This paper describes the design, construction and testing of a dual-output power converter concept where the large components, such as the DC link capacitor and heat-sink, are shared between two actuators which are used sequentially in the deployment of aircraft landing gear. This mutual component approach combines the advantages of dual-use power converters with the flexibility of one power converter per application. Practical results of the converter operating are presented for a range of test conditions in order to validate the simulation study.
An Electromechanically Actuated Nose Landing Gear Using a Dual-Output Motor Control Unit
Sae Technical Papers
Power Systems Conference ; 2010
2010-11-02
Conference paper
English
ELECTROMECHANICALLY ACTUATED CONTROL ROD FOR FLIGHT VEHICLES
European Patent Office | 2020
|Hydraulic actuated brake and electromechanically actuated brake systems
Tema Archive | 2001
|Hydraulic actuated brake and electromechanically actuated brake systems
British Library Conference Proceedings | 2001
|SELECTIVELY SELF-LOCKING ELECTROMECHANICALLY AND HYDRAULICALLY ACTUATED MOTOR VEHICLE BRAKE
European Patent Office | 2016
|Selectively self-locking electromechanically and hydraulically actuated motor vehicle brake
European Patent Office | 2019
|