RCAIDE.Library.Plots.Performance.plot_load_diagram

plot_load_diagram#

plot_load_diagram(results, save_figure=False, show_legend=True, save_filename='Aircraft_Loading_Trim_Dragram', file_type='.png', static_margin_lower_limit=-0.1, static_margin_upper_limit=1.0, static_margin_resolution=12, x_axis_lower_limit=None, x_axis_upper_limit=None, y_axis_lower_limit=None, y_axis_upper_limit=None, show_component_vectors=False, width=11, height=7)[source]#

Creates a comprehensive aircraft loading diagram showing mass and center of gravity relationships.

Parameters:

results (RCAIDE.Framework.Core.Data) –

Results from load and trim diagram analysis containing:

loading_massnumpy.ndarray
Aircraft mass for loading diagram [kg]
loading_LEMAC_locationnumpy.ndarray
LEMAC location as percentage of reference chord [%]
trim_results.LEMAC_locationnumpy.ndarray
LEMAC location for trim diagram [%]
trim_results.massnumpy.ndarray
Aircraft mass for trim diagram [kg]
trim_results.static_marginnumpy.ndarray
Static margin values [unitless]
MTOWfloat
Maximum takeoff weight [kg]
MLWfloat
Maximum landing weight [kg]

Returns:

Creates and displays a matplotlib figure with the loading diagram

Return type:

None

Notes

This function generates a comprehensive aircraft loading diagram that visualizes the relationship between aircraft mass, loading, and center of gravity position. The diagram includes fuel loading curves, payload loading curves, weight limits, and stability contours to provide a complete view of the aircraft’s loading envelope.

Major Assumptions

Convex hull calculation is valid for the data points

Definitions

‘Loading Diagram’: Plot showing aircraft mass versus center of gravity position for different loading conditions.
‘Convex Hull’: Smallest convex polygon that contains all the data points.
‘Static Margin’: Distance between center of gravity and neutral point as percentage of reference chord.
‘LEMAC’: Leading Edge Mean Aerodynamic Chord reference point for center of gravity calculations.