FiniteBurn Object

Description

The FiniteBurn models the effect of a finite thrust maneuver on a Spacecraft orbit. See Finite Burns for more information.

Inheritance Hierarchy: Object->ThrustEvent->Burn->FiniteBurn

Available In Editions:

Engineer

Mission

Timing Precision Mode

This page describes functionality in millisecond timing precision mode. Millisecond timing precision mode is deprecated and will be removed in a future release. We recommend that you migrate your Mission Plans to nanosecond timing precision mode.

Click here to see the documentation for this object in nanosecond timing precision mode.

Name	Description	Attributes
AttitudeSystem	Determines the attitude frame in which the Finite Burn will be applied to the spacecraft.	Type: Variable Access: Read/Write
BurnDirection	The components of the thrust vector in the coordinates of the attitude system specified by the chosen AttitudeSystem.	Type: Array Access: Read/Write
BurnDuration	The duration of the maneuver.	Type: Variable Access: Read/Write Units: s
DeclaredName	The name of the object as declared.	Type: String Access: Read-Only
ExecutionPhase	Reveals which portion of the event sequence is currently executing.	Type: Variable Access: Read-Only
LinearTangentSteering	The property used to set up or edit Linear Tangent Steering settings.	Type: LinearTangentSteering Access: Read-Only
ManeuverOffsetTime	The offset time from the current Spacecraft epoch at which to apply the maneuver. The Spacecraft will be propagated to the offset time. A negative offset time can be used.	Type: Variable Access: Read/Write Units: s
Name	The name displayed for this object in output windows such as views, plots, and reports.	Type: String Access: Read/Write
NetDeltaV	Returns the net Delta-V (change in velocity) obtained from applying the FiniteBurn to a Spacecraft using the Maneuver command. The net Delta-V calculation assumes that the FiniteBurn object uses the "Attitude" reference frame. The returned array is in the Spacecraft Body Coordinate system. This property is not updated unless a Spacecraft is maneuvered, even if any of the FiniteBurn properties are changed.	Type: Array Access: Read-Only Units: km/s
ObjectId	The unique identifier for the object.	Type: Variable Access: Read-Only
ObjectType	The type of the object.	Type: String Access: Read-Only
OD	This property contains the OD settings for all the FiniteBurn properties that can be estimated.	Type: FiniteBurnODProperties Access: Read-Only
ThrustScaleFactor	The overall thrust scale factor for the maneuver.	Type: Variable Access: Read/Write
ThrustSteeringMethod	Set the steering method to use throughout the burn.	Type: String Access: Read/Write

Name

Description

Attributes

ManeuverStartTime

The offset time from the current Spacecraft epoch at which to apply the maneuver. The Spacecraft will be propagated to the offset time. A negative offset time can be used.

This property has been Deprecated. Please use ManeuverOffsetTime instead.

Type: Variable

Access: Read/Write

Units: s

X_Component

For AttitudeSystem = 0, ICRF X-directed unit vector component of the maneuver.

For AttitudeSystem = 1, Velocity directed unit vector component of the maneuver.

For AttitudeSystem = 2, Co-Velocity directed unit vector component of the maneuver.

For AttitudeSystem = 3, the Spacecraft's attitude is adjusted so that Spacecraft.EulerAngle1 is temporarily set to the value specified by FiniteBurn.X_Component for the duration of the maneuver. The Euler angle is evaluated in degrees and is referenced to the Spacecraft's attitude reference frame. The Euler Sequence used by the FiniteBurn object is defined by the Spacecraft object's Euler Sequence. Individual thruster orientations defined in the Thruster object(s) are used for directing delta-v.

For AttitudeSystem = 4, Y cross Z directed unit vector component of the maneuver.

For AttitudeSystem = 5, Position directed component of the maneuver.

This property has been Deprecated. Please use the BurnDirection vector instead.

Type: Variable

Access: Read/Write

Y_Component

For AttitudeSystem = 0, ICRF Y-directed unit vector component of the maneuver.

For AttitudeSystem = 1, Orbit Normal directed unit vector component of the maneuver.

For AttitudeSystem = 2, Negative Orbit Normal directed unit vector component of the maneuver.

For AttitudeSystem = 3, the Spacecraft's attitude is adjusted so that Spacecraft.EulerAngle2 is temporarily set to the value specified by FiniteBurn.Y_Component for the duration of the maneuver. The Euler angle is evaluated in degrees and is referenced to the Spacecraft's attitude reference frame. The Euler Sequence used by the FiniteBurn object is defined by the Spacecraft object's Euler Sequence. Individual thruster orientations defined in the Thruster object(s) are used for directing delta-v.

For AttitudeSystem = 4, Negative Orbit Normal directed unit vector component of the maneuver.

For AttitudeSystem = 5, Velocity directed component of the maneuver.

This property has been Deprecated. Please use the BurnDirection vector instead.

Type: Variable

Access: Read/Write

Z_Component

For AttitudeSystem = 0, ICRF Z-directed unit vector component of the maneuver.

For AttitudeSystem = 1, Orbit Bi-Normal directed unit vector component of the maneuver.

For AttitudeSystem = 2, Nadir directed unit vector component of the maneuver.

For AttitudeSystem = 3, the Spacecraft's attitude is adjusted so that Spacecraft.EulerAngle3 is temporarily set to the value specified by FiniteBurn.Z_Component for the duration of the maneuver. The Euler angle is evaluated in degrees and is referenced to the Spacecraft's attitude reference frame. The Euler Sequence used by the FiniteBurn object is defined by the Spacecraft object's Euler Sequence. Individual thruster orientations defined in the Thruster object(s) are used for directing delta-v.

For AttitudeSystem = 4, Intersection Normal to the Earth's Surface directed unit vector component of the maneuver.

For AttitudeSystem = 5, Orbit Normal directed component of the maneuver.

This property has been Deprecated. Please use the BurnDirection vector instead.

Type: Variable

Access: Read/Write