TransferMath Class Reference

Public Member Functions
delegate double	BisectFunc (double x)
	Delegate for Bisect method. More...

Static Public Member Functions
static double	AlignmentTime (TransferDataSimple transferDataSimple, Orbit sourceOrbit, Orbit targetOrbit, double startUT, double offsetDegrees=0d)
	The time in seconds from current UT that the phase angles of the Source and Target body orbits will align. More...
static double	Bisect (BisectFunc f, double minimum, double maximum, double acceptableRange=0.01, int maxIter=15)
	Bisection method More...
static double	CalcCircularizeDV (TransferDataSimple transferDataSimple, double newApoapsis)
	Calculate Circularization dV. More...
static double	CalcSameSOITransferDV (TransferDataSimple transferDataSimple, Orbit startOrbit)
	Calculate same SOI Hohmann Transfer dV. More...
static bool	CalculateCorrection (TransferDataSimple transferDataSimple, double startUT, SafeAbortBackgroundWorker bw)
	Calculate a Correction Burn if orbits are inclined. Will only process if relative inclination is > 1. More...
static void	CalculateStartEndXferTimes (CelestialBody sourceBody, CelestialBody targetBody, double offsetDegrees, out double startTime, out double endTime)
	Calculates the start and end transfer window times where the phase angle between source and target planet is within offset degrees occuring after the current time. More...
static void	CalculateStartEndXferTimes (CelestialBody sourceBody, CelestialBody targetBody, double afterUT, double offsetDegrees, out double startTime, out double endTime)
	Calculates the start and end transfer window times where the phase angle between source and target planet is within offset degrees. More...
static void	CalculateStartEndXferTimes (TransferDataSimple transferDataSimple, CelestialBody sourceBody, CelestialBody targetBody, double offsetDegrees, out string startTime, out string endTime)
	Calculates the start and end transfer window times where the phase angle between source and target planet is within offset degrees. More...
static bool	ChangingPeriapsis (Orbit start, Orbit target, double UT)
	Are we changing Periapsis to reach target. More...
static Vector3d	DeltaVToInterceptAtTime (Orbit o, double initialUT, Orbit target, double DT, out Vector3d secondDV)
static double	FinalizeLambert (TransferDataSimple transferDataSimple, double startUT, Orbit startOrbit, Orbit targetOrbit)
	Finalize Lambert solution. More...
static bool	FindIntercept (TransferDataSimple transferDataSimple, Orbit startOrbit, CelestialBody targetBody, Vector3d dV, double UT, bool sameSOIXfer, double initialClosestApproach, SafeAbortBackgroundWorker bw, out Vector3d adjustedDV)
static double	HohmannTimeOfFlight (Orbit origin, Orbit destination)
	Calculates the time of flight for a Hohmann transfer between origin and destination , assuming the orbits are circular and coplanar. More...
static void	LambertSolver (double mu, Vector3d r1, Vector3d v1, Vector3d r2, Vector3d v2, double tof, int nrev, out Vector3d vi, out Vector3d vf)
	Solve Lambert's Problem. More...
static double	Root (BisectFunc f, double a, double b, double tol, int maxIterations=50, int sign=0)
	Brent's Algorithm for root finding. More...
static double	SafeOrbitRadius (CelestialBody body)
	Returns the minimum safe orbit radius for body. More...
static bool	SameSOITransfer (TransferDataSimple transferDataSimple)
	Is the transfer within the Same SOI? More...
static void	SuperiorLambert (double mu, Vector3d r1, Vector3d v1, Vector3d r2, Vector3d v2, double tof, out Vector3d vi, out Vector3d vf)
	Superior Lambert solution using Gim J. Der derivative on Sun's solution. More...
static double	TransferDV (TransferDataSimple transferDataSimple, double startUT)
	Calculate the Transfer dV for a simple Transfer. Target and Source body must have already been set. More...

Static Public Attributes
static double	safetyEnvelope = 1.025
	The safety Envelope for setting minimum Radius on Transfer Orbits. More...

Member Function Documentation

static double TransferMath.AlignmentTime ( TransferDataSimple  transferDataSimple, Orbit  sourceOrbit, Orbit  targetOrbit, double  startUT, double  offsetDegrees = 0d  )

inlinestatic

The time in seconds from current UT that the phase angles of the Source and Target body orbits will align.

Parameters

transferDataSimple	This is the instance of the TransferDataSimple.
sourceOrbit	This is the source Orbit
targetOrbit	This is the target Orbit
startUT	This is the starting UT to use for the calcs.
offsetDegrees	This optional offset in degrees will be applied to the optimal angle calculation

Returns

static double TransferMath.Bisect ( BisectFunc  f, double  minimum, double  maximum, double  acceptableRange = 0.01, int  maxIter = 15  )

inlinestatic

Bisection method

Parameters

f	single dimension function
minimum	minimum value
maximum	maximum value
acceptableRange	acceptable range
maxIter	maximum iterations

Returns

delegate double TransferMath.BisectFunc

(

double

x

)

Delegate for Bisect method.

Parameters

x

Returns

static double TransferMath.CalcCircularizeDV ( TransferDataSimple  transferDataSimple, double  newApoapsis  )

inlinestatic

Calculate Circularization dV.

Parameters

transferDataSimple
newApoapsis	Should include radius of CB

Returns

static double TransferMath.CalcSameSOITransferDV ( TransferDataSimple  transferDataSimple, Orbit  startOrbit  )

inlinestatic

Calculate same SOI Hohmann Transfer dV.

Parameters

transferDataSimple	TransferDataSimple data instance
startOrbit	The starting orbit

Returns

The dV to complete the transfer and circularization dV if required.

static bool TransferMath.CalculateCorrection ( TransferDataSimple  transferDataSimple, double  startUT, SafeAbortBackgroundWorker  bw  )

inlinestatic

Calculate a Correction Burn if orbits are inclined. Will only process if relative inclination is > 1.

Parameters

bw	BackgroundWorker
transferDataSimple	the TransferDataSimple data instance
startUT	The start UT to start from

Returns

True if a correction was made. False If a correct was not made.

static void TransferMath.CalculateStartEndXferTimes ( CelestialBody  sourceBody, CelestialBody  targetBody, double  offsetDegrees, out double  startTime, out double  endTime  )

inlinestatic

Calculates the start and end transfer window times where the phase angle between source and target planet is within offset degrees occuring after the current time.

Parameters

sourceBody	Starting Celestial Body for the Transfer
targetBody	Ending Celestial Body for the Transfer
offsetDegrees	How many degrees either side of the optimum phase angle do we want to use for start and finish
startTime	The start time in UT of the TRansfer Window
endTime	The end time in UT of the TRansfer Window

static void TransferMath.CalculateStartEndXferTimes ( CelestialBody  sourceBody, CelestialBody  targetBody, double  afterUT, double  offsetDegrees, out double  startTime, out double  endTime  )

inlinestatic

Calculates the start and end transfer window times where the phase angle between source and target planet is within offset degrees.

Parameters

sourceBody	Starting Celestial Body for the Transfer
targetBody	Ending Celestial Body for the Transfer
afterUT	The time after which the middled of the transfer should be
offsetDegrees	How many degrees either side of the optimum phase angle do we want to use for start and finish
startTime	The time in seconds from afterUT to the start of the window
endTime	The time in seconds from afterUT to the end of the window

static void TransferMath.CalculateStartEndXferTimes ( TransferDataSimple  transferDataSimple, CelestialBody  sourceBody, CelestialBody  targetBody, double  offsetDegrees, out string  startTime, out string  endTime  )

inlinestatic

Calculates the start and end transfer window times where the phase angle between source and target planet is within offset degrees.

Parameters

transferDataSimple	Transfer data object related to this transfer
sourceBody	Starting Celestial Body for the Transfer
targetBody	Ending Celestial Body for the Transfer
offsetDegrees	How many degrees either side of the optimum phase angle do we want to use for start and finish
startTime	The time in seconds from current UT to the start of the window
endTime	The time in seconds from current UT to the end of the window

static bool TransferMath.ChangingPeriapsis ( Orbit  start, Orbit  target, double  UT  )

inlinestatic

Are we changing Periapsis to reach target.

Parameters

start	Start orbit
target	Target orbit
UT	The burn start UT

Returns

static Vector3d TransferMath.DeltaVToInterceptAtTime ( Orbit  o, double  initialUT, Orbit  target, double  DT, out Vector3d  secondDV  )

inlinestatic

static double TransferMath.FinalizeLambert ( TransferDataSimple  transferDataSimple, double  startUT, Orbit  startOrbit, Orbit  targetOrbit  )

inlinestatic

Finalize Lambert solution.

Parameters

transferDataSimple
startUT
startOrbit
targetOrbit

Returns

static bool TransferMath.FindIntercept ( TransferDataSimple  transferDataSimple, Orbit  startOrbit, CelestialBody  targetBody, Vector3d  dV, double  UT, bool  sameSOIXfer, double  initialClosestApproach, SafeAbortBackgroundWorker  bw, out Vector3d  adjustedDV  )

inlinestatic

static double TransferMath.HohmannTimeOfFlight ( Orbit  origin, Orbit  destination  )

inlinestatic

Calculates the time of flight for a Hohmann transfer between origin and destination , assuming the orbits are circular and coplanar.

Returns

The time of flight.

Parameters

origin	The origin orbit.
destination	The destination orbit.

static void TransferMath.LambertSolver ( double  mu, Vector3d  r1, Vector3d  v1, Vector3d  r2, Vector3d  v2, double  tof, int  nrev, out Vector3d  vi, out Vector3d  vf  )

inlinestatic

Solve Lambert's Problem.

Parameters

mu	Gravity
r1	Position at Origin
v1	Velocity at Origin
r2	Position at Destination
v2	Velocity at Destination
tof	Time of Flight (secs)
nrev	Number of Orbits
vi	Velocity Vector at Ejection
vf	Velocity Vector at Arrival

static double TransferMath.Root ( BisectFunc  f, double  a, double  b, double  tol, int  maxIterations = 50, int  sign = 0  )

inlinestatic

Brent's Algorithm for root finding.

Parameters

f	single dimension function to find the root of
a	first value
b	second value
tol	tolerance
maxIterations	maximum iterations
sign

Returns

static double TransferMath.SafeOrbitRadius ( CelestialBody  body )

inlinestatic

Returns the minimum safe orbit radius for body.

Parameters

body

Returns

static bool TransferMath.SameSOITransfer ( TransferDataSimple  transferDataSimple )

inlinestatic

Is the transfer within the Same SOI?

Parameters

transferDataSimple

Returns

static void TransferMath.SuperiorLambert ( double  mu, Vector3d  r1, Vector3d  v1, Vector3d  r2, Vector3d  v2, double  tof, out Vector3d  vi, out Vector3d  vf  )

inlinestatic

Superior Lambert solution using Gim J. Der derivative on Sun's solution.

Parameters

mu
r1
v1
r2
v2
tof
vi
vf

static double TransferMath.TransferDV ( TransferDataSimple  transferDataSimple, double  startUT  )

inlinestatic

Calculate the Transfer dV for a simple Transfer. Target and Source body must have already been set.

Parameters

transferDataSimple	This is the instance of the TransferDataSimple.
vessel	This is the Vessel - should be the ActiveVessel.
startUT	This is the starting UT to use for the calcs.

Returns

Member Data Documentation

double TransferMath.safetyEnvelope = 1.025

static

The safety Envelope for setting minimum Radius on Transfer Orbits.

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The documentation for this class was generated from the following file:

• KSP/Assets/Scripts/Manuever Planning/TransferMath.cs