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.
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