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Merge Tutorials with DC3
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| """ | ||
| Job Control File documentation | ||
| The Job Control (jcl) is a python class which defines the model and and the simulation and is imported at | ||
| the beginning of every simulation. Unlike a conventional parameter file, this allows scripting/programming | ||
| of the input, e.g. to convert units, generate mutiple load cases, etc. | ||
| Note that this documentation of parameters is comprehensive, but a) not all parameters are necessary for | ||
| every kind of simulation and b) some parameters are for experts only --> your JCL might be much smaller. | ||
| """ | ||
| import os | ||
| import pathlib | ||
|
|
||
| import numpy as np | ||
|
|
||
| from loadskernel.units import ft2m, tas2Ma | ||
|
|
||
|
|
||
| class jcl: | ||
|
|
||
| def __init__(self): | ||
| model_root = pathlib.Path(__file__).parent.parent.resolve() | ||
|
|
||
| # Give your aircraft a name and set some general parameters | ||
| self.general = {'aircraft': 'DC3', | ||
| # Reference span width (from tip to tip) | ||
| 'b_ref': 29.0, | ||
| # Reference chord length | ||
| 'c_ref': 3.508, | ||
| # Reference area | ||
| 'A_ref': 91.7, | ||
| # Mean aerodynamic center, also used as moments reference point | ||
| 'MAC_ref': [8.566, 0.0, 0.0], | ||
| } | ||
| """ | ||
| The electronic flight control system (EFCS) provides the "wireing" of the pilot commands | ||
| xi, eta and zeta with the control surface deflections. This is aircraft-specific and needs | ||
| to be implemented as a python module. | ||
| """ | ||
| # Electronic flight control system | ||
| self.efcs = {'version': 'efcs_dc3', # Name of the corresponding python module | ||
| # Path where to find the EFCS module | ||
| 'path': os.path.join(model_root, 'efcs'), | ||
| } | ||
| # Read the structural geometry | ||
| self.geom = {'method': 'mona', # ModGen and/or Nastran (mona) BDFs | ||
| # bdf file(s) with GRIDs and CORDs (CORD1R and CORD2R) | ||
| 'filename_grid': [os.path.join(model_root, 'fem', 'structure_only.bdf')], | ||
| # bdf file(s) with CQUADs and CTRIAs, for visualization only, e.g. outer skin on the aircraft | ||
| # 'filename_shell': [], | ||
| # bdf file(s) with MONPNT-cards | ||
| # 'filename_monpnt': 'monpnt.bdf', | ||
| # The following matrices are required for some mass methods. However, the stiffness is geometry | ||
| # and not mass dependent. Overview: | ||
| # KGG via DMAP Alter und OP4 - required for mass method = 'modalanalysis', 'guyan' or 'B2000' | ||
| # USET via DMAP Alter und OP4 - required for mass method = 'modalanalysis', 'guyan' | ||
| # matrix GM via DMAP Alter und OP4 - required for mass method = 'modalanalysis', 'guyan' | ||
| # bdf file(s) with ASET1-card - required for mass method = 'guyan' | ||
| # matrix R_trans frum B2000 - required for mass method = 'B2000' | ||
| 'filename_h5': os.path.join(model_root, 'fem', 'SOL103_structure_only.mtx.h5'), | ||
| 'filename_uset': os.path.join(model_root, 'fem', 'uset.op2'), | ||
| } | ||
| # Settings for the aerodynamic model | ||
| self.aero = {'method': 'freq_dom', | ||
| # 'mona_steady' - steady trim and quasi-steady time domain simulations | ||
| # 'mona_unsteady' - unsteady time domain simulation based on the RFA, e.g. for gust | ||
| # 'freq_dom' - frequency domain simulations, e.g. gust, continuous turbulence, flutter, etc | ||
| # 'nonlin_steady' - steady trim and quasi-steady time domain simulations with some non-linearities | ||
| # 'cfd_steady' - steady trim | ||
| # 'cfd_unsteady' - unsteady time domain simulation, e.g. for gust | ||
| # | ||
| # True or False, aerodynamic feedback of elastic structure on aerodynamics can be deactivated. | ||
| # You will still see deformations, but there is no coupling. | ||
| 'flex': True, | ||
| # aerogrid is given by CAERO1, CAERO7 or by CQUAD4 cards | ||
| 'method_caero': 'CAERO1', | ||
