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  • tombrinkdenis/aircraft-design
  • unicado/aircraft-design
  • alfin.johny/aircraft-design
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with 293 additions and 251 deletions
constraint_analysis/src/energy_based/energy_based.cpp
View file @ e90e39d8
......@@ -105,7 +105,9 @@ void EnergyBased::operator()()
break;
}
}
Mattingly::constraint_analysis constraint_analysis_plotting = constraint_analysis_tool;
readMission mission_data(missionCSV);
assess_constraints(W_over_S_data, constraint_analysis_tool, mission_data, engine);
......@@ -141,9 +143,30 @@ void EnergyBased::operator()()
/* Plot the complete design chart with constraints, boundaries and design point*/
std::string plotting = this->configuration()->at("module_configuration_file/control_settings/plot_output/enable/value");
if (plotting == "true") {
WS_start = 50;
WS_end = 820;
WS_size = WS_end - WS_start + 1; // Range from 50 to 820, inclusive
std::vector<double> W_over_S_data(WS_size);
for (int i = 0; i < WS_size; ++i) {
W_over_S_data[i] = (WS_start + i) * 9.81;
}
this->constraint_list = {};
this->boundaries = {};
assess_constraints(W_over_S_data, constraint_analysis_plotting, mission_data, engine);
Simple_Analysis min_finder_2 = Simple_Analysis(this->constraint_list, this->aircraft_xml(), this->boundaries);
min_finder_2.find_dominant_curve();
ConstraintAnalysis_Plot ca_plot;
ca_plot.fill_infeasible_area(W_over_S_data, min_finder.dominant_thrust_to_weight, boundaries);
ca_plot.fill_infeasible_area(W_over_S_data, min_finder_2.dominant_thrust_to_weight, boundaries);
for (auto ca_case : this->constraint_list)
{
ca_plot.add_curve(ca_case.wing_loading, ca_case.thrust_to_weight, ca_case.constraint_case);
......
mission_analysis/mission_analysis_conf.xml
View file @ e90e39d8
......@@ -159,12 +159,12 @@
<upper_boundary>1.0</upper_boundary>
</relative_time_passed>
</polar_switch_mission_point>
<glideslope_interception_distance description="Buffer distance to hit the glideslope exactly">
<glide_slope_interception_distance description="Buffer distance to hit the glide slope exactly">
<value>1000.</value>
<unit>m</unit>
<lower_boundary>0.0</lower_boundary>
<upper_boundary>1000000</upper_boundary>
</glideslope_interception_distance>
</glide_slope_interception_distance>
<use_breguet_estimation_in_cruise description="Switch to activate fuel estimation using Breguet range equation in mid fidelity methods. Switch: true (On) / false (Off)">
<value>false</value>
</use_breguet_estimation_in_cruise>
......
mission_analysis/src/libs/condition_methods/flight_conditions.cpp
View file @ e90e39d8
......@@ -70,9 +70,9 @@ FlightConditions::FlightConditions(std::vector<MissionFileDataHandler::MissionDa
/* Initialization of rate of climb */
ROC(0.),
/* Initialization of path angle parameters */
glidepath_angle(0.),
mean_glidepath_angle(0.),
end_glidepath_angle(0.),
glide_path_angle(0.),
mean_glide_path_angle(0.),
end_glide_path_angle(0.),
/* Initialization of acceleration factors */
acceleration(0.),
mean_acceleration(0.),
......@@ -114,37 +114,38 @@ void FlightConditions::update_operating_condition(const OperatingConditions& oc)
/* Set Initial flight conditions */
void FlightConditions::set_initial_flight_track() {
switch (this->mission_data->at(this->operating_condition->mission_step).mode) {
case ACCELERATE:
case FLCHANGE:
case FLCHANGESIMULATION: {
case ACCELERATE: {
this->ROC = this->mission_data->at(this->operating_condition->mission_step).ROC;
this->glidepath_angle = fabs(this->ROC) < 1.e-3 ? 0. : asin(this->ROC / this->TAS);
this->glide_path_angle = fabs(this->ROC) < 1.e-3 ? 0. : asin(this->ROC / this->TAS);
break;
}
case CLIMBCONSTCAS:
case CLIMBTOCRUISE:
case CLIMBTOSERVICECEILING:
case FlightConditions::DESCENT:
case FREEFLIGHT: { // use kinetic energy to climb/descent
this->glidepath_angle = asin((std::min(1., (this->thrust - this->drag) / this->aircraft_mass / G_FORCE)));
this->ROC = sin(this->glidepath_angle) * this->TAS;
case DESCENT:
case FLCHANGE:
case FLCHANGESIMULATION:
case FREEFLIGHT: { // use kinetic energy to climb/descend
this->glide_path_angle = asin((std::min(1., (this->thrust - this->drag) / this->aircraft_mass / G_FORCE)));
this->ROC = sin(this->glide_path_angle) * this->TAS;
// If highest possible ROC (all thrust used) is above maximum ROC, set to maximum ROC
if (this->mission_data->at(this->operating_condition->mission_step).ROC > 0.
