RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Cryogenic_Tank

Cryogenic_Tank#

class Cryogenic_Tank(*args, **kwarg)[source]#

Bases: Non_Integral_Tank

A non-integral cryogenic fuel tank for liquid hydrogen, liquid natural gas, or other cryogenic propellants.

The user must set fuel and design_inlet_temperature for the specific cryogenic propellant being stored.

geometry_type#

Tank shape: ‘cylindrical’, ‘conformal’, or ‘prismatic’ (default: ‘cylindrical’).

Type:

str

design_inlet_temperature#

Nominal inlet temperature of the cryogen [K] (default: None).

Type:

float or None

design_altitude#

Design altitude for thermal/structural sizing [m].

Type:

float

design_heat_flux#

Maximum allowable heat leak per unit area [W/m²] (default: 20).

Type:

float

design_total_heat_transfer#

Maximum allowable total heat leak [W] (default: 2000).

Type:

float

ullage_volume_fraction#

Fraction of internal volume reserved for ullage (default: 0.07).

Type:

float

safety_factor#

Structural factor of safety (default: 1.6).

Type:

float

pressure_factor#

Internal pressure multiplier for sizing (default: 5).

Type:

float

compute_volume(wings, fuselages, fuel_tanks)[source]#

Computes the net fuel volume and cryogenic structure/insulation sizing.

The method operates in two stages. First, the outer envelope is determined from the wing geometry (or from user-supplied dimensions for standalone tanks). Second, cryogenic-specific sizing works inward from that envelope to compute insulation thickness, structural wall thickness, and the resulting net fuel volume.

Cylindrical#

  • Wing spanwise: outer envelope from compute_wing_non_integral_tank_volume

  • Wing transverse: outer envelope from compute_wing_transverse_non_integral_tank_volume

  • Standalone: outer envelope from compute_rounded_end_cylindrical_tank_volume

    using user-set lengths.external and diameters.external

  • Then: compute_cryogenic_cylindrical_tank_volume sizes

    insulation and structure inward

Conformal#

  • Wing spanwise: outer envelope from compute_wing_integral_tank_volume

  • Wing transverse: outer envelope from compute_wing_transverse_integral_tank_volume

  • Then: compute_cryogenic_conformal_tank_volume sizes

    insulation and structure inward

Prismatic#

  • Uses user-set lengths.external, widths.external, heights.external

  • Then: compute_cryogenic_conformal_tank_volume sizes

    insulation and structure inward

compute_moments_of_inertia(vehicle, center_of_gravity=[[0, 0, 0]])[source]#

Computes the moment of inertia tensor for a fuel tank.

Parameters:

center_of_gravity (list, optional) – Reference point coordinates for moment calculation, defaults to [[0, 0, 0]]

Returns:

I – 3x3 moment of inertia tensor in kg*m^2

Return type:

ndarray

compute_center_of_gravity(vehicle)[source]#

Computes the center of gravity for a fuel tank.

Parameters:

center_of_gravity (list, optional) – Reference point coordinates for moment calculation, defaults to [[0, 0, 0]]

Returns:

I – 3x3 moment of inertia tensor in kg*m^2

Return type:

ndarray