Name
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Description
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DeclaredName
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The name of the object as declared.
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DisplayName
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The name displayed for this object in output windows such as views, plots, and reports.
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FinalCenterOfGravity
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The final location of the center of gravity of the propellant in the Tank. The location is based on the Tank's reference location (TankReference). This will be used as a data point in the interpolation calculation of the Tank's center of gravity.
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FinalMass
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The final mass of the propellant in the Tank. This will be used as a data point in the interpolation calculation of the center of gravity and moment of inertia.
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FinalMOI
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The tank moment of inertia tensor.
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InitialCenterOfGravity
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The final location of the center of gravity of the propellant in the Tank. The location is based on the Tank's reference location (TankReference). This will be used as a data point in the interpolation calculation of the Tank's center of gravity.
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InitialMass
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The initial mass of the tank.
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InitialMOI
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The tank moment of inertia tensor.
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MassMixPartsPer
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Indicates the ratio of mass supplied by this Tank when more than one Tank is being used to supply a Thruster. This property sets the number of parts supplied by this Tank; the resulting ratio is calculated as parts supplied by this Tank per total parts supplied by all Tanks for a given Thruster. This property is used in the calculation of the Thruster AveragePreInletPress, AveragePreInletRefTemp, and AveragePreInletTemp properties. If only one Tank is used at a time, this property should be set to 1.
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MOI
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The tank moment of inertia tensor.
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ObjectId
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The unique identifier for the object.
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ObjectType
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The type of the object.
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TankCenterOfGravity
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The center of gravity associated with the fuel mass in the tank. This location is determined based on the tank's reference location, fill line orientation, tank volume, fuel mass, and fuel density. The location is referenced from the origin of the Spacecraft BCS and is measured in meters.
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TankFuelDensity
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The density of the fuel in the Tank.
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TankMass
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The current mass of the fuel in the Tank. This property is updated as fuel is consumed.
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TankOrientation
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The unit vector in the Spacecraft body coordinate system that defines the primary axis (or z-axis) of the tank. The tank's fill line is oriented perpendicular to this axis. The tank's center of gravity is determined based on this fill line orientation, the tank reference location, tank volume, fuel mass, and fuel density.
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TankPressure
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The pressure of the Tank. The Thruster.AveragePreInletPress property indicates the weighted average pressure (based on mix ratio) for all Tanks attached to that Thruster with open valves.
If the TestTankConsistency property of a Thruster is set to 1, the pressure for each Tank attached to that Thruster cannot differ by more than the MaxPressureDiff for that Thruster. If the ForceTankConsistency property of a Thruster includes pressure equalization, the pressure of each Tank attached to that Thruster will be equalized post-burn using a weighted average of all attached Tanks, based on their mix ratios.
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TankPressureControl
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Specifies whether to model a reduction of tank pressure as mass is depleted (blow down system), or to model a pressure-regulated system.
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TankReference
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The geometric center of the SphericalTank. This location is referenced from the origin of the Spacecraft BCS. The tank's center of gravity is determined based on this reference location, the fill line orientation, tank volume, fuel mass, and fuel density.
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TankRefTemperature
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The temperature of the Tank when it is first loaded with fuel. The Thruster.AveragePreInletRefTemp indicates the weighted average reference temperature (based on mix ratio) for all Tanks attached to that Thruster with open valves. The AveragePreInletRefTemp is used in the calculation of Thrust and Isp along with the AveragePreInletTemp, ThrusterInletPressure, and Thruster coefficients.
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TankSecondaryOrientation
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The vector representing the secondary axis of the tank orientation with respect to the body centered coordinate system.
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TankTemperature
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The temperature of the Tank. The Thruster.AveragePreInletTemp property indicates the weighted average temperature (based on mix ratio) for all Tanks attached to that Thruster with open valves. The AveragePreInletTemp is used in the calculation of Thrust and Isp along with the AveragePreInletRefTemp, ThrusterInletPressure, and Thruster coefficients.
If the TestTankConsistency property of a Thruster is set to 1, the temperatures of all Tanks attached to that Thruster cannot differ by more than the MaxTempDiff for that Thruster. If the ForceTankConsistency property of a Thruster includes temperature equalization, the temperature of each Tank attached to that Thruster will be equalized post-burn using a weighted average of all attached Tanks, based on their mix ratios.
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TankVolume
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The physical volume of the Tank.
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