The development of electrical actuation systems for aerospace flight surface control
Başlık:
The development of electrical actuation systems for aerospace flight surface control
Yazar:
Binnie, Jonathan Nicholas, author.
ISBN:
9780355978537
Yazar Ek Girişi:
Fiziksel Tanımlama:
1 electronic resource (447 pages)
Genel Not:
Source: Dissertation Abstracts International, Volume: 76-08C.
Özet:
Electrical actuation system are analysed and prototypes developed for the flight control of aircraft. The work focuses chi producing electrical systems which represent viable alternatives to existing hydraulic systems. Two aspects are investigated; the replacement of conventional position valve control systems with directly coupled electric actuators, and the development of an alternative form of primary flight surface actuation driven from an electrically power source. A fundamental study is carried out into the selection of the most suitable electrical machines for position valve control on aircraft. Four types of machine are found suitable for detailed analysis namely the linear reluctance motor, the linear D.C. motor, the solenoid actuator, and the limited angle torquer. Modelling results highlight a novel form of linear D.C. motor as being promising for the whole range of specifications examined. Prototype development and testing of the linear D.C. motor design verifies the impressive performance predictions. A toroidal limited angle torquer is also shown to be suitable for one of the range of specifications. In analysing many forms of solenoid actuator, solution proposals are made to reduce their control problems which make them less attractive for this application. Finally, a novel linear reluctance motor is developed and shown to be a poor contender in comparison with the other devices designed. As a result of the research, attractive solutions for this application are produced which satisfy both the static and the dynamic performance requirements. From the development of a self-contained actuation system for the control of a primary flight surface such as the rudder or aileron, research is described into the choice of the power electronic drive, the electric motor, and hydraulic pump to be used. Out of several possible hardware topologies, an electro-hydraulic actuation system is chosen which embodies the minimum amount of mechanical complexity. To achieve this mechanical simplicity, it is necessary to develop a technically complex power electronic drive unit in order to control the system via the motor. The drive created is made up from elementary electronic components to provide a novel form of vector control of the motor using Hall effect sensors and a pulse width modulated current source inverter. A complete working prototype system is produced albeit with some problems remaining. To complement the prototype actuation system a detailed non-linear model is developed which predicts an attractive performance for the system. This model will enable future systems to be analysed during the design stage in order to ensure that the system manufactured will meet its dynamic performance requirements.
Notlar:
School code: 1543
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Yer Numarası | Demirbaş Numarası | Shelf Location | Lokasyon / Statüsü / İade Tarihi |
---|---|---|---|
XX(683889.1) | 683889-1001 | Proquest E-Tez Koleksiyonu | Arıyor... |
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