Disclosed is a novel jet-propelled lift-increasing and stability-increasing amphibious aircraft and an application method thereof. An air intake fan connects and communicates with an air intake end of a pressurized air storage tank, an air outlet end of the pressurized air storage tank connects and communicates with a shunting pipeline, the shunting pipeline respectively connects and communicates with a plurality of air chambers, each connection of the plurality of air chambers and the shunting pipeline is provided with an adjusting valve, and the plurality of air chambers are distributed in a plurality of positions of the bottom of the aircraft, and are configured to jet air outwards. A navigation state sensing device is configured to detect navigation data of the aircraft and send the navigation data to an intelligent analysis device. The intelligent analysis device is configured to analyze the navigation data, obtain a control scheme and send to a jet control device. The jet control device controls open and closed states of the adjusting valves according to the control scheme to adjust a jet state of the plurality of air chambers. By adjusting the jet quantity of each position of the bottom of the aircraft from various positions, the aircraft is assisted to stably fly. The problems in the prior art are practically solved.

Disclosed is a novel jet-propelled lift-increasing and stability-increasing amphibious aircraft and an application method thereof. An air intake fan connects and communicates with an air intake end of a pressurized air storage tank, an air outlet end of the pressurized air storage tank connects and communicates with a shunting pipeline, the shunting pipeline respectively connects and communicates with a plurality of air chambers, each connection of the plurality of air chambers and the shunting pipeline is provided with an adjusting valve, and the plurality of air chambers are distributed in a plurality of positions of the bottom of the aircraft, and are configured to jet air outwards. A navigation state sensing device is configured to detect navigation data of the aircraft and send the navigation data to an intelligent analysis device. The intelligent analysis device is configured to analyze the navigation data, obtain a control scheme and send to a jet control device. The jet control device controls open and closed states of the adjusting valves according to the control scheme to adjust a jet state of the plurality of air chambers. By adjusting the jet quantity of each position of the bottom of the aircraft from various positions, the aircraft is assisted to stably fly. The problems in the prior art are practically solved.

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 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.

An aircraft controlled by compressed air according to an embodiment of the present invention comprises: a fuselage (10) having main wings (20) on both sides thereof; a first nozzle (12) mounted to the roof of the fuselage (10); second nozzles (22) mounted on the top surfaces of the main wings (20); a first tank (31) disposed in the fuselage (10) or the main wings (20) and storing compressed air; and a main control valve (40) for controlling the compressed air so that the compressed air is provided to the first nozzle (12) or the second nozzles (22).

An aircraft controlled by compressed air according to an embodiment of the present invention comprises: a fuselage (10) having main wings (20) on both sides thereof; a first nozzle (12) mounted to the roof of the fuselage (10); second nozzles (22) mounted on the top surfaces of the main wings (20); a first tank (31) disposed in the fuselage (10) or the main wings (20) and storing compressed air; and a main control valve (40) for controlling the compressed air so that the compressed air is provided to the first nozzle (12) or the second nozzles (22).

This present disclosure relates generally to propulsion systems and, more particularly, to adaptive ducted fan propulsion systems for use with aircraft such as unmanned aerial vehicles. Embodiments of ADF systems in accordance with the present disclosure feature automatic, fast operation, increase the intake section of the air mass fed to a propeller, and can increase thrust by 35%-40% as compared to existing ducted fans.

One example includes an aircraft retrofit system to provide a retrofitted aircraft from an original aircraft. The system includes a plurality of multi-axis vectoring nozzles configured to replace a respective plurality of original nozzles of a respective plurality of original engines of the original aircraft and empennage of the original aircraft, such that the retrofitted aircraft includes no empennage. The system also includes retrofit electronics for controlling the plurality of multi-axis vectoring nozzles to provide yaw control of the retrofitted aircraft.

An emergency landing apparatus for an aircraft and a method of operating the emergency landing apparatus is provided. The emergency landing apparatus comprises: one or more rocket motors arranged to eject efflux in order to provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and control circuitry configured to: cause the one or more rocket motors to eject efflux and provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and cause redirection of the efflux ejected by the one or more rocket motors, during the emergency landing of the aircraft, in order to reduce the upwards thrust provided by the one or more rocket motors.

An active flow control system for generating yaw control moments for an aircraft during hover flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.