RCAIDE.Framework.External_Interfaces.OpenVSP.import_vsp_vehicle
import_vsp_vehicle#
- import_vsp_vehicle(tag, main_wing_tag=None, network_type=None, propulsor_type=None, blended_wing_body=False, last_blended_wing_body_center_body_section_index=None, units_type='SI', use_scaling=True, calculate_wetted_area=True)[source]#
This reads an OpenVSP vehicle geometry and writes it into a RCAIDE vehicle format. Includes wings, fuselages, and rotors.
Assumptions: 1. OpenVSP vehicle is composed of conventionally shaped fuselages, wings, and rotors. 1a. OpenVSP fuselage: generally narrow at nose and tail, wider in center). 1b. Fuselage is designed in VSP as it appears in real life. That is, the VSP model does not rely on
superficial elements such as canopies, stacks, or additional fuselages to cover up internal lofting oddities.
- 1c. This program will NOT account for multiple geometries comprising the fuselage. For example: a wingbox mounted beneath
is a separate geometry and will NOT be processed.
Fuselage origin is located at nose. VSP file origin can be located anywhere, preferably at the forward tip of the vehicle or in front (to make all X-coordinates of vehicle positive).
Written for OpenVSP 3.21.1
Source: N/A
Inputs: tag <str> path to .vsp3 file main_wing_tag <str> VSP geometry name of the main wing (optional). If None, the
largest non-vertical wing by reference area is promoted to RCAIDE.Library.Components.Wings.Main_Wing automatically.
- network_type RCAIDE.Framework.Networks.Network (optional). If None, propulsion
geometry is skipped and only airframe components are imported.
- propulsor_type RCAIDE.Library.Components.Powertrain.Propulsors.Propulsor (optional).
Required alongside network_type to import rotors/nacelles.
blended_wing_body <bool> set True for blended wing body configurations (default False) units_type <str> ‘SI’ (default), ‘imperial’, or ‘inches’ use_scaling <bool> apply VSP scaling factor (default True) calculate_wetted_area <bool> compute wetted areas via OpenVSP (default True)
Outputs: Writes RCAIDE vehicle with these geometries from VSP: (All values default to SI. Any other 2nd argument outputs Imperial.)
- Wings.Wing. (* is all keys)
origin [m] in all three dimensions spans.projected [m] chords.root [m] chords.tip [m] aspect_ratio [-] sweeps.quarter_chord [radians] twists.root [radians] twists.tip [radians] thickness_to_chord [-] dihedral [radians] symmetric <boolean> tag <string> areas.reference [m^2] areas.wetted [m^2] Segments.
tag <string> twist [radians] percent_span_location [-] .1 is 10% root_chord_percent [-] .1 is 10% dihedral_outboard [radians] sweeps.quarter_chord [radians] thickness_to_chord [-] airfoil <NACA 4-series, 6 series, or airfoil file>
- Fuselages.Fuselage.
origin [m] in all three dimensions width [m] lengths.
total [m] nose [m] tail [m]
- heights.
maximum [m] at_quarter_length [m] at_three_quarters_length [m]
effective_diameter [m] fineness.nose [-] ratio of nose section length to fuselage effective diameter fineness.tail [-] ratio of tail section length to fuselage effective diameter areas.wetted [m^2] tag <string> segment[]. (segments are in ordered container and callable by number)
vsp.shape [point,circle,round_rect,general_fuse,fuse_file] vsp.xsec_id <10 digit string> percent_x_location percent_z_location height width length effective_diameter tag
vsp.xsec_num <integer of fuselage segment quantity> vsp.xsec_surf_id <10 digit string>
- Propellers.Propeller.
location[X,Y,Z] [radians] rotation[X,Y,Z] [radians] tip_radius [m] hub_radius [m]