app/src/aircrafts.cpp - master - wmigor/z-plane

app/src/aircrafts.cpp
308 строк8 KB
wmigor
сохранение/загрузка
8 часов назад
8 часов назад81be381
#include "aircrafts.h"
#include "Wheel.h"
#include <asim/Constants.h>
#include <asim/Propeller.h>
#include <asim/PistonEngine.h>

using namespace asim;


std::vector<Propeller::Element> buildPropellerElementsC172()
{
	std::vector<Propeller::Element> elements;
	elements.resize(10);

	elements[0].radius = 0.1426;
	elements[0].chord = 0.0845;
	elements[0].pitch = glm::radians(56.35);
	elements[0].length = 0.0853;

	elements[1].radius = 0.2279;
	elements[1].chord = 0.1132;
	elements[1].pitch = glm::radians(45.81);
	elements[1].length = 0.0853;

	elements[2].radius = 0.3131;
	elements[2].chord = 0.1419;
	elements[2].pitch = glm::radians(36.83);
	elements[2].length = 0.0853;

	elements[3].radius = 0.3984;
	elements[3].chord = 0.1392;
	elements[3].pitch = glm::radians(30.48);
	elements[3].length = 0.0853;

	elements[4].radius = 0.4836;
	elements[4].chord = 0.1268;
	elements[4].pitch = glm::radians(25.87);
	elements[4].length = 0.0853;

	elements[5].radius = 0.5689;
	elements[5].chord = 0.1144;
	elements[5].pitch = glm::radians(22.40);
	elements[5].length = 0.0853;

	elements[6].radius = 0.6541;
	elements[6].chord = 0.1021;
	elements[6].pitch = glm::radians(19.72);
	elements[6].length = 0.0853;

	elements[7].radius = 0.7394;
	elements[7].chord = 0.0897;
	elements[7].pitch = glm::radians(17.59);
	elements[7].length = 0.0853;

	elements[8].radius = 0.8246;
	elements[8].chord = 0.0774;
	elements[8].pitch = glm::radians(15.87);
	elements[8].length = 0.0853;

	elements[9].radius = 0.9099;
	elements[9].chord = 0.0651;
	elements[9].pitch = glm::radians(14.45);
	elements[9].length = 0.0853;

	return elements;
}

std::shared_ptr<Airfoil> createNaca2412Airfoil(double zeroLiftAngle, const std::string &name)
{
	auto airfoil = std::make_shared<Airfoil>();
	airfoil->name = name;
	airfoil->baseSettings.zeroLiftAngle = zeroLiftAngle;
	return airfoil;
}

std::shared_ptr<Airfoil> createClarkAirfoil()
{
	auto airfoil = std::make_shared<Airfoil>();
	airfoil->name = "Clark";
	airfoil->baseSettings.zeroLiftAngle = glm::radians(-5.25);
	airfoil->baseSettings.dragMin = 0.01;
	airfoil->baseSettings.liftSlope = 5.1;
	return airfoil;
}

void addContactPoints(const AircraftPhysics *physics, RigidBody *body)
{
	for (auto wing : physics->getWings())
	{
		const auto &sections = wing->getSections();
		if (sections.empty())
			continue;

		const auto &section = sections[sections.size() - 1];
		auto point = section.getPosition(1.0);
		body->addContactPoint(point, 0.1);
		if (section.mirror)
			body->addContactPoint(glm::reflect(point, asim::Constants::Right), 0.1);
	}

	for (auto thruster : physics->getThrusters())
		body->addContactPoint(thruster->position, 0.1);
}

Aircraft *createC172()
{
	auto physics = new AircraftPhysics();
	physics->mass = 930.0;
	physics->inertia = glm::dvec3(2644.0, 4372.0, 1285.0);
	physics->massCenter = glm::dvec3(0.0, 1.0, 0.0);

	physics->addWheel(asim::Wheel {glm::dvec3(0.0, -0.1, -0.7), 0.2, glm::radians(30.0)});
	physics->addWheel(asim::Wheel {glm::dvec3(-1.0, 0.0, 0.7), 0.2, 0.0});
	physics->addWheel(asim::Wheel {glm::dvec3(1.0, 0.0, 0.7), 0.2, 0.0});
	auto aircraft = new Aircraft(physics);
	auto body = aircraft->getBody();
	body->position.y = 2.0;

	auto engine = new PistonEngine(160.0 * Constants::HP_TO_W, 2700.0 / Constants::TO_RPM);

	Propeller::Config propellerConfig(createClarkAirfoil());
	auto elements = buildPropellerElementsC172();
	auto propeller = new Propeller(propellerConfig, elements, engine);
	propeller->position = glm::dvec3(0.0, 1.0, -2.2);
	physics->addThruster(propeller);

	Fuselage::Config fuselageConfig;
	fuselageConfig.position = glm::dvec3(0.0, 1.0, 2.0);

	auto naca2412zero = createNaca2412Airfoil(0.0, "NACA2412_zero");
	auto naca2412 = createNaca2412Airfoil(glm::radians(-2.5), "NACA2412");

	physics->addFuselage(new Fuselage(fuselageConfig));

	{
		WingSection wing(naca2412);
		wing.span = 2.6215;
		wing.chord = 1.585;
		wing.dihedral = glm::radians(1.0);
		wing.incidence = glm::radians(3.0);
		wing.position = glm::dvec3(0.0, 1.509, -0.09);

		ControlSurface flap;
		flap.type = ControlSurfaceType::Flap;
		flap.start = 0.3;
		flap.end = 1.0;
		flap.fraction = 0.3;
		flap.minAngle = glm::radians(0.0);
		flap.maxAngle = glm::radians(30.0);
		wing.controlSurfaces.push_back(flap);

