Maneuver related Calc Objects.
| Name |
Dimension |
Type |
Description |
| Time |
DateFormat |
Real Number |
Time. |
| DeltaV |
Rate |
Real Number |
Delta-V magnitude integrated along the trajectory
path. |
| FuelMass |
MassUnit |
Real Number |
Fuel mass remaining. |
| Fuel_Density |
SmallDensity |
Real Number |
Density of the fuel. |
| Fuel_Used |
MassUnit |
Real Number |
Fuel used since the initial state of the
spacecraft. |
| Inertial_DeltaV_Magnitude |
Rate |
Real Number |
The magnitude of accumulated Delta-V integrated in
inertial coordinates. Computed by integrating the thrust
acceleration over time. |
| Inertial_DeltaVx |
Rate |
Real Number |
The X component of accumulated Delta-V integrated
in inertial coordinates. |
| Inertial_DeltaVy |
Rate |
Real Number |
The Y component of accumulated Delta-V integrated
in inertial coordinates. |
| Inertial_DeltaVz |
Rate |
Real Number |
The Z component of accumulated Delta-V integrated
in inertial coordinates. |
| Specific_Impulse |
SpecificImpulseUnit |
Real Number |
The specific impulse during the maneuver,
accounting for all engines, computed using the rocket
equation. |
| Tank_Pressure |
PressureUnit |
Real Number |
Fuel tank pressure. |
| Tank_Temperature |
Temperature |
Real Number |
Fuel tank temperature. |
| Thrust_Vector_X |
ForceUnit |
Real Number |
The X component of the total thrust vector. The
Calc Object allows a choice of coordinate systems. The default is
Earth Centered Inertial. |
| Thrust_Vector_Y |
ForceUnit |
Real Number |
The Y component of the total thrust vector. The
Calc Object allows a choice of coordinate systems. The default is
Earth Centered Inertial. |
| Thrust_Vector_Z |
ForceUnit |
Real Number |
The Z component of the total thrust vector. The
Calc Object allows a choice of coordinate systems. The default is
Earth Centered Inertial. |
| Total_Mass |
MassUnit |
Real Number |
Total mass (fuel plus dry mass). |
| Total_Mass_Flow_Rate |
Mass Per Time |
Real Number |
The total mass flow rate, accounting for all
engines, during a maneuver. |