Class / Patent application number | Description | Number of patent applications / Date published |
244051000 | AIRCRAFT, STEERING PROPULSION | 12 |
20100224722 | Airship and Vectored Propeller Drive Therefor - A propulsion unit for an airship comprises a driveshaft, having a gimbal mount to a mounting frame attachable to a fuselage, the gimbal being mounted in the mounting frame and comprising an inner ring and an outer ring having orthogonal rotational axes, the inner ring including a propeller unit having a conical housing pivotable on trunnions with the gimbal and a propeller affixed to a propeller shaft coaxial with the axis of the conical housing. The outer ring includes a toroidal Orientation of the conical housing and propeller shaft is accomplished by actuators, a first actuator controlling the angle of the outer ring relative to the framework and a second actuator controlling the angle of the conical housing relative to the outer ring. | 09-09-2010 |
20130020432 | SYSTEM AND METHOD FOR AN AIR VEHICLE - A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system. | 01-24-2013 |
244052000 | Fluid | 10 |
20080245925 | Aircraft configuration - Some aircraft configurations have an engine arrangement comprising engines as part of an aft fuselage. In order to accommodate such engine arrangement positions, wings are rearwardly displaced compared to other aircraft configurations for balance across the fuselage. By creating empennage functions utilising the nacelle of engines as well as flaps to create rudder and elevator functions, it is possible to accommodate larger engine sizes more suitable for noise control with a reduced necessity for designed rearward movement of wings. | 10-09-2008 |
20100044501 | Method And System For Controlling Fluid Flow In Relation To A Foil And Harnessing Energy Therefrom - A method and system | 02-25-2010 |
20100127115 | "POWER JET CONTROLLER" BALL TAYPE - It illustrated in FIG. | 05-27-2010 |
20120037751 | SUPERSONIC FLYING WING - A bidirectional flying wing maximizes efficiency and reduces sonic boom during supersonic flight. The flying wing has bilateral symmetry across two perpendicular planes and a substantially isentropic compression bottom surface that minimizes the shock wave projected downward during flight. The flying wing may be rotated to provide a high aspect ratio and a low sweep angle during subsonic flight. The flying wing may be rotated to provide a low aspect ratio and a high sweep angle during supersonic flight. | 02-16-2012 |
20120104161 | VARIABLE GEOMETRY AIRCRAFT PYLON STRUCTURE AND RELATED OPERATION TECHNIQUES - An aircraft control structure can be utilized for purposes of drag management, noise control, or aircraft flight maneuvering. The control structure includes a high pressure engine nozzle, such as a bypass nozzle or a core nozzle of a turbofan engine. The nozzle exhausts a high pressure fluid stream, which can be swirled using a deployable swirl vane architecture. The control structure also includes a variable geometry pylon configured to be coupled between the nozzle and the aircraft. The variable geometry pylon has a moveable pylon section that can be deployed into a deflected state to maintain or alter a swirling fluid stream (when the swirl vane architecture is deployed) for drag management purposes, or to assist in the performance of aircraft flight maneuvers. | 05-03-2012 |
20120256044 | FLIGHT VEHICLE, PROPULSION SYSTEM AND THRUST VECTORING SYSTEM - One embodiment of the present invention is a unique flight vehicle. Another embodiment is a unique propulsion system. Another embodiment is a unique thrust vectoring system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for flight vehicles, propulsion systems and thrust vectoring systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 10-11-2012 |
20120318910 | Propulsive Anti-Torque Nozzle System with External Rotating Sleeve for a Rotorcraft - The system of the present application includes a system duct in fluid communication with a tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout. The system further includes an anti-torque nozzle exteriorly proximate to the anti-torque cutout and a pro-torque nozzle exteriorly proximate to the pro-torque cutout. A rotating sleeve is configured to selectively allow airflow into at least one of the anti-torque nozzle and the pro-torque nozzle. A thrust nozzle is in fluid communication with the system duct. An upper clamshell and a lower clamshell are each configured to selectively control airflow in the thrust nozzle. | 12-20-2012 |
20120318911 | Anti-Torque Nozzle System with Internal Sleeve Valve for a Rotorcraft - The system of the present application includes a duct for receiving airflow from within a duct portion of a tailboom. The airflow is a mixture of fan driven air and engine exhaust. The system includes a fixed nozzle assembly with an anti-torque nozzle, a pro-torque nozzle and a thrust nozzle. A rotating sleeve valve is located within the fixed nozzle assembly. The rotating sleeve valve located within the fixed nozzle assembly and is configured to selectively redirect airflow into one or more of the anti-torque nozzle, the pro-torque nozzle and the thrust nozzle. | 12-20-2012 |
20130026285 | FLIGHT CONTROL SYSTEM USING THRUST DEVICES - A flight control system use in relation to an aviation vehicle having a thrust vectoring device for producing thrust, an air deflecting device for producing thrust having a box structure, and a computing system for receiving operation requirements is used to orient the thrust device and/or air deflecting device. | 01-31-2013 |
20160075428 | THRUST VECTORING APPARATUS AND FLYING OBJECT HAVING THRUST VECTORING APPARATUS - The thrust vectoring apparatus has a nozzle, a jet tab arranged behind the nozzle, a rotation shaft | 03-17-2016 |