The use of only one primary sort of energy is the present trend of aircraft design and its force systens. There are designed electromagnetical force systems for control of ther moving parts of aircraft structure. Great demands are laid on energy and dynamic characteristics at some force systems, especially at aircraft control system, and therefore there are developed electro-hydrostatic actuators, suitable for aircraft for aircraft control system, which could graduallly replace commonly used hydraulic servo-controol system. Not only electric signals but also required electric outputs are led into these electro-hydraulic actuators. Using a hydrostatic converter it is changed into mechanical output controlling the aircraft control system. The goal of work is to set requirements for characteristic and conception of electro – hydrostatic actuators for aircraft control systems. Further, on the basis of theoretical analysis , computer modeling and experiment, the design optimisation of electro-ghydrostatic actuator should be done for small business aircraft from the point of view of dimmensions and dynamic characteristics.
| Identifer | oai:union.ndltd.org:nusl.cz/oai:invenio.nusl.cz:239938 |
| Date | January 2016 |
| Creators | Kraus, Jan |
| Contributors | Němec, Zdeněk, Rousek, Miroslav, Třetina, Karel |
| Publisher | Vysoké učení technické v Brně. Fakulta strojního inženýrství |
| Source Sets | Czech ETDs |
| Language | Czech |
| Detected Language | English |
| Type | info:eu-repo/semantics/doctoralThesis |
| Rights | info:eu-repo/semantics/restrictedAccess |
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