![Plasma Actuator Simulation and Application: Developing a New Model for Actuator-driven Flow and the Design of a Plasma Actuator Controlled UAV için kapak resmi Plasma Actuator Simulation and Application: Developing a New Model for Actuator-driven Flow and the Design of a Plasma Actuator Controlled UAV için kapak resmi](/client/assets/d79c3e4af2b6d196/ctx/images/no_image.png)
Plasma Actuator Simulation and Application: Developing a New Model for Actuator-driven Flow and the Design of a Plasma Actuator Controlled UAV
Başlık:
Plasma Actuator Simulation and Application: Developing a New Model for Actuator-driven Flow and the Design of a Plasma Actuator Controlled UAV
Yazar:
Laten, Jeffrey B., author.
ISBN:
9780438107496
Yazar Ek Girişi:
Fiziksel Tanımlama:
1 electronic resource (112 pages)
Genel Not:
Source: Masters Abstracts International, Volume: 57-06M(E).
Advisors: Raymond P. LeBeau Committee members: Srikanth Gururajan; Mark McQuilling.
Özet:
The dielectric barrier discharge (DBD) plasma actuator is now an established approach to modifying flows via an electromagnetic field. A typical DBD plasma actuator arrangement includes two offset electrodes separated by a dielectric material, with one electrode exposed to the air. An alternating voltage on the order of several to tens of kilovolts is applied across the electrodes and a weakly ionized gas develops over the enclosed electrode. The electric field then accelerates these charged particles, which in turn through interactions with the neutral molecules accelerate the local flow, creating a parallel wall jet up to 10 m/s with no moving parts.
Over the past dozen years many experimental and numerical studies have been performed using these devices. Various actuator configurations have been tested for use in flow control applications including separation control for vehicle drag reduction or lift augmentation of an airfoil. DBD actuators are also being investigated as a method of aircraft flight control.
A small technology demonstration UAV and lightweight plasma system were designed to test the feasibility of roll and pitch control using trailing edge mounted plasma actuators in lieu of moving control surfaces. The onboard 400W, 7.8kV plasma system is capable of producing a wall jet with velocities over 3.2 m/s. Due to the low efficiency and control power of modern plasma actuators, the aircraft configuration was optimized for maximum maneuverability, and the resulting tandem wing configuration is expected to achieve pitch and roll rates up to 41 deg/s in flight, which are adequate for general maneuvering.
Plasma actuators have been modeled numerically using two distinct methodologies. Phenomenological models attempt to resolve the plasma region by approximating the charge density distribution through higher level processes, such as empirical fits, or electric circuit modeling. Kinetic models attempt to directly capture the ionizations of different species, the resulting chemistry, and then determine the charge distribution.
The surface charge density boundary condition, as well as the thrust scaling, and Debye length parameters in the Suzen-Huang phenomenological plasma actuator were modified which resulted in improved accuracy in the jet velocity and thrust scaling in quiescent conditions. A new phenomenological model was also developed which showed plasma development qualitatively consistent with experiment.
Notlar:
School code: 0193
Konu Başlığı:
Tüzel Kişi Ek Girişi:
Mevcut:*
Yer Numarası | Demirbaş Numarası | Shelf Location | Lokasyon / Statüsü / İade Tarihi |
---|---|---|---|
XX(695269.1) | 695269-1001 | Proquest E-Tez Koleksiyonu | Arıyor... |
On Order
Liste seç
Bunu varsayılan liste yap.
Öğeler başarıyla eklendi
Öğeler eklenirken hata oldu. Lütfen tekrar deneyiniz.
:
Select An Item
Data usage warning: You will receive one text message for each title you selected.
Standard text messaging rates apply.