A propulsion system for an aircraft includes a plenum having an intake port and an output port. A fan is coupled to a motor configured to power the fan, and the powered fan is configured to compress ambient air entering the intake port. One or more ejectors are fluidically coupled to the plenum via one or more valves. A nozzle is disposed within the output port and includes a set of vanes. The system operates in a first configuration in which the nozzle vanes are closed and the compressed ambient air exits the plenum only through the one or more valves into the one or more ejectors. The system operates in a second configuration in which the one or more valves are closed, the nozzle vanes are open and the compressed ambient air exits the plenum only through the output port.

A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

A VTOL aircraft has a substantially delta-shaped lifting body fuselage with airfoils disposed along all three sides. In vertical flight mode the airfoils act as exhaust diverters. A flow of exhaust gas flows from a centrally located vertical flight gas diffuser over the top surface of the lifting body and then is directed downward by the airfoils to provide vertical lift. In vertical flight mode, the entirety of the exhaust from the engine is diverted to the vertical flight gas diffuser by means of a transition duct that diverts the flow of gas through a 90 upward bend into the vertical flight gas diffuser. In horizontal flight mode the transition duct is fully retracted to permits the entirety of the engine thrust to be directed rearward to propel the aircraft in a horizontal flight mode.

An aircraft includes at least two propulsion units being pivotable and arranged adjacent to each other along an arrangement direction. The propulsion units include a propulsion rotor and a duct for guiding air to the rotor. The duct has a non-circular inlet portion, a circular downstream portion located downstream of the inlet portion along the airflow direction, and an air guiding portion guiding air from the non-circular inlet portion to the circular downstream portion and establishing the transition therebetween. The air guiding portion has upper and lower portions. The aircraft further includes at least one septum interposed between rotation axes of two adjacent propulsion rotors. The septum extends on the upstream side along the airflow direction with respect to the circular downstream portion and between the upper and lower air guiding portions and has a guiding surface having at least one tangential plane parallel to the rotation axis.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are 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 includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

A VTOL aircraft having thrust and directional control comprises a fan for providing a centrifugal flow of air. At least one duct allows for and directs air flow. At least one nozzle allows for exhaust release. Each of the at least one nozzle has a first end attached to one of each of the at least one duct. Each of the at least one nozzle has a turn measuring 90? and faces downward from the second end of each of the at least one duct. Each of the at least one nozzle has a second end at which is a vane for redirecting airflow. The VTOL aircraft also has an attachment for landing.

Systems and methods to control an amount of axial clearance within a clutch transmission system are disclosed. A propulsion system includes a clutch transmission system having clutch vibratory response clearance control logic configured to iteratively control the amount of axial clearance within the clutch transmission system so as to achieve a desired, e.g., consistent and/or limited, clutch vibratory response.

An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

A VTOL aircraft having thrust and directional control comprises a fan for providing a centrifugal flow of air. At least one duct allows for and directs air flow. At least one nozzle allows for exhaust release. Each of the at least one nozzle has a first end attached to one of each of the at least one duct. Each of the at least one nozzle has a turn measuring 90? and faces downward from the second end of each of the at least one duct. Each of the at least one nozzle has a second end at which is a vane for redirecting airflow. The VTOL aircraft also has an attachment for landing.

The present invention relates to a hybrid VTOL jet car comprising a light weight floatable chassis adapted for carrying a payload, a retractable tail section attached to a light weight floatable chassis at rear end adapted for stabilizing the hybrid VTOL jet car, a plurality of wheels at the bottom of the hybrid VTOL jet car, a plurality of retractable wings on the sides of light weight floatable chassis, adapted for maneuvering the hybrid VTOL jet car. Disclosed embodiments further comprising a plurality of thrust-producing engines adapted for generating the thrust required for driving the hybrid VTOL jet car on a surface as well as in the air and a plurality of parachutes attached to the hybrid VTOL jet car to safely land the hybrid VTOL jet car under emergency.