| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244990200 |
Specific control connection or actuator
| 153 |
| 244076000 |
Automatic
| 141 |
| 244220000 |
Pilot operated
| 109 |
| 244087000 |
Rudders and empennage
| 58 |
| 244096000 |
Airship control
| 36 |
| 244990140 |
Trim tab | 3 |
| 20090072085 | LIVE TRIM TABS - A trim tab is disclosed for use on an aerodynamic foil that has first and second surfaces which extend between a leading edge and a trailing edge. Structurally, the trim tab includes a tab member that is bounded by slits formed through each surface to extend from the trailing edge toward the leading edge. Also, the tab member is bounded by a slot formed between the slits on the second surface to establish a flange between the slot and the trailing edge. Further, the trim tab includes an actuator that is mounted on the foil between the slot and the leading edge. The actuator includes an actuator arm that is connected to the flange. As a result, extension and retraction of the actuator moves the tab member about a hinge-less tab that is created on the first surface. | 03-19-2009 |
| 20090146003 | FLIGHT CONTROL USING MULTIPLE ACTUATORS ON PRIMARY CONTROL SURFACES WITH TABS - A flight control system for an aircraft directs a primary surface that is pivotable with respect to the aircraft with a moveable tab located at the end of the primary surface. A primary surface actuator maintains a position of the primary surface. A tab actuator moves the tab with respect to the primary flight control surface. A controller configured to coordinate the movement of the primary flight control surface with the movement of the tab by deflecting the tab with respect to the primary flight control surface, thereby allowing aerodynamic forces acting upon the deflected tab to position the primary flight control surface at a desired position. The primary flight control surface can then be maintained at the desired position by the primary surface actuator. | 06-11-2009 |
| 20100019083 | CONTROL SURFACE OF AIRCRAFT - Aircraft control surface ( | 01-28-2010 |
| 244990130 |
Flutter control | 3 |
| 20110253832 | Slat support assembly - A support assembly for deployment and retraction of an aero surface from an aircraft is disclosed. The assembly comprises a guide track, a primary support arm having one end coupled to a carriage mounted on the track such that the primary support arm is rotatable relative to the carriage about multiple axes, and a control arm having one end coupled to the primary support arm and a second end pivotably attachable to a fixed support forming part of the structure of the aircraft. The assembly being configured such that, when the carriage is driven along the guide track, the control arm causes the primary support arm to pivot about said multiple axes to deploy and/or retract an aero surface pivotally attached to an opposite end of the primary support member along an arcuate path. | 10-20-2011 |
| 20160009374 | System and Method for Distributed Active Fluidic Bleed Control | 01-14-2016 |
| 20160016653 | AIRCRAFT COMPONENT ROTARY DEVICE - A rotary device assembly is provided and includes an input shaft coupled to a torque generating device, an output shaft and a rotary device disposed to transmit first torque from the input shaft to the output shaft and configured with no-back capability to prevent second torque applied to the output shaft from being transmitted to the input shaft in an event the second torque deceeds a torque-limiting threshold and the no-back capability and torsional lock-up capability to prevent an overload of the torque generating device in an event the second torque exceeds the torque-limiting threshold. | 01-21-2016 |
| 244990120 |
Drag | 2 |
| 20110024556 | Aircraft with yaw control by differential drag - An aircraft having an elongated fuselage and a lifting surface fastened to the fuselage. The aircraft has a device for controlling the torque around the yaw axis GZ of the aircraft in which aerodynamic forms that have devices to generate aerodynamic drag are fastened to each end of the lifting surface at non-zero distances from each side of a vertical plane of symmetry XZ of the aircraft. The drag-generating devices are commanded to produce a different aerodynamic drag at each of the two ends to generate a yaw torque on the aircraft. The aerodynamic forms, for example, have winglets improving the aerodynamics of the lifting surface, and provided with aerodynamic drag generators. | 02-03-2011 |
| 20160185449 | FLUID-VECTORING SYSTEM - A jet aircraft includes an aircraft integrated, fluid vectoring, exhaust nozzle system. Implementation of this disclosure may eliminate or reduce the size of the aircraft vertical stabilizer and rudder assembly, thereby potentially improving aircraft survivability and increasing aircraft thrust-to-weight ratio. | 06-30-2016 |
| 244091000 |
Vertical fins | 2 |
| 20090026311 | Aircraft tail assembly - An aircraft tail assembly planform comprising curvilinear leading edges ( | 01-29-2009 |
| 20130270390 | AIRCRAFT HAVING AN AIRCRAFT FUSELAGE AND AN AIR SUCKING FUSELAGE COMPONENT - An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices. | 10-17-2013 |
| 244093000 |
Stabilizing weights | 1 |
