Control of an aircraft electric fuel pump drive

Author

Cathey, J.J. ; Weimer, Joseph A.

Author_Institution

Dept. of Electr. Eng., Kentucky Univ., Lexington, KY, USA

Volume

24

Issue

2

fYear

1988

fDate

3/1/1988 12:00:00 AM

Firstpage

171

Lastpage

176

Abstract

The concept of designing a high-speed, permanent magnet, brushless DC motor aircraft fuel pump drive using a cycloconverter link is examined. A combination of sinusoidal and DC steady-state analysis is used to produce a simple model of the system. A closed-loop control system with an outer loop based on speed and an inner loop based on current is postulated wherein a proportional-plus-integral controller is placed in the forward path to assure minimum speed error. Gains are then set to assure that the eigenvalues of the linearized control system lie within the left half s-plane over the entire full range

Keywords

DC motors; aerospace control; aircraft; closed loop systems; electric drives; permanent magnet motors; pumps; two-term control; velocity control; DC steady-state analysis; aircraft electric fuel pump drive; brushless DC motor; closed-loop control; current control; cycloconverter link; eigenvalues; linearized control system; minimum speed error; permanent magnet; proportional-plus-integral controller; sinusoidal analysis; speed control; two-term control; Aerospace control; Aircraft; Brushless DC motors; Control systems; Eigenvalues and eigenfunctions; Error correction; Fuel pumps; Magnetic analysis; Proportional control; Steady-state;

fLanguage

English

Journal_Title

Aerospace and Electronic Systems, IEEE Transactions on

Publisher

ieee

ISSN

0018-9251

Type

jour

DOI

10.1109/7.1050

Filename

1050