )
centralBodies.push_back( "Mars" );

// Set initial state
Eigen::Vector6d systemInitialState = TODO (add Cartesian initial state w.r.t. Mars )
Eigen::Vector6d systemInitialState;
systemInitialState

// Create acceleration models and propagation settings.
basic_astrodynamics::AccelerationMap accelerationModelMap = createAccelerationModelsMap(
Expand All @@ -90,7 +92,7 @@ int main( )
std::vector<std::shared_ptr<SingleDependentVariableSaveSettings> > dependentVariables;
dependentVariables.push_back(
std::make_shared<SingleDependentVariableSaveSettings>(
altitude_dependent_variable, "Vehicle", "Earth" ));
altitude_dependent_variable, "Vehicle", "Mars" ));
dependentVariables.push_back(
std::make_shared<BodyAerodynamicAngleVariableSaveSettings>(
"Vehicle", reference_frames::longitude_angle ));
Expand All @@ -99,10 +101,10 @@ int main( )
"Vehicle", reference_frames::latitude_angle ));
dependentVariables.push_back(
std::make_shared<SingleDependentVariableSaveSettings>(
local_density_dependent_variable, "Vehicle", "Earth" ));
local_density_dependent_variable, "Vehicle", "Mars" ));
dependentVariables.push_back(
std::make_shared<SingleAccelerationDependentVariableSaveSettings>(
aerodynamic, "Vehicle", "Earth", 0 ));
aerodynamic, "Vehicle", "Mars", 0 ));

// Set propagation/integration settings
std::shared_ptr<PropagationTimeTerminationSettings> terminationSettings =
Expand Down

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