fr.cnes.sirius.patrius.forces.maneuvers

Class ConstantThrustError

java.lang.Object

fr.cnes.sirius.patrius.math.parameter.Parameterizable

fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

fr.cnes.sirius.patrius.forces.maneuvers.ConstantThrustError

All Implemented Interfaces:

ForceModel, GradientModel, IJacobiansParameterizable, IParameterizable, Serializable

public final class ConstantThrustError
extends JacobiansParameterizable
implements ForceModel, GradientModel

This class is a model of the error of a simple maneuver with constant thrust.

The architecture of this force model is similar to ConstantThrustManeuver class.

The maneuver is associated to two triggering EventDetector (one to start the thrust, the other one to stop the thrust): the maneuver is triggered only if the underlying event generates a STOP event, in which case this class will generate a RESET_STATE event (the stop event from the underlying object is therefore filtered out).

Since:

2.3

Version:

$Id: ConstantThrustError.java 17582 2017-05-10 12:58:16Z bignon $

Author:

Tiziana Sabatini

See Also:

Serialized Form

Concurrency :

not thread-safe

Concurrency comment :

internal mutable attributes

Constructor Summary

Constructors

Constructor and Description
ConstantThrustError(AbsoluteDate date, double duration, double cx, double cy, double cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in spacecraft frame.
ConstantThrustError(AbsoluteDate date, double duration, double ax, double bx, double ay, double by, double az, double bz, AbsoluteDate date0) Create a constant thrust error model whose x, y and z components are linear functions: fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in spacecraft frame.
ConstantThrustError(AbsoluteDate date, double duration, Frame frame, double cx, double cy, double cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided frame.
ConstantThrustError(AbsoluteDate date, double duration, Frame frame, double ax, double bx, double ay, double by, double az, double bz, AbsoluteDate date0) Create a constant thrust error model whose x, y and z components are linear functions: fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided frame.
ConstantThrustError(AbsoluteDate date, double duration, Frame frame, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz) Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.
ConstantThrustError(AbsoluteDate date, double duration, Frame frame, Parameter cx, Parameter cy, Parameter cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided frame.
ConstantThrustError(AbsoluteDate date, double duration, Frame frame, Parameter ax, Parameter bx, Parameter ay, Parameter by, Parameter az, Parameter bz, AbsoluteDate date0) Create a constant thrust error model whose x, y and z components are linear functions: fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided frame.
ConstantThrustError(AbsoluteDate date, double duration, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz) Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.
ConstantThrustError(AbsoluteDate date, double duration, LOFType lofType, double cx, double cy, double cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame.
ConstantThrustError(AbsoluteDate date, double duration, LOFType lofType, double ax, double bx, double ay, double by, double az, double bz, AbsoluteDate date0) Create a constant thrust error model whose x, y and z components are linear functions: fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided local orbital frame.
ConstantThrustError(AbsoluteDate date, double duration, LOFType lofType, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz) Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.
ConstantThrustError(AbsoluteDate date, double duration, LOFType lofType, Parameter cx, Parameter cy, Parameter cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame.
ConstantThrustError(AbsoluteDate date, double duration, LOFType lofType, Parameter ax, Parameter bx, Parameter ay, Parameter by, Parameter az, Parameter bz, AbsoluteDate date0) Create a constant thrust error model whose x, y and z components are linear functions: fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in provided local orbital frame.
ConstantThrustError(AbsoluteDate date, double duration, Parameter cx, Parameter cy, Parameter cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in spacecraft frame.
ConstantThrustError(AbsoluteDate date, double duration, Parameter ax, Parameter bx, Parameter ay, Parameter by, Parameter az, Parameter bz, AbsoluteDate date0) Create a constant thrust error model whose x, y and z components are linear functions: fx = ax*t + bx fy = ay*t + by fz = az*t + bz Errors components are expressed in spacecraft frame.
ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, Frame frame, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided frame.
ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, Frame frame, Parameter cx, Parameter cy, Parameter cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided frame.
ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in spacecraft frame.
ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, LOFType lofType, IParamDiffFunction fx, IParamDiffFunction fy, IParamDiffFunction fz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame.
ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, LOFType lofType, Parameter cx, Parameter cy, Parameter cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in provided local orbital frame.
ConstantThrustError(EventDetector startEventDetector, EventDetector stopEventDetector, Parameter cx, Parameter cy, Parameter cz) Create a constant thrust error model whose x, y and z components are constant functions: fx = cx fy = cy fz = cz Errors components are expressed in spacecraft frame.

