gemseo.problems.mdo.sobieski.core.structure module#
Structure discipline for the Sobieski's SSBJ use case.
- class SobieskiStructure(sobieski_base)[source]#
Bases:
SobieskiDiscipline
Structure discipline for the Sobieski's SSBJ use case.
- Parameters:
sobieski_base (SobieskiBase) -- The Sobieski base.
- execute(x_shared, y_21, y_31, x_1, true_cstr=False, c_0=None, c_1=None, c_2=None)[source]#
Compute the structural outputs and the structural constraints.
- Parameters:
x_shared (ndarray) -- The values of the shared design variables, where
x_shared[0]
is the thickness-to-chord ratio,x_shared[1]
is the altitude,x_shared[2]
is the Mach number,x_shared[3]
is the aspect ratio,x_shared[4]
is the wing sweep andx_shared[5]
is the wing surface area.y_21 (ndarray) -- The lift coefficient.
y_31 (ndarray) -- The engine weight.
x_1 (ndarray) -- The wing taper ratio
x_1[0]
and the wingbox x-sectional areax_1[1]
.true_cstr (bool) --
If
True
, return the value of the constraint outputs. Otherwise, return the distance to the corresponding constraint thresholds.By default it is set to False.
c_0 (ndarray | None) -- The minimum fuel weight. If
None
, useSobieskiBase.constants()
.c_1 (ndarray | None) -- The miscellaneous weight. If
None
, useSobieskiBase.constants()
.c_2 (ndarray | None) -- The maximum load factor. If
None
, useSobieskiBase.constants()
.
- Returns:
The structural outputs and the structural constraints.
- Return type:
tuple[ndarray, ndarray, ndarray, ndarray, ndarray]
- linearize(x_shared, y_21, y_31, x_1, true_cstr=False, c_0=None, c_1=None, c_2=None)[source]#
Derive the structural outputs and the structural constraints.
- Parameters:
x_shared (ndarray) -- The values of the shared design variables, where
x_shared[0]
is the thickness-to-chord ratio,x_shared[1]
is the altitude,x_shared[2]
is the Mach number,x_shared[3]
is the aspect ratio,x_shared[4]
is the wing sweep andx_shared[5]
is the wing surface area.y_21 (ndarray) -- The lift coefficient.
y_31 (ndarray) -- The engine weight.
x_1 (ndarray) -- The wing taper ratio
x_1[0]
and the wingbox x-sectional areax_1[1]
.true_cstr (bool) --
If
True
, return the value of the constraint outputs. Otherwise, return the distance to the corresponding constraint thresholds.By default it is set to False.
c_0 (float | None) -- The minimum fuel weight. If
None
, useSobieskiBase.constants()
.c_1 (float | None) -- The miscellaneous weight. If
None
, useSobieskiBase.constants()
.c_2 (float | None) -- The maximum load factor. If
None
, useSobieskiBase.constants()
.
- Returns:
The derivatives of the structural outputs and the structural constraints.
- Return type:
- STRESS_LIMIT = 1.09#
- TWIST_LOWER_LIMIT = 0.8#
- TWIST_UPPER_LIMIT = 1.04#