Aircraft Generator Design and Analysis
Presenter(s)
David Gross
Files
Description
Aircraft electrical power demands have been rapidly growing due to an increased amount of electrical load onboard aircraft. This increased load has come about as electrical sources for various aircraft subsystems, such as pumps, compressors and flight controls, replace mechanical sources. The main source of electrical power on an aircraft is a generator. The power demand on an aircraft is not constant, but rather dynamic, and the nature of these power demands causes increased temperatures and complex/dynamic loads, for which many contemporary generators are not designed. Because of the need for high amounts of reliable electrical power among future aircraft, future generators should be designed for reliability, stability, power density and long-term durability. The objective of this thesis project is to determine if generator sizing techniques (e.g. equations, assumptions, rule-of-thumb metrics) can be calculated to a reasonable accuracy for preliminary machine design optimization and analysis.
Publication Date
4-18-2018
Project Designation
Honors Thesis
Primary Advisor
Guru Subramanyam
Primary Advisor's Department
Electrical and Computer Engineering
Keywords
Stander Symposium project
Recommended Citation
"Aircraft Generator Design and Analysis" (2018). Stander Symposium Projects. 1355.
https://ecommons.udayton.edu/stander_posters/1355
