Clayton Second semester 2008 (Day)
On completion of this unit students will have an understanding of the key elements of aircraft performance analysis as used in aerospace vehicle design. The design of mechanical elements for aerospace applications, including the use of solid modelling software and introductory finite element analysis of structural strength will be covered. A student project involving the initial design stages of a flight vehicle will integrate these studies. Various characteristics of aircraft performance and their design implications will be examined including whole-aircraft drag polar, power plant characterisation, thrust required in level flight, maximum speed estimation, minimum speed and high-lift devices, rate of climb, gliding, range, endurance, accelerated flight, structural limitations on performance, design for longitudinal and lateral stability. Mission analysis and preliminary weight estimation based on a design concept will be examined together with the aerodynamic synthesis to satisfy performance requirements, power plant selection, overall vehicle layout and balance. Trade-offs as a necessary part of the design will be apparent to students on completion of this unit.
Examination (2 hours): 50%
Project work: 50%
Students must pass both components to gain a pass in this unit.
Five hours of contact time per week - 3 hours lectures and 2 hours practice sessions or laboratories per week. In addition it is expected student will spend a further 7 hours of private study per week.