A gas turbine engine used in aviation that produces shaft power and drives an aircraft propeller typically through a gearbox.
Published in Chapter:
Preliminary Sizing and Performance Calculations of Unmanned Air Vehicles
Ali Dinc (American University of the Middle East, Kuwait)
Copyright: © 2019
|Pages: 31
DOI: 10.4018/978-1-5225-7709-6.ch009
Abstract
In this chapter, preliminary sizing and performance calculations of unmanned air vehicles (UAV), with relation to its propulsion system, are explained. Starting with the mission profile of the air vehicle, which is one of the important design drivers, the UAV is sized for the requirements. The requirements in design consist of a set of target values (e.g., payload amount to be carried, range, endurance time, cost, etc.). Additionally, the parameters within mission profile such as cruising altitude and speed of aircraft affect engine type, power level required, fuel quantity, and therefore general dimensions and the gross weight of the aircraft. It is often an iterative process to size the air vehicle and engine together. UAV is designed in a loop of calculations in which sizing, flight performance, and engine performance are done for each phase of the mission or flight profile to satisfy the overall design mission and requirements.