Voting Result: 3.46540153486
Overview for DM-2 Titan
DM-II is a very robust unmanned aircraft, designed to carry safely and efficiently, various types of payloads with high speed and range versatility.
The initial design goal was to design an aircraft able to be deployed fast, for response in emergency situations, such as medical or search and rescue equipment needs. The inspiration came from various incidents that have happened lately in Mediterranean Sea, where small boats have sunk. In such situations, a small and fast aircraft containing Search and Rescue equipment might be able to save lives. Therefore, an automatic payload bay has been included in the design.
DM-II is designed to be very efficient at cruising speeds, to maximize effective range, while maintaining good performance during vertical takeoff. The weighting factors during initial concept were:
- Optimum cruise performance (long range, high speed)
- Good VTOL performance
- Simple solutions approach (Easy maintenance)
- Good ergonomics for human use
The above requirements led to the design of an aircraft with a single high aspect ratio wing, to achieve high efficiency during horizontal flight. The vertical takeoff requirement is assessed through 8 motors in X8 configuration, mounted on two nacelles embedded on the main wing of the aircraft. The booms and propellers are aligned with the airflow during cruise minimizing the drag penalty. Also, the X8 configuration gives the required redundancy in case of motor failure during vertical takeoff, making the aircraft safe for use even in crowded places.
On the tail, a V-Tail is used for stability and authority. Its inherent coupling of rudder with elevator gives authority even with one of the two servos failing, allowing the aircraft to land safely.
The payload bay is located in the fuselage right under the main wing. Its location ensures versatility regarding the payload, as the center of the payload tray is located on the center of mass of the aircraft, minimizing the effect of the payload to the center of gravity of the aircraft. The payload is lowered and then slides out of the aircraft. An automatic unloading mechanism ensures that payload unloading is ergonomically viable for manual operation.
In case of sensors payload the automatic unloading mechanism can be removed allowing for at least 0,5 kg more payload capacity.
The batteries providing the energy required are a combination of 18650 Li-Ion Cells for cruise (High specific energy 237Wh/kg, cannot provide massive power needed during vertical takeoff, maximum discharge rate 3.3C) and Lithium Polymer Cells for VTOL (Lower specific energy 131Wh/kg, Very high maximum power draw capacity, maximum sustained discharge rate >35C, peak 70C).
Finally, regarding redundancy, a fatal failure of the aircraft is almost impossible, due to layered power supply of flight control components, but even in this case, a parachute can be deployed, safely terminating the flight.