Abstract:
Flapping wing aerial vehicles are nowadays in demand due to surveillance, civil needs, espionage and border missions.A lot of challenges exists in the development of autonomous
flight missions for the flapping wing aerial vehicles which weigh
less than 2 kg. This research focused on the development of data
driven control system mathematical model and implementation
on flapping wing platform in order to realize the autonomous
flight.In this research,behavior of flapping wing aerial system
is investigated using inertial measurement unit, barometer, GPS
and wireless telemetry. In order to develop the mathematical
model estimation as we utilized the real time telemetry data
by doing flights in the fields.System parameters data was feed
back to ground station with wireless telemetry which would do
processing of the data to develop the mathematical model for the
pitch, roll, yaw and height control behavior. Instead of relying on
the theoretical mathematical models, which often are challenging
to implement due to a lot complex mathematical calculations
involved, system identification approach has been utilized and
practically implemented with successful results.
Index Terms—Mathematical Modeling , Autonomous
Flight,Wireless Sensors, PID Controller, Linear Feedback
Control, Flapping Bird,Ground Control Station.
Authors:
1. Zarrar Haider (Brookfield Villages & UCC, Ireland
)
2. Kashif Ali (PIEAS, Pakistan)
3. Malik Zohaib (EST, Pakistan)
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Page(s): 44-50
Date of Publication: 19 September 2024
