MAE4416 Orbital mechanics and spaceflight dynamics
Faculty of Engineering
MAE4416 Orbital mechanics and spaceflight dynamics is a level 4, 6-credit-point, undergraduate unit from the Faculty of Engineering, offered in 2026 in Semester 1 at Clayton. It needs MAE3405 and (MAE2505, MMA2004, MAE2405 or MEC2401).
- Credit points
- 6
- Offered in 2026
- Semester 1
- Clayton
- Assessment
- Exam 60%
- and 3 other tasks
- Workload
- 144 hours
- per semester
This is the 2026 handbook entry. See the 2027 entry.
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Requisites
Before MAE4416
Prerequisites
Pass these before you enrol.
Prohibitions
You can't enrol if you have passed any of these.
After MAE4416
No unit lists MAE4416 as a prerequisite in the 2026 handbook.
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.
Offerings in 2026
| Teaching period | Campus | Mode |
|---|---|---|
| First semester | Clayton | On campus |
Assessment
- Mid-semester testsQuiz / TestThreshold hurdle10%
- Weekly problem sets and quizzesQuiz / TestThreshold hurdle10%
- AssignmentsWrittenThreshold hurdle20%
- Final assessment (3 hours)ExaminationThreshold hurdle60%
Assessment details may change. Please refer to the assessment information in Moodle closer to the start of the teaching period.
Learning outcomes
When you finish this unit, you should be able to:
- 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 and teaching
- Workshops24 hours
- Practical activities24 hours
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.
Learning resources
Required resources
Pre-recorded videos, lecture notes, practical problem sets, textbook.
Where it fits
MAE4416 is part of 1 area of study in the 2026 handbook.
Contacts
- Unit Coordinators
- Professor Mark Thompson
- Chief Examiners
- Professor Mark Thompson
Common questions
What are the prerequisites for MAE4416?
You need MAE3405 and (MAE2505, MMA2004, MAE2405 or MEC2401) before you enrol.
When is MAE4416 offered?
In 2026, MAE4416 runs in Semester 1 at Clayton.
How much work is MAE4416?
The handbook expects about 144 hours of study across the semester. No students have rated its difficulty yet.
Does MAE4416 have an exam?
Yes. The exam is worth 60% of the final mark, alongside 3 other tasks.
Which majors and minors include MAE4416?
MAE4416 is part of Aerospace engineering.