Abstract: Vertical takeoff and landing (VTOL) aircraft are provided with fixed-position port and starboard wings extending laterally from an elongate fuselage having an empennage at an aft end of the fuselage and a propeller to provide horizontal thrust to the aircraft in a direction of the longitudinal axis thereof. A series of port and starboard rotor units are provided, each of which includes axially opposed rotor blades, and a motor to rotate the rotor blades and provide vertical thrust to the aircraft. A logic control unit (LCU) controllably sets an angular position of the opposed rotor blades along a position axis relative to the longitudinal axis of the aircraft in response to determining an optimal position of the rotor blades during cruise flight operation to thereby minimize airflow disruption over the fixed-position wings.

Abstract: Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.

Abstract: Vertical take-off and landing (VTOL) aircraft include a fuselage having a center of gravity (CG) and defining mutually orthogonal X-, Y- and Z-axes. An even number of positionally mirror imaged port and starboard side rotors are provided laterally of the fuselage in spaced relationship to a plane established by the XZ axes while an even number of fuselage rotors are positioned along an X-axis centerline of the fuselage. Improved stability during failure of an engine/motor/rotor is achieved by causing one-half of the side rotors to rotate in one direction about the Z-axis and a remaining one-half of the side rotors rotate in a counter direction relative thereto, while one-half of the fuselage rotors rotate in one direction about the Z-axis and a remaining one-half of the fuselage rotors rotated in a counter direction relative thereto.

Abstract: Seat assemblies are provided which include a seat base structure, a seat cushion supported by the seat base structure and at least a lateral outboard seat lip positioned relative to the seat cushion so as to assist a passenger during seat entry and exit. The lateral outboard seat lip is preferably attached relative to the seat cushion for manual movements between an extended position wherein the outboard seat lip extends outwardly thereby increasing effective surface area of the seat cushion and a deflected position wherein the outboard seat lip extends upwardly or downwardly relative to the seat cushion so as to thereby decrease the effective surface area of the seat cushion.

Abstract: Methodologies to deal with electrical systems and power source failures for electric vertical takeoff and landing aircraft (eVTOL) design with distributed propulsion using multiple electric motors minimize required power source energy to perform an emergency landing procedure. Interconnecting electric loads and power sources in the “Ring Topology” concept considers combination of electric loads and power sources in order to reduce the impact on the loss of a power source, as well as to better utilize the remaining energy of the remaining power sources if any load becomes unavailable.

Abstract: Seat assemblies are provided which include a seat base structure, a seat cushion supported by the seat base structure and at least a lateral outboard seat lip positioned relative to the seat cushion so as to assist a passenger during seat entry and exit. The lateral outboard seat lip is preferably attached relative to the seat cushion for manual movements between an extended position wherein the outboard seat lip extends outwardly thereby increasing effective surface area of the seat cushion and a deflected position wherein the outboard seat lip extends upwardly or downwardly relative to the seat cushion so as to thereby decrease the effective surface area of the seat cushion.

Abstract: Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.

Abstract: Vertical takeoff and landing (VTOL) aircraft are provided with fixed-position port and starboard wings extending laterally from an elongate fuselage having an empennage at an aft end of the fuselage and a propeller to provide horizontal thrust to the aircraft in a direction of the longitudinal axis thereof. A series of port and starboard rotor units are provided, each of which includes axially opposed rotor blades, and a motor to rotate the rotor blades and provide vertical thrust to the aircraft. A logic control unit (LCU) controllably sets an angular position of the opposed rotor blades along a position axis relative to the longitudinal axis of the aircraft in response to determining an optimal position of the rotor blades during cruise flight operation to thereby minimize airflow disruption over the fixed-position wings.

Abstract: Methodologies to deal with electrical systems and power source failures for electric vertical takeoff and landing aircraft (eVTOL) design with distributed propulsion using multiple electric motors minimize required power source energy to perform an emergency landing procedure. Interconnecting electric loads and power sources in the “Ring Topology” concept considers combination of electric loads and power sources in order to reduce the impact on the loss of a power source, as well as to better utilize the remaining energy of the remaining power sources if any load becomes unavailable.

Abstract: Vertical take-off and landing (VTOL) aircraft include a fuselage having a center of gravity (CG) and defining mutually orthogonal X-, Y- and Z-axes. An even number of positionally mirror imaged port and starboard side rotors are provided laterally of the fuselage in spaced relationship to a plane established by the XZ axes while an even number of fuselage rotors are positioned along an X-axis centerline of the fuselage. Improved stability during failure of an engine/motor/rotor is achieved by causing one-half of the side rotors to rotate in one direction about the Z-axis and a remaining one-half of the side rotors rotate in a counter direction relative thereto, while one-half of the fuselage rotors rotate in one direction about the Z-axis and a remaining one-half of the fuselage rotors rotated in a counter direction relative thereto.