structural2VRP_feat {AvInertia} | R Documentation |

Transform feather specific inertial properties to current position

structural2VRP_feat(m_f, I_fCG, CG_start, start, end, normal)

`m_f` |
a scalar representing the mass of the feather (kg) |

`I_fCG` |
a 3x3 matrix representing the moment of inertia tensor with the origin at the feather calamus end and within the feather frame of reference |

`CG_start` |
a 1x3 vector representing the center of gravity of the feather with the origin at the feather calamus end and within the feather frame of reference |

`start` |
a 1x3 vector representing the location of the feather calamus end with the origin at the VRP and within the full bird frame of reference |

`end` |
a 1x3 vector representing the location of the feather tip with the origin at the VRP and within the full bird frame of reference |

`normal` |
a 1x3 vector representing the normal to the plane of the feather vanes within the full bird frame of reference |

a list that includes:

Ia 3x3 matrix representing the moment of inertia tensor of a simplified feather with the origin at the VRP and within the full bird frame of reference

CGa 1x3 vector representing the center of gravity position of a simplified feather with the origin at the VRP and within the full bird frame of reference

ma double that returns the feather mass

# 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)

[Package *AvInertia* version 0.0.1 Index]