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The proposed Unmanned Aircraft System (UAS) consists of an Unmanned Aircraft (UA) and a highly mobile Ground Control Station (GCS). The UAS was designed with cost effectiveness, mass manufacturability, redundancy, durability, modularity, energy efficiency, and sustainability in mind.
The UAV
The UAV
The UAV is a fixed wing, twin propeller, conventional tailplane. This is a simple and efficient design.
Two 16-inch propellers provide a high maximum thrust that allows the UA to get airborne within a distance of under four times its own wingspan. They also serve to provide redundant yaw control alongside the all-moving vertical tail.
Large ailerons in the wings and all-moving tail surfaces provide sufficient maneuverability and control at low speeds and during cruise.
An advanced flight controller paired with an innovative telemetry system allows for manual or automatic flight, taking the UAV to its destination with speed and efficiency.
Telescopic carbon fiber tubes make up the structure of the wing & tail spars and the tail boom, all of which can be rapidly attached and detached from the fuselage with the press of a button.
The main aerodynamic surfaces are multiple sections of closed-cell XPS foam, which slide onto the carbon fiber tubes and can be quickly replaced if damaged. They are wrapped in a thin glossy thermoplastic, which reduces drag and increases the UA’s water resistance.
The fuselage shell is 3D printed from a special foaming filament which is 60% lighter than standard PLA. It is painted and lacquered to reduce drag and protect it and the internal avionics from the elements.
The integrated barometer and LiDar sensor allow for soft touchdowns when the UA returns from its automatic humanitarian aid missions.
A carbon fiber landing gear strut and impact absorbing tires reduce stresses on the airframe. The rubberised joint interfaces and foam mounting pads dampen propeller vibrations, ensuring the flight controllers' accelerometers observe minimum noise.
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