Convert DampingMoment listener to simulation extension
This commit is contained in:
JoePfeiffer
parent
c3d2d5fc16
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17a4f1ffdb
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package net.sf.openrocket.simulation.extension.impl;
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import java.util.ArrayList;
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import java.util.List;
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import java.util.Map;
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import org.slf4j.Logger;
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import org.slf4j.LoggerFactory;
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import net.sf.openrocket.aerodynamics.AerodynamicCalculator;
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import net.sf.openrocket.aerodynamics.AerodynamicForces;
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import net.sf.openrocket.aerodynamics.FlightConditions;
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import net.sf.openrocket.aerodynamics.WarningSet;
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import net.sf.openrocket.motor.MotorConfiguration;
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import net.sf.openrocket.rocketcomponent.FlightConfiguration;
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import net.sf.openrocket.rocketcomponent.RocketComponent;
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import net.sf.openrocket.simulation.FlightDataBranch;
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import net.sf.openrocket.simulation.FlightDataType;
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import net.sf.openrocket.simulation.SimulationConditions;
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import net.sf.openrocket.simulation.SimulationStatus;
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import net.sf.openrocket.simulation.exception.SimulationException;
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import net.sf.openrocket.simulation.extension.AbstractSimulationExtension;
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import net.sf.openrocket.simulation.listeners.AbstractSimulationListener;
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import net.sf.openrocket.unit.UnitGroup;
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public class DampingMoment extends AbstractSimulationExtension {
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private static final Logger log = LoggerFactory.getLogger(DampingMoment.class);
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// Save it as a FlightDataType
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private static final FlightDataType cdm = FlightDataType.getType("Damping moment coefficient", "Cdm", UnitGroup.UNITS_COEFFICIENT);
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private static final ArrayList<FlightDataType> types = new ArrayList<FlightDataType>();
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DampingMoment() {
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types.add(cdm);
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}
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@Override
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public List<FlightDataType> getFlightDataTypes() {
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return types;
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}
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@Override
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public void initialize(SimulationConditions conditions) throws SimulationException {
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log.debug("initializing...");
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conditions.getSimulationListenerList().add(new DampingMomentListener());
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}
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@Override
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public String getName() {
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return "Damping Moment Coeficient(Cdm)";
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}
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@Override
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public String getDescription() {
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return "Calculate damping moment coefficient after every simulation step and publish to FlightData as Cdm";
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}
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private class DampingMomentListener extends AbstractSimulationListener {
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@Override
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public FlightConditions postFlightConditions(SimulationStatus status, FlightConditions flightConditions) throws SimulationException {
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//status.getFlightData().setValue(cdm, aerodynamicPart + propulsivePart);
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status.getFlightData().setValue(cdm, calculate(status, flightConditions));
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return flightConditions;
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}
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private double calculate(SimulationStatus status, FlightConditions flightConditions) {
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// Work out the propulsive/jet damping part of the moment.
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// dm/dt = (thrust - ma)/v
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FlightDataBranch data = status.getFlightData();
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List<Double> mpAll = data.get(FlightDataType.TYPE_MOTOR_MASS);
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List<Double> time = data.get(FlightDataType.TYPE_TIME);
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if (mpAll == null || time == null) {
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return Double.NaN;
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}
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int len = mpAll.size();
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// This isn't as accurate as I would like
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double mdot = Double.NaN;
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if (len > 2) {
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// Using polynomial interpolator for derivative. Doesn't help much
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//double[] x = { time.get(len-5), time.get(len-4), time.get(len-3), time.get(len-2), time.get(len-1) };
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//double[] y = { mpAll.get(len-5), mpAll.get(len-4), mpAll.get(len-3), mpAll.get(len-2), mpAll.get(len-1) };
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//PolyInterpolator interp = new PolyInterpolator(x);
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//double[] coeff = interp.interpolator(y);
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//double dt = .01;
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//mdot = (interp.eval(x[4], coeff) - interp.eval(x[4]-dt, coeff))/dt;
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mdot = (mpAll.get(len - 1) - mpAll.get(len - 2)) / (time.get(len - 1) - time.get(len - 2));
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}
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double cg = data.getLast(FlightDataType.TYPE_CG_LOCATION);
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// find the maximum distance from nose to nozzle.
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double nozzleDistance = 0;
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FlightConfiguration config = status.getConfiguration();
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for (MotorConfiguration inst : config.getActiveMotors()) {
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double x_position= inst.getX();
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double x = x_position + inst.getMotor().getLaunchCGx();
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if (x > nozzleDistance) {
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nozzleDistance = x;
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}
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}
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// now can get the propulsive part
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double propulsivePart = mdot * Math.pow(nozzleDistance - cg, 2);
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// Work out the aerodynamic part of the moment.
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double aerodynamicPart = 0;
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AerodynamicCalculator aerocalc = status.getSimulationConditions().getAerodynamicCalculator();
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// Must go through each component ...
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Map<RocketComponent, AerodynamicForces> forces = aerocalc.getForceAnalysis(status.getConfiguration(), flightConditions, status.getWarnings());
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for (Map.Entry<RocketComponent, AerodynamicForces> entry : forces.entrySet()) {
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RocketComponent comp = entry.getKey();
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if (!comp.isAerodynamic())
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continue;
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//System.out.println(comp.toString());
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double CNa = entry.getValue().getCNa(); //?
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double Cp = entry.getValue().getCP().length();
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double z = comp.getAxialOffset();
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aerodynamicPart += CNa * Math.pow(z - Cp, 2);
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}
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double v = flightConditions.getVelocity();
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double rho = flightConditions.getAtmosphericConditions().getDensity();
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double ar = flightConditions.getRefArea();
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aerodynamicPart = aerodynamicPart * .5 * rho * v * ar;
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return aerodynamicPart + propulsivePart;
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}
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}
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}
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@ -0,0 +1,13 @@
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package net.sf.openrocket.simulation.extension.impl;
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import net.sf.openrocket.plugin.Plugin;
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import net.sf.openrocket.simulation.extension.AbstractSimulationExtensionProvider;
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@Plugin
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public class DampingMomentProvider extends AbstractSimulationExtensionProvider {
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public DampingMomentProvider() {
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super(DampingMoment.class, "Post-step flight conditions", "Damping Moment Coefficient (Cdm)");
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}
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}
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@ -1,116 +0,0 @@
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package net.sf.openrocket.simulation.listeners.example;
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import java.util.List;
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import java.util.Map;
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import net.sf.openrocket.aerodynamics.AerodynamicCalculator;
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import net.sf.openrocket.aerodynamics.AerodynamicForces;
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import net.sf.openrocket.aerodynamics.FlightConditions;
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import net.sf.openrocket.aerodynamics.WarningSet;
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import net.sf.openrocket.motor.MotorConfiguration;
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import net.sf.openrocket.rocketcomponent.FlightConfiguration;
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import net.sf.openrocket.rocketcomponent.RocketComponent;
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import net.sf.openrocket.simulation.FlightDataBranch;
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import net.sf.openrocket.simulation.FlightDataType;
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import net.sf.openrocket.simulation.SimulationStatus;
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import net.sf.openrocket.simulation.exception.SimulationException;
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import net.sf.openrocket.simulation.listeners.AbstractSimulationListener;
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import net.sf.openrocket.unit.UnitGroup;
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public class DampingMoment extends AbstractSimulationListener {
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private static final FlightDataType type = FlightDataType.getType("Damping moment coefficient", "Cdm", UnitGroup.UNITS_COEFFICIENT);
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// unused
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//private static final FlightDataType[] typeList = { type };
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@Override
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public FlightConditions postFlightConditions(SimulationStatus status, FlightConditions flightConditions) throws SimulationException {
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// Save it as a flightdatatype
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//status.getFlightData().setValue(type, aerodynamicPart + propulsivePart);
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status.getFlightData().setValue(type, calculate(status, flightConditions));
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return flightConditions;
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}
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private double calculate(SimulationStatus status, FlightConditions flightConditions) {
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// Work out the propulsive/jet damping part of the moment.
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// dm/dt = (thrust - ma)/v
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FlightDataBranch data = status.getFlightData();
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List<Double> mpAll = data.get(FlightDataType.TYPE_MOTOR_MASS);
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List<Double> time = data.get(FlightDataType.TYPE_TIME);
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if (mpAll == null || time == null) {
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return Double.NaN;
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}
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int len = mpAll.size();
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// This isn't as accurate as I would like
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double mdot = Double.NaN;
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if (len > 2) {
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// Using polynomial interpolator for derivative. Doesn't help much
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//double[] x = { time.get(len-5), time.get(len-4), time.get(len-3), time.get(len-2), time.get(len-1) };
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//double[] y = { mpAll.get(len-5), mpAll.get(len-4), mpAll.get(len-3), mpAll.get(len-2), mpAll.get(len-1) };
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//PolyInterpolator interp = new PolyInterpolator(x);
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//double[] coeff = interp.interpolator(y);
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//double dt = .01;
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//mdot = (interp.eval(x[4], coeff) - interp.eval(x[4]-dt, coeff))/dt;
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mdot = (mpAll.get(len - 1) - mpAll.get(len - 2)) / (time.get(len - 1) - time.get(len - 2));
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}
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double cg = data.getLast(FlightDataType.TYPE_CG_LOCATION);
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// find the maximum distance from nose to nozzle.
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double nozzleDistance = 0;
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FlightConfiguration config = status.getConfiguration();
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for (MotorConfiguration inst : config.getActiveMotors()) {
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double x_position= inst.getX();
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double x = x_position + inst.getMotor().getLaunchCGx();
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if (x > nozzleDistance) {
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nozzleDistance = x;
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}
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}
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// now can get the propulsive part
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double propulsivePart = mdot * Math.pow(nozzleDistance - cg, 2);
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// Work out the aerodynamic part of the moment.
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double aerodynamicPart = 0;
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AerodynamicCalculator aerocalc = status.getSimulationConditions().getAerodynamicCalculator();
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// Must go through each component ...
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Map<RocketComponent, AerodynamicForces> forces = aerocalc.getForceAnalysis(status.getConfiguration(), flightConditions, status.getWarnings());
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for (Map.Entry<RocketComponent, AerodynamicForces> entry : forces.entrySet()) {
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RocketComponent comp = entry.getKey();
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if (!comp.isAerodynamic())
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continue;
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//System.out.println(comp.toString());
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double CNa = entry.getValue().getCNa(); //?
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double Cp = entry.getValue().getCP().length();
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double z = comp.getAxialOffset();
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aerodynamicPart += CNa * Math.pow(z - Cp, 2);
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}
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double v = flightConditions.getVelocity();
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double rho = flightConditions.getAtmosphericConditions().getDensity();
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double ar = flightConditions.getRefArea();
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aerodynamicPart = aerodynamicPart * .5 * rho * v * ar;
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return aerodynamicPart + propulsivePart;
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}
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}
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