15results about "Aircraft navigation control" patented technology

A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

A disc-shaped, vertically launching and landing aircraft, featuring the following: - an apron that widens towards the underside; - a disc-shaped rotor positioned on the underside of the apron and rotating relative to the apron; and - a plurality of blades arranged standing on an upper surface of the rotor and positioned radially from the center of the rotor, - wherein a cutout is formed in each of the majority of wings and - wherein, as the rotor rotates, the centrifugal force causes an airflow along the wing rotating with the rotor, wherein the airflow is swirled in a spiral by an airflow passing over the wing cutout in a direction substantially orthogonal to the wing, wherein the airflow flows along the wing in a radial direction of the rotor while swirling in the spiral, and wherein the airflow being expelled downwards through the skirt causes an upward movement.

An apparatus to determine take-off and landing times for a Rotary wing aircraft by the measurement and analysis of the atmospheric pressure changes around or within the aircraft. This may be done acco

The invention relates to a propulsion device comprising a platform, a thrust unit, support means arranged to maintain and support said thrust unit, cooperating rigidly with said platform via one or more suitable mechanical connections, projecting means cooperating rigidly with the platform via suitable mechanical connections, and a central foot passing through the center of inertia of the propulsion device and cooperating rigidly with the platform via a suitable mechanical connection at its proximal end. To allow the propulsion device to land on reception surfaces that are relatively small compared to the propulsion device and / or moving, the projecting means and the central foot are arranged so that the central foot can ensure the initial contact between said device and a reception surface of said device.

A propulsion system includes at least one conduit, the conduit configured to carry distribute motive fluid, the conduit further configured to collapse when not supplied with motive fluid from a compressor and inflate when supplied with motive fluid from a compressor, and at least one ejector in fluid communication with the at least one conduit, wherein the compressor supplies compressed air to the at least one ejector for producing thrust, and wherein the at least one ejector, when not in use, is retractable into a volume of an airfoil streamlining the outside of said airfoil.

This invention discloses a multi-segment, large-angle two-dimensional vector nozzle, its method, and its application, belonging to the field of aero-engines. It includes a circular-to-square section, with a circular interface at the front end connected to the engine outlet, and an angle deflection mechanism arranged along the axial extension direction of the rear square outlet. The angle deflection mechanism includes circumferentially arranged side plates and follower components. Two side plates are symmetrically arranged on both sides of the rear square outlet, and two sets of follower components are coupled to the upper and lower sides of the rear square outlet, respectively, and located between the two side plates. The two side plates and the upper and lower follower components form the jet outlet. The follower components are composed of multiple angle adjustment plates sequentially hinged, allowing relative rotation between adjacent angle adjustment plates. By adjusting the rotation angle of each angle adjustment plate, the deflection angle of the jet outlet is adjusted, achieving a maximum deflection angle of 90°. This invention solves the problem that conventional two-dimensional vector nozzles cannot achieve large-angle vector deflection in the prior art.

The application relates to the technical field of aircraft transition control, and particularly discloses a transition active control device and method based on a micro high-speed vortex jet pipe; the device comprises a micro flexible jet pipe structure arranged on a wall surface far from a boundary layer and communicated with micro holes arranged on the wall surface; the micro flexible jet pipe structure is arranged in correspondence with a region dominated by transition in the boundary layer; jet flow generated by the micro flexible jet pipe structure enters the boundary layer, sub-instability waves are excited or vortex structures are induced in the boundary layer, and active control of the boundary layer transition is realized. The micro flexible high-speed jet pipe array arranged in a local region of the wall surface realizes transition control of different regions dominated by instability modes in a complex three-dimensional boundary layer under different working conditions.

This invention discloses a hybrid electric canard vertical takeoff and landing (VTOL) aircraft equipped with a vector nozzle and ducted fans. The aircraft includes a fuselage with a streamlined canard configuration. Symmetrical canards are arranged on the front of the fuselage, each equipped with a left and right electric ducted fan. The inlet and outlet of each electric ducted fan are sealed with ducted fans. Main wings are located on both sides of the mid-fuselage, and a vertical tail assembly is located at the rear. The main engine is located at the rear of the fuselage, with a vector nozzle connected to its tail. The main engine is electrically connected to an energy management system via a generator to provide energy to the left and right electric ducted fans, achieving hybrid electric propulsion. This arrangement constitutes a hybrid lift structure of "front canard ducted fan + rear vector nozzle," which, combined with a hybrid electric power system, enables smooth switching between four flight modes: VTOL, hovering, transition, and forward flight.

A two-dimensional gimbaled propeller produces a vector thrust. A directional propeller produces a two-dimensional propulsion thrust vector without producing adverse moments or translational forces. By directing the vector through the aerodynamic center of the propeller, the forces required to control the propulsion vector are minimized, decoupled from the power source that is delivered to the propeller through a drive shaft with a fixed orientation.

Aspects described herein may relate to aerial structures such as aircraft. An aerial structure may include a fuselage, a wing attached to the fuselage, and a plurality of propulsion systems configured to generate thrust. A propulsion system may include a plurality of propulsors, such as propulsor fans. A propulsor fan may be configured to be actuated between a conventional take-off and landing (CTOL) flight mode, a short take-off and landing (STOL) flight mode, a vertical take-off and landing (VTOL) flight mode, and vertical / short takeoff and landing (V / STOL) operations.

A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control surface (50) which is pivotal about a generally horizontal axis. Electric rotors (60) are mounted to the wings (20, 22, 30, 32), the electric rotors (60) being pivotal with the trailing control surface (50) between a first position in which each rotor (60) has a generally vertical axis of rotation, and a second position in which each rotor (60) has a generally horizontal axis of rotation; wherein at least one of the wings (20, 22, 30, 32) has a first and a second electric rotor (60) which are each mounted having non-parallel axes of rotation so that the thrust lines of the first and second electric rotors are different.

Aircraft comprising a flight control and / or drag reduction device (40) for blowing a stream (30) of compressed air into a flow zone around at least one wing (20). Method for modifying the drag and / or lift of at least one wing (20) using such a device (40). Figure for the abstract: Fig. 5

Electric propulsion systems, including electrostatic ion thrusters, for operation in oxygen containing environments, such as very low Earth orbit, may include an oxygen transport membrane, a cathode, and a thruster. The oxygen transport membrane is used to separate oxygen from other constituents in a feed gas resulting in an oxygen rich gas (or permeate) and an oxygen depleted gas (or retentate). The oxygen depleted gas is routed to the cathode. The oxygen rich feed gas is routed to the thruster, such as a Hall Effect Thruster (HET).

The present invention provides a power system for aircraft and a corresponding operating method that enables sufficient resilience to electrical failures in an efficient manner. [Solution] The power distribution network (306) of the aircraft's power system (300) operates in at least one normal operating mode such that it provides load balancing with respect to electrical loads (AA, BB, CC, DD) across power sources (A, B, C, D), and the power distribution network (306) operates in at least one electrical fault mitigation operating mode such that in the event of an electrical fault, the network portion of the power distribution network (306) having the electrical fault is isolated from at least one other network portion of the power distribution network.