private void ProxGeometry_CheckedChanged(object sender, EventArgs e)
{
IAgSatellite sat = CommonData.StkRoot.GetObjectFromPath("Satellite/" + CommonData.TargetName) as IAgSatellite;
IAgStkObject satObj = sat as IAgStkObject;
if (ProxGeometry.Checked)
{
if (CommonData.RunList[0].IsSpherical)
{
sat.VO.Proximity.Ellipsoid.IsVisible = true;
IAgCrdnAxes axes = satObj.Vgt.Axes["RIC"];
sat.VO.Proximity.Ellipsoid.ReferenceFrame = axes;
sat.VO.Proximity.Ellipsoid.XSemiAxisLength = CommonData.RunList[0].UserMinRange;
sat.VO.Proximity.Ellipsoid.YSemiAxisLength = CommonData.RunList[0].UserMinRange;
sat.VO.Proximity.Ellipsoid.ZSemiAxisLength = CommonData.RunList[0].UserMinRange;
}
else
{
sat.VO.Proximity.ControlBox.IsVisible = true;
IAgCrdnAxes axes = satObj.Vgt.Axes["RIC"];
sat.VO.Proximity.ControlBox.ReferenceFrame = axes;
sat.VO.Proximity.ControlBox.XAxisLength = CommonData.RunList[0].UserMinR;
sat.VO.Proximity.ControlBox.YAxisLength = CommonData.RunList[0].UserMinI;
sat.VO.Proximity.ControlBox.ZAxisLength = CommonData.RunList[0].UserMinC;
}
}
else
{
sat.VO.Proximity.Ellipsoid.IsVisible = false;
sat.VO.Proximity.ControlBox.IsVisible = false;
}
}
public void MoonAction()
{
IAgStkGraphicsSceneManager manager = ((IAgScenario)m_Root.CurrentScenario).SceneManager;
IAgCrdnAxes moonAxes = ((IAgCrdnSystemAssembled)m_Root.CentralBodies["Moon"].Vgt.Systems["ICRF"]).ReferenceAxes.GetAxes();
if (manager.Scenes.Count > 0)
{
manager.Scenes[0].Camera.ViewCentralBody("Moon", moonAxes);
}
m_Panning = false;
}
private IAgCrdnVector GetVectorFromAxes(IAgStkObject stkObject, IAgCrdnAxes axes, string axis)
{
// Get axis by name
try
{
return(stkObject.Vgt.Vectors[$"{((IAgCrdn)axes).Name}.{axis}"]);
}
catch
{
throw new Exception("Unable to get axis vector.");
}
}
private bool VectorIsValid(IAgCrdnVector vector)
{
// If vector cannot be evaluated at scenario start (0 EpSec), it's invalid
IAgCrdnAxes axes = m_referenceSatellite.Vgt.Axes["Body"];
string dateFormat = CommonData.StkRoot.UnitPreferences.GetCurrentUnitAbbrv("DateFormat");
string epoch = CommonData.StkRoot.ConversionUtility.ConvertDate("EpSec", dateFormat, "0");
IAgCrdnVectorFindInAxesResult result = vector.FindInAxes(epoch, axes);
return(result.IsValid);
}
private IAgCrdnAxes CreateAxes(IAgStkObject stkObject, string name, IAgCrdnAxes referenceAxes, string alignedAxis, string constrainedAxis, double angle)
{
IAgCrdnAxesFactory factory = stkObject.Vgt.Axes.Factory;
double[] eulerAngles = GetEulerArray(alignedAxis, constrainedAxis, angle);
// Check if component exists.
CheckExistingVgtComponent(stkObject.Vgt.Axes, name);
IAgCrdnAxesFixed axes = factory.Create(name, "", AgECrdnAxesType.eCrdnAxesTypeFixed) as IAgCrdnAxesFixed;
axes.ReferenceAxes.SetAxes(referenceAxes);
axes.FixedOrientation.AssignEulerAngles(AgEEulerOrientationSequence.e123, eulerAngles[0], eulerAngles[1], eulerAngles[2]);
return(axes as IAgCrdnAxes);
}
public void Orbit_generation()
{
//load_orbit_file();
scenarioCheck();
var format = new NumberFormatInfo();
format.NegativeSign = "-";
format.NumberDecimalSeparator = ".";
// planetodetic.Lat = Double.Parse(lat2[i], format);
for (int i = 0; i < orbitmissioncount; i++)
{
//debug infomation///////
if (orbitdata[i].misnum == orbitdata[i].cod_id && orbitdata[i].used == 1 && orbitdata[i].efileused == false)
{
//generate the timeline file
TL_file_generator(orbitdata[i].name, orbitdata[i].name);
Console.Write("Misnum == cod_id\n");
Console.Write("Mission= " + orbitdata[i].name + "\n" + orbitdata[i].epoch + " " + orbitdata[i].epoch_time + " ");
Console.Write(orbitdata[i].sma + " " + orbitdata[i].ecc + " " + orbitdata[i].inc + " " + orbitdata[i].raan + " " + orbitdata[i].aop + " " + orbitdata[i].ma + "\n");
string centerbodyname;
if (orbitdata[i].centerbody == 1)
{
centerbodyname = "Earth";
}
else if (orbitdata[i].centerbody == 2)
{
centerbodyname = "Moon";
}
else
{
centerbodyname = "Earth";
}
// AGI.STKObjects.IAgSatellite sat = (IAgSatellite)m_oApplication.CurrentScenario.Children.New(AGI.STKObjects.AgESTKObjectType.eSatellite, mission2[i]);
//sat.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorTwoBody);
try
{
//create a new sat with the cod orbit details;
orbitdata[i].MisSat = (IAgSatellite)m_oApplication.CurrentScenario.Children.NewOnCentralBody(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name, centerbodyname);
//AGI.STKObjects.IAgSatellite sat = (IAgSatellite)m_oApplication.CurrentScenario.Children.NewOnCentralBody(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name, centerbodyname);
}catch
{
//sat already exists reset the scenario;
this.m_oApplication.CloseScenario();
scenarioCheck();
Orbit_generation();
return;
}
//disable the leading ground track
groundtrack_set(orbitdata[i].MisSat, groundtrack_displayed);
//set the propagator type to HPOP
orbitdata[i].MisSat.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorHPOP);
//TODO update below code to use sat not hpop;
AGI.STKObjects.IAgVePropagatorHPOP hpop = (AGI.STKObjects.IAgVePropagatorHPOP)orbitdata[i].MisSat.Propagator;
IAgOrbitState orbit = hpop.InitialState.Representation;
//create the string to hold the missions epoch date & time
string cmb_epoch = orbitdata[i].epoch;
cmb_epoch += " ";
cmb_epoch += orbitdata[i].epoch_time;
DateTime epochDT = Convert.ToDateTime(orbitdata[i].epoch);
DateTime startDT = Convert.ToDateTime(orbitdata[i].start_date);
DateTime endDT;
if (orbitdata[i].endopt == 0)
{
endDT = startDT;
endDT = endDT.AddDays((double)orbitdata[i].duration);
orbitdata[i].end_time = orbitdata[i].start_time;
}
else
{
endDT = Convert.ToDateTime(orbitdata[i].end_date);
}
//hpop.ForceModel.EclipsingBodies.AssignEclipsingBody( centerbodyname);
//check the centerbody of the provided orbit data;
if (orbitdata[i].centerbody == 1)
{// centerbody == EARTH
Console.Write("centerbody2[i]) == 1 \n");
Console.Write("\n Centralbodyfile=" + hpop.ForceModel.CentralBodyGravity.File + "\n");
hpop.ForceModel.Drag.Use = false;
hpop.ForceModel.SolarRadiationPressure.Use = false;
}
else if (orbitdata[i].centerbody == 2)
{//CenterBody == Moon
Console.Write("centerbody2[i]) == 2 \n");
hpop.ForceModel.Drag.Use = false;
hpop.ForceModel.SolarRadiationPressure.Use = false;
Console.Write("\n Centralbodyfile=" + hpop.ForceModel.CentralBodyGravity.File + "\n");
//change gravity file for HPOP use with the moon
hpop.ForceModel.CentralBodyGravity.File = "STKData\\CentralBodies\\Moon\\LP100K.grv";
}
//hpop.InitialState.Representation.Assign(orbit);
Console.Write("set epochtime = " + epochDT.ToString("dd MMM yyyy ") + orbitdata[i].epoch_time + "\n");
//set the epoch date/time from the orbit bin file
hpop.InitialState.Representation.Epoch = (epochDT.ToString("dd MMM yyyy ") + orbitdata[i].epoch_time);
Console.Write("set start/stop times = " + (startDT.ToString("dd MMM yyyy ") + orbitdata[i].start_time) + " / " + startDT.AddDays(1).ToString("dd MMM yyyy ") + "\n");
//only proagate the orbit 1 day from the start date/time to get the required data to convert to a Fixed coordnate system
hpop.EphemerisInterval.SetStartAndStopTimes((startDT.ToString("dd MMM yyyy ") + orbitdata[i].start_time), startDT.AddDays(1).ToString("dd MMM yyyy "));
//hpop.EphemerisInterval.SetStartAndStopTimes((startDT.ToString("dd MMM yyyy ") + orbitdata[i].start_time), (endDT.ToString("dd MMM yyyy ") + orbitdata[i].end_time));
hpop.InitialState.Representation.AssignClassical(AgECoordinateSystem.eCoordinateSystemJ2000, orbitdata[i].sma, orbitdata[i].ecc, orbitdata[i].inc, orbitdata[i].aop, orbitdata[i].raan, orbitdata[i].ma);
hpop.Propagate();
//check if the orbit is earth centered and that the
// orbit start date is different from the Mission model date
if (orbitdata[i].centerbody == 1 && orbitdata[i].start_date != startdate)
{
Console.Write("Startdate != orbit_start date converting to Cartesian elements for fixed system" + "\n");
IAgStkObject sat = m_oApplication.CurrentScenario.Children[orbitdata[i].name];
// Get the satellite's ICRF cartesian position at 180 EpSec using the data provider interface
IAgDataProviderGroup dpGroup = sat.DataProviders["Cartesian Position"] as IAgDataProviderGroup;
Array elements = new object[] { "x", "y", "z" };
//***TODO*** find J2000 group instead of ICRF
IAgDataPrvTimeVar dp = dpGroup.Group["ICRF"] as IAgDataPrvTimeVar;
//get the elements at the start date/time of the orbit using in NPAS
IAgDrResult dpResult = dp.ExecSingleElements(hpop.StartTime, ref elements);
Console.Write("hpop.startTime=" + hpop.StartTime + "\n");
double xICRF = (double)dpResult.DataSets[0].GetValues().GetValue(0);
double yICRF = (double)dpResult.DataSets[1].GetValues().GetValue(0);
double zICRF = (double)dpResult.DataSets[2].GetValues().GetValue(0);
// Get the satellite's ICRF cartesian velocity at 180 EpSec using the data provider interface
dpGroup = sat.DataProviders["Cartesian Velocity"] as IAgDataProviderGroup;
//***TODO*** find J2000 group instead of ICRF
dp = dpGroup.Group["ICRF"] as IAgDataPrvTimeVar;
//get the elements at the start date/time of the orbit using in NPAS
dpResult = dp.ExecSingleElements(hpop.StartTime, ref elements);
double xvelICRF = (double)dpResult.DataSets[0].GetValues().GetValue(0);
double yvelICRF = (double)dpResult.DataSets[1].GetValues().GetValue(0);
double zvelICRF = (double)dpResult.DataSets[2].GetValues().GetValue(0);
Console.Write("J2000 cartesian vectors\n");
Console.Write("X=" + xICRF + " Y=" + yICRF + " Z=" + zICRF + "\n");
Console.Write("Xd=" + xvelICRF + " Yd=" + yvelICRF + " Zd=" + zvelICRF + "\n");
// Create a position vector using the ICRF coordinates
IAgCrdnAxes axesICRF = sat.Vgt.WellKnownAxes.Earth.ICRF;
IAgCartesian3Vector vectorICRF = m_oApplication.ConversionUtility.NewCartesian3Vector();
vectorICRF.Set(xICRF, yICRF, zICRF);
// Create a velocity vector using the ICRF coordinates
IAgCartesian3Vector vectorvelICRF = m_oApplication.ConversionUtility.NewCartesian3Vector();
vectorvelICRF.Set(xvelICRF, yvelICRF, zvelICRF);
// Use the TransformWithRate method to transform ICRF to Fixed
IAgCrdnAxes axesFixed = sat.Vgt.WellKnownAxes.Earth.Fixed;
IAgCrdnAxesTransformWithRateResult result = axesICRF.TransformWithRate(hpop.StartTime, axesFixed, vectorICRF, vectorvelICRF);
// Get the Fixed position and velocity coordinates
double xFixed = result.Vector.X;
double yFixed = result.Vector.Y;
double zFixed = result.Vector.Z;
double xvelFixed = result.Velocity.X;
double yvelFixed = result.Velocity.Y;
double zvelFixed = result.Velocity.Z;
Console.Write("converted cartesian vectors" + "\n");
Console.Write("X=" + xFixed + " Y=" + yFixed + " Z=" + zFixed + "\n");
Console.Write("Xd=" + xvelFixed + " Yd=" + yvelFixed + " Zd=" + zvelFixed + "\n");
DateTime start, stop;
start = Convert.ToDateTime(startdate);
stop = Convert.ToDateTime(enddate);
//set the epoch and start date/time to the selected scenario date/time
hpop.InitialState.Representation.Epoch = (start.ToString("dd MMM yyyy "));
hpop.EphemerisInterval.SetStartAndStopTimes((start.ToString("dd MMM yyyy ")), (stop.ToString("dd MMM yyyy ")));
hpop.InitialState.Representation.AssignCartesian(AgECoordinateSystem.eCoordinateSystemFixed, xFixed, yFixed, zFixed, xvelFixed, yvelFixed, zvelFixed);
hpop.InitialState.Representation.Epoch = (start.ToString("dd MMM yyyy "));
hpop.EphemerisInterval.SetStartAndStopTimes((start.ToString("dd MMM yyyy ")), (stop.ToString("dd MMM yyyy ")));
//propagate new orbit
hpop.Propagate();
}
orbitdata[i].Missensor = generate_sensor(orbitdata[i].name, "Stations");
orbitdata[i].MisChain = generate_chain(orbitdata[i].name, "Stations", orbitdata[i].name + "_sensor");
}
else if (orbitdata[i].used == 1 && orbitdata[i].efileused == false)
{
//generate the missions timeline file inside the orignial cod mis name
//don't generate multiple orbits on top of each other;
TL_file_generator(orbitdata[i].name, missionindex[orbitdata[i].cod_id]);
orbitdata[i].MisChain = null;
Console.Write("Misnum != cod_id && orbitdata[i].used == 1 for " + orbitdata[i].name + "\n");
}
else if (orbitdata[i].used == 1 && orbitdata[i].efileused == true)
{
TL_file_generator(orbitdata[i].name, missionindex[orbitdata[i].cod_id]);
orbitdata[i].MisSat = (IAgSatellite)m_oApplication.CurrentScenario.Children.New(AGI.STKObjects.AgESTKObjectType.eSatellite, orbitdata[i].name);
//disable the leading ground track
groundtrack_set(orbitdata[i].MisSat, groundtrack_displayed);
//set the propagator type to STK E file
orbitdata[i].MisSat.SetPropagatorType(AGI.STKObjects.AgEVePropagatorType.ePropagatorStkExternal);
AGI.STKObjects.IAgVePropagatorStkExternal EFileProp = (AGI.STKObjects.IAgVePropagatorStkExternal)orbitdata[i].MisSat.Propagator;
//strip the file name from the entire director name;
EFileProp.Filename = (Efile_directory + orbitdata[i].efilename.Split('/').Last().ToString());
//propagate the efile orbit
EFileProp.Propagate();
//add new sensor to the current sat and change the sensor type to target
orbitdata[i].Missensor = generate_sensor(orbitdata[i].name, "Stations");
//add a new chain for the current sat
orbitdata[i].MisChain = generate_chain(orbitdata[i].name, "Stations", orbitdata[i].name + "_sensor");
}
else
{
orbitdata[i].MisChain = null;
Console.Write("Misnum != cod_id for " + orbitdata[i].name + "\n");
}
}
}
private void CreateAttitudeButton_Click(object sender, EventArgs e)
{
try
{
progressBar.Visible = true;
UpdateProgress(0);
// Check inputs
CheckUserInputs();
// Get inputs
string alignedVectorName = alignedVectorComboBox.SelectedItem.ToString();
string constrainedVectorName = constrainedVectorComboBox.SelectedItem.ToString();
double angleLimit = Convert.ToDouble(angleLimitTextBox.Text);
string alignedBodyAxis = GetBodyAxis(VectorType.eAligned);
string constrainedBodyAxis = GetBodyAxis(VectorType.eConstrained);
UserInputs inputs = new UserInputs
{
AlignedVectorName = alignedVectorName,
AlignedBodyAxis = alignedBodyAxis,
ConstrainedVectorName = constrainedVectorName,
ConstrainedBodyAxis = constrainedBodyAxis,
AngleLimit = angleLimit
};
UpdateProgress(25);
// Duplicate the satellite to create a reference sat. All AWB components are created on this reference sat to avoid circular logic.
m_referenceSatellite = DuplicateObject(m_selectedObject);
UpdateProgress(50);
// Create AWB components from user inputs
IAgCrdnVector scheduledVector = CreateAlignedScheduledVector(inputs);
UpdateProgress(75);
// Set final attitude profile
IAgCrdnVector selectedConstrainedVector = GetVectorFromObject((IAgStkObject)m_selectedObject, constrainedVectorName);
SetAlignedConstrainedAttitude(m_selectedObject, scheduledVector, alignedBodyAxis, selectedConstrainedVector, constrainedBodyAxis);
if (showGraphicsCheckBox.Checked == true)
{
// Get AWB components to display
IAgCrdnAxes selectedBodyAxes = m_selectedObject.Vgt.Axes["Body"];
IAgCrdnVector selectedConstrainedBodyVector = GetVectorFromAxes((IAgStkObject)m_selectedObject, selectedBodyAxes, constrainedBodyAxis);
IAgCrdnVector selectedAlignedVector = GetVectorFromObject((IAgStkObject)m_selectedObject, alignedVectorName);
IAgCrdnAngle displayAngle = CreateAngle((IAgStkObject)m_selectedObject, $"Off_{constrainedVectorName}", selectedConstrainedVector, selectedConstrainedBodyVector);
// Display in 3D Graphics window.
ShowAttitudeGraphics(selectedAlignedVector, selectedConstrainedVector, selectedBodyAxes, displayAngle);
// Add negative body axis if necessary
if (constrainedBodyAxis.Contains("-"))
{
IAgCrdnVector bodyVector = m_selectedObject.Vgt.Vectors[$"Body.{constrainedBodyAxis}"];
DisplayElement(AgEGeometricElemType.eVectorElem, (IAgCrdn)bodyVector, Color.RoyalBlue);
}
}
UpdateProgress(100);
}
catch (Exception exception)
{
MessageBox.Show(exception.Message, "Error", MessageBoxButtons.OK, MessageBoxIcon.Error);
}
progressBar.Visible = false;
}
private void ShowAttitudeGraphics(IAgCrdnVector alignedVector, IAgCrdnVector constrainedVector, IAgCrdnAxes bodyAxes, IAgCrdnAngle offAxisAngle)
{
// Show aligned vector and constrained vector
DisplayElement(AgEGeometricElemType.eVectorElem, (IAgCrdn)alignedVector, Color.Yellow);
DisplayElement(AgEGeometricElemType.eVectorElem, (IAgCrdn)constrainedVector, Color.LawnGreen);
// Show body axes
DisplayElement(AgEGeometricElemType.eAxesElem, (IAgCrdn)bodyAxes, Color.RoyalBlue);
// Display angle from constraint vector to Body axis on original satellite to show limited atttiude.
DisplayElement(AgEGeometricElemType.eAngleElem, (IAgCrdn)offAxisAngle, Color.White);
}
private IAgCrdnAxes CreateAxes(IAgStkObject stkObject, string name, IAgCrdnCondition satisfactionCondition, IAgCrdnAxes onScheduleAxes, IAgCrdnAxes offScheduleAxes)
{
// Check if component exists.
CheckExistingVgtComponent(stkObject.Vgt.Axes, name);
// No Object Model for Scheduled Axes, so Connect command must be used.
string commandString = $"VectorTool * {stkObject.ClassName}/{stkObject.InstanceName} Create Axes {name} \"Scheduled\" Schedule" +
$" \"{((IAgCrdn)satisfactionCondition).Path}.SatisfactionIntervals\" OnSchedule \"{((IAgCrdn)onScheduleAxes).Path}\"" +
$" UseOffSchedule On OffSchedule \"{((IAgCrdn)offScheduleAxes).Path}\" UseAdditionalCondition Off UseSlew Off";
try
{
CommonData.StkRoot.ExecuteCommand(commandString);
}
catch
{
throw new Exception($"Command failed while creating {name} Axes.");
}
return(stkObject.Vgt.Axes[name]);
}
private IAgCrdnVector CreateAlignedScheduledVector(UserInputs inputs)
{
// Unpack inputs
string alignedVectorName = inputs.AlignedVectorName;
string alignedBodyAxis = inputs.AlignedBodyAxis;
string constrainedVectorName = inputs.ConstrainedVectorName;
string constrainedBodyAxis = inputs.ConstrainedBodyAxis;
double angleLimit = inputs.AngleLimit;
// Get vectors from user input
IAgCrdnVector duplicateAlignedVector = GetVectorFromObject((IAgStkObject)m_referenceSatellite, alignedVectorName);
IAgCrdnVector duplicateConstrainedVector = GetVectorFromObject((IAgStkObject)m_referenceSatellite, constrainedVectorName);
// Make sure vectors are valid
CheckInputVector(duplicateAlignedVector);
CheckInputVector(duplicateConstrainedVector);
// Create Body vector string for naming
string constrainedBodyVectorName = $"Body.{constrainedBodyAxis}";
// Get body vector
IAgCrdnAxes duplicateBodyAxes = m_referenceSatellite.Vgt.Axes["Body"];
IAgCrdnVector duplicateConstrainedBodyVector = GetVectorFromAxes((IAgStkObject)m_referenceSatellite, duplicateBodyAxes, constrainedBodyAxis);
// Set duplicate satellite's attitude to Aligned & Constrained with user input vectors. This is the unconstrained attitude that our
// final satellite's attitude is based on.
SetAlignedConstrainedAttitude(m_referenceSatellite, duplicateAlignedVector, alignedBodyAxis, duplicateConstrainedVector, constrainedBodyAxis);
// Create angle from constraint vector to specified body axis. Set condition to find when this angle exceeds user limit
IAgCrdnAngle constraintToBodyAngle = CreateAngle((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}To{constrainedBodyVectorName}", duplicateConstrainedVector, duplicateConstrainedBodyVector);
IAgCrdnCalcScalar constraintToBodyScalar = CreateScalar((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}To{constrainedBodyVectorName}Value", constraintToBodyAngle);
IAgCrdnCondition constraintToBodyCondition = CreateCondition((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}To{constrainedBodyVectorName}Condition", constraintToBodyScalar, AgECrdnConditionThresholdOption.eCrdnConditionThresholdOptionBelowMax, angleLimit);
// Create angle from constraint vector to aligned vector and set condition from 0 to 90 deg. This is because the attitude profile is flipped
// if the angle is between 90 and 180 deg.
IAgCrdnAngle constraintToAlignedAngle = CreateAngle((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}To{alignedVectorName}", duplicateConstrainedVector, duplicateAlignedVector);
IAgCrdnCalcScalar constraintToAlignedScalar = CreateScalar((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}To{alignedVectorName}Value", constraintToAlignedAngle);
IAgCrdnCondition constraintToAlignedCondition = CreateCondition((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}To{alignedVectorName}Condition", constraintToAlignedScalar, AgECrdnConditionThresholdOption.eCrdnConditionThresholdOptionInsideMinMax, 0, 90);
// Create axes aligned with the constraint vector and constrained with the aligned vector.
IAgCrdnAxes alignedConstrainedAxes = CreateAxes((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}Axes", duplicateConstrainedVector, constrainedBodyAxis, duplicateAlignedVector, alignedBodyAxis);
// Rotate the new axes by both the positive and negative Angle Offset value.
IAgCrdnAxes positiveRotatedAxes = CreateAxes((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}Axes_RotatedPositive", alignedConstrainedAxes, alignedBodyAxis, constrainedBodyAxis, angleLimit);
IAgCrdnAxes negativeRotatedAxes = CreateAxes((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}Axes_RotatedNegative", alignedConstrainedAxes, alignedBodyAxis, constrainedBodyAxis, -angleLimit);
// Create scheduled axes
IAgCrdnAxes scheduledAxes;
double[] alignedAxisVector = GetCartesianArray(alignedBodyAxis);
double[] constrainedAxisVector = GetCartesianArray(constrainedBodyAxis);
// If the cross product vector of the aligned body axis and constrained body axis is positive, the axes need to be
// positively rotated when the angle between the aligned vector and constrained vector is between 0 deg and 90 deg.
// If the angle is between 90 and 180, the axes need to be negatively rotated. This is flipped if the cross product
// is negative.
if (NormalVectorIsPositive(alignedAxisVector, constrainedAxisVector))
{
scheduledAxes = CreateAxes((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}Axes_Scheduled", constraintToAlignedCondition, positiveRotatedAxes, negativeRotatedAxes);
}
else
{
scheduledAxes = CreateAxes((IAgStkObject)m_referenceSatellite, $"{constrainedVectorName}Axes_Scheduled", constraintToAlignedCondition, negativeRotatedAxes, positiveRotatedAxes);
}
// Create scheduled vector to point along alignment vector when constraint is not broken, and hold at constraint when violated.
IAgCrdnVector alignedScheduledAxis = GetVectorFromAxes((IAgStkObject)m_referenceSatellite, scheduledAxes, alignedBodyAxis);
IAgCrdnVector scheduledVector = CreateVector((IAgStkObject)m_referenceSatellite, $"{alignedVectorName}Scheduled", constraintToBodyCondition, duplicateAlignedVector, alignedScheduledAxis);
return(scheduledVector);
}