&& this->ROC > this->mission_data->at(this->operating_condition->mission_step).ROC) {
this->ROC = this->mission_data->at(this->operating_condition->mission_step).ROC; //fix ROC for climb to maximum given climb rate
this->glidepath_angle = asin(this->ROC / this->TAS);
this->glide_path_angle = asin(this->ROC / this->TAS);
}
break;
}
case DECELERATE:
case APPROACH:
case LANDING: {
this->glidepath_angle = this->mission_data->at(this->operating_condition->mission_step).glidepath;
this->ROC = sin(this->glidepath_angle) * this->TAS;
this->glide_path_angle = this->mission_data->at(this->operating_condition->mission_step).glide_path;
this->ROC = sin(this->glide_path_angle) * this->TAS;
break;
}
default: //use kinetic energy to accelerate/decelerate
this->glidepath_angle = 0.;
this->ROC = sin(this->glidepath_angle) * this->TAS;
this->glide_path_angle = 0.;
this->ROC = sin(this->glide_path_angle) * this->TAS;
}
}
......@@ -167,8 +168,8 @@ void FlightConditions::set_initial_acceleration_factors(const double& braking_co
this->acceleration = 0.;
break;
default:
//according to Newton's law F = m * a. Acceleration force F_a = (Thrust - drag - m * sin(glidepath_angle) * g) = m * a
this->acceleration = (this->thrust - this->drag - this->aircraft_mass * sin(this->glidepath_angle) * G_FORCE) / this->aircraft_mass;
//according to Newton's law F = m * a. Acceleration force F_a = (Thrust - drag - m * sin(glide_path_angle) * g) = m * a
this->acceleration = (this->thrust - this->drag - this->aircraft_mass * sin(this->glide_path_angle) * G_FORCE) / this->aircraft_mass;
}
}
......@@ -187,7 +188,7 @@ void FlightConditions::set_initial_thrust() {
case CRUISECI:
case APPROACH:
case GSINTERCEPTION: {
double required_thrust(sin(this->glidepath_angle) * this->aircraft_mass * G_FORCE + this->aircraft_mass * this->acceleration + this->drag);
double required_thrust(sin(this->glide_path_angle) * this->aircraft_mass * G_FORCE + this->aircraft_mass * this->acceleration + this->drag);
/* Set engine rating to required thrust:
* if required thrust is smaller than idle thrust, the engine library throws engine_status = 3, which is caught here and the rating is then set to idle
* in the almost impossible case that in descent or cruise the required thrust exceeds maximum available thrust, the engine library throws engine_status = 2
......@@ -247,38 +248,38 @@ void FlightConditions::set_flight_track() {
case FLCHANGE:
case FLCHANGESIMULATION: { //constant ROC
this->ROC = this->mission_data->at(this->operating_condition->mission_step).ROC;
this->end_glidepath_angle = fabs(this->ROC) < 1.e-3 ? 0. : asin(this->ROC / this->end_TAS);
this->mean_glidepath_angle = (this->glidepath_angle + this->end_glidepath_angle) / 2.;
this->ROC = sin(this->mean_glidepath_angle) * (this->TAS + this->end_TAS) / 2.;
this->end_glide_path_angle = fabs(this->ROC) < 1.e-3 ? 0. : asin(this->ROC / this->end_TAS);
this->mean_glide_path_angle = (this->glide_path_angle + this->end_glide_path_angle) / 2.;
this->ROC = sin(this->mean_glide_path_angle) * (this->TAS + this->end_TAS) / 2.;
break;
}
case CLIMBCONSTCAS:
case CLIMBTOCRUISE:
case CLIMBTOSERVICECEILING:
case DESCENT:
case FREEFLIGHT: { // use kinetic energy to climb/descent
this->end_glidepath_angle = asin((std::min(1., (this->end_thrust - this->end_drag) / this->end_aircraft_mass / G_FORCE)));
this->ROC = sin(this->end_glidepath_angle) * this->end_TAS;
case FREEFLIGHT: { // use kinetic energy to climb/descend
this->end_glide_path_angle = asin((std::min(1., (this->end_thrust - this->end_drag) / this->end_aircraft_mass / G_FORCE)));
this->ROC = sin(this->end_glide_path_angle) * this->end_TAS;
if (this->mission_data->at(this->operating_condition->mission_step).ROC > 0.
