Title
Description

A basic bang-bang control about single axis was implemented in this scenario.
The model of a linearized spacecraft dynamics with a proportional and derivative
control was considered, which is shown in the illustration below.

Block Diagram

Inputs

J                             Spacecraft Moment of inertia
wn                           Desired natural frequency
damping                   Desired damping coefficient
Torque                    Torque level of the bang-bang actuator
Dead Zone               Range in which no torque should be applied
theta_com                Commanded angular position

Initial Condition

theta                     Spacecraft angular position for an actuator with no constraint
thetaDot                Spacecraft angular velocity for an actuator with no constraint
thetaBang              Spacecraft angular position for the bang-bang actuator
thetaDotBang         Spacecraft angular velocity for the bang-bang actuator