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.

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.

DeclaredName

The name of the object as declared.

DisplayName

The name displayed for this object in output windows such as views, plots, and reports.

DutyCycle

The percentage of ontime 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 postburn. 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.

ThrusterC13

Thirteenth coefficient of the thrust performance polynomial.

ThrusterC14

Fourteenth coefficient of the thrust performance polynomial.

ThrusterC15

Fifteenth coefficient of the thrust performance polynomial.

ThrusterC16

Sixteenth coefficient of the thrust performance polynomial.

ThrusterC2

Second coefficient of the thrust performance polynomial.

ThrusterC3

Third coefficient of the thrust performance polynomial.

ThrusterC4

Fourth coefficient of the thrust performance polynomial.

ThrusterC5

Fifth coefficient of the thrust performance polynomial.

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.PC16. 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 ontime 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.
