diff --git a/wing_design/src/taw/cantilever/cantileverWingDesignTaw.cpp b/wing_design/src/taw/cantilever/cantileverWingDesignTaw.cpp
index b2f57e1fe5e1c3f926c858313b144f721d427357..12fbb32dfe9ee15be0998704a4e9a8785e6cae3b 100644
--- a/wing_design/src/taw/cantilever/cantileverWingDesignTaw.cpp
+++ b/wing_design/src/taw/cantilever/cantileverWingDesignTaw.cpp
@@ -216,17 +216,10 @@ void Wing::standard_design() {
config->high_lift_device_type_trailing_edge.value());
data->control_devices = devices;
data->control_devices_deflections = deflections;
- /* Set control device deflections for user defined control devices */
- // if (config->control_device_mode.value().compare("mode_0") == 0) {
- // for (auto item : config->user_defined_control_devices) {
- // data->control_devices_deflections.push_back(
- // {item.deflection_full_negative.value(), item.deflection_full_positive.value()});
- // }
- // }
/* Check control device boundaries - if inside fuselage */
- if ((config->control_device_mode.value().compare("mode_0") == 0) &&
- (rtIO->aircraft_configuration_type().compare("tube_and_wing") == 0)) {
+ if ((config->control_device_mode.value() == "mode_0") &&
+ (rtIO->aircraft_configuration_type() == "tube_and_wing")) {
double eta_fuselage_max = geom2::measure::width_max(data->fuselage) / geom2::measure::span(data->wing);
for (auto& device : data->control_devices) {
size_t sec_id = 0;
@@ -248,8 +241,8 @@ bool Wing::is_wing_kinked_check() {
myRuntimeInfo->out << "Wing kink check ..." << std::endl;
/* Check if mounting is low & landing gear mounted on wing */
- if (data->specification_wing_mounting.value().compare("low") == 0 &&
- data->specification_landing_gear_mounting.value().compare("wing_mounted") == 0) {
+ if (data->specification_wing_mounting.value()== "low" &&
+ data->specification_landing_gear_mounting.value() == "wing_mounted") {
myRuntimeInfo->out << "Wing is kinked ... [TRUE]" << std::endl;
return true;
} else {
@@ -262,7 +255,7 @@ double Wing::get_max_thickness_to_chord_ratio() {
// Get maximum thickness to chord ratio based on wing profile and thickness mode
// If user - get maximum thickness from elements
// Else use max_thickness to chord ratio from sweep calculation method
- if (config->wing_profile_and_thickness_calculation_mode.value().compare("mode_0") == 0) {
+ if (config->wing_profile_and_thickness_calculation_mode.value() == "mode_0") {
std::vector<double> to_check;
for (auto item : config->user_thickness_to_chord) {
to_check.push_back(item.value());
@@ -646,8 +639,7 @@ void Wing::flops_mass() {
const double W3 = A6 * (1.0 - 0.3 * config->flops_fcomp.value()) * pow(wing_area_sqrft, A7);
// Wing bending material weight intertia relief adjustment
- bool wing_mounted_engines = true; /* needs to be updated */
- const int NEW = 2;
+ const int NEW = data->specification_number_of_wing_mounted_engines;
const double CAYE = 1.0 - 0.03 * NEW;
const double W1 = (dg * CAYE * W1NIR + W2 + W3) / (1.0 + W1NIR) - W2 - W3;
@@ -682,21 +674,16 @@ void Wing::flops_mass() {
myRuntimeInfo->out << "y ... " << data->wing_mass_properties.data["y"].value() << std::endl;
myRuntimeInfo->out << "z ... " << data->wing_mass_properties.data["z"].value() << std::endl;
- // Calculate wing inertia's ... To Do
}
/**
- * \brief Chiozzotto weight estimation relationship mass estimation