| # bdf file(s) with CAERO1 or CQUAD4-cards for aerogrid. IDs in ascending order. | ||
| 'filename_caero_bdf': [os.path.join(model_root, 'aero', 'vt', 'vt.CAERO1'), | ||
| os.path.join(model_root, 'aero', 'left-ht', 'left-ht.CAERO1'), | ||
| os.path.join(model_root, 'aero', 'right-ht', 'right-ht.CAERO1'), | ||
| os.path.join(model_root, 'aero', 'left-wing', 'left-wing.CAERO1'), | ||
| os.path.join(model_root, 'aero', 'right-wing', 'right-wing.CAERO1'), | ||
| ], | ||
| # DMI Matrix for camber and twist correction. Same order as the aerogrid. | ||
| 'filename_DMI_W2GJ': [os.path.join(model_root, 'fem', 'w2gj_list.DMI_merge')], | ||
| # bdf file(s) with AESURF-cards | ||
| 'filename_aesurf': [os.path.join(model_root, 'aero', 'vt', 'vt.AESURF'), | ||
| os.path.join(model_root, 'aero', 'left-ht', 'left-ht.AESURF'), | ||
| os.path.join(model_root, 'aero', 'right-ht', 'right-ht.AESURF'), | ||
| os.path.join(model_root, 'aero', 'left-wing', 'left-wing.AESURF'), | ||
| os.path.join(model_root, 'aero', 'right-wing', 'right-wing.AESURF'), | ||
| ], | ||
| # bdf file(s) with AELIST-cards | ||
| 'filename_aelist': [os.path.join(model_root, 'aero', 'vt', 'vt.AELIST'), | ||
| os.path.join(model_root, 'aero', 'left-ht', 'left-ht.AELIST'), | ||
| os.path.join(model_root, 'aero', 'right-ht', 'right-ht.AELIST'), | ||
| os.path.join(model_root, 'aero', 'left-wing', 'left-wing.AELIST'), | ||
| os.path.join(model_root, 'aero', 'right-wing', 'right-wing.AELIST'), | ||
| ], | ||
| # The hingeline of a CS is given by a CORD. Either the y- or the z-axis is taken as hingeline. 'y', 'z' | ||
| 'hingeline': 'y', | ||
| # 'vlm' (panel-aero), 'dlm' (panel-aero) or 'nastran' (external form matrices) | ||
| 'method_AIC': 'dlm', | ||
| 'key': ['VC'], | ||
| 'Ma': [0.50], | ||
| # reduced frequencies for DLM, Nastran Definition! | ||
| 'k_red': [0.001, 0.1, 0.3, 0.6, 1.0, 1.5, 2.0, 3.0], | ||
| # number of poles for rational function approximation (RFA) | ||
| 'n_poles': 4, | ||
| } | ||
| # Set the was in which the aerodynamic forces are applied to the structure. | ||
| self.spline = {'method': 'nearest_neighbour', # Options: 'nearest_neighbour', 'rbf' or 'nastran' | ||
| # Possibility to use only a subset of the structural grid for splining. True or False | ||
| 'splinegrid': False, | ||
| # bdf file(s) with GRIDs to ne used | ||
| 'filename_splinegrid': ['splinegrid.bdf'] | ||
| } | ||
| # Settings for the structural dynamics. | ||
| self.mass = {'method': 'modalanalysis', # Inplemented interfaces: 'f06', 'modalanalysis', 'guyan', 'CoFE', 'B2000' | ||
| 'key': ['M3'], | ||
| # MGG via DMAP Alter and OP4 - always required | ||
| 'filename_h5': [os.path.join(model_root, 'fem', 'SOL103_M3.mtx.h5')], | ||
| # True or False, omits first six modes | ||
| 'omit_rb_modes': True, | ||
| # list(s) of modes to use | ||
| 'modes': [np.arange(1, 22)], | ||
| } | ||
| # Modal damping can be applied as a factor of the stiffness matrix. | ||
| self.damping = {'method': 'modal', | ||
| 'damping': 0.02, | ||
| } | ||
| # The international standard atmosphere (ISA) | ||
| self.atmo = {'method': 'ISA', | ||
| 'key': ['FL000', 'FL055', 'FL075', 'FL210'], | ||
| # Altitude in meters | ||
| 'h': ft2m([0, 5500, 7500, 21000,]), | ||
| } | ||
| # Setting of the rigid body equations of motion | ||
| self.eom = {'version': 'waszak'} # 'linear' or 'waszak' | ||
| """ | ||
| The trimcase defines the maneuver load case, one dictionary per load case. | ||
| There may be hundreds or thousands of load cases, so at some point it might be beneficial to script this section or | ||
| import an excel sheet. | ||
| """ | ||
| self.trimcase = [{'desc': 'CC.M3.OVCFL000.KE-Method', # Descriptive string of the maneuver case | ||
| # Kind of trim condition, blank for trim about all three axes, for more trim conditions see | ||
| # trim_conditions.py | ||
| 'maneuver': '', | ||
| # Subcase ID number, for Nastran in acending order | ||