&& this->ROC > this->mission_data->at(this->operating_condition->mission_step).ROC) {
this->ROC = this->mission_data->at(this->operating_condition->mission_step).ROC; //fix ROC for climb to maximum given climb rate
this->end_glidepath_angle = asin(this->ROC / this->end_TAS);
this->end_glide_path_angle = asin(this->ROC / this->end_TAS);
}
this->mean_glidepath_angle = (this->glidepath_angle + this->end_glidepath_angle) / 2.;
this->ROC = sin(this->mean_glidepath_angle) * (this->TAS + this->end_TAS) / 2.;
this->mean_glide_path_angle = (this->glide_path_angle + this->end_glide_path_angle) / 2.;
this->ROC = sin(this->mean_glide_path_angle) * (this->TAS + this->end_TAS) / 2.;
break;
}
case DECELERATE:
case APPROACH:
case LANDING: {
this->end_glidepath_angle = this->mission_data->at(this->operating_condition->mission_step).glidepath;
this->mean_glidepath_angle = (this->glidepath_angle + this->end_glidepath_angle) / 2.;
this->ROC = sin(this->mean_glidepath_angle) * (this->TAS + this->end_TAS) / 2.;
this->end_glide_path_angle = this->mission_data->at(this->operating_condition->mission_step).glide_path;
this->mean_glide_path_angle = (this->glide_path_angle + this->end_glide_path_angle) / 2.;
this->ROC = sin(this->mean_glide_path_angle) * (this->TAS + this->end_TAS) / 2.;
break;
}
default:
this->mean_glidepath_angle = (this->glidepath_angle + this->end_glidepath_angle) / 2.;
this->ROC = sin(this->mean_glidepath_angle) * (this->TAS + this->end_TAS) / 2.;
this->mean_glide_path_angle = (this->glide_path_angle + this->end_glide_path_angle) / 2.;
this->ROC = sin(this->mean_glide_path_angle) * (this->TAS + this->end_TAS) / 2.;
}
}
......@@ -294,13 +295,13 @@ void FlightConditions::set_acceleration_factors(const double& braking_coefficien
this->end_acceleration = this->get_ground_run_acceleration(this->end_thrust, this->end_drag, lift_force, this->end_aircraft_mass * G_FORCE,
minimum_acceleration, friction_coefficient);
} else {
// Acceleration according to Newton's law F = m * a. Acceleration force F_a = (Thrust - drag - m * sin(glidepath_angle) * g) = m * a
this->end_acceleration = (this->end_thrust - this->end_drag - this->end_aircraft_mass * sin(this->end_glidepath_angle) * G_FORCE) / this->end_aircraft_mass;
// Acceleration according to Newton's law F = m * a. Acceleration force F_a = (Thrust - drag - m * sin(glide_path_angle) * g) = m * a
this->end_acceleration = (this->end_thrust - this->end_drag - this->end_aircraft_mass * sin(this->end_glide_path_angle) * G_FORCE) / this->end_aircraft_mass;
}
if (accuracyCheck(this->mean_glidepath_angle, 0., ACCURACY_HIGH) || accuracyCheck(this->delta_h, 0., ACCURACY_HIGH)) {
if (accuracyCheck(this->mean_glide_path_angle, 0., ACCURACY_HIGH) || accuracyCheck(this->delta_h, 0., ACCURACY_HIGH)) {
this->mean_acceleration = (this->acceleration + this->end_acceleration) / 2.;
} else {
this->mean_acceleration = (pow(this->end_TAS, 2.) - pow(this->TAS, 2.)) / (2. * this->delta_h / sin(this->mean_glidepath_angle));
this->mean_acceleration = (pow(this->end_TAS, 2.) - pow(this->TAS, 2.)) / (2. * this->delta_h / sin(this->mean_glide_path_angle));
}
if (accuracyCheck(this->mean_acceleration, 0., ACCURACY_LOW)) { //set numerical instability to zero
this->mean_acceleration = 0.;
......@@ -308,7 +309,7 @@ void FlightConditions::set_acceleration_factors(const double& braking_coefficien
}
void FlightConditions::set_thrust() {
double required_thrust(sin(this->mean_glidepath_angle) * this->end_aircraft_mass * G_FORCE + this->end_aircraft_mass * this->mean_acceleration + this->end_drag);
double required_thrust(sin(this->mean_glide_path_angle) * this->end_aircraft_mass * G_FORCE + this->end_aircraft_mass * this->mean_acceleration + this->end_drag);
switch (this->mission_data->at(this->operating_condition->mission_step).mode) {
case CRUISE:
case CRUISECI:
......@@ -373,7 +374,7 @@ void FlightConditions::activate_spoilers() {
case CRUISECI:
case APPROACH:
case GSINTERCEPTION: {
if (!this->aero->useSpoiler((this->end_thrust - sin(this->mean_glidepath_angle) * this->end_aircraft_mass * G_FORCE -
if (!this->aero->useSpoiler((this->end_thrust - sin(this->mean_glide_path_angle) * this->end_aircraft_mass * G_FORCE -
this->end_aircraft_mass * this->mean_acceleration), &this->end_drag))
throwError(__FILE__, __func__, __LINE__, "drag too low to maintain requested flight state.");
myRuntimeInfo->info << "end_drag after spoiler: " << this->end_drag << std::endl;
......@@ -407,35 +408,35 @@ void FlightConditions::set_way_and_time() {
* --> in the end the flight path vector must be corrected by track angle to get the range back
* in general (from standstill): v = a * t; s = 1/2 * a * t^2
* here: end_TAS = TAS + mean_acceleration * delta_t; delta_x = TAS * delta_t + 1/2 * mean_acceleration * delta_t^2 (constant motion + accelerated motion)
