core_mission module¶
SSBJ Mission computation¶
Classes:
|
Class defining mission analysis for Sobieski problem and related method to the mission problem such as disciplines computation, constraints, reference optimum. |
- class gemseo.problems.sobieski.core_mission.SobieskiMission(sobieski_base)[source]¶
Bases:
object
Class defining mission analysis for Sobieski problem and related method to the mission problem such as disciplines computation, constraints, reference optimum.
Constructor.
Attributes:
Methods:
blackbox_mission
(x_shared, y_14, y_24, y_34)THIS SECTION COMPUTES THE A/C RANGE from Breguet's law.
Computation of partial derivative of log of weight ratio wrt fuel weight.
Computation of partial derivative of log of weight ratio wrt total weight.
compute_drange_dfuelweight
(x_shared, y_14, ...)Computation of range derivative wrt fuel weight.
compute_drange_dtotalweight
(x_shared, y_14, ...)Computation of range derivative wrt total weight.
compute_dtheta_dh
(x_shared)Computation of air temperature and its derivative wrt altitude.
compute_dweightratio_dwf
(y_14)Computation of partial derivative of weight ratio wrt fuel weight.
compute_dweightratio_dwt
(y_14)Computation of derivative of weight ratio wrt total weight.
compute_range
(x_shared, y_14, y_24, y_34)Computation of range from Breguet formula.
compute_sqrt_theta
(x_shared)Computation of air temperature a.
compute_weight_ratio
(y_14)Computation of weight ratio of Breguet formula.
derive_blackbox_mission
(x_shared, y_14, ...)THIS SECTION COMPUTES THE A/C RANGE from Breguet's law.
- DTYPE_COMPLEX = 'complex128'¶
- DTYPE_DOUBLE = 'float64'¶
- blackbox_mission(x_shared, y_14, y_24, y_34)[source]¶
THIS SECTION COMPUTES THE A/C RANGE from Breguet’s law.
- Parameters
x_shared (numpy array) –
shared design variable vector:
x_shared[0]: thickness/chord ratio
x_shared[1]: altitude
x_shared[2]: Mach
x_shared[3]: aspect ratio
x_shared[4]: wing sweep
x_shared[5]: wing surface area
y_14 (numpy array) –
shared variables coming from blackbox_structure:
y_14[0]: total aircraft weight
y_14[1]: fuel weight
y_24 (numpy array) – shared variables coming from blackbox_aerodynamics (lift/drag ratio)
y_34 (numpy array) – shared variables coming from blackbox_propulsion (SFC)
- Returns
y_4: range value
- Return type
numpy array
- compute_dlnweightratio_dwf(y_14)[source]¶
Computation of partial derivative of log of weight ratio wrt fuel weight.
- Parameters
y_14 (numpy array) –
shared variables coming from blackbox_structure:
y_14[0]: total aircraft weight
y_14[1]: fuel weight
- Returns
d(ln(weight ratio)/d(fuel weight)
- Return type
numpy array
- compute_dlnweightratio_dwt(y_14)[source]¶
Computation of partial derivative of log of weight ratio wrt total weight.
- Parameters
y_14 (numpy array) –
shared variables coming from blackbox_structure:
y_14[0]: total aircraft weight
y_14[1]: fuel weight
- Returns
d(ln(weight ratio)/d(total weight)
- Return type
numpy array
- compute_drange_dfuelweight(x_shared, y_14, y_24, y_34, sqrt_theta)[source]¶
Computation of range derivative wrt fuel weight.
- Parameters
x_shared (numpy array) – shared design variable vector
y_14 (numpy array) – shared variables coming from blackbox_structure
y_24 (numpy array) – shared variables coming from blackbox_aerodynamics
y_34 (numpy array) – shared variables coming from blackbox_propulsion
sqrt_theta (numpy array) – square root of air temperature
- Returns
d(range) / d(fuel weight)
- Return type
numpy array
- compute_drange_dtotalweight(x_shared, y_14, y_24, y_34, sqrt_theta)[source]¶
Computation of range derivative wrt total weight.
- Parameters
x_shared (numpy array) – shared design variable vector
y_14 (numpy array) – shared variables coming from blackbox_structure
y_24 (numpy array) – shared variables coming from blackbox_aerodynamics
y_34 (numpy array) – shared variables coming from blackbox_propulsion
sqrt_theta (numpy array) – square root of air temperature
- Returns
d(range) / d(total weight)
- Return type
numpy array
- compute_dtheta_dh(x_shared)[source]¶
Computation of air temperature and its derivative wrt altitude.
- Parameters
x_shared (numpy array) – shared design variable vector
- Returns
square root of air temperature, dtheta_dh
- Return type
numpy array
- static compute_dweightratio_dwf(y_14)[source]¶
Computation of partial derivative of weight ratio wrt fuel weight.
- Parameters
y_14 (numpy array) –
shared variables coming from blackbox_structure:
y_14[0]: total aircraft weight
y_14[1]: fuel weight
- Returns
dweightratio_dfuelweight
- Return type
numpy array
- static compute_dweightratio_dwt(y_14)[source]¶
Computation of derivative of weight ratio wrt total weight.
- Parameters
y_14 (numpy array) –
shared variables coming from blackbox_structure:
y_14[0]: total aircraft weight
y_14[1]: fuel weight
- Returns
dweightratio_dtotalweight
- Return type
numpy array
- compute_range(x_shared, y_14, y_24, y_34)[source]¶
Computation of range from Breguet formula.
- Parameters
x_shared (numpy array) –
shared design variable vector:
x_shared[0]: thickness/chord ratio
x_shared[1]: altitude
x_shared[2]: Mach
x_shared[3]: aspect ratio
x_shared[4]: wing sweep
x_shared[5]: wing surface area
y_14 (numpy array) –
shared variables coming from blackbox_structure:
y_14[0]: total aircraft weight
y_14[1]: fuel weight
y_24 (numpy array) – shared variables coming from blackbox_aerodynamics (lift/drag ratio)
y_34 (numpy array) – shared variables coming from blackbox_propulsion (SFC)
- Returns
range value
- Return type
numpy array
- compute_sqrt_theta(x_shared)[source]¶
Computation of air temperature a.
- Parameters
x_shared (numpy array) – shared design variable vector
- Returns
square root of air temperature
- Return type
numpy array
- static compute_weight_ratio(y_14)[source]¶
Computation of weight ratio of Breguet formula.
- Parameters
y_14 (numpy array) –
shared variables coming from blackbox_structure
y_14[0]: total aircraft weight
y_14[1]: fuel weight
- Returns
Wt / (Wt -Wf)
- Return type
numpy array
- derive_blackbox_mission(x_shared, y_14, y_24, y_34)[source]¶
THIS SECTION COMPUTES THE A/C RANGE from Breguet’s law.
- Parameters
x_shared (numpy array) –
shared design variable vector:
x_shared[0]: thickness/chord ratio
x_shared[1]: altitude
x_shared[2]: Mach
x_shared[3]: aspect ratio
x_shared[4]: wing sweep
x_shared[5]: wing surface area
y_14 (numpy array) –
shared variables coming from blackbox_structure:
y_14[0]: total aircraft weight
y_14[1]: fuel weight
y_24 – shared variables coming from blackbox_aerodynamics (lift/drag ratio)
y_34 (numpy array) – shared variables coming from blackbox_propulsion (SFC)
- Returns
jacobian matrix of partial derivatives
- Return type
dict(dict(ndarray))