Some usefull scripts for the Nastran's 145 solution (Flutter Analysis) using the pyNastran package.

Overview

DeepSource

nastran-aero-flutter

This project is intended to analyse the Supersonic Panel Flutter using the NASTRAN software.

The project uses the pyNastran and the python scientific packeges (i.e scipy, numpy, matplotlib).

Currently, the focus is to use the aerodynamic Piston Theory, available on NASTRAN with the CAERO5 element. But it can be extended to use with any aerodynamic element.

This software is result of a research project of the Department of Mechanical Engineering at the Federal University of Minas Gerais (UFMG).

Use

An exemple of utilization is on the run_analysis.py script.

First it generates the plate structure and required properties.

import numpy as np
from nastran.structures.panel import LaminatedStructuralPlate
from nastran.structures.composite import OrthotropicMaterial

a, b = 100, 100

p1 = np.array([0, 0, 0])
p2 = p1 + np.array([a, 0, 0])
p3 = p1 + np.array([a, b, 0])
p4 = p1 + np.array([0, b, 0])

cfrp = OrthotropicMaterial(1, 54000., 18000., 0.3, 7200., 2.6e-9)

nchord, nspan = 10, 10

lam = LaminatedStructuralPlate.create_sawyer_plate(p1, p2, p3, p4, nspan, nchord, 1, 45, 6, 0.1, cfrp)

Then you can add the analysis properties for SOL 145 Aeroelastic Dynamic Flutter. The PanelFlutterPistonAnalysisModel class is a wrapper of the pyNastran's BDF class.

from nastran.aero.analysis.panel_flutter import PanelFlutterPistonAnalysisModel

config = {
    'vref': 1000.,                      # used to calculate the non-dimensional dynamic pressure must be the same in control case (mm/s in the case)
    'ref_rho': 1.225e-12,               # air density reference (ton/mm^3 in the case)
    'ref_chord': 300.,                  # reference chord (mm in the case)
    'n_modes': 15,                      # number searched modes in modal analysis
    'frequency_limits': 
        [.0, 3000.],                    # the range of frequency (Hz) in modal analysis
    'method': 'PK',                     # the method for solving flutter (it will determine the next parameters
    'densities_ratio': [.5],            # rho/rho_ref -> 1/2 simulates the "one side flow" of the panel (? reference ?)
    'machs': [3.5, 4.5, 5.5, 6.5],      # Mach numbers
    'alphas': [.0, .0, .0, .0],         # AoA (°) -> 0 is more conservative (? reference ?)
    'reduced_frequencies': 
        [.001, .01, .1, .2, .4, .8],    # reduced frequencies (k) (check influence)
    'velocities':                       # velocities (mm/s in the case)
        np.linspace(10, 100, 10)*1000,
}

params =  {
    'VREF': 1000.0,
    'COUPMASS': 1,
    'LMODES': 20,
    # 'POST': [-1]
}

analysis = PanelFlutterPistonAnalysisModel(lam.bdf, params=params)
analysis.set_global_case_from_dict(config)

You can add "super" panels, that is just a wrapper of CAEROx elements that make one element.

from nastran.aero.superpanels import SuperAeroPanel5

spanel_p = SuperAeroPanel5(1, p1, p2, p3, p4, nchord, nspan, theory='VANDYKE')
analysis.add_superpanel(spanel_p)

You can set multiple subcases for example varing the boundary conditions.

cases_labels = {
    1: "Loaded edges SS & unloaded edges SS",
    2: "Loaded edges SS & unloaded edges CP",
    3: "Loaded edges SS & unloaded edges SS/CP",
}

spc_cases = {
    1: ('123', '123', '123', '123'),             # loaded edges SS, unloaded edges SS
    2: ('123', '123', '123456', '123456'),       # loaded edges SS, unloaded edges CP
    3: ('123', '123', '123', '123456'),          # loaded edges SS, unloaded edges SS/CP
}

for i, spcs in spc_cases.items():
    spc_id = analysis.idutil.get_next_sid()
    for comp, nds in zip(list(spcs), lam.limit_nodes()):
        if comp == '':
            continue
        analysis.model.add_spc1(spc_id, comp, nds, comment=cases_labels[i])
    sub_config = {
        'LABEL': cases_labels[i],
        'SPC': spc_id,
    }
    analysis.create_subcase_from_dict(PanelFlutterSubcase, i, sub_config)

Then you must write all cards to the BDF object and export the file.

analysis.write_cards()
analysis.model.write_bdf('pflutter.bdf', enddata=True)

Then you can run the analysis and post-processes.

Outputs

The postprocessing generates DataFrames objects from the .f06 result files.

from nastran.aero.post import read_f06, get_critical_roots, plot_vf_vg

df = read_f06("pflutter.f06")

critic_df = get_critical_roots(df)

fig = plot_vf_vg(df.xs((1,3.5))) # Subcase, Mach
fig.show()

And Plots

V-f

V-g

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  • Bump pywin32 from 227 to 301

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  • Chordwise camber geometry (curved panel)

    Chordwise camber geometry (curved panel)

    Piston Theory on Nastran has a set of parameters called Thickness Integrals, which is to account for foil thickness in an aerodynamic sense, but it must retain the chord rigidity assumption. For a panel, which has a chord-wise flexibility one element could not represent the behavior of the panel. Instead, if a set of elements is utilized it can achieve representation of the model and comply with the rigidity of the chord of the element at the same time.

    Currently, only a flat panel (plate) is implemented, but in theory, we can in implement curved panels too.

    enhancement 
    opened by vsdsantos 0
Releases(v0.2.1-alpha)
Owner
zuckberj
open source, aerospace
zuckberj
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