Orbital mechanics and spaceflight dynamics

This unit introduces the core concepts of orbital mechanics and spaceflight dynamics. You will use a vector calculus approach to derive equations of motion for two-body problems. Kepler's Laws will be developed from Newtonian mechanics, and central-force orbits as conic sections demonstrated. Orbits in three dimensions will be considered, and orbital position as a function of time. Orbital manoeuvres, including Hohmann and non-Hohmann transfers, phasing manoeuvres and inclination changes will be discussed.  The unit will also cover back-of-the-envelope style interplanetary mission planning using the method of patched conics. Spacecraft and satellite attitude dynamics will be considered in the context of rigid body dynamics.