Constant-Density-Polyhedron-Dynamical-Model

The MATLAB model here presented performs trajectory propagations based on the Constant Density Polyhedron algorithm proposed by Werner[1].

DynamicalModel.mlx

Use script 'DynamicalModel.mlx' to compute trajectories. A list of sample orbits can be found below.

importSTLmodel.mlx

Use script 'importSTLmodel.mlx' to import 3D astronomical body shapes in STL format. More astronomical bodies in STL format can be found here: https://nasa3d.arc.nasa.gov/models After importing the STL model, a workspace is created containing the triangulation data of the body shape. Note that the function 'selectBody.mlx' must be changed as well to include the new body shape.

Sample Orbits

state_vector = [-1689.9 4086.1 5136.9 -6.0545 -4.4489 1.541].*10^3; %Earth ISS orbit

state_vector = [8000 0 0 0 0 7.05556].*10^3; %Earth Circular orbit

state_vector = [8000 0 0 0 9 0].*10^3; %Earth elliptical orbit

state_vector = [7000 0 0 0 0.39128 0 ]; %Toutatis high altitude circular orbit

state_vector = [2600 0 0 0 0.6315 0 ]; %Toutatis low altitude circular orbit

state_vector = [3000 0 0 0 0.75 0 ] %Toutatis elliptical orbit

state_vector = [3000 0 0 -0.9 0.4 0 ]; %Toutatis landing trajectory

state_vector = [350 0 0 0 0.17 0]; %Bennu elliptical orbit

state_vector = [350 0 0 0 0.127 0]; %Bennu circular orbit

state_vector = [346.41 0 200 0 0.1184 0]; %Bennu low altitude circular orbit with inclination

state_vector = [0 1600 0 -0.2 -0.2 0.1]; %HW1 landing trajectory

state_vector = [0 2000 0 0.4766 0 0]; %HW1 low altitude Circular orbit

state_vector = [0 5500 0 0.2933 0 0]; %HW1 high altitude circular orbit

Reference

[1] Exterior gravitation of a polyhedron derived and compared with harmonic and mascon gravitation representations of asteroid 4769 Castalia. Robert A. Werner and Daniel J. Scheeres 1996