MAE3405 · Aerospace propulsion

Overview

This unit builds on concepts in MAE3401 and relates aircraft and rocket engines to the laws of thermodynamics, various fuel-air power cycles, their real behaviour plus fuel and combustion chemistry. The efficiency and performance of aircraft engines based on electric, piston and gas turbine platforms are examined along with rotor and propeller design for subsonic speed. For jets and turbofan engines, nozzle design for transonic to supersonic speed is covered, as are supersonic engines. The unit concludes with an introduction to rocket motors and their design and performance for both atmospheric and space flight.

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

Offerings

Assessment

The Handbook lists an examination for this unit.

Continuous assessment: 40% Final assessment: 60% This unit contains a hurdle requirement 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. Analyse various fuel-air power cycles and electric power plants used in propulsion systems through the application of thermodynamic principles to develop an understanding of their performance and efficiency.
2. Assess the energy sources and fuels used in propulsion systems through simple chemistry and thermodynamic calculations to determine fuelling requirements and emissions.
3. Discuss the differences between real aircraft combustion engines and their fuel-air analogues to develop an understanding of the capabilities and limitations of the various analytical approaches.
4. Demonstrate critical understanding of propeller and rotor design through the application of momentum and blade element theories.
5. Evaluate the thermodynamic performance of intakes and nozzles under subsonic and supersonic conditions to develop an understanding of changing design requirements across various flight regimes.
6. Simulate the performance of chemical and electric propulsion systems for spacecraft through basic rocketry calculations.

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 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.