| 'subcase': 1, | ||
| # Setting of the operational point | ||
| # The flight speed is given by the Mach number | ||
| 'Ma': tas2Ma(70.0, 0.0), | ||
| # Aero key | ||
| 'aero': 'VC', | ||
| # Atmo key | ||
| 'altitude': 'FL000', | ||
| # Mass key | ||
| 'mass': 'M3', | ||
| # Load factor Nz | ||
| 'Nz': 1.0, | ||
| # Velocities and accelerations given in ISO 9300 coordinate system (right-handed, forward-right-down) | ||
| # Roll rate in rad/s | ||
| 'p': 0.0 / 180.0 * np.pi, | ||
| # Pitch rate in rad/s | ||
| 'q': 0.0 / 180.0 * np.pi, | ||
| # Yaw rate in rad/s | ||
| 'r': 0.0, | ||
| # Roll acceleration in rad/s^2 | ||
| 'pdot': 0.0, | ||
| # Pitch acceleration in rad/s^2 | ||
| 'qdot': 0.0, | ||
| # Yaw acceleration in rad/s^2 | ||
| 'rdot': 0.0, | ||
| }, | ||
| {'desc': 'CC.M3.OVCFL000.PK-Method', # Descriptive string of the maneuver case | ||
| # Kind of trim condition, blank for trim about all three axes, for more trim conditions see | ||
| # trim_conditions.py | ||
| 'maneuver': '', | ||
| # Subcase ID number, for Nastran in acending order | ||
| 'subcase': 2, | ||
| # Setting of the operational point | ||
| # The flight speed is given by the Mach number | ||
| 'Ma': tas2Ma(70.0, 0.0), | ||
| # Aero key | ||
| 'aero': 'VC', | ||
| # Atmo key | ||
| 'altitude': 'FL000', | ||
| # Mass key | ||
| 'mass': 'M3', | ||
| # Load factor Nz | ||
| 'Nz': 1.0, | ||
| # Velocities and accelerations given in ISO 9300 coordinate system (right-handed, forward-right-down) | ||
| # Roll rate in rad/s | ||
| 'p': 0.0 / 180.0 * np.pi, | ||
| # Pitch rate in rad/s | ||
| 'q': 0.0 / 180.0 * np.pi, | ||
| # Yaw rate in rad/s | ||
| 'r': 0.0, | ||
| # Roll acceleration in rad/s^2 | ||
| 'pdot': 0.0, | ||
| # Pitch acceleration in rad/s^2 | ||
| 'qdot': 0.0, | ||
| # Yaw acceleration in rad/s^2 | ||
| 'rdot': 0.0, | ||
| }] | ||
| """ | ||
| For every trimcase, a corresponding simcase is required. For maneuvers, it may be empty self.simcase = [{}]. | ||
| A time simulation is triggered if the simcase contains at least 'dt' and 't_final' | ||
| """ | ||
| self.simcase = [{'gust': False, # True or False, enables 1-cosine gust according to CS-25 | ||
| # True or False, enables continuous turbulence excitation | ||
| 'turbulence': False, | ||
| # True or False, calculates limit turbulence according to CS-25 | ||
| 'limit_turbulence': False, | ||
| # True or False, enables playback of control surface signals via efcs | ||
| 'cs_signal': False, | ||
| # True or False, enables a generic controller e.g. to maintain p, q and r | ||
| 'controller': False, | ||
| # True or False, enables a generic landing gear | ||
| 'landinggear': False, | ||
| # True or False, enables calculation of rigid and elastic derivatives | ||
| 'derivatives': False, | ||
| # True or False, enables flutter check with k, ke or pk method | ||
| 'flutter': True, | ||
| # flutter parameters for k and ke method | ||
| 'flutter_para': {'method': 'ke', 'k_red': np.linspace(3.0, 0.001, 100)}}, | ||
| {'gust': False, # True or False, enables 1-cosine gust according to CS-25 | ||
| # True or False, enables continuous turbulence excitation | ||
| 'turbulence': False, | ||
| # True or False, calculates limit turbulence according to CS-25 | ||
| 'limit_turbulence': False, | ||
| # True or False, enables playback of control surface signals via efcs | ||
| 'cs_signal': False, | ||
| # True or False, enables a generic controller e.g. to maintain p, q and r | ||
| 'controller': False, | ||
| # True or False, enables a generic landing gear | ||
| 'landinggear': False, | ||
| # True or False, enables calculation of rigid and elastic derivatives | ||
| 'derivatives': False, | ||
| # True or False, enables flutter check with k, ke or pk method | ||
| 'flutter': True, | ||
| # flutter parameters for pk method | ||
| 'flutter_para': {'method': 'pk', 'Vtas': np.linspace(20.0, 300.0, 20)}}] | ||
| # End |
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