An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise a first shield configured to be disposed around a rotor of the UAM vehicle, the first shield having an annular shape, the first shield configured to be disposed radially outward from a blade tip of a rotary blade, the first shield configured to redirect sound waves from a substantially radial direction to a second direction, the second direction being orthogonal to the radial direction.

An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise a first shield configured to be disposed around a rotor of the UAM vehicle, the first shield having an annular shape, the first shield configured to be disposed radially outward from a blade tip of a rotary blade, the first shield configured to redirect sound waves from a substantially radial direction to a second direction, the second direction being orthogonal to the radial direction.

A propulsion device, including a platform configured to support a passenger thereon; a thrust engine coupled to the platform, wherein the thrust engine is configured to provide a thrust output substantially along a first axis; a deflector assembly positioned proximate the thrust output, wherein the deflector assembly includes two deflecting guides to divert the thrust output into at least two thrust vectors angled with respect to the first axis; an actuator coupled to each deflecting guide to controllably adjust a position of the deflecting guides with respect to the thrust engine; and a controller in communication with the actuator, wherein the controller is configured to operate the actuator in response to one or more signals from at least one of the passenger and a sensor coupled to the platform.

A wing ring flying saucer is disclosed, which is operative to be driven to fly fast without needing an extra engine, and can turn, brake and fly backwards. The method of flying the wing ring flying saucer is as follows: airfoils of the wing ring or flow generators are enabled to repeat the same inclining process while passing by a specific section in circular motions of two times or more than three times in succession, so that a force perpendicular to the axial direction is created from an original resultant force in line with the axial direction of the wing ring (that is, a resultant force created by lift produced by all the airfoils), thereby enabling the wing ring flying saucer to fly, turn and go backwards at a relatively high speed.

A flying object according to the present invention has been developed to have a plurality of rotor blades or jet engines, and to reduce the risk of a crash even if any one of the rotor blades or jet engines is damaged. The flying object comprises: a flying fuselage; a plate-shaped protection member having a plurality of through-holes formed on the same circumference thereof; a driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means, or a rotating means for rotating the protection member around a shaft member, wherein the diameter of the protection member, the interval between the rotational axes of the rotor blades facing each other, the length of the shaft member, and the length of the flying fuselage have a predetermined ratio.

A flying object according to the present invention has been developed to have a plurality of rotor blades or jet engines, and to reduce the risk of a crash even if any one of the rotor blades or jet engines is damaged. The flying object comprises: a flying fuselage; a plate-shaped protection member having a plurality of through-holes formed on the same circumference thereof; a driving means arranged in each of the through-holes; and a tilting means for tilting each of the driving means, or a rotating means for rotating the protection member around a shaft member, wherein the diameter of the protection member, the interval between the rotational axes of the rotor blades facing each other, the length of the shaft member, and the length of the flying fuselage have a predetermined ratio.

A duct for a ducted-rotor aircraft includes a hub, a duct ring, and a plurality of stators that extend outward from the hub. The hub may be configured to support a motor. The duct ring defines a trailing edge. The duct ring is coupled to each of the plurality of stators such that all or substantially all of each of the plurality of stators is located aft of the trailing edge of the duct ring.

A duct for a ducted-rotor aircraft includes a hub, a duct ring, and a plurality of stators that extend outward from the hub. The hub may be configured to support a motor. The duct ring defines a trailing edge. The duct ring is coupled to each of the plurality of stators such that all or substantially all of each of the plurality of stators is located aft of the trailing edge of the duct ring.

A linear thruster aircraft includes: an airframe, including an elongated mounting nacelle and a main body; an aircraft control unit with a processor, a non-transitory memory, and an input/output component; and at least one linear thruster arrangement with at least four thrusters mounted along at least one elongated axis of the elongated mounting nacelle, such that the thrusters are configured to provide lift, pitch, roll, and yaw movement. Optionally, the linear thruster arrangement can include alternating lateral and vertical offsets of the thrusters from the elongated axis, and pairs of thrusters can be vertically overlapping.

In an embodiment, a ducted fan assembly includes a housing that further includes a rotor. The ducted fan assembly also includes a plurality of stators that extend outward from the housing. The ducted fan assembly also includes a control vane pivotally attached to at least one of the plurality of stators. The ducted fan assembly also includes a rim that extends around at least a portion of a perimeter of the ducted fan assembly and is supported by the plurality of stators and the control vane, where the rim defines an opening surrounding at least a portion of the housing.