Performance and Design Optimization of the F-Helix eVTOL Concept

The objective of the paper is to study the F-Helix connected to the rotor hub. Lift is entirely generated by its two eVTOL concept. This concept modifies the SH-4 Silvercraft light bladed rotor. The absence of torque exchanged between the helicopter to use electric propulsion and a tip driven rotor. It fuselage and the main rotor greatly reduces the yaw moment is intended to compete with rotorcraft in the light-weight class required to trim and control the aircraft, such that small fans and address future urban air mobility needs. The elimination of can replace the tail rotor and no tail boom is required. The shaft driven propulsion is intended to reduce weight and drag in order to accommodate the added weight of batteries for energy removal of the tail boom reduces weight and drag, and allows storage. Once the configuration of the rotorcraft is established, the rotor mast height to be reduced. The main transmission the design is optimized to produce the least power required is eliminated leading to lower air frame weight and reduced while still meeting the structural and physical constraints of maintenance costs. The weight saved this way is allocated its components. Next, a simulation model is developed to assess to the battery pack powering the eFans, thus justifying the the rotorcraft performance in hover and forward flight. The all-electric approach. Unlike other current eVTOL concepts, payload/range performance is then evaluated for a typical aerial F-Helix has a low disk loading and a relatively high rotor urban transportation mission. Finally, the performance of the inertia, which makes it capable of autorotation. Lastly, F-Helix eVTOL configuration is compared to the SH-4. is based on an existing platform: the Silvercraft SH-4. Table I shows the general characteristics of the SH-4.