compute_feat_inertia {AvInertia}  R Documentation 
Compute the inertia of the individual feathers
compute_feat_inertia(dat_mat, dat_feat_curr, dat_bird_curr)
dat_mat 
Dataframe related to the current species input as a dataframe with the following structure:

dat_feat_curr 
Dataframe related to the current bird wing feathers input as a dataframe with the following structure:
NOTE: Alula feathers will be treated as point mass so only the mass of the feathers is required. Other columns can be left blank. 
dat_bird_curr 
Dataframe related to the current bird wing that must include the following columns:

A list with one entry per flight feather. Each primary feather includes the following variables:
I_pria 3x3 matrix representing the moment of inertia about each feather calamus tip (kgm^2).
CG_pria 1x3 vector (x,y,z) representing the center of gravity of the primary feather (m).
m_pria double representing the mass of the primary feather (kg).
Each secondary feather includes the following variables:
I_seca 3x3 matrix representing the moment of inertia about each feather calamus tip (kgm^2).
CG_seca 1x3 vector (x,y,z) representing the center of gravity of the primary feather (m).
m_seca double representing the mass of the primary feather (kg).
# refer to the vignette library(AvInertia) # load data data(dat_id_curr, package = "AvInertia") data(dat_bird_curr, package = "AvInertia") data(dat_feat_curr, package = "AvInertia") data(dat_bone_curr, package = "AvInertia") data(dat_mat, package = "AvInertia") data(clean_pts, package = "AvInertia") # 1. Determine the center of gravity of the bird's torso (including the legs) dat_torsotail_out = massprop_restbody(dat_id_curr, dat_bird_curr) # 2. Calculate the inertia of the flight feathers about the tip of the calamus feather_inertia < compute_feat_inertia(dat_mat, dat_feat_curr, dat_bird_curr) # 3. Determine the center of gravity of one of the bird's wings dat_wing_out = massprop_birdwing(dat_id_curr, dat_bird_curr, dat_bone_curr, dat_feat_curr, dat_mat, clean_pts, feather_inertia, plot_var = 0) # Visualize the center of gravity of each wing component in the x and y axis dat_wing_out = massprop_birdwing(dat_id_curr, dat_bird_curr, dat_bone_curr, dat_feat_curr, dat_mat, clean_pts, feather_inertia, plot_var = "yx") # or the y and z axis dat_wing_out = massprop_birdwing(dat_id_curr, dat_bird_curr, dat_bone_curr, dat_feat_curr, dat_mat, clean_pts, feather_inertia, plot_var = "yz") # 4. Combine all data and obtain the center of gravity, moment of inertia # and principal axes of the bird curr_full_bird = combine_inertialprop(dat_torsotail_out,dat_wing_out, dat_wing_out, dat_id_curr, dat_bird_curr, symmetric=TRUE)