BladeAD.utils.var_groups
Module Contents
Classes
Data class for aircraft states. |
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Data class for atmospheric states. Default values are for sea-level. |
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Rotor analysis inputs data class. |
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Rotor analysis outputs data class. |
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Data class for rotor mesh parameters. |
- class BladeAD.utils.var_groups.AircaftStates
Bases:
csdl_alpha.VariableGroupData class for aircraft states.
- Parameters
- uUnion[float, int, csdl.Variable, np.ndarray]
u velocity component
- vUnion[float, int, csdl.Variable, np.ndarray]
v velocity component
- wUnion[float, int, csdl.Variable, np.ndarray]
w velocity component
- pUnion[float, int, csdl.Variable, np.ndarray]
p angular velocity component (roll rate)
- qUnion[float, int, csdl.Variable, np.ndarray]
q angular velocity component (pitch rate)
- rUnion[float, int, csdl.Variable, np.ndarray]
r angular velocity component (yaw rate)
- phiUnion[float, int, csdl.Variable, np.ndarray]
phi euler angle
- thetaUnion[float, int, csdl.Variable, np.ndarray]
theta euler angle
- psiUnion[float, int, csdl.Variable, np.ndarray]
psi euler angle
- xUnion[float, int, csdl.Variable, np.ndarray]
x position (not used in rotor analysis)
- yUnion[float, int, csdl.Variable, np.ndarray]
y position (not used in rotor analysis)
- zUnion[float, int, csdl.Variable, np.ndarray]
z position (not used in rotor analysis)
- p: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- phi: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- psi: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- q: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- r: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- theta: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- u: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- v: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- w: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- x: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- y: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- z: Union[float, int, csdl_alpha.Variable, numpy.ndarray] = 0
- class BladeAD.utils.var_groups.AtmosStates
Bases:
csdl_alpha.VariableGroupData class for atmospheric states. Default values are for sea-level.
- Parameters
- densityUnion[float, int, csdl.Variable]
Density of the atmosphere (kg/m^3)
- speed_of_soundUnion[float, int, csdl.Variable]
Speed of sound (m/s)
- temperatureUnion[float, int, csdl.Variable]
Temperature (K)
- pressureUnion[float, int, csdl.Variable]
Pressure (Pa)
- dynamic_viscosityUnion[float, int, csdl.Variable]
Dynamic viscosity (Pa.s)
- density: Union[float, int, csdl_alpha.Variable] = 1.22518316
- dynamic_viscosity: Union[float, int, csdl_alpha.Variable] = 1.735e-05
- pressure: Union[float, int, csdl_alpha.Variable] = 101325
- speed_of_sound: Union[float, int, csdl_alpha.Variable] = 343.0
- temperature: Union[float, int, csdl_alpha.Variable] = 288.16
- class BladeAD.utils.var_groups.RotorAnalysisInputs
Bases:
csdl_alpha.VariableGroupRotor analysis inputs data class.
- Parameters
- rpmcsdl.Variable
The rpm of the rotor
- mesh_velocitycsdl.Variable
The mesh velocity (u_x, u_y, u_z) of the thrust origin
- mesh_parametersRotorMeshParameters
Instance of of RotorMeshParameters that stores information about the rotor geometry
- atmos_statesAtmosStates(), optional
Instance of AtmosStates data class, by default AtmosStates() (states at sea-level)
- ac_statesAcStates(), optional
Instance of AcStates() (if provided thrust will be decomposed into forces in the body-fixed reference frame based on aircraft orientation), by default None
- theta_0Union[csdl.Variable, int, float], optional
Collective pitch at r/R=0.75; zero-th harmonic of blade pitch motion (radians); note that it is up to the user to specify the blade twist such that it is zero at r/R=0.75, by default 0
- theta_1_cUnion[csdl.Variable, int, float], optional
Cyclic pitch angle: cosine coefficient for first harmonic (radians), by default 0
- theta_1_sUnion[csdl.Variable, int, float], optional
Cyclic pitch angle: sine coefficient for first harmonic (radians), by default 0
- xi_0Union[csdl.Variable, int, float], optional
Mean lag angle; zero-th harmonic of blade lag motion (radians), by default 0
- xi_1_cUnion[csdl.Variable, int, float], optional
Cyclic lag angle; cosine coefficient for first harmonic (radians), by default 0
- xi_1_sUnion[csdl.Variable, int, float], optional
Cyclic lag angle; sin coefficient for first harmonic (radians), by default 0
- ac_states
- atmos_states
- mesh_parameters: RotorMeshParameters
- mesh_velocity: csdl_alpha.Variable
- rpm: csdl_alpha.Variable
- theta_0: Union[csdl_alpha.Variable, int, float] = 0
- theta_1_c: Union[csdl_alpha.Variable, int, float] = 0
- theta_1_s: Union[csdl_alpha.Variable, int, float] = 0
- xi_0: Union[csdl_alpha.Variable, int, float] = 0
- xi_1_c: Union[csdl_alpha.Variable, int, float] = 0
- xi_1_s: Union[csdl_alpha.Variable, int, float] = 0
- class BladeAD.utils.var_groups.RotorAnalysisOutputs
Bases:
csdl_alpha.VariableGroupRotor analysis outputs data class.
