Development of Unmanned Aerial Vehicle (UAV) For Wildlife Surveillance
Kyuho Lee , Scot Bowman and Peter Ifju
Micro Air Vehicle Lab, Department of Aerospace and Mechanical Engineering
The University of Florida UAV is constructed primarily of Kevlar, fiberglass, and carbon fiber in order to deliver a high strength with low weight. The vehicle is electrically-powered, with speed and flight duration dependent somewhat on payload (and thus on the capacity and weight of the onboard power supply). Advances in electronics and battery technology will result in performance increases. An autopilot allows for autonomous flight and navigation along pre-programmed paths; manual control can override autopilot anytime for safety and also is normally used for landing.
History and Original Design Specifications
The University of Florida, Department of Aerospace and Mechanical Engineering designed a UAV with overall airplane performance to fit within the imposed design and application requirements of the Florida Cooperative Fish and Wildlife Research Unit:
Figure 1. Pressure distributions over the wing and a visual of airflow such as tip and wing rear side vortexes during a simulation of maximum Cl/Cd flight condition.
| Endurance | 30 min |
| Navigation | GPS / autopilot |
| Payloads | Interchangeable digital camcorder, digital still camera in visible and near-IR spectra, and thermal-IR video cameras |
| Data transmission range | 5-10 km |
| Cruise speed and climb rate | cruise speed 80 km/h climb rate 2 m/s |
| Take-off and landing | Hand launched; short or rough-field landings; parachute and amphibious landing capabilities |
| Wing span | maximum 2 m |
| Propulsion | electric motor |
| Airframe | robust construction, easy repairable, inexpensive manufacturing cost, less radio communication interference due to airframe structure, major parts separately replaced (modular changeability), waterproof construction |
| Camera system | flight stability (for camera stabilization and unskilled pilots), camera lens in a safer location |
| Operation | one man operable |
| Mission altitude | 60+ m |
Several significant technical challenges were overcome to meet these requirements, including (1) Robust airframe (2) High imagery video transmissions and on-board recording (3) GPS way points navigation (4) Amphibious capabilities, and (5) One man operable and cartable.
Figure 2. Assembled prototype Wildlife Surveillance UAV .
Considerations in the design included aerodynamics of the airfoil, structure, stabilization, propulsion systems, and avionics such as the autopilot system, camera recording and antenna sytems, and reception maximization at the ground station.
The airplane aerodynamic efficiency was designed to be most efficient at a cruising speed of about 22 m/s. A suitable propulsion system was also installed to be the most efficient at this velocity. However, field tests provided evidence that in order for the airplane to be used for its intended application, RF communication needs to be more reliable. The airplane was designed not only around flight requirements, but also around an inexpensive price range. The plane costs much less then it counterparts and is designed for easy part replacements (modular design). The airplane also proved itself very durable after withstanding three crashes with minimal damage. With these two primary objectives met and more stable RF communication, the airplane would fit the complete criteria of a wildlife surveillance UAV.
Figure 3. The virtual cockpit software.
2007 Update
We are constantly improving the UAV system. We are in the process of making improvements to the UAV platform to allow for increased payload (approx. 1 kg), increased flight duration, and waterproofing for missions that might necessitate water landings. Further refinements we are pursuing include the capability to operate and track the UAV from a mobile ground platform, a capability that would allow for longer-range transect surveys such as in marine areas or coastal zones.