* Climb/Descent: delta_x = delta_h / sin(mean_glidepath_angle) --> delta_t^2 + 2 * TAS / mean_acceleration - 2 * delta_h / sin(mean_glidepath_angle) / mean_acceleration = 0
* delta_t = -TAS / mean_acceleration +/- sqrt((TAS/mean_acceleration)^2 + 2 * delta_h / sin(mean_glidepath_angle) / mean_acceleration)
* mean_acceleration = (TAS_end^2 - TAS^2) / (2 * delta_h / sin(mean_glidepath_angle))
* Climb/Descent: delta_x = delta_h / sin(mean_glide_path_angle) --> delta_t^2 + 2 * TAS / mean_acceleration - 2 * delta_h / sin(mean_glide_path_angle) / mean_acceleration = 0
* delta_t = -TAS / mean_acceleration +/- sqrt((TAS/mean_acceleration)^2 + 2 * delta_h / sin(mean_glide_path_angle) / mean_acceleration)
* mean_acceleration = (TAS_end^2 - TAS^2) / (2 * delta_h / sin(mean_glide_path_angle))
*/
if (accuracyCheck(this->mean_acceleration, 0., 0.01)) { //constant motion
if (!accuracyCheck(this->TAS, 0., ACCURACY_LOW) && !accuracyCheck(this->mean_glidepath_angle, 0., ACCURACY_LOW)) {
this->delta_t = this->delta_h / sin(this->mean_glidepath_angle) / this->TAS;
if (!accuracyCheck(this->TAS, 0., ACCURACY_LOW) && !accuracyCheck(this->mean_glide_path_angle, 0., ACCURACY_LOW)) {
this->delta_t = this->delta_h / sin(this->mean_glide_path_angle) / this->TAS;
} else { // this condition is only met if CRUISE and, there, delta_x is preset
this->delta_t = this->delta_x / this->TAS;
}
} else if (!accuracyCheck(this->mean_acceleration, 0., ACCURACY_LOW)) {
if (accuracyCheck(this->mean_glidepath_angle, 0., ACCURACY_LOW)) { // horizontal acceleration
if (accuracyCheck(this->mean_glide_path_angle, 0., ACCURACY_LOW)) { // horizontal acceleration
this->delta_t = (this->end_TAS - this->TAS) / this->mean_acceleration;
} else if (this->mean_acceleration < 0.) { // deceleration in climb/descent
this->delta_t = -sqrt(pow(this->TAS / this->mean_acceleration, 2.) +
2. * this->delta_h / sin(this->mean_glidepath_angle) / this->mean_acceleration) - this->TAS / this->mean_acceleration;
2. * this->delta_h / sin(this->mean_glide_path_angle) / this->mean_acceleration) - this->TAS / this->mean_acceleration;
} else { // acceleration in climb/descent
this->delta_t = sqrt(pow(this->TAS / this->mean_acceleration, 2.) +
2. * this->delta_h / sin(this->mean_glidepath_angle) / this->mean_acceleration) - this->TAS / this->mean_acceleration;
2. * this->delta_h / sin(this->mean_glide_path_angle) / this->mean_acceleration) - this->TAS / this->mean_acceleration;
}
} else {
myRuntimeInfo->err << "TAS: " << this->TAS << std::endl;
myRuntimeInfo->err << "end_TAS: " << this->end_TAS << std::endl;
myRuntimeInfo->err << "mean_acceleration: " << this->mean_acceleration << std::endl;
myRuntimeInfo->err << "mean_glidepath_angle: " << this->mean_glidepath_angle << std::endl;
myRuntimeInfo->err << "mean_glide_path_angle: " << this->mean_glide_path_angle << std::endl;
myRuntimeInfo->err << "delta_h: " << this->delta_h << std::endl;
throwError(__FILE__, __func__, __LINE__, "BUG in program. Abort program.");
}
this->delta_x = this->TAS * this->delta_t + 0.5 * this->mean_acceleration * pow(this->delta_t, 2.); // s = v*t + 1/2*a*t^2 = constant motion + accelerated motion
/* Shift vector in ground distance direction */
this->delta_x *= cos(this->mean_glidepath_angle);
this->delta_x *= cos(this->mean_glide_path_angle);
}
mission_analysis/src/libs/condition_methods/flight_conditions.h
View file @ e90e39d8
......@@ -91,9 +91,9 @@ class FlightConditions {
double ROC; /**< Rate of climb [m/s] */
double glidepath_angle; /**< Path angle at the beginning of the segment [rad] */
double mean_glidepath_angle; /**< Mean path angle of the segment [rad] */
double end_glidepath_angle; /**< Path angle at the end of the segment [rad] */
double glide_path_angle; /**< Path angle at the beginning of the segment [rad] */
double mean_glide_path_angle; /**< Mean path angle of the segment [rad] */
double end_glide_path_angle; /**< Path angle at the end of the segment [rad] */
double acceleration; /**< Acceleration at the beginning of the segment [m/s^2] */
double mean_acceleration; /**< Mean acceleration of the segment [m/s^2] */
......@@ -149,7 +149,7 @@ class FlightConditions {
* \details the equations of constant and accelerated motion are used to get way and time values for the segment
*/
void set_way_and_time();
/** \brief Function sets initial segment values for glidepath_angle and ROC
/** \brief Function sets initial segment values for glide_path_angle and ROC
*/
void set_initial_flight_track();
/** \brief Function sets initial segment values for the acceleration factor
......@@ -181,7 +181,7 @@ class FlightConditions {
* \details the engine is set to a rating/spool speed
*/
void set_initial_thrust();
/** \brief Function sets values for end_glidepath_angle, mean_glidepath_angle, and ROC
/** \brief Function sets values for end_glide_path_angle, mean_glide_path_angle, and ROC
*/
void set_flight_track();
/** \brief Function sets a value for end_thrust
......