| 20120267474 | HEAVIER THAN AIR INTERNAL BALLAST - A vehicle suitable for use in high-altitude applications use may include a gas impermeable body and a flexible barrier separating the body into multiple sections or compartments. The compartments may include a lift compartment for holding lift gas, such as lighter than air gas, and a ballast compartment for holding a ballast, such as heavier than air gas. A valve may permit passage of the ballast from the ballast compartment to an exterior of the body. The body may have an oblong shape, with fins attached to an exterior back end thereof. The vehicle may have only internal ballast compartments, without including a hopper external to the body. | 10-25-2012 |
| 244990100 |
Fuselage | 1 |
| 20140332625 | SUBSONIC PLANE OR FLIGHT SIMULATOR THEREOF, ADJUSTABLE FUSELAGE CONTROL SURFACE, COMPUTER PROGRAM PRODUCT AND METHOD - The invention relates to a subsonic plane or flight simulator, actually or simulatedly comprising an elongate fuselage with a cockpit placed near a first, front end of the fuselage, two wings disposed on opposite sides of the fuselage, provided with ailerons, and a tail located near a second, rear end of the fuselage, which is provided with an elevator and a rudder. The fuselage is furthermore provided with at least one adjustable fuselage control surface for controlling the plane. The fuselage control surface is adjustable between a neutral rest position and at least one working position in which the fuselage control surface extends away from the fuselage. | 11-13-2014 |
| Entries |
| Document | Title | Date |
|---|
| 20080283660 | Aircraft Braking System - A method of braked pivot turning an aircraft, the aircraft comprising a fuselage and a landing gear assembly located to one side thereof. The landing gear comprises a bogie with wheels mounted thereon, at least one wheel being located on a first side of the bogie and at least one wheel being located on a second side of the bogie. The method includes the steps of applying thrust ( | 11-20-2008 |
| 20090179109 | System and method for adjusting control surfaces for wind tunnel models - A system and a method for adjusting and locking a control surface that is movably arranged on a wind-tunnel aircraft model and comprises a drive arrangement for driving the control surface, and a locking arrangement. The drive arrangement comprises a first drive motor, arranged in a fixed manner relative to the control surface, at least one first connecting rod eccentrically connectable to the first drive motor, and at least one lever, whose one end can be held on the first connecting rod and whose other end can be held on a fixed point of the aircraft model. The locking arrangement can be attached in a fixed manner relative to the control surface and is further designed to block a relative movement between the control surface and the aircraft model. | 07-16-2009 |
| 20090218442 | TRAILING EDGE AIRCRAFT STRUCTURE WITH OVERHANGING COVER - An aircraft structure comprising: a rear spar; and a composite cover attached to the rear spar and having an overhanging portion extending to its rear. The overhanging portion of the cover comprises one or more ramps along which the thickness of the cover reduces. A second cover is attached to the rear spar and overhangs to its rear. A hinge rib is attached to one or both of the covers, and an aerodynamic control element such as an aileron, rudder or elevator is pivotally mounted to the hinge rib. | 09-03-2009 |
| 20100170982 | Aircraft without pilot (for commercial and military use) - My innovated aircraft doesn't need pilots to fly in the designated airport; rather, it needs air worthy aircraft and airport's communication/navigation systems. By responding with the communication/navigation system of the airport and inbuilt system of my innovated aircraft, it can do all the jobs of the present aircraft but without requiring any pilot to fly. Therefore, aircraft accident due to pilot error, hijacking etc can be controlled on the aircraft and air transport will be safer than that of present aircraft. | 07-08-2010 |
| 20110174920 | FLIGHT CONTROL SYSTEM ESPECIALLY SUITED FOR VTOL VEHICLES - Flight control systems have plural control subsystems with redundancies organized so as to provide continued but degraded control power over critical aircraft flight operating parameters even if any one complete control subsystem catastrophically fails. One example described in detail for a VTOL craft includes four groups of controls, each group comprising inputs relating to six degrees of freedom of the vehicle, at least one control computer and a plurality of actuators; each group utilizing 25% of required flight control power for the vehicle. | 07-21-2011 |
| 20110210200 | CONTROL SURFACE ASSEMBLIES WITH TORQUE TUBE BASE - Control surface assemblies have a torque tube base. In one embodiment, a method includes moving an aerospace vehicle through a medium; and moving at least a portion of a control surface assembly to generate a force for controlling the vehicle. | 09-01-2011 |
| 20120211598 | Variable Pitch Airfoils - An apparatus may comprise an inflatable control surface for an aircraft and an end of the inflatable control surface configured for attachment to a fuselage of the aircraft. The end of the inflatable control surface may be configured to be rotated about an axis to control movement of the aircraft during flight. | 08-23-2012 |
