Orbital mechanics and spaceflight dynamics

What it covers

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.

Assessment

Hurdle tasks must be passed regardless of your overall mark.

When and where