Mei Chiin
Cheong
(Commenced: 01-Jan-2010, Concluded: 30-Nov-2010)
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This project presents a study on
the feasibility of utilizing the response forces generated by Dielectric
Barrier Discharge (DBD) plasma actuators to be implemented as an alternative propulsive
system for Micro Air Vehicle (MAV) applications. The momentum transfer
performance of the actuators was verified experimentally and results obtained
were used to dictate the design works of the plasma thrusters that would be
used to propel MAVs. The experimental works of the
project encompassed an investigative research to determine and quantify the
momentum transfer performance of the DBD actuators. A suitable methodology to
measure the response forces generated by the actuators was developed and the
required experimental rig was designed, constructed and independently
verified to ensure that results obtained were valid and useful. Experimental
results were compared with existing literature to ensure that experimental
results were consistent with published results. This provided confirmation
that the force generating capabilities of the DBD actuators investigated were
sufficient to provide useful forces for MAV applications. Further experimental works engaged
were aimed at determining the actuator configurations suitable for the
purpose of the project. A selected number of actuator configurations were
tested and their force generating capabilities were compared. The influence
of varying the applied voltage on the response forces generated was concurrently
investigated during these experiments. This provided the basis of comparison
for the performance of each actuator configuration tested when all other
variables remained constant. The influence of variation of the
geometry of the DBD actuator on the force generating capability was also
investigated. Experiments were conducted to determine the relationship
between the response forces generated and the angle between electrodes of the
DBD actuators tested. A suitable experimental rig was designed and
constructed in order to allow these experimental works to be conducted
effectively. Results obtained from the
experiments of the project were then used to dictate the design works of the
plasma thrusters for MAV applications. A technical task was developed to
determine the design criteria for the plasma thrusters. Actuator
configurations that generated the largest response forces were considered in
the design of the plasma thrusters and implemented onto suitable airframes to
provide propulsion for MAVs. The final design of the plasma
thrusters obtained marked the achievement of all primary goals of the project
and the completion of the project. Project Sponsors
·
The Sir
Ross & Sir Keith Smith Fund Project
Deliverables
Image Galleries:
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![arjomandi[1]](Design%20and%20build%20of%20a%20plasma%20thruster%20for%20MAV%20applications_files/image001.jpg)
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