Class / Patent application number | Description | Number of patent applications / Date published |
244087000 | Rudders and empennage | 58 |
20090020644 | CONTRA-BEVEL DRIVEN CONTROL SURFACE - A contra-bevel driven control mechanism repositions a control surface in a fluid environment such as an aerodynamic or hydrodynamic environment. This involves mechanically coupling an airfoil and a control surface. The control surface may pivot about a spanwise axis between upwardly deflected and downwardly deflected positions. A forward beveled rotor mounted to the airfoil and an aft beveled rotor mounted to the control surface counter rotate. The forward beveled rotor rotates about a forward chordwise axis within the airfoil while the aft beveled rotor rotates about an aft chordwise axis within the control surface. The angular rotation between the forward beveled rotor and the aft beveled rotor deflects the aft beveled rotor and the aft chordwise axis within the control surface. Additionally, this method allows the control surface to be deflected with maximum mechanical advantage when the control surface is fully deflected | 01-22-2009 |
20090057483 | ELASTIC PRE-DEFORMED FAIRINGS FOR AIRCRAFTS - A fairing for streamlining the junction between the horizontal stabilizer and the fuselage or the fin of an aircraft, comprising an upper fairing shell, a lower fairing shell, a leading edge extension, and several fittings to join the upper and lower fairing shells to the horizontal stabilizer. The upper and lower fairing shells are solid laminates of composite material that are designed with a shape, composition, and thickness such that they can be elastically deformed when they are fitted to the horizontal stabilizer, providing a contact force permitting them to lay permanently in contact with the fuselage or fin. A process for manufacturing the fairing shells. | 03-05-2009 |
20090065636 | METHOD AND DEVICE FOR ENHANCING THE BRAKING EFFICIENCY OF AN AIRCRAFT DURING THE GROUND RUN THEREOF - According to the invention, the elevators ( | 03-12-2009 |
20090072083 | Actuation system with redundant motor actuators - A multi-redundant motor may be used to implement a relatively small, lightweight redundant actuator assembly package. The motor is implemented as a brushless DC motor and includes N-number of stators and M-number of rotors. Each stator has a plurality of independent stator coils disposed thereon, and N is an integer greater than two. Each permanent magnet rotor is disposed between, and is spaced axially apart from, two of the stators. Each rotor has a plurality of magnetic dipoles disposed thereon, and M is an integer equal to (N−1). | 03-19-2009 |
20090159742 | Lifting structure for aircraft - It is essentially applicable to a horizontal stabilizer that includes two side symmetrical boxes that converge at one end (its root) thereof in a shared center area in order to connect integrally in said central area. | 06-25-2009 |
20090230240 | AERODYNAMIC FAN CONTROL EFFECTOR - A fan control effector for an aircraft comprises at least one blade configured to be pivotably deployable in a radially outward direction from a retracted position to a deployed position such that the blade extends out of the aircraft. The fan control effector may be mounted in a symmetrical arrangement about a longitudinal axis on opposing wings of the aircraft. Furthermore, the fan control effector may comprise any number of blades for independent deployment outwardly from the wing. The blades are configured to be angularly deployable along a direction that is non-parallel to the longitudinal axis of the aircraft. The blades may be configured to be deployable sequentially from the wing starting with an initial deployment of an aft-most one of the blades. | 09-17-2009 |
20090250551 | METHOD FOR IMPROVING ROLL STEERING OF AN AIRCRAFT AND AIRCRAFT USING SAME - The invention concerns a method which consists in subdividing the direction of the control surface into at least two elements ( | 10-08-2009 |
20090256025 | STABILIZING AND DIRECTIONAL-CONTROL SURFACE OF AIRCRAFT - Stabilizing and directional-control surface of an aircraft, said surface comprising a vertical stabilizer ( | 10-15-2009 |
20090283632 | Aircraft Attitude Control Configuration - An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface. | 11-19-2009 |
20090289144 | TRIMMABLE HORIZONTAL STABILIZER - A trimmable horizontal stabilizer is provided adjacent to the fuselage of an aircraft and has a predetermined aerodynamic profile. A movable elevator is arranged adjacent to the horizontal stabilizer. The horizontal stabilizer has a load-bearing structure which extends in the span direction and is firmly connected to the fuselage of the aircraft, and movable areas which are connected to the load-bearing structure such that they can move and can be moved independently of the elevator in order to trim the horizontal stabilizer by varying the aerodynamic profile. | 11-26-2009 |
20100032519 | AIRPLANE WITH A MODIFIABLE SURFACE OF VERTICAL EMPANNAGE - An aircraft has a vertical fin fastened to the rear and above a fuselage of elongated form, essentially in a vertical plane of symmetry of the aircraft. The vertical fin has at least two stable positions, an extended position and a returned position, such that a surface of the vertical fin, subjected to an aerodynamic flow when the aircraft is in flight, is modified in position or in surface between the returned position and the extended position, so that the aerodynamic drag of the vertical fin is reduced in the returned position under given flight conditions compared to the extended position. The change from one surface to another of the vertical fin is accomplished by modifying the geometry of the vertical fin or by displacing the vertical fin relative to the fuselage so that the vertical fin, for example, is more or less inside the fuselage, or more or less immersed in the wake zone of the fuselage in which the local dynamic pressure Pd is reduced relative to the infinitely upstream dