View source: R/anatomicalmassprop.R
massprop_muscles | R Documentation |
Calculate the moment of inertia of a muscle modeled as a solid cylinder distributed along the bone length
massprop_muscles(m, rho, l, start, end)
m |
Mass of muscle (kg). |
rho |
Density of muscle (kg/m^3). |
l |
Length of the muscle group (m). |
start |
a 1x3 vector (x,y,z) representing the 3D point where bone starts. Frame of reference: VRP | Origin: VRP. |
end |
a 1x3 vector (x,y,z) representing the 3D point where bone ends. Frame of reference: VRP | Origin: VRP. |
This function returns a list that includes:
Ia 3x3 matrix representing the moment of inertia tensor of a muscle modeled as a solid cylinder distributed along the bone length.
CGa 1x3 vector representing the center of gravity position of a muscle modeled as a solid cylinder distributed along the bone length.
ma double that returns the input muscle mass.
Parallel axis theorem does not apply between two arbitrary points. One point must be the object's center of gravity.
Christina Harvey
# 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)
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