Rigid body dynamics model

Submodule RigidBody provides simulation algorithm for the simple rigid body spacecraft attitude dynamics. This model does not include the flexible structural appendages.

FlexibleSpacecraft.RigidBody — Module

module RigidBody

module that consists variables and functions needed for the simulation of rigid body spacecraft attitude dynamics. Internal module for FlexibleSpacecraft.jl

Usage

include("RigidBody.jl")
using .RigidBody

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Parameter settings for rigid body attitude dynamics

Parameter setting YAML files should be organized as follows:

property: dynamics
name: example spacecraft
note: This model is for test purpose

dynamicsmodel: Rigid body # This must be set `Rigid body`

platform:
    inertia: [ # inertia matrix of the spacecraft
        50000, 0, 0,
        0, 50000, 0,
        0, 0, 50000
        ]

dynamicsmodel should be set Rigid body to tell the software that you are using the rigid body dynamics model.

Public interfaces

FlexibleSpacecraft.RigidBody.RigidBodyModel — Type

struct RigidBodyModel

Data container of rigid body spacecraft model. Used to specify and configure the parameter settings for simulation and control model in FlexibleSpacecraft.jl

Fields of struct RigidBodyModel

inertia::SMatrix{3, 3, <:Real}: Inertia matrix of spacecraft platform

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FlexibleSpacecraft.RigidBody.update_angularvelocity — Function

function update_angularvelocity(model::RigidBodyModel, currentTime::Real, angularvelocity::Union{Vector{<:Real}, SVector{3, <:Real}}, Tsampling::Real, currentbodyframe::Frame, disturbance::Union{Vector{<:Real}, SVector{3, <:Real}})::SVector{3, <:Real}

calculate angular velocity at next time step using 4th order Runge-Kutta method

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