Title
Simulation Control

time step: Time step for the numerical integration routine
time: Duration of the simulation periond in seconds

Description

A flexible spacecraft is modeled as a central rigid body with two massless beams
attachd symmetrically to the side of the central body. Each beam has a
concentrated mass at the tip. The flexibility comes from the flexural rigidity EI of
the beams.
2D Flexible Spacecraft Illustration
Inputs

J:                     Moment of inertia
m:                     Tip mass
a:                     Distance as indicated in the illustration above (m)
L:                     Length of the beam (m)
EI:                     Flexural rigidity of the beam (N m2)

Initial Condition

Alpha:             Spacecraft angular position
u1:                 Position of the first mass
u2:                 Position of the second mass
AlphaDot:        Spacecraft angular velocity
u1Dot:             Velocity of the first mass
u2Dot:             Velocity of the second mass

Input and Output