Source code for RCAIDE.Library.Plots.Aerodynamics.plot_aerodynamic_forces

# RCAIDE/Library/Plots/Performance/Aerodynamics/plot_aerodynamic_forces.py
# 
# 
# Created:  Jul 2023, M. Clarke

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#  IMPORT
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from RCAIDE.Framework.Core import Units
from RCAIDE.Library.Plots.Common import set_axes, plot_style
import matplotlib.pyplot as plt
import matplotlib.cm as cm
import numpy as np 

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#  PLOTS
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[docs] def plot_aerodynamic_forces(results, save_figure = False, show_legend = True, save_filename = "Aerodynamic_Forces", file_type = ".png", width = 11, height = 7): """ Creates a multi-panel visualization of aerodynamic forces throughout flight. Parameters ---------- results : Results RCAIDE results data structure containing: - segments[i].conditions.frames Frame data containing: - body.thrust_force_vector[:,0] Thrust force in body frame [N] - wind.force_vector[:,0] Drag force in wind frame [N] - wind.force_vector[:,2] Lift force in wind frame [N] - segments[i].conditions.energy Energy data containing: - power[:,0] Total power in watts - segments[i].conditions.frames.inertial.time[:,0] Time history for each segment - segments[i].tag Segment identifier string save_figure : bool, optional Flag for saving the figure (default: False) show_legend : bool, optional Flag to display segment legend (default: True) save_filename : str, optional Name of file for saved figure (default: "Aerodynamic_Forces") file_type : str, optional File extension for saved figure (default: ".png") width : float, optional Figure width in inches (default: 11) height : float, optional Figure height in inches (default: 7) Returns ------- fig : matplotlib.figure.Figure Notes ----- Creates visualization showing: - Aerodynamic force magnitudes - Power requirements - Force balance evolution - Time history of forces **Definitions** 'Lift' Force perpendicular to airflow 'Drag' Force parallel to airflow 'Thrust' Propulsive force 'Power' Rate of energy use See Also -------- RCAIDE.Library.Plots.Aerodynamics.plot_aerodynamic_coefficients : Non-dimensional force plots RCAIDE.Library.Plots.Aerodynamics.plot_drag_components : Drag breakdown analysis """ # get plotting style ps = plot_style() parameters = {'axes.labelsize': ps.axis_font_size, 'xtick.labelsize': ps.axis_font_size, 'ytick.labelsize': ps.axis_font_size, 'axes.titlesize': ps.title_font_size} plt.rcParams.update(parameters) # get line colors for plots line_colors = cm.inferno(np.linspace(0,0.9,len(results.segments))) fig = plt.figure(save_filename) fig.set_size_inches(width,height) for i in range(len(results.segments)): time = results.segments[i].conditions.frames.inertial.time[:,0] / Units.min Power = results.segments[i].conditions.energy.power[:,0] Thrust = results.segments[i].conditions.frames.body.thrust_force_vector[:,0] Lift = -results.segments[i].conditions.frames.wind.force_vector[:,2] Drag = -results.segments[i].conditions.frames.wind.force_vector[:,0] segment_tag = results.segments[i].tag segment_name = segment_tag.replace('_', ' ') # power axis_1 = plt.subplot(2,2,1) axis_1.set_ylabel(r'Power (MW)') axis_1.plot(time,Power/1E6, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width, label = segment_name) set_axes(axis_1) axis_2 = plt.subplot(2,2,2) axis_2.plot(time, Thrust/1000, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width) axis_2.set_ylabel(r'Thrust (kN)') set_axes(axis_2) axis_3 = plt.subplot(2,2,3) axis_3.plot(time, Lift/1000, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width) axis_3.set_xlabel('Time (mins)') axis_3.set_ylabel(r'Lift (kN)') set_axes(axis_3) axis_4 = plt.subplot(2,2,4) axis_4.plot(time,Drag/1000 , color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width) axis_4.set_xlabel('Time (mins)') axis_4.set_ylabel(r'Drag (kN)') set_axes(axis_4) if show_legend: leg = fig.legend(bbox_to_anchor=(0.5, 0.95), loc='upper center', ncol = 4) leg.set_title('Flight Segment', prop={'size': ps.legend_font_size, 'weight': 'heavy'}) # Adjusting the sub-plots for legend fig.tight_layout() fig.subplots_adjust(top=0.8) # set title of plot title_text = 'Aerodynamic Forces' fig.suptitle(title_text) if save_figure: plt.savefig(save_filename + file_type) return fig