- Parameters
- axial_induced_velocitycsdl.Variable
Axial induced velocity (at rotor disk)
- tangential_induced_velocitycsdl.Variable
Tangential induced velocity (at rotor disk)
- sectional_thrustcsdl.Variable
Sectional thrust dT (N)
- sectional_torquecsdl.Variable
Sectional torque dQ (N.m)
- sectional_dragcsdl.Variable
Sectional drag dD (N)
- total_thrustcsdl.Variable
Total thrust (N)
- total_torquecsdl.Variable
Total torque (N.m)
- total_powercsdl.Variable
Total power (W)
- efficiencycsdl.Variable
Efficiency
- figure_of_meritcsdl.Variable
Figure of merit (hover efficiency metric)
- thrust_coefficientcsdl.Variable
Thrust coefficient
- torque_coefficientcsdl.Variable
Torque coefficient
- power_coefficientcsdl.Variable
Power coefficient
- residualcsdl.Variable, optional
Residual (if available), by default None
- forcescsdl.Variable, optional
Forces (if available based on body-fixed reference frame specified by ACStates), by default None
- momentscsdl.Variable, optional
Moments (if available based on body-fixed reference frame specified by ACStates) about specified reference point, by default None
- sectional_inflow_anglecsdl.Variable, optional
Sectional inflow angle (if available), by default None
- axial_induced_velocity: csdl_alpha.Variable
- efficiency: csdl_alpha.Variable
- figure_of_merit: csdl_alpha.Variable
- forces: csdl_alpha.Variable
- moments: csdl_alpha.Variable
- power_coefficient: csdl_alpha.Variable
- residual: csdl_alpha.Variable
- sectional_drag: csdl_alpha.Variable
- sectional_inflow_angle
- sectional_thrust: csdl_alpha.Variable
- sectional_torque: csdl_alpha.Variable
- tangential_induced_velocity: csdl_alpha.Variable
- thrust_coefficient: csdl_alpha.Variable
- torque_coefficient: csdl_alpha.Variable
- total_power: csdl_alpha.Variable
- total_thrust: csdl_alpha.Variable
- total_torque: csdl_alpha.Variable
- class BladeAD.utils.var_groups.RotorMeshParameters
Bases:
csdl_alpha.VariableGroupData class for rotor mesh parameters.
- Parameters
- thrust_vectorUnion[np.ndarray, csdl.Variable]
Thrust vector
- thrust_originUnion[np.ndarray, csdl.Variable]
Thrust origin
- chord_profileUnion[np.ndarray, csdl.Variable]
Chord profile (m)
- twist_profileUnion[np.ndarray, csdl.Variable]
Twist profile (radians)
- radiusUnion[float, int, csdl.Variable]
Radius of the rotor (m)
- num_radialint
Number of radial nodes
- num_azimuthalint
Number of azimuthal nodes
- num_bladesint
Number of blades
- norm_hub_radiusfloat
Normalmized hub radius (default=0.2)
- chord_profile: Union[numpy.ndarray, csdl_alpha.Variable]
- norm_hub_radius: float = 0.2
- num_azimuthal: int
- num_blades: int
- num_radial: int
- radius: Union[float, int, csdl_alpha.Variable]
- thrust_origin: Union[numpy.ndarray, csdl_alpha.Variable]
- thrust_vector: Union[numpy.ndarray, csdl_alpha.Variable]
- twist_profile: Union[numpy.ndarray, csdl_alpha.Variable]