Dissertation/ Thesis
Hybrid actuation in primary flight control systems : a force-fight inhibiting system architecture
| العنوان: | Hybrid actuation in primary flight control systems : a force-fight inhibiting system architecture |
|---|---|
| المؤلفون: | Röben, Tobias |
| المساهمون: | Stumpf, Eike, Moormann, Dieter |
| المصدر: | Aachen 1 Online-Ressource (xi, 145 Seiten) : Illustrationen (2018). doi:10.18154/RWTH-2019-00621 = Dissertation, Rheinisch-Westfälische Technische Hochschule Aachen, 2018 |
| سنة النشر: | 2018 |
| المجموعة: | RWTH Aachen University: RWTH Publications |
| مصطلحات موضوعية: | info:eu-repo/classification/ddc/620, EHA, EHSA, EMA, PFC, active/active, actuation, actuator, control, force fight, hybrid actuation, more electric aircraft, power-by-wire, primary flight control system |
| جغرافية الموضوع: | DE |
| الوصف: | In civil aviation industry effort for optimization and increase of efficiency has been concentrated on single subsystems for decades. Nowadays the whole system architecture is getting into focus. A common approach to reduce system integration effort and increase efficiency is to substitute hydraulic and bleed-air powered systems by electrically powered ones. This applies especially for large aircraft, where the distribution of centralized generated hydraulic power is costly. Meanwhile alterations towards More Electric Aircraft (MEA) have been implemented for non-critical respectively backup systems. The consequent next step is to apply those concepts to critical systems, like Primary Flight Control (PFC), which so far rely on a triplex redundant hydraulic power distribution system. Herein pipes are connecting the central hydraulic power source with the actuation sinks distributed all over the aircraft dimensions. The integration of this rigid piping is elaborate and implies transfer losses as well as leakage of toxic fluid. Power-by-wire actuators in comparison facilitate the complete omission of hydraulics. Nevertheless, since there are safety and reliability challenges and less experience with electrically driven actuators, hybrid configurations arise in the meantime. Within those configurations hydraulic actuators are working adjacent to electric ones on the same control surface. Power distribution is of both electric and hydraulic type and therefore dissimilar. Considering such a hybrid actuator configuration to operate an aircraft control surface, an active/active mode is intended. This is most efficient and leads to less system size and weight, because the actuators are sharing their workload equally and can thus be dimensioned accordingly. Besides an active/passive mode is hardly applicable within a hybrid configuration featuring an electromechanic drive. Due to its transmission it bears high inertia on output level, when driven generatively. Furthermore dissipation of this electric energy becomes ... |
| نوع الوثيقة: | doctoral or postdoctoral thesis |
| اللغة: | English |
| Relation: | https://publications.rwth-aachen.de/record/753456; https://publications.rwth-aachen.de/search?p=id:%22RWTH-2019-00621%22 |
| الاتاحة: | https://publications.rwth-aachen.de/record/753456 https://publications.rwth-aachen.de/search?p=id:%22RWTH-2019-00621%22 |
| Rights: | info:eu-repo/semantics/openAccess |
| رقم الانضمام: | edsbas.EE114949 |
| قاعدة البيانات: | BASE |
| الوصف غير متاح. |