Method Summary

Modifier and Type	Method and Description
void	addContribution(SpacecraftState s, TimeDerivativesEquations adder) Compute the contribution of the constant thrust error model to the perturbing acceleration.
void	addDAccDParam(SpacecraftState state, Parameter param, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters.
void	addDAccDState(SpacecraftState state, double[][] dAccdPos, double[][] dAccdVel) Compute acceleration derivatives with respect to state parameters.
Vector3D	computeAcceleration(SpacecraftState s) Compute the acceleration due to the force.
boolean	computeGradientPosition() This method returns true if the acceleration partial derivatives with respect to position have to be computed.
boolean	computeGradientVelocity() This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.
AbsoluteDate	getEndDate() Return the maneuver stop date (if a date or a DateDetector as been provided).
EventDetector[]	getEventsDetectors() Get the discrete events related to the model.
AbsoluteDate	getStartDate() Return the maneuver start date (if a date or a DateDetector as been provided).
boolean	isFiring() Returns maneuver status (firing or not).
void	setFiring(boolean isFiring) Set maneuver status.

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.JacobiansParameterizable

addJacobiansParameter, addJacobiansParameter, addJacobiansParameter, supportsJacobianParameter

Methods inherited from class fr.cnes.sirius.patrius.math.parameter.Parameterizable

addParameter, getParameters, supportsParameter

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Methods inherited from interface fr.cnes.sirius.patrius.math.parameter.IParameterizable

getParameters, supportsParameter

Constructor Detail

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           IParamDiffFunction fx,
                           IParamDiffFunction fy,
                           IParamDiffFunction fz)

Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.

Errors components are expressed in spacecraft frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

fx - the parameterizable and differentiable function representing the x component of the thrust error.

fy - the parameterizable and differentiable function representing the y component of the thrust error.

fz - the parameterizable and differentiable function representing the z component of the thrust error.

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           Parameter ax,
                           Parameter bx,
                           Parameter ay,
                           Parameter by,
                           Parameter az,
                           Parameter bz,
                           AbsoluteDate date0)

Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

Errors components are expressed in spacecraft frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

ax - the parameter representing the slope of the linear function for the x component of the constant thrust error.

bx - the parameter representing the zero value of the linear function for the x component of the constant thrust error.

ay - the parameter representing the slope of the linear function for the y component of the constant thrust error.

by - the parameter representing the zero value of the linear function for the y component of the constant thrust error.

az - the parameter representing the slope of the linear function for the z component of the constant thrust error.

bz - the parameter representing the zero value of the linear function for the z component of the constant thrust error.

date0 - the zero value date

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           double ax,
                           double bx,
                           double ay,
                           double by,
                           double az,
                           double bz,
                           AbsoluteDate date0)

Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

Errors components are expressed in spacecraft frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

ax - the slope of the linear function for the x component of the constant thrust error.

bx - the zero value of the linear function for the x component of the constant thrust error.

ay - the slope of the linear function for the y component of the constant thrust error.

by - the zero value of the linear function for the y component of the constant thrust error

az - the slope of the linear function for the z component of the constant thrust error

bz - the zero value of the linear function for the z component of the constant thrust error

date0 - the zero value date

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           Parameter cx,
                           Parameter cy,
                           Parameter cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in spacecraft frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

cx - the parameter for the x component of the constant thrust error

cy - the parameter for the y component of the constant thrust error

cz - the parameter for the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           double cx,
                           double cy,
                           double cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in spacecraft frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

cx - the x component of the constant thrust error

cy - the y component of the constant thrust error

cz - the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           Frame frame,
                           IParamDiffFunction fx,
                           IParamDiffFunction fy,
                           IParamDiffFunction fz)

Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.