+ * \brief Chiozzotto weight estimation relationship mass estimation - assumes symmetric engine distribution on wings
*
*/
void Wing::chiozzotto_wer_mass() {
myRuntimeInfo->out << "Wing mass estimation using ... CHIOZZOTTO" << std::endl;
myRuntimeInfo->out << "Calculating ... " << std::endl;
- std::cout << "===================================" << std::endl;
- std::cout << "========= HARDCODED VALUES ========" << std::endl;
- std::cout << "In function: " << __func__ << std::endl;
- std::cout << "L#664 - Engines_mass_and_eta {{5307.267993,0.3}}" << std::endl;
- std::cout << "===================================" << std::endl;
+
std::map<std::string, std::tuple<double, double>> min_max_mtom = {
{"AL ASW", {20000, 250000}}, {"AL USW", {20000, 250000}}, {"AL FSW", {20000, 250000}},
@@ -749,9 +736,8 @@ void Wing::chiozzotto_wer_mass() {
// Vector with data for one half ->
// More than one engine -> k_e = k_e_1 * k_e_2
- std::vector<std::tuple<double, double>> engines_mass_and_eta = {{5307.267993, 0.3}};
double wing_loading = data->sizing_point_wing_loading.value();
- if (data->sizing_point_wing_loading.unit().compare("kg/m^2") == 0) {
+ if (data->sizing_point_wing_loading.unit() == "kg/m^2") {
wing_loading *= G_FORCE;
}
@@ -764,6 +750,8 @@ void Wing::chiozzotto_wer_mass() {
const double pressure_at_zero = isa.getPressureISA(0.0);
const double pressure_at_design_altitude = isa.getPressureISA(data->specification_design_altitude.value());
+ std::vector<std::tuple<double, double>> engines_mass_and_eta = data->wing_mounted_engine_data;
+
// Calculation of EAS Design
const double v_eas_design = data->specification_design_mach.value() * speed_of_sound_at_zero *
sqrt(pressure_at_design_altitude / pressure_at_zero);
@@ -847,7 +835,9 @@ void Wing::chiozzotto_wer_mass() {
// Engine relief factor
double k_e = 1.;
for (auto engine : engines_mass_and_eta) {
- const auto [engine_mass, engine_relative_spanwise_position] = engine;
+ const auto [engine_mass, engine_spanwise_position] = engine;
+ /* If engines exist, the spanwise position is absolute, if engines not exist, the default values are in rel. half span */
+ double engine_relative_spanwise_position = data->engines_exist ? std::fabs(engine_spanwise_position)/half_span : engine_spanwise_position;
k_e *= (1 - C_er * pow(engine_relative_spanwise_position, E_eta_er) * pow(engine_mass / mtom, E_K_er));
}
// Secondary structure mass
diff --git a/wing_design/src/taw/tawWingDesignData.cpp b/wing_design/src/taw/tawWingDesignData.cpp
index dbd444959f335073706dfe7d3eb1f3dc905b6ada..665be368eb6cd9f6167cb80ac092c1dbdc0db565 100644
--- a/wing_design/src/taw/tawWingDesignData.cpp
+++ b/wing_design/src/taw/tawWingDesignData.cpp
@@ -46,12 +46,50 @@ void taw::cantilever::WingDesignData::read(const node& xml) {
specification_maximum_load_factor.read(xml);
sizing_point_wing_loading.read(xml);
mtom_mass_properties.read(xml);
- read_number_of_wing_mounted_engines(xml);
+ read_wing_mounted_engine_information(xml);
}
-void taw::cantilever::WingDesignData::read_number_of_wing_mounted_engines(const node& xml) {
- auto propulsors = xml.find("requirements_and_specifications/design_specification/propulsion/propulsor",1);
- std::cout << "SIZE PROPULSORS: " << propulsors << std::endl;
+void taw::cantilever::WingDesignData::read_wing_mounted_engine_information(const node& xml) {
