MAE4416 · Orbital mechanics and spaceflight dynamics

Overview

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.

Areas of study: E3001 Bachelor of Engineering (Honours) - Specialisation: Aerospace engineering

Offerings

Assessment

The Handbook lists an examination for this unit.

Continuous assessments: 40% Final assessment: 60% This unit contains threshold hurdle requirements that you must achieve to be able to pass the unit. You are required to achieve at least 45% in the total continuous assessment component and at least 45% in the final assessment component. The consequence of not achieving a hurdle requirement is a fail grade (NH) and a maximum mark of 45 for the unit.

Assessment details may change. Please refer to the assessment information in Moodle closer to the start of the teaching period.

Requisites

Learning outcomes

1. Calculate vector solutions to the two-body problem, understanding orbits as conic sections.
2. Compute orbital position as a function of time for various types of orbit.
3. Formulate expressions for orbits in three dimensions utilising the orbital state vector.
4. Calculate orbital transfers and evaluate their suitability, including Hohmann and non-Hohmann transfers, phase changes and plane changes.
5. Simulate interplanetary missions using the method of patched conics while considering orbital position as a function of time.
6. Calculate spacecraft attitude dynamics from the perspective of rigid-body motion.
7. Analyse rocket and launch dynamics, including rocket performance and multi-staging.

Workload

The minimum total expected workload to achieve the learning outcomes for this unit is 144 hours per semester typically comprising a mixture of 3-6 hours of scheduled learning activities and 6-9 hours of independent study per week. Scheduled activities may include a combination of teacher-directed learning, peer-directed learning and online engagement. Independent study may include associated readings, assessment and preparation for scheduled activities.

Student experience, not official rules. Nothing here changes what the Handbook says.