View source: R/anatomicalmassprop.R
massprop_skin | R Documentation |
Calculate the moment of inertia of skin or tertiaries modeled as a flat triangular plate
massprop_skin(m, rho, pts)
m |
Mass of skin (kg) |
rho |
Density of skin (kg/m^3) |
pts |
a 3x3 matrix that represent three points that define the vertices of the triangle. Frame of reference: VRP | Origin: VRP Must be numbered in a counterclockwise direction for positive area, otherwise signs will be reversed. each point should be a different of the matrix as follows:
|
This function returns a list that includes: point mass
Ia 3x3 matrix representing the moment of inertia tensor of skin modeled as a flat triangular plate
CGa 1x3 vector representing the center of gravity position of skin modeled as a flat triangular plate
ma double that returns the input skin mass
Parallel axis theorem does not apply between two arbitrary points. One point must be the object's center of gravity.
Caution: The skin frame of reference assumes that the z axis is normal to the incoming points.
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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