| 20120241556 | APPARATUS FOR ADJUSTING A SURFACE OF AN AIRCRAFT MODEL, SURFACE UNIT, AIRCRAFT MODEL, AND USE OF AN AIRCRAFT MODEL - An apparatus for adjusting a surface of an aircraft model includes, but is not limited to a first linear adjustment unit with a first retaining body that is movable along a first axis, a second linear adjustment unit with a second retaining body that is movable along a second axis, and an angle adjustment unit. The second linear adjustment unit is arranged on the first retaining body, and the angle adjustment unit is arranged on the second retaining body and is configured to adjust and lock an angle between an attachment surface and a retaining surface. Consequently, precise positioning of surfaces of a wind-tunnel aircraft model does not require specially manufactured and individually adapted fittings for each setting position to be moved to. | 09-27-2012 |
| 20130240667 | Aircraft comprising fairings for correcting its dissymmetry or lateral asymmetry - An aircraft having an asymmetry or a lateral geometric dissymmetry and comprising at least one pair of wings to each of which are fixed at least one fairing, each fairing comprising a surface connected to the lower surface of the wing and extending longitudinally in the direction of a longitudinal axis of the fuselage. The surface of at least one of the fairings has at least one local geometric deformation which is suitable for producing a corrective rolling moment to compensate for the undesirable rolling moment produced by the asymmetry or the lateral dissymmetry of the aircraft. | 09-19-2013 |
| 20130292511 | DIELECTRIC BARRIER DISCHARGE FLIGHT CONTROL SYSTEM THROUGH MODULATED BOUNDARY LAYER TRANSITION - An aerodynamic control system incorporates multiple Dielectric Barrier Discharge (DBD) flow control actuators adjacent a surface of an airborne vehicle in a path of laminar boundary layer flow over the surface. A control computer receives a control input and selectively distributes power to an activation array selected from the DBD flow control actuators for transition to a first operating condition tripping the laminar boundary layer at selected streamwise locations for turbulent flow. When the control computer removes the distributed power the DBD flow control actuators return to a second operating condition restoring the laminar boundary layer. | 11-07-2013 |
| 20140312168 | Control Surface for Creating Variable Camber Along a Wing - An apparatus and method for controlling a shape of an outer surface of a control surface. In one illustrative embodiment, an apparatus comprises a control surface and a shaping system associated with the control surface. The control surface is associated with a portion of an aft edge of a wing. The control surface comprises a plurality of segments in which each of the plurality of segments comprises a number of sections. The shaping system is configured to move each segment in the plurality of segments independently of other segments in the plurality of segments to control a shape of an outer surface of the control surface. | 10-23-2014 |
| 20150108271 | Differential Throttling Control Enhancement - A system for enhancing movement of a multi-engine flight vehicle about either of pitch or yaw axes. The engines are oriented relative the centerline of the flight vehicle and a portion of the engines have a positive tangential cant and the remaining engines have a negative tangential cant. The attitude of the flight vehicle about the pitch, yaw and roll axes is controlled by differentially throttling the multi-engine flight vehicle. | 04-23-2015 |
| 20150298822 | ROTARY-WING DRONE PROVIDED WITH A VIDEO CAMERA DELIVERING STABILIZED SEQUENCES OF IMAGES - The drone ( | 10-22-2015 |
| 20160023782 | BIDIRECTIONAL CONTROL SURFACES FOR USE WITH HIGH SPEED VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS - Vehicles with bidirectional control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. | 01-28-2016 |
| 20160137286 | SHAPE-VARIABLE GAP COVERING BETWEEN CONTROL SURFACES AND ADJACENT STRUCTURAL COMPONENTS ON AIRCRAFTS - A transition piece, which can be mounted in a recess, and which can form a continuous surface from a structural component of an airplane to a control surface, which is connected to the structural component in a pivotable manner is described. The transition piece can be mounted between an edge of the structural component and a lateral edge of the control surface such that the transition piece is fastened in a pivotable manner both to the edge of the structural component and to the lateral edge of the control surface. According to an example, the transition piece has a planar design and can be deformed within said plane, that is, the transition piece can be stretched or compressed within this plane. | 05-19-2016 |
| 20190144112 | CHARGING A RECHARGEABLE BATTERY OF AN UNMANNED AERIAL VEHICLE IN FLIGHT USING A HIGH VOLTAGE POWER LINE | 05-16-2019 |
| 20220135199 | NEUTRALLY BUOYANT VEHICLE MANEUVERING SYSTEM AND METHODS FOR SAME - A towed atmospheric balloon system includes an atmospheric balloon including a quantity of lift gas and a neutral buoyancy towing system coupled with the atmospheric balloon. The neutral buoyancy towing system includes one or more towing thrusters configured to move the towed atmospheric balloon system in a neutrally buoyant condition between altitudes, and a power source operatively coupled with the towing thruster. Wherein a composite mass of the towed atmospheric balloon system includes component masses of the atmospheric balloon and the neutral buoyancy towing system, and the composite mass is static and neutral buoyancy is maintained with movement between altitudes. At differing altitudes the composite mass of the towed atmospheric balloon system is static and the and the system remains neutrally buoyant. | 05-05-2022 |
