Geometric Pseudospectral Method on SE(3) for Rigid-Body Dynamics with Application to Aircraft

Table 1

Parameters of numerical test.

Time	𝑡∈[0,240] s
Mass	𝑚=1 kg
Moment of inertia	𝐽=diag[1,2.8,2] kg·m^2
Initial orientation	𝑅𝑎𝑏(0)=𝐼3×3
Initial position	𝑝^𝑎𝑎𝑏(0)=[0,0,0]^𝑇 m
Initial linear velocity	𝜐^𝑏𝑎𝑏(0)=[0,0,1]^𝑇 m/s
Initial angular velocity	𝜔^𝑏𝑎𝑏(0)=[1,1,0]^𝑇 rad/s