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Actuators in aviation
Jetela, Václav ; Horák, Marek (referee) ; Bencalík, Karol (advisor)
The bachelor thesis with name “Actuators in aviation” deals with complete review of hydraulic and electric powered actuators used in aircrafts in a first part. Second part of the thesis is dedicated to review of hydraulic systems. Each chapter contains description of function and schematic drawings. There are mentioned construction designs of actuator test stand for performance testing. Last part of the thesis includes comparison of actuators according to the performance and application in aircrafts.
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Structure Optimization of Electro-Hydrostatic Actuator for General Aviation Aircraft
Kraus, Jan ; Němec, Zdeněk (referee) ; Rousek, Miroslav (referee) ; Třetina, Karel (advisor)
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.
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Structure Optimization of Electro-Hydrostatic Actuator for General Aviation Aircraft
Kraus, Jan ; Němec, Zdeněk (referee) ; Rousek, Miroslav (referee) ; Třetina, Karel (advisor)
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.
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Actuators in aviation
Jetela, Václav ; Horák, Marek (referee) ; Bencalík, Karol (advisor)
The bachelor thesis with name “Actuators in aviation” deals with complete review of hydraulic and electric powered actuators used in aircrafts in a first part. Second part of the thesis is dedicated to review of hydraulic systems. Each chapter contains description of function and schematic drawings. There are mentioned construction designs of actuator test stand for performance testing. Last part of the thesis includes comparison of actuators according to the performance and application in aircrafts.
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