An aircraft includes an airframe, ducted fans, and ducts for carrying pressurized air for lift and thrust supplied by the fans. The ducts form part of the airframe and carry static and dynamic loads applied to the airframe. Ducting members supply lift and thrust and transmit them to other airframe components. The ducts also carry the ducted air to exits set distant from the fans to permit flight control of the aircraft. Ducting members also form airfoils creating lift for the aircraft.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

An aircraft includes an airframe, ducted fans, and ducts for carrying pressurized air for lift and thrust supplied by the fans. The ducts form part of the airframe and carry static and dynamic loads applied to the airframe. Ducting members supply lift and thrust and transmit them to other airframe components. The ducts also carry the ducted air to exits set distant from the fans to permit flight control of the aircraft. Ducting members also form airfoils creating lift for the aircraft.

A ducted-fan unmanned aerial vehicle (UAV) capable of low-energy high-rate maneuvers for both vertical roll control and horizontal pitch control. The maneuverability of the UAV is enhanced by equipping the ducted fans with respective piezoelectric-actuated thrust vectoring flaps. Thrust vector control is achieved by controlling the angular positions of a plurality of thrust vector flaps pivotably coupled at respective outlets of a plurality of ducts having fan rotors at the inlets. Each thrust vectoring flap has only one degree of freedom in the frame of reference of the UAV, namely, rotation about a single axis that is perpendicular to the axis of the duct. The angular position of the flap is controlled by sending electrical signals to a piezoelectric actuator (e.g., a piezoelectric bimorph actuator) having a voltage sufficient to cause the piezoelectric actuator to bend.

A ducted-fan unmanned aerial vehicle (UAV) capable of low-energy high-rate maneuvers for both vertical roll control and horizontal pitch control. The maneuverability of the UAV is enhanced by equipping the ducted fans with respective piezoelectric-actuated thrust vectoring flaps. Thrust vector control is achieved by controlling the angular positions of a plurality of thrust vector flaps pivotably coupled at respective outlets of a plurality of ducts having fan rotors at the inlets. Each thrust vectoring flap has only one degree of freedom in the frame of reference of the UAV, namely, rotation about a single axis that is perpendicular to the axis of the duct. The angular position of the flap is controlled by sending electrical signals to a piezoelectric actuator (e.g., a piezoelectric bimorph actuator) having a voltage sufficient to cause the piezoelectric actuator to bend.

Systems and methods related to passive variable pitch propellers are described. For example, an aerial vehicle may include one or more passive variable pitch propellers, and such propellers may include one or more passively movable propeller blades having respective hinges, flexible joints, or torsionally flexible joints. Based at least in part on current flight configurations, required thrust, and/or desired advance ratios, the passively movable propeller blades may modify their coning angles and/or pitches, such that the passive variable pitch propellers may operate with improved efficiency in two or more flight configurations. For example, in a VTOL flight configuration, the passive variable pitch propellers may have increased coning angles and decreased pitches, whereas in a horizontal flight configuration, the passive variable pitch propellers may have decreased coning angles and increased pitches.

Systems and methods related to passive variable pitch propellers are described. For example, an aerial vehicle may include one or more passive variable pitch propellers, and such propellers may include one or more passively movable propeller blades having respective hinges, flexible joints, or torsionally flexible joints. Based at least in part on current flight configurations, required thrust, and/or desired advance ratios, the passively movable propeller blades may modify their coning angles and/or pitches, such that the passive variable pitch propellers may operate with improved efficiency in two or more flight configurations. For example, in a VTOL flight configuration, the passive variable pitch propellers may have increased coning angles and decreased pitches, whereas in a horizontal flight configuration, the passive variable pitch propellers may have decreased coning angles and increased pitches.

A hydro flight jet board comprising of a flexible Y manifold capable of third axis movement, a horizontal rocker arm, pivot hinge and a vertical hinge arm and a thrust unit.

A propeller-enclosed airlifting air tube apparatus contains a unique multi air-tube structure that functions as a plurality of air outtakes to produce stable lift force with one or more propellers enclosed in the apparatus. By encapsulating the propellers within the outer shells, the airlifting air tube apparatus is able to reduce potential bodily harm and property damage risks during a flight operation in a densely-populated environment or in another environment involving tight spaces. The airlifting air tube apparatus encapsulates one or more pairs of contra-rotating propellers inside a drone casing to enhance operational safety while minimizing the overall footprint of the apparatus. Furthermore, the airlifting air tube apparatus incorporates a novel airflow control dish-based flight control steering unit configured to change directions and altitudes of the apparatus by dynamically adjusting the airflow to each outtake air tube with the airflow control dish.