Monocopter Duct & Gas-Dynamic Vane Unit

Here is the comprehensive engineering and technical description of the UAV concept, translated into professional, academic English. It is structured and formatted for immediate use in technical documentation, project presentations, research papers, or patent applications. Engineering and Technical Description of a Single-Rotor UAV with Gas-Dynamic Control (Monocopter Model) 1. Project Abstract This project presents an engineering model of an unmanned aerial vehicle (UAV) utilizing a single-rotor configuration with airflow vectoring. Unlike classic multirotor systems (e.g., quadcopters), where thrust vectoring and control over pitch, roll, and yaw are achieved by varying the RPM of independent motors, this design utilizes a single main rotor combined with four adjustable air vanes (aerodynamic control surfaces). This layout—often referred to as a "monocopter" or "coaxial flow" configuration—significantly enhances propulsion aerodynamic efficiency, reduces power consumption, and provides high maneuverability by dynamically redirecting the downwash airflow. 2. Structural Layout and Components The vehicle design features vertical-axial symmetry and consists of the following key sub-assemblies: • Fuselage (Central Pylon): A lightweight carbon fiber frame or a 3D-printed structural chassis that rigidly links the powertrain, electronics, and actuators. • Powertrain: A single high-power brushless DC (BLDC) motor positioned at the top or center of the fuselage, with the main lifting rotor (propeller) mounted directly to its shaft. • Aerodynamic Duct: A shroud or ducting ring (impeller duct) that optimizes the laminar airflow from the main rotor and channels it strictly vertically downward. • Gas-Dynamic Control Unit: An assembly of four mechanical vanes (control surfaces) arranged in a cross configuration at the bottom of the air duct, directly beneath the rotor. Each vane is actuated by an individual, high-speed digital servo motor.

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