		WingSection wing2(naca2412);
		wing2.span = 3.8785;
		wing2.taper = 0.73;
		wing2.sweep = glm::radians(-2.5);
		wing2.twist = glm::radians(-3.0);
		wing2.twistPower = 1.5;
		wing2.dihedral = glm::radians(2.5);

		ControlSurface aileron;
		aileron.type = ControlSurfaceType::Aileron;
		aileron.start = 0.0;
		aileron.end = 0.95;
		aileron.fraction = 0.2;
		aileron.minAngle = glm::radians(-20.0);
		aileron.maxAngle = glm::radians(10.0);
		wing2.controlSurfaces.push_back(aileron);

		physics->addWing(new asim::Wing(std::vector<WingSection>({wing, wing2})));
	}

	{
		WingSection elevator(naca2412zero);
		elevator.span = 1.7;
		elevator.chord = 1.3;
		elevator.taper = 0.5;
		elevator.position = glm::dvec3(0.0, 1.0, 4.82);

		ControlSurface flap;
		flap.type = ControlSurfaceType::Elevator;
		flap.start = 0.0;
		flap.end = 1.0;
		flap.fraction = 0.4;
		flap.minAngle = glm::radians(-23.0);
		flap.maxAngle = glm::radians(15.0);
		elevator.controlSurfaces.push_back(flap);

		physics->addWing(new asim::Wing(std::vector<WingSection>({elevator})));
	}

	{
		WingSection rudder(naca2412zero);
		rudder.span = 1.7;
		rudder.chord = 1.5;
		rudder.taper = 0.4;
		rudder.sweep = glm::radians(39.0);
		rudder.dihedral = glm::radians(90.0);
		rudder.position = glm::dvec3(0.0, 1.1, 4.665);
		rudder.mirror = false;

		ControlSurface flap;
		flap.type = ControlSurfaceType::Rudder;
		flap.start = 0.0;
		flap.end = 1.0;
		flap.fraction = 0.5;
		flap.minAngle = glm::radians(-17.7);
		flap.maxAngle = glm::radians(17.7);
		rudder.controlSurfaces.push_back(flap);

		physics->addWing(new asim::Wing(std::vector<WingSection>({rudder})));
	}

	addContactPoints(physics, body);

	return aircraft;
}

Aircraft *createYak55m()
{
	auto physics = new AircraftPhysics();
	auto aircraft = new Aircraft(physics);
	auto body = aircraft->getBody();
	body->setMass(1000.0);
	body->setInertia(glm::dvec3(3000.0, 3500.0, 1200.0));
	body->setMassCenter(glm::dvec3(0.0, 1.0, 0.0));

	auto naca2412zero = createNaca2412Airfoil(0.0, "NACA2412_zero");
	auto naca2412 = createNaca2412Airfoil(glm::radians(-2.5), "NACA2412");

	{
		WingSection wing(naca2412);
		wing.span = 4.65;
		wing.chord = 2.095;
		wing.taper = 0.5;
		wing.sweep = glm::radians(-1.0);
		wing.dihedral = glm::radians(2.0);
		wing.twist = glm::radians(-2.5);
		wing.incidence = glm::radians(1.5);
		wing.position = glm::dvec3(0.0, 0.831, -0.1);

		ControlSurface flap;
		flap.type = ControlSurfaceType::Flap;
		flap.start = 0.1;
		flap.end = 0.4;
		flap.fraction = 0.4;
		flap.minAngle = glm::radians(0.0);
		flap.maxAngle = glm::radians(30.0);
		wing.controlSurfaces.push_back(flap);

		ControlSurface aileron;
		aileron.type = ControlSurfaceType::Aileron;
		aileron.start = 0.6;
		aileron.end = 0.95;
		aileron.fraction = 0.2;
		aileron.minAngle = glm::radians(0.0);
		aileron.maxAngle = glm::radians(30.0);
		wing.controlSurfaces.push_back(aileron);

		physics->addWing(new asim::Wing(std::vector<WingSection>({wing})));
	}

	{
		WingSection elevator(naca2412zero);
		elevator.span = 1.607;
		elevator.chord = 1.184;
		elevator.taper = 0.6;
		elevator.sweep = glm::radians(2.0);
		elevator.dihedral = glm::radians(0.0);
		elevator.position = glm::dvec3(0.0, 1.387, 4.54);

		ControlSurface flap;
		flap.type = ControlSurfaceType::Elevator;
		flap.start = 0.0;
		flap.end = 1.0;
		flap.fraction = 0.5;
		flap.minAngle = glm::radians(-30.0);
		flap.maxAngle = glm::radians(30.0);
		elevator.controlSurfaces.push_back(flap);

		physics->addWing(new asim::Wing(std::vector<WingSection>({elevator})));
	}

	{
		WingSection rudder(naca2412zero);
		rudder.span = 1.554;
		rudder.chord = 1.441;
		rudder.taper = 0.7;
		rudder.sweep = glm::radians(7.0);
		rudder.dihedral = glm::radians(90.0);
		rudder.position = glm::dvec3(0.0, 1.085, 4.54);
		rudder.mirror = false;

		ControlSurface flap;
		flap.type = ControlSurfaceType::Rudder;
		flap.start = 0.0;
		flap.end = 1.0;
		flap.fraction = 0.5;
		flap.minAngle = glm::radians(-30.0);
		flap.maxAngle = glm::radians(30.0);
		rudder.controlSurfaces.push_back(flap);

		physics->addWing(new asim::Wing(std::vector<WingSection>({rudder})));
	}

	addContactPoints(physics, body);

	return aircraft;
}