mission_analysis/src/libs/mission_file_data_handler/mission_file_data_handler.cpp
View file @ e90e39d8
......@@ -73,10 +73,10 @@ void MissionFileDataHandler::read_departure_steps(const double& max_operating_sp
data.CAS = 0.; // End CAS [m/s]
data.mach = 0.; // Mach number
data.mach_switch = false;
data.glidepath = 0.; // Glide angle [rad]
data.glide_path = 0.; // Glide angle [rad]
data.rel_segment_length = 0.; // Flight route for cruise
data.auto_altitude_steps = 0.;
data.ground_distance = 0.;
data.auto_FL_optimum = false;
data.round_to_regular_FL = false;
data.CI = 0.; // Cost index [kg/min], scaled 0 to 999 according to Sperry/Honeywell [1]
......@@ -167,10 +167,9 @@ void MissionFileDataHandler::read_flight_steps(double* average_shaft_bleed, doub
data.CAS = 0.; // End CAS [m/s]
data.mach = 0.; // Mach number
data.mach_switch = false;
data.glidepath = 0.; // Glide angle [rad]
data.glide_path = 0.; // Glide angle [rad]
data.rel_segment_length = 0.; // Flight route for cruise
data.auto_altitude_steps = 0.;
data.ground_distance = 0.;
data.CI = 0.; // Cost index [kg/min], scaled 0 to 999 according to Sperry/Honeywell [1]
data.transfer_time = 0.;
data.transfer_rate = 0.;
......@@ -324,10 +323,9 @@ void MissionFileDataHandler::read_approach_steps(const double& max_operating_spe
data.CAS = 0.; // End CAS [m/s]
data.mach = 0.; // Mach number
data.mach_switch = false;
data.glidepath = 0.; // Glide angle [rad]
data.glide_path = 0.; // Glide angle [rad]
data.rel_segment_length = 0.; // Flight route for cruise
data.auto_altitude_steps = 0.;
data.ground_distance = 0.;
data.auto_FL_optimum = false;
data.round_to_regular_FL = false;
data.CI = 0.; // Cost index [kg/min], scaled 0 to 999 according to Sperry/Honeywell [1]
......@@ -370,12 +368,11 @@ void MissionFileDataHandler::read_approach_steps(const double& max_operating_spe
if (data.mode_name == "descend") { // Mode: descend
data.mode = FlightConditions::APPROACH;
data.altitude = EndnodeReadOnly<double>(subpath + num2Str(i) + "/altitude").read(mission_xml).value();
data.glidepath = EndnodeReadOnly<double>(subpath + num2Str(i) + "/glide_path").read(mission_xml).value();
data.glide_path = EndnodeReadOnly<double>(subpath + num2Str(i) + "/glide_path").read(mission_xml).value();
data.energy_carrier_id = descent_id;
} else if (data.mode_name == "change_speed") { // Mode: change speed
data.mode = FlightConditions::DECELERATE;
data.ground_distance = EndnodeReadOnly<double>(subpath + num2Str(i) + "/ground_distance").read(mission_xml).value();
data.glidepath = EndnodeReadOnly<double>(subpath + num2Str(i) + "/glide_path").read(mission_xml).value();
data.glide_path = EndnodeReadOnly<double>(subpath + num2Str(i) + "/glide_path").read(mission_xml).value();
data.CAS = EndnodeReadOnly<double>(subpath + num2Str(i) + "/calibrated_airspeed").read(mission_xml).value();
if (data.CAS > max_operating_speed) {
throwError(__FILE__, __func__, __LINE__,
......@@ -386,7 +383,7 @@ void MissionFileDataHandler::read_approach_steps(const double& max_operating_spe
} else if (data.mode_name == "landing") { // Mode: landing
data.mode = FlightConditions::LANDING;
data.altitude = EndnodeReadOnly<double>(subpath + num2Str(i) + "/altitude").read(mission_xml).value();
data.glidepath = EndnodeReadOnly<double>(subpath + num2Str(i) + "/glide_path").read(mission_xml).value();
data.glide_path = EndnodeReadOnly<double>(subpath + num2Str(i) + "/glide_path").read(mission_xml).value();
data.energy_carrier_id = landing_id;
} else if (data.mode_name == "level_glide_slope_interception") { // Mode: level glide slope interception
data.mode = FlightConditions::GSINTERCEPTION;
......
