# RCAIDE/Library/Plots/Performance/Mission/plot_flight_conditions.py
#
#
# Created: Jul 2023, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
import RCAIDE
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
# ----------------------------------------------------------------------------------------------------------------------
# PLOTS
# ----------------------------------------------------------------------------------------------------------------------
[docs]
def plot_flight_conditions(results,
save_figure = False,
show_legend = True,
save_filename = "Flight Conditions",
file_type = ".png",
width = 11, height = 7):
"""
Creates a multi-panel visualization of flight conditions over a mission profile.
Parameters
----------
results : Results
RCAIDE results data structure containing:
- segments[i].conditions.frames.inertial.time[:,0]
Time history for each segment
- segments[i].conditions.freestream.velocity[:,0]
Airspeed history for each segment
- segments[i].conditions.frames.body.inertial_rotations[:,1,None]
Pitch angle history for each segment
- segments[i].conditions.frames.inertial.aircraft_range[:,0]
Range history for each segment
- segments[i].conditions.freestream.altitude[:,0]
Altitude history for each segment
- segments[i].tag
Name/identifier of each segment
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: "Flight Conditions")
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
Handle to the generated figure containing four subplots:
- Altitude vs time
- Airspeed vs time
- Range vs time
- Pitch angle vs time
Notes
-----
Creates a four-panel plot showing:
1. Altitude profile
2. Airspeed variation
3. Range covered
4. Aircraft pitch attitude
Requires the following data in results:
- frames.inertial.time
- frames.inertial.position_vector
- frames.body.inertial_rotations
- freestream.velocity
- freestream.altitude
**Major Assumptions**
* Time is in minutes
* Altitude is in feet
* Airspeed is in mph
* Range is in nautical miles
* Pitch angle is in degrees
**Definitions**
'Altitude'
Height above reference plane
'Range'
Ground distance covered
'Pitch Angle'
Nose-up/down attitude relative to horizon
See Also
--------
RCAIDE.Library.Plots.Mission.plot_aircraft_velocities : Detailed velocity analysis
RCAIDE.Library.Plots.Mission.plot_flight_trajectory : 3D trajectory visualization
"""
# 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)
axis_1 = fig.add_subplot(2,2,1)
axis_2 = fig.add_subplot(2,2,2)
axis_3 = fig.add_subplot(2,2,3)
axis_4 = fig.add_subplot(2,2,4)
aileron_flag = False
elevator_flag = False
rudder_flag = False
slat_flag = False
flap_flag = False
spoiler_flag = False
# loop through wings to determine what control surfaces are present
for wing in results.segments[0].analyses.aerodynamics.vehicle.wings:
for control_surface in wing.control_surfaces:
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Aileron:
aileron_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator:
elevator_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Rudder:
rudder_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Slat:
slat_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Flap:
flap_flag = True
if type(control_surface) == RCAIDE.Library.Components.Wings.Control_Surfaces.Spoiler:
spoiler_flag = True
for i in range(len(results.segments)):
time = results.segments[i].conditions.frames.inertial.time[:,0] / Units.min
airspeed = results.segments[i].conditions.freestream.velocity[:,0] / Units['mph']
Range = results.segments[i].conditions.frames.inertial.aircraft_range[:,0]/ Units.nmi
altitude = results.segments[i].conditions.freestream.altitude[:,0]/Units.feet
segment_tag = results.segments[i].tag
segment_name = segment_tag.replace('_', ' ')
axis_1.plot(time, altitude, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width, label = segment_name)
axis_2.plot(time, airspeed, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width)
axis_3.plot(time, Range, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width)
if i == 0:
if elevator_flag:
elevator_deflection = results.segments[i].conditions.control_surfaces.elevator.deflection[:,0] / Units.deg
axis_4.plot(time, elevator_deflection, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width, label = ' elevator ' )
if flap_flag:
flap_deflection = results.segments[i].conditions.control_surfaces.flap.deflection[:,0] / Units.deg
axis_4.plot(time, flap_deflection , color = line_colors[i], marker = ps.markers[2], linewidth = ps.line_width, label = ' flap' )
if slat_flag:
slat_deflection = results.segments[i].conditions.control_surfaces.slat.deflection[:,0] / Units.deg
axis_4.plot(time, slat_deflection , color = line_colors[i], marker = ps.markers[3], linewidth = ps.line_width, label = ' slat' )
if aileron_flag:
aileron_deflection = results.segments[i].conditions.control_surfaces.aileron.deflection[:,0] / Units.deg
axis_4.plot(time, aileron_deflection , color = line_colors[i], marker = ps.markers[4], linewidth = ps.line_width, label = ' aileron' )
if rudder_flag:
rudder_deflection = results.segments[i].conditions.control_surfaces.rudder.deflection[:,0] / Units.deg
axis_4.plot(time, rudder_deflection , color = line_colors[i], marker = ps.markers[5], linewidth = ps.line_width, label = ' rudder' )
if spoiler_flag:
spoiler_deflection = results.segments[i].conditions.control_surfaces.spoiler.deflection[:,0] / Units.deg
axis_4.plot(time, spoiler_deflection , color = line_colors[i], marker = ps.markers[6], linewidth = ps.line_width, label = ' spoiler' )
else:
if elevator_flag:
elevator_deflection = results.segments[i].conditions.control_surfaces.elevator.deflection[:,0] / Units.deg
axis_4.plot(time, elevator_deflection, color = line_colors[i], marker = ps.markers[0], linewidth = ps.line_width)
if flap_flag:
flap_deflection = results.segments[i].conditions.control_surfaces.flap.deflection[:,0] / Units.deg
axis_4.plot(time, flap_deflection , color = line_colors[i], marker = ps.markers[2], linewidth = ps.line_width)
if slat_flag:
slat_deflection = results.segments[i].conditions.control_surfaces.slat.deflection[:,0] / Units.deg
axis_4.plot(time, slat_deflection , color = line_colors[i], marker = ps.markers[3], linewidth = ps.line_width)
if aileron_flag:
aileron_deflection = results.segments[i].conditions.control_surfaces.aileron.deflection[:,0] / Units.deg
axis_4.plot(time, aileron_deflection , color = line_colors[i], marker = ps.markers[4], linewidth = ps.line_width)
if rudder_flag:
rudder_deflection = results.segments[i].conditions.control_surfaces.rudder.deflection[:,0] / Units.deg
axis_4.plot(time, rudder_deflection , color = line_colors[i], marker = ps.markers[5], linewidth = ps.line_width)
if spoiler_flag:
spoiler_deflection = results.segments[i].conditions.control_surfaces.spoiler.deflection[:,0] / Units.deg
axis_4.plot(time, spoiler_deflection , color = line_colors[i], marker = ps.markers[6], linewidth = ps.line_width)
axis_1.set_ylabel(r'Altitude (ft)')
set_axes(axis_1)
axis_2.set_ylabel(r'Airspeed (mph)')
set_axes(axis_2)
axis_3.set_xlabel('Time (mins)')
axis_3.set_ylabel(r'Range (nmi)')
set_axes(axis_3)
axis_4.set_xlabel('Time (mins)')
axis_4.set_ylabel(r'Control Surface Deflection (deg)')
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'})
axis_4.legend(loc='upper center')
# Adjusting the sub-plots for legend
fig.tight_layout()
fig.subplots_adjust(top=0.75)
# set title of plot
title_text = 'Flight Conditions'
fig.suptitle(title_text)
if save_figure:
plt.savefig(save_filename + file_type)
return fig