Errors components are expressed in provided frame.

WARNING : This constructor must not be used with a LocalOrbitalFrame, acceleration computation would fail.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

frame - the maneuver frame

fx - the parameterizable and differentiable function representing the x component of the thrust error.

fy - the parameterizable and differentiable function representing the y component of the thrust error.

fz - the parameterizable and differentiable function representing the z component of the thrust error.

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           Frame frame,
                           Parameter ax,
                           Parameter bx,
                           Parameter ay,
                           Parameter by,
                           Parameter az,
                           Parameter bz,
                           AbsoluteDate date0)

Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

Errors components are expressed in provided frame.

WARNING : This constructor must not be used with a LocalOrbitalFrame,
acceleration computation would fail.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

frame - the maneuver frame

ax - the parameter representing the slope of the linear function for the x component of the constant thrust error.

bx - the parameter representing the zero value of the linear function for the x component of the constant thrust error.

ay - the parameter representing the slope of the linear function for the y component of the constant thrust error.

by - the parameter representing the zero value of the linear function for the y component of the constant thrust error.

az - the parameter representing the slope of the linear function for the z component of the constant thrust error.

bz - the parameter representing the zero value of the linear function for the z component of the constant thrust error.

date0 - the zero value date

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           Frame frame,
                           double ax,
                           double bx,
                           double ay,
                           double by,
                           double az,
                           double bz,
                           AbsoluteDate date0)

Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

Errors components are expressed in provided frame.

WARNING : This constructor must not be used with a LocalOrbitalFrame,
acceleration computation would fail.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

frame - the maneuver frame

ax - the slope of the linear function for the x component of the constant thrust error.

bx - the zero value of the linear function for the x component of the constant thrust error.

ay - the slope of the linear function for the y component of the constant thrust error.

by - the zero value of the linear function for the y component of the constant thrust error

az - the slope of the linear function for the z component of the constant thrust error

bz - the zero value of the linear function for the z component of the constant thrust error

date0 - the zero value date

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           Frame frame,
                           Parameter cx,
                           Parameter cy,
                           Parameter cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided frame.

WARNING : This constructor must not be used with a LocalOrbitalFrame,
acceleration computation would fail.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

frame - the maneuver frame

cx - the parameter for the x component of the constant thrust error

cy - the parameter for the y component of the constant thrust error

cz - the parameter for the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           Frame frame,
                           double cx,
                           double cy,
                           double cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided frame.

WARNING : This constructor must not be used with a LocalOrbitalFrame,
acceleration computation would fail.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

frame - the maneuver frame

cx - the x component of the constant thrust error

cy - the y component of the constant thrust error

cz - the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           LOFType lofType,
                           IParamDiffFunction fx,
                           IParamDiffFunction fy,
                           IParamDiffFunction fz)

Create a constant thrust error model whose x, y and z components are parameterizable and differentiable function.

Errors components are expressed in provided local orbital frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

lofType - the LOF type of the maneuver frame

fx - the parameterizable and differentiable function representing the x component of the thrust error.

fy - the parameterizable and differentiable function representing the y component of the thrust error.

fz - the parameterizable and differentiable function representing the z component of the thrust error.

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           LOFType lofType,
                           Parameter ax,
                           Parameter bx,
                           Parameter ay,
                           Parameter by,
                           Parameter az,
                           Parameter bz,
                           AbsoluteDate date0)

Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

Errors components are expressed in provided local orbital frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

lofType - the LOF type of the maneuver frame

ax - the parameter representing the slope of the linear function for the x component of the constant thrust error

bx - the parameter representing the zero value of the linear function for the x component of the constant thrust error

ay - the parameter representing the slope of the linear function for the y component of the constant thrust error

by - the parameter representing the zero value of the linear function for the y component of the constant thrust error

az - the parameter representing the slope of the linear function for the z component of the constant thrust error

bz - the parameter representing the zero value of the linear function for the z component of the constant thrust error

date0 - the zero value date

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           LOFType lofType,
                           double ax,
                           double bx,
                           double ay,
                           double by,
                           double az,
                           double bz,
                           AbsoluteDate date0)

