Name
|
Description
|
AveragePreInletPress
|
Average Tank pressure prior to Thruster inlet. This is a weighted average (based on mix ratio) of the Tank.TankPressure property of all attached Tanks with open valves. This property is used in the calculation of the Thruster.ThrusterInletPressure along with the Thruster pressure drop coefficients.
|
AveragePreInletRefTemp
|
Average Tank reference temperature prior to Thruster inlet. This is a weighted average (based on mix ratio) of the Tank.TankRefTemperature property of all attached Tanks with open valves. This property is used in the calculation of Thrust and Isp along with the AveragePreInletTemp, ThrusterInletPressure, and Thruster coefficients.
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AveragePreInletTemp
|
Average Tank temperature prior to Thruster inlet. This is a weighted average (based on mix ratio) of the Tank.TankTemperature property of all attached Tanks with open valves. This property is used in the calculation of Thrust and Isp along with the AveragePreInletRefTemp, ThrusterInletPressure, and Thruster coefficients.
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DeclaredName
|
The name of the object as declared.
|
DisplayName
|
The name displayed for this object in output windows such as views, plots, and reports.
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DutyCycle
|
The percentage of on-time of the thruster during a burn. This property scales the mass depletion and the acceleration due to thrust.
|
ForceTankConsistency
|
Determines whether the temperature and/or pressure of the attached Tanks are equalized post-burn. The equalized temperature and/or pressure are computed as a weighted average of all attached Tanks, based on their mix ratios.
|
IspScaleFactor
|
Scale factor applied to the Isp that is used in determining mass flow.
|
MaxPressureDiff
|
The maximum pressure difference that is allowed between Tanks attached to this Thruster, if consistency checking is enabled by setting TestTankConsistency to 1.
|
MaxTempDiff
|
Maximum temperature difference that is allowed between Tanks attached to this Thruster, if consistency checking is enabled by setting TestTankConsistency to 1.
|
ObjectId
|
The unique identifier for the object.
|
ObjectType
|
The type of the object.
|
Orientation
|
Dimensionless unit vector representing pointing direction of the applied acceleration in the Spacecraft body coordinate frame. This is only used to determine the direction of applied acceleration when a Finite Burn using the "Attitude" system is used to maneuver the Spacecraft. Otherwise, the FiniteBurn or ImpulsiveBurn object specifies the direction of the maneuver.
|
Position
|
The vector representing the dry vehicle center of mass (i.e. no attached Tanks are included in this property) referenced from the origin of the Spacecraft's body fixed frame. This property is used in calculating the CenterOfMass, which includes all attached Tanks in its calculation.
|
ScaleFactor
|
A measure of the efficiency of the thruster. This property adjusts the acceleration due to thrust without changing the mass depletion.
|
TankValve
|
Determines the state of a valve controlling mass flow from a set of tanks to the thruster. A value of 0 indicates no mass will flow and a value of 1 indicates mass will flow.
|
TestTankConsistency
|
Determines whether temperature and pressure consistency checks are performed when multiple Tanks simultaneously feed a Thruster.
|
ThrusterC1
|
First coefficient of the thrust performance polynomial.
|
ThrusterC10
|
Tenth coefficient of the thrust performance polynomial.
|
ThrusterC11
|
Eleventh coefficient of the thrust performance polynomial.
|
ThrusterC12
|
Twelfth coefficient of the thrust performance polynomial.
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ThrusterC13
|
Thirteenth coefficient of the thrust performance polynomial.
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ThrusterC14
|
Fourteenth coefficient of the thrust performance polynomial.
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ThrusterC15
|
Fifteenth coefficient of the thrust performance polynomial.
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ThrusterC16
|
Sixteenth coefficient of the thrust performance polynomial.
|
ThrusterC2
|
Second coefficient of the thrust performance polynomial.
|
ThrusterC3
|
Third coefficient of the thrust performance polynomial.
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ThrusterC4
|
Fourth coefficient of the thrust performance polynomial.
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ThrusterC5
|
Fifth coefficient of the thrust performance polynomial.
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ThrusterC6
|
Sixth coefficient of the thrust performance polynomial.
|
ThrusterC7
|
Seventh coefficient of the thrust performance polynomial.
|
ThrusterC8
|
Eighth coefficient of the thrust performance polynomial.
|
ThrusterC9
|
Ninth coefficient of the thrust performance polynomial.
|
ThrusterGravityConst
|
The value of the gravitational acceleration at the surface of the Earth. Used in the conversion of specific impulse between English and MKS units. The default value is 9.81 m/s^2 but can be adjusted to the value adopted by the thruster manufacturer. Used for mass depletion.
|
ThrusterInletPressure
|
Pressure at the Thruster inlet. This is calculated based on the Thruster.AveragePreInletPressure property and the pressure drop coefficients, Thruster.PC1-6. This property is used in the calculation of Thrust and Isp along with the AveragePreInletTemp, AveragePreInletRefTemp, and Thruster coefficients.
|
ThrusterK1
|
First coefficient of the specific impulse performance polynomial.
|
ThrusterK10
|
Tenth coefficient of the specific impulse performance polynomial.
|
ThrusterK11
|
Eleventh coefficient of the specific impulse performance polynomial.
|
ThrusterK12
|
Twelfth coefficient of the specific impulse performance polynomial.
|
ThrusterK13
|
Thirteenth coefficient of the specific impulse performance polynomial.
|
ThrusterK14
|
Fourteenth coefficient of the specific impulse performance polynomial.
|
ThrusterK15
|
Fifteenth coefficient of the specific impulse performance polynomial.
|
ThrusterK16
|
Sixteenth coefficient of the specific impulse performance polynomial.
|
ThrusterK2
|
Second coefficient of the specific impulse performance polynomial.
|
ThrusterK3
|
Third coefficient of the specific impulse performance polynomial.
|
ThrusterK4
|
Fourth coefficient of the specific impulse performance polynomial.
|
ThrusterK5
|
Fifth coefficient of the specific impulse performance polynomial.
|
ThrusterK6
|
Sixth coefficient of the specific impulse performance polynomial.
|
ThrusterK7
|
Seventh coefficient of the specific impulse performance polynomial.
|
ThrusterK8
|
Eighth coefficient of the specific impulse performance polynomial.
|
ThrusterK9
|
Ninth coefficient of the specific impulse performance polynomial.
|
ThrusterOn
|
Determines whether a thruster is on or off. Individual valves connected to a Thruster can also be opened or closed using the Valve.State property.
|
ThrusterPC1
|
First coefficient of the polynomial to model the pressure drop from Tank to Thruster
|
ThrusterPC2
|
Second coefficient of the polynomial to model the pressure drop from Tank to Thruster
|
ThrusterPC3
|
Third coefficient of the polynomial to model the pressure drop from Tank to Thruster
|
ThrusterPC4
|
Fourth coefficient of the polynomial to model the pressure drop from Tank to Thruster
|
ThrusterPC5
|
Fifth coefficient of the polynomial to model the pressure drop from Tank to Thruster
|
ThrusterPC6
|
Sixth coefficient of the polynomial to model the pressure drop from Tank to Thruster
|
Type
|
The type of thruster.
|
UnboundedDutyCycle
|
The percentage of on-time of the thruster during a burn. This property offers the same functionality as the DutyCycle property, but doesn't have range restrictions. It is recomended that the primary DutyCycle property be used, but this property is supported to offer compatibility with previous versions of FreeFlyer. This property scales the mass depletion and the acceleration due to thrust.
|
Valves
|
The Valves that connect the thruster to tanks.
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