+ auto propulsors_reqs = xml.getVector("aircraft_exchange_file/requirements_and_specifications/design_specification/propulsion/propulsor",1);
+
+ std::vector<int> wing_mounted_engine_ids;
+ for (size_t i = 0; i < propulsors_reqs.size(); ++i) {
+ if (EndnodeReadOnly<std::string>("position/parent_component").read(*propulsors_reqs.at(i)).value() == "wing") {
+ specification_number_of_wing_mounted_engines++;
+ wing_mounted_engine_ids.push_back(i);
+ }
+ }
+ /* floor uneven number of engines -> chiozzotto only uses one side of the wing */
+ size_t number_of_wing_mounted_engine_half = static_cast<size_t>(std::floor(specification_number_of_wing_mounted_engines / 2.));
+ if (xml.find("aircraft_exchange_file/component_design/propulsion") == 0) {
+ myRuntimeInfo->out << "Using default values for engines if chiozzotto mass method is selected" << std::endl;
+ myRuntimeInfo->out << "Assume engine + pylon + nacelle ~4000kg and postion between 0.35 and 0.8 eta, starting at 0.35 for first engine" << std::endl;
+ engines_exist = false;
+
+ double engine_mass = 4000.0; /*<-- 4000kg per engine assumed each */
+ double eta_min = 0.35;
+ double eta_max = 0.8;
+ for(size_t i = 0; i < number_of_wing_mounted_engine_half; ++i) {
+ double eta_engine = std::lerp(eta_min,eta_max,i/number_of_wing_mounted_engine_half);
+ wing_mounted_engine_data.push_back({engine_mass, eta_engine});
+ }
+ }
+ else {
+ auto propulsors_comp = xml.getVector("aircraft_exchange_file/component_design/propulsion/specific/propulsion",1);
+ for (size_t i = 0; i < number_of_wing_mounted_engine_half; ++i) {
+ MassPropertiesIO pylon = MassPropertiesIO("nacelle@0","nacelle");
+ MassPropertiesIO nacelle = MassPropertiesIO("pylon@0","pylon");
+ MassPropertiesIO engine = MassPropertiesIO("engine","engine");
+ pylon.read(*propulsors_comp.at(wing_mounted_engine_ids.at(i)));
+ nacelle.read(*propulsors_comp.at(wing_mounted_engine_ids.at(i)));
+ engine.read(*propulsors_comp.at(wing_mounted_engine_ids.at(i)));
+ double propulsion_mass = pylon.data["mass"].value() + nacelle.data["mass"].value() + engine.data["mass"].value();
+ double propulsion_position = engine.data["y"].value();
+ wing_mounted_engine_data.push_back({propulsion_mass,propulsion_position});
+
+ }
+ }
+
}
void taw::cantilever::WingDesignData::read_fuselage(std::filesystem::path path,
diff --git a/wing_design/src/taw/tawWingDesignData.h b/wing_design/src/taw/tawWingDesignData.h
index a82486f113cf468795a1f09b3198d5c5b5da9004..60f3f80ba84cfe0a0930339c0d60a8f19962debf 100644
--- a/wing_design/src/taw/tawWingDesignData.h
+++ b/wing_design/src/taw/tawWingDesignData.h
@@ -27,7 +27,8 @@ class WingDesignData {
void read(const node& xml);
void read_fuselage(std::filesystem::path acxml, std::filesystem::path geometry_data_dir);
- void read_number_of_wing_mounted_engines(const node& xml);
+ void read_wing_mounted_engine_information(const node& xml);
+
void update(node& xml);
void update_wing(node& xml);
@@ -44,7 +45,9 @@ class WingDesignData {
EndnodeReadOnly<double> sizing_point_wing_loading;
EndnodeReadOnly<double> track_based_relative_kink;
Endnode<double> spanwise_kink;
- uint8_t specification_number_of_wing_mounted_engines;
+ size_t specification_number_of_wing_mounted_engines;
+ std::vector<std::tuple<double,double>> wing_mounted_engine_data;
+ bool engines_exist = true;
MassPropertiesIO mtom_mass_properties;
MassPropertiesIO wing_mass_properties;