Abstract
This paper discusses the design route followed in the development of a permanent magnet (PM) machine for electrical power generation on board a rotorcraft (helicopter). The focus of the machine design is to optimise system power density, efficiency, and robustness – all of which are crucial considerations in aerospace applications. A matrix of designs was created consisting of two stators with different winding conductors – copper and aluminium – and three rotors, each using different containment sleeve materials. These include two semi-permeable metallic sleeves, which act to decrease the effective air gap. Combinations of the different materials will yield different system-level power densities and efficiencies. Here, all the designs are presented along with the initial test results for the baseline machine combination validating the design predictions.
Highlights
In common with fixed-wing aircraft, substantial efforts are being made within the rotorcraft sector to develop more electric aircraft (MEA), where mechanical and hydraulic systems are replaced with electrical implementations [1, 2, 3, 4]
The copper wound stator was prioritised over the aluminium one. This decision took into account the conservatism shown towards aluminium at present and has allowed continuing small-scale studies on aluminium to be conducted in parallel
The measured EMF has a slightly higher fundamental component than the design predictions. This is because the design values incorporate the permanent magnet (PM) material's thermal coefficient of Br and are presented for the machine's in-service temperature, whereas the measured values are taken at room temperature
Summary
In common with fixed-wing aircraft, substantial efforts are being made within the rotorcraft sector to develop more electric aircraft (MEA), where mechanical and hydraulic systems are replaced with electrical implementations [1, 2, 3, 4] This move promises a range of potential system benefits including lower maintenance costs, greater efficiency, enhanced reliability, and reduced fuel burn. The question is whether new machine designs, which incorporate modern high-performance materials and are optimised with the use of modern design tools, can offer competitive specific outputs to the existing, mature, wound-field designs Underpinning this is the need to achieve the high reliabilities demanded in the aerospace sector. The design process features three variations of rotor containment material and two different winding materials
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
