The propulsion unit including a casing having an inner curved surface and an outer curved surface, at least one tire disposed within the casing within a duct defined by the inner curved surface and the outer curved surface, a first propeller and a second propeller having a plurality of blades extending from within the casing toward a center axis of the casing, and one or more motors housed within the casing, the one or motor being configured to operate the at least one tire, the first propeller, and the second propeller independently of one another. There is also provided a vehicle with one or more propulsion units of the present disclosure.

A system and method for improving the flight control and efficiency of an aerial vehicle. Many embodiments are directed to a rotor-shroud assembly system where a plurality of rotor blades are connected to the internal side of a shroud and are set up to pivot through the use of a pitching mechanism. The entire assembly is configured to rotate when attached to a motor.

A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section wherein a downstream end forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and further comprising at least one actuator mechanism with at least one cylinder configured to cooperate with one or more components, projections, etc., embedded in an inner surface of the radially outer wall so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.

A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

In an aspect, a system for propeller parking control for an electric aircraft. The system include at least a sensor and a computing device. A sensor may be configured to generate angular datum. The computing device may be configured to generate a trajectory command as a function of angular datum. The computing device may also be configured to initiate the transition from hover to fixed-wing flight as a function of a trajectory command.

In an aspect, a system for fixed-pitch lift configured for use in an electric aircraft includes a plurality of flight components mechanically coupled thereto, each configured to provide lift to the electric aircraft. The electric aircraft also includes a first pusher mechanically coupled to a first owing of the electric aircraft, wherein the first pusher is configured to provide forward flight to the electric aircraft, a second pusher mechanically coupled to a second wing of the electric aircraft, wherein the second pusher is configured to provide forward flight to the electric aircraft as well, a sensor that is configured to detect vertical lift and forward flight from a pilot control and generate a command datum, as a function of the pilot control, a flight controller which may include a computing device configured to receive the command datum and direct the electric aircraft, as a function of the command datum.

A system (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, includes at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).

An improved efficiency propeller for aircraft includes a blade structure mounted onto a propeller hub, a servo unit, and a cantilevered base. A distinctive feature of the invention is that the blade structure includes a main mast, which is mounted onto a propeller hub and forms the spine of the leading edge of the blade structure, and at least one secondary mast aligned with the main mast, and turning spacers with struts fitted with a strut are mounted onto the main mast, and the struts are covered by lateral pieces of a skin module, and the overlapping and flexible lateral piece of the skin module form a skin.

A propeller control system of an air mobility is configured to insert a movable part forming a propeller into a fixed part in a situation where the air mobility is stored and crashes, thereby reducing an entire length of the propeller. As a result, an entire size of the air mobility is reduced when the air mobility is stored, which may prevent secondary accidents caused by fragments generated by contact of the rotated propeller with the ground in the situation where the air mobility crashes.

A method and device is provided for increasing the efficiency of jet drives by recuperating effective power from the propulsion flow. A ducted propeller in the propeller housing, driven by a driving engine via a drive shaft, conveys the fluid for the jet drive out of the interior V.sub.i of a radial turbine. The fluid is accelerated axially and ejected backwards against the direction of travel. This creates thrust. Because the pressure in the interior of the turbine decreases, new fluid from the environment flows directly via the blades of the rotating radial turbine from the outside to the inside, thereby driving them. A guide apparatus is missing. The power of the radial turbine is transmitted via a transmission to the drive shaft of the propeller, which relieves the driving engine and increases the efficiency of the jet drive. The invention is particularly suitable for electric drives.