Unmanned aerial vehicle
An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method for assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises a wing structure comprising elongated equal first and second wings; a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure; and four propellers, each mounted to a respective one of the first and second wings, and first and second sections, for powering the UAV during both vertical and horizontal flight modes.
1. A method of transitioning between a vertical flight mode and a horizontal flight mode, the method comprising the steps of:
providing a UAV having:
a wing structure comprising elongated equal first and second wings,
a support structure comprising first and second sections coupled to a middle position of the wing structure and extending in opposite directions perpendicular to the wing structure,
four propellers, each mounted to a respective one of the first and second wings, and first and second sections;
a single powerplant continuously connected to each of the propellers during both the vertical and horizontal flight modes, the powerplant having a power rating based on at least a weight of the UAV; and
electronic components configured to control the UAV based on an aerodynamic model covering a linear aerodynamic range of angles-of-attack;
operating the powerplant to drive the propellers to perform a vertical climb to a speed equal to at least a stall speed of the UAV; and
at a predetermined height of the UAV and said speed, executing a circular maneuver about a vertical plane to transition from the vertical flight mode to the horizontal flight mode, the circular maneuver having a radius based on said speed,
wherein angles-of-attack of the wing structure are within a linear aerodynamic range throughout the transition.
2. The method as claimed in claim 1 , wherein rotational speeds of the respective propellers are independently controlled.
3. The method as claimed in claim 1 , wherein the same flight controls are used for both vertical and horizontal flight modes.
4. The method as claimed in claim 1 , wherein flight controls for roll, pitch and yaw in vertical and horizontal flight modes are decoupled.
5. The method as claimed in claim 1 , wherein the steps of operating the powerplant and executing a circular maneuver are performed autonomously by the electronic components.