mission_analysis/src/libs/mission_file_data_handler/mission_file_data_handler.h
View file @ e90e39d8
......@@ -71,9 +71,8 @@ class MissionFileDataHandler {
double CAS; /**< End CAS [m/s] */
double mach; /**< Mach number [-] */
bool mach_switch; /**< Switch for using Mach */
double glidepath; /**< Glide angle [rad] */
double glide_path; /**< Glide angle [rad] */
double rel_segment_length; /**< Relative segment length in cruise */
double ground_distance; /**< Ground distance [m] */
bool auto_FL_optimum; /**< Switch to auto select optimum flight level */
bool round_to_regular_FL; /**< Switch for rounding to regular flight level */
double auto_altitude_steps; /**< Altitude change for optimum altitude in cruise [ft] */
......
mission_analysis/src/libs/multi_engine_propulsion/multi_engine_propulsion.cpp
View file @ e90e39d8
......@@ -146,7 +146,7 @@ double MultiEnginePropulsion::get_aircraft_fuelflow(const int& energy_carrier_id
// Loop through all propulsors running on that energy carrier
for (uint16_t i(0); i < this->propulsors[energy_carrier_id].size(); i++) {
// Trick: Propulsors with same engines have multiple IDs -> size() scales overall fuelflow acordingly
total_fuel_flow += this->propulsors[energy_carrier_id][i].engine.get_aircraft_fuelflow() * this->propulsors[energy_carrier_id][i].engine_id.size();
total_fuel_flow += this->propulsors[energy_carrier_id][i].engine.get_fuelflow() * this->propulsors[energy_carrier_id][i].engine_id.size();
}
return total_fuel_flow;
}
......
mission_analysis/src/standard_mission/output/standard_mission_output.cpp
View file @ e90e39d8
......@@ -224,7 +224,7 @@ void StandardMissionOutput::generate_mission_profile_data() {
<< my_mission_ptr->mission_profile.at(i).end_fuel_cg << "; ";
}
csvStream << my_mission_ptr->mission_profile.at(i).end_angle_of_attack << "; "
<< convertUnit(RADIAN, DEGREE, my_mission_ptr->mission_profile.at(i).end_glidepath_angle) << "; "
<< convertUnit(RADIAN, DEGREE, my_mission_ptr->mission_profile.at(i).end_glide_path_angle) << "; "
<< my_mission_ptr->mission_profile.at(i).end_stabilizer_incidence;
for (uint8_t k(0); k < my_mission_ptr->mission_profile.at(i).end_origin_polar[1].size(); ++k) {
csvStream << "; " << my_mission_ptr->mission_profile.at(i).end_origin_polar[1].at(k);
......
mission_analysis/src/standard_mission/standard_mission/standard_mission.cpp
View file @ e90e39d8
......@@ -190,8 +190,8 @@ StandardMission::StandardMission(const std::shared_ptr<RuntimeIO>& rtIO) :
step_height_cruise(0.),
cruise_profile_start(0),
cruise_profile_end(0),
top_of_climb_range("top_of_climb_range", "Flown range from takeoff to top of climb (= start of initial cruise altitude (ICA))", 0, "kg", 0, 500000),
top_of_descent_range("top_of_descent_range", "Flown range from takeoff to top of descent", 0, "kg", 0, 5000000),
top_of_climb_range("top_of_climb_range", "Flown range from takeoff to top of climb (= start of initial cruise altitude (ICA))", 0, "m", 0, 500000),
top_of_descent_range("top_of_descent_range", "Flown range from takeoff to top of descent", 0, "m", 0, 5000000),
descent_range(0.),
descent_range_next_FL(0.),
top_of_descent_altitude(0.),
......@@ -399,7 +399,7 @@ void StandardMission::run() {
break;
/* Mode: descend to approach */
case FlightConditions::DESCENT:
myRuntimeInfo->out << "Descent to 10.000 ft ... " << std::endl;
myRuntimeInfo->out << "Descend to 10.000 ft ... " << std::endl;
this->cruise_profile_end = this->mission_profile.size() - 1; // Set index
this->change_altitude_at_constant_speed(&oc, &fc, i);
break;
......@@ -424,7 +424,7 @@ void StandardMission::run() {
break;
/* Mode: glide slope interception */
case FlightConditions::GSINTERCEPTION:
this->glideslope_interception(&oc, &fc, i);
this->glide_slope_interception(&oc, &fc, i);
break;
/* Mode: climb (change flight level) with a constant calibrated airspeed or Mach number at a fixed rate of climb */
case FlightConditions::FLCHANGE:
......@@ -849,9 +849,9 @@ void StandardMission::requirements_mission_update() {
"design_approach_speed"
};
bool takeoff_check(EndnodeReadOnly<double>("requirements_and_specifications/requirements/top_level_aircraft_requirements/landing_field_length").read(rtIO->acxml).value() >
bool takeoff_check(EndnodeReadOnly<double>("requirements_and_specifications/requirements/top_level_aircraft_requirements/takeoff_distance").read(rtIO->acxml).value() >
EndnodeReadOnly<double>("assessment/takeoff/takeoff_distance_normal_safety").read(rtIO->acxml).value());
bool landing_check(EndnodeReadOnly<double>("requirements_and_specifications/requirements/top_level_aircraft_requirements/takeoff_distance").read(rtIO->acxml).value() >
bool landing_check(EndnodeReadOnly<double>("requirements_and_specifications/requirements/top_level_aircraft_requirements/landing_field_length").read(rtIO->acxml).value() >
EndnodeReadOnly<double>("assessment/landing/needed_runway_length").read(rtIO->acxml).value());
bool approach_check(approach_speed_required + ACCURACY_LOW >= // ACCURACY_LOW added to avoid floating point issues for equal values
EndnodeReadOnly<double>("assessment/performance/approach/approach_speed").read(rtIO->acxml).value());
......
mission_analysis/src/standard_mission/standard_mission/standard_mission.h
View file @ e90e39d8
......@@ -253,7 +253,7 @@ class StandardMission : public Strategy {
double end_L_over_D; /**< Lift over drag coefficient at the end of the segment [-] */
double end_specific_air_range; /**< Specific air range at the end of the segment [m/kg] */
std::string end_aero_config; /**< Aerodynamic configuration at the end of the segment */
double end_glidepath_angle; /**< Path angle at the end of the segment [deg] */
double end_glide_path_angle; /**< Path angle at the end of the segment [deg] */
double end_TAS; /**< True airspeed at the end of the segment [m/s] */
double end_mach; /**< Mach number at the end of the segment [-] */
double end_CAS; /**< Calibrated airspeed at the end of the segment [m/s] */
......@@ -459,7 +459,7 @@ class StandardMission : public Strategy {
* \param fc: pointer to a flight condition object
* \param a_mission_step: reference to a mission step [-]
* \param simulation_mode Constant reference to a switch if the function should run the estimation mode or the real mode; default is the real mode
* \return range_for_descent if simulation_mode is active, the needed range to descent to approach is returned [m]
* \return range_for_descent if simulation_mode is active, the needed range to descend to approach is returned [m]
*/
double calculate_climb_or_descent(OperatingConditions* oc, FlightConditions* fc,
const uint16_t& a_mission_step, const bool& simulation_mode = false);
......@@ -467,7 +467,7 @@ class StandardMission : public Strategy {
* \param last_segment_free_flight_switch Constant reference to a switch if the last mission segment is a free_flight segment
*/
void estimate_descent(const bool& last_segment_free_flight_switch);
/** \brief Function estimates the descend distance of the approach route
/** \brief Function estimates the descent distance of the approach route
* \param oc: reference to an operating condition object
* \param fc: reference to a flight condition object
* \param top_of_descent_mass: mass at top of descent [kg]
......@@ -485,21 +485,21 @@ class StandardMission : public Strategy {
*/
std::pair<double, double> iterate_descent(double* segmend_end_range, double* top_of_descent_aircraft_mass, const double& current_descent_distance,
const OperatingConditions& oc, const FlightConditions& fc, const uint16_t& a_mission_step);
/** \brief Function to calculate glideslope interception
/** \brief Function to calculate glide_slope interception
* \param oc: pointer to an operating condition object
* \param fc: pointer to a flight condition object
* \param a_mission_step: reference to a mission step [-]
* \param simulation_mode Constant reference to a switch if the function should run the estimation mode or the real mode; default is the real mode
* \return range_for_descent Needed range to descent to perform a glide slope landing [m]
* \return range_for_descent Needed range to descend to perform a glide slope landing [m]
*/
double glideslope_interception(OperatingConditions* oc, FlightConditions* fc, const uint16_t& a_mission_step,
double glide_slope_interception(OperatingConditions* oc, FlightConditions* fc, const uint16_t& a_mission_step,
const bool& simulation_mode = false);
/** \brief Function for landing
* \param oc: pointer to an operating condition object
* \param fc: pointer to a flight condition object
* \param a_mission_step: reference to a mission step [-]
* \param simulation_mode Constant reference to a switch if the function should run the estimation mode or the real mode; default is the real mode
* \return range_for_descentToTouchdown the needed range to descent from screen height (50ft) to touchdown is returned [m]
* \return range_for_descentToTouchdown the needed range to descend from screen height (50ft) to touchdown is returned [m]
*/
double landing(OperatingConditions* oc, FlightConditions* fc, const uint16_t& a_mission_step, const bool& simulation_mode = false);
/** \brief Function changes speed at constant rate of climb
......@@ -507,7 +507,7 @@ class StandardMission : public Strategy {
* \param fc: pointer to a flight condition object
* \param a_mission_step: reference to a mission step [-]
* \param simulation_mode Constant reference to a switch if the function should run the estimation mode or the real mode; default is the real mode
* \return range_for_descent if simulation_mode is active, the needed range to descent to approach is returned [m]
* \return range_for_descent if simulation_mode is active, the needed range to descend to approach is returned [m]
*/
double change_speed_at_constant_ROC(OperatingConditions* oc, FlightConditions* fc,
const uint16_t& a_mission_step, const bool& simulation_mode = false);
......@@ -517,7 +517,7 @@ class StandardMission : public Strategy {
* \param fc: pointer to a flight condition object
* \param a_mission_step: reference to a mission step [-]
* \param simulation_mode Constant reference to a switch if the function should run the estimation mode or the real mode; default is the real mode
* \return descentRange if simulation_mode is active, the needed range to descent to approach is returned [m]
* \return descent_range if simulation_mode is active, the needed range to descend to approach is returned [m]
*/
double change_altitude_at_constant_speed(OperatingConditions* oc, FlightConditions* fc,
const uint16_t& a_mission_step, const bool& simulation_mode = false);
......@@ -549,7 +549,7 @@ class StandardMission : public Strategy {
*/
void calculate_econ_cruise_speed(double* econ_mach_number, const double& altitude, const double CI,
const double& aircraft_mass, const std::string& config, const std::string& rating);
/** \brief Function simulates a flight level change.
/** \brief Function simulates a flight level change to check if it is possible
* \param fc: pointer to a flight conditions
* \param oc: constant reference to object of operating conditions
* \param altitude_change_step: altitude change within the step [m]
......@@ -595,7 +595,7 @@ class StandardMission : public Strategy {
*/
void set_segment_initial_conditions(FlightConditions* fc, const bool& use_mission_condition = true, const double& an_end_CL = NAN);
/** \brief Function sets initial segment iteration start values
* \details values for glidepath_angle, a, liftcoefficient, drag and thrust are set
* \details values for glide_path_angle, a, liftcoefficient, drag and thrust are set
* \param fc: pointer to a flight condition object
* \param an_end_CL constant reference to an end lift coefficient of the segment; if not preset, it is calculated from constant level flight [-]
*/
......@@ -653,13 +653,10 @@ class StandardMission : public Strategy {
/** \brief Function decides whether the flight level is changed.
* \param cruise_flight_condition: constant reference to object of cruise flight conditions
* \param next_FL_flight_condition: constant reference to object of flight level change flight conditions
* \param cost_index: reference to cost index [kg/min], scaled 0 to 999 according to Sperry/Honeywell [1]
* \param cruise_range: reference to the cruise range from reference mission point (end_range) to end of constant level cruise segment [m]
* \param cruise_fuel: reference to the cruise fuel used from reference mission point (end_range) to end of constant level cruise segment [kg]
* \return true or false [-]
*/
bool decide_FL_change(const FlightConditions& cruise_flight_condition, const FlightConditions& next_FL_flight_condition,
const double& cost_index, const double& cruise_range, const double& cruise_fuel);
bool decide_FL_change(const FlightConditions& cruise_flight_condition, const FlightConditions& next_FL_flight_condition, const double& cruise_range);
/** \brief Function calculates the optimum flight level
* \param optimum_altitude: pointer to altitude [m]
* \param mach: reference to a Mach number [-]
......@@ -825,10 +822,10 @@ class StandardMission : public Strategy {
inline double calculate_cost_function(const int &energy_carrier_id, const double &mach, const double &altitude,
const double &aircraft_mass, const std::string& config, const std::string &rating,
const double &bleed, const double &shaft_power, const double& cost_index) {
double theCostFunction;
theCostFunction = 1. / this->static_flight_specific_air_range(energy_carrier_id, mach, altitude, aircraft_mass, config, rating) +
double the_cost_function;
the_cost_function = 1. / this->static_flight_specific_air_range(energy_carrier_id, mach, altitude, aircraft_mass, config, rating) +
cost_index / convertUnit(MINUTE, SECOND, 1.) / convertUnit(MACH, TRUEAIRSPEED, altitude, this->atm, mach);
return theCostFunction;
return the_cost_function;
}
/** \brief Function to find number of elements having the same keywords in their names
* \param xml xml file
......