Create a constant thrust error model whose x, y and z components are linear functions:
fx = ax*t + bx
fy = ay*t + by
fz = az*t + bz

Errors components are expressed in provided local orbital frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

lofType - the LOF type of the maneuver frame

ax - the slope of the linear function for the x component of the constant thrust error

bx - the zero value of the linear function for the x component of the constant thrust error

ay - the slope of the linear function for the y component of the constant thrust error

by - the zero value of the linear function for the y component of the constant thrust error

az - the slope of the linear function for the z component of the constant thrust error

bz - the zero value of the linear function for the z component of the constant thrust error

date0 - the zero value date

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           LOFType lofType,
                           Parameter cx,
                           Parameter cy,
                           Parameter cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided local orbital frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

lofType - the LOF type of the maneuver frame

cx - the parameter for the x component of the constant thrust error

cy - the parameter for the y component of the constant thrust error

cz - the parameter for the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(AbsoluteDate date,
                           double duration,
                           LOFType lofType,
                           double cx,
                           double cy,
                           double cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided local orbital frame.

Parameters:

date - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

lofType - the LOF type of the maneuver frame

cx - the x component of the constant thrust error

cy - the y component of the constant thrust error

cz - the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(EventDetector startEventDetector,
                           EventDetector stopEventDetector,
                           IParamDiffFunction fx,
                           IParamDiffFunction fy,
                           IParamDiffFunction fz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in spacecraft frame.

Parameters:

startEventDetector - event detector upon which thrust should starts

stopEventDetector - event detector upon which thrust should stops

fx - the parameterizable and differentiable function representing the x component of the thrust error.

fy - the parameterizable and differentiable function representing the y component of the thrust error.

fz - the parameterizable and differentiable function representing the z component of the thrust error.

ConstantThrustError

public ConstantThrustError(EventDetector startEventDetector,
                           EventDetector stopEventDetector,
                           Parameter cx,
                           Parameter cy,
                           Parameter cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in spacecraft frame.

Parameters:

startEventDetector - event detector upon which thrust should starts

stopEventDetector - event detector upon which thrust should stops

cx - the x component of the constant thrust error

cy - the y component of the constant thrust error

cz - the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(EventDetector startEventDetector,
                           EventDetector stopEventDetector,
                           Frame frame,
                           IParamDiffFunction fx,
                           IParamDiffFunction fy,
                           IParamDiffFunction fz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided frame.

WARNING : This constructor must not be used with a LocalOrbitalFrame,
acceleration computation would fail.

Parameters:

startEventDetector - event detector upon which thrust should starts

stopEventDetector - event detector upon which thrust should stops

frame - the maneuver frame

fx - the parameterizable and differentiable function representing the x component of the thrust error.

fy - the parameterizable and differentiable function representing the y component of the thrust error.

fz - the parameterizable and differentiable function representing the z component of the thrust error.

ConstantThrustError

public ConstantThrustError(EventDetector startEventDetector,
                           EventDetector stopEventDetector,
                           Frame frame,
                           Parameter cx,
                           Parameter cy,
                           Parameter cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided frame.

WARNING : This constructor must not be used with a LocalOrbitalFrame,
acceleration computation would fail.

Parameters:

startEventDetector - event detector upon which thrust should starts

stopEventDetector - event detector upon which thrust should stops

frame - the maneuver frame

cx - the x component of the constant thrust error

cy - the y component of the constant thrust error

cz - the z component of the constant thrust error

ConstantThrustError

public ConstantThrustError(EventDetector startEventDetector,
                           EventDetector stopEventDetector,
                           LOFType lofType,
                           IParamDiffFunction fx,
                           IParamDiffFunction fy,
                           IParamDiffFunction fz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided local orbital frame.

Parameters:

startEventDetector - event detector upon which thrust should starts

stopEventDetector - event detector upon which thrust should stops

lofType - the LOF type of the maneuver frame

fx - the parameterizable and differentiable function representing the x component of the thrust error.

fy - the parameterizable and differentiable function representing the y component of the thrust error.

fz - the parameterizable and differentiable function representing the z component of the thrust error.

ConstantThrustError

public ConstantThrustError(EventDetector startEventDetector,
                           EventDetector stopEventDetector,
                           LOFType lofType,
                           Parameter cx,
                           Parameter cy,
                           Parameter cz)

Create a constant thrust error model whose x, y and z components are constant functions:
fx = cx
fy = cy
fz = cz

Errors components are expressed in provided local orbital frame.

Parameters:

startEventDetector - event detector upon which thrust should starts

stopEventDetector - event detector upon which thrust should stops

lofType - the LOF type of the maneuver frame

cx - the x component of the constant thrust error

cy - the y component of the constant thrust error

cz - the z component of the constant thrust error

Method Detail

setFiring

public void setFiring(boolean isFiring)

Set maneuver status. This method is meant to be used if the propagation starts during a maneuver. As a result thrust will be firing at the beginning of the propagation and stops when crossing stop event.

Used in conjunction with isFiring(), the user can stop/restart a propagation during a maneuver.

Parameters:

isFiring - true if propagation should start during the maneuver

isFiring

public boolean isFiring()

Returns maneuver status (firing or not).

Used in conjunction with setFiring(boolean), the user can stop/restart a propagation during a maneuver.

Returns:

true if maneuver is thrust firing.

getStartDate

public AbsoluteDate getStartDate()

Return the maneuver start date (if a date or a DateDetector as been provided).

Returns:

the maneuver start date if a date or a DateDetector as been provided, null otherwise.

getEndDate

public AbsoluteDate getEndDate()

Return the maneuver stop date (if a date or a DateDetector as been provided).

Returns:

the maneuver stop date if a date or a DateDetector as been provided, null otherwise.

addContribution

public void addContribution(SpacecraftState s,
                            TimeDerivativesEquations adder)
                     throws PatriusException

Compute the contribution of the constant thrust error model to the perturbing acceleration. The contribution is zero when the date is outside the thrust time interval.

Specified by:

addContribution in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

adder - object where the contribution should be added

Throws:

PatriusException - if some specific error occurs

computeAcceleration

public Vector3D computeAcceleration(SpacecraftState s)
                             throws PatriusException

Compute the acceleration due to the force.

Specified by:

computeAcceleration in interface ForceModel

Parameters:

s - current state information: date, kinematics, attitude

Returns:

acceleration in the SpacecraftState frame

Throws:

PatriusException - if some specific error occurs

getEventsDetectors

public EventDetector[] getEventsDetectors()

Get the discrete events related to the model.

Specified by:

getEventsDetectors in interface ForceModel

Returns:

array of events detectors or null if the model is not related to any discrete events

addDAccDState

public void addDAccDState(SpacecraftState state,
                          double[][] dAccdPos,
                          double[][] dAccdVel)
                   throws PatriusException

Compute acceleration derivatives with respect to state parameters.

Specified by:

addDAccDState in interface IJacobiansParameterizable

Parameters:

state - spacecraft state

dAccdPos - acceleration derivatives with respect to position

dAccdVel - acceleration derivatives with respect to velocity

Throws:

PatriusException - if derivatives cannot be computed

addDAccDParam

public void addDAccDParam(SpacecraftState state,
                          Parameter param,
                          double[] dAccdParam)
                   throws PatriusException

Compute acceleration derivatives with respect to additional parameters.

Specified by:

addDAccDParam in interface IJacobiansParameterizable

Parameters:

state - spacecraft state

param - the parameter with respect to which derivatives are required

dAccdParam - acceleration derivatives with respect to specified parameters

Throws:

PatriusException - if derivatives cannot be computed

computeGradientPosition

public boolean computeGradientPosition()

This method returns true if the acceleration partial derivatives with respect to position have to be computed.

Specified by:

computeGradientPosition in interface GradientModel

Returns:

true if the derivatives have to be computed, false otherwise

computeGradientVelocity

public boolean computeGradientVelocity()

This method returns true if the acceleration partial derivatives with respect to velocity have to be computed.

Specified by:

computeGradientVelocity in interface GradientModel

Returns:

true if the derivatives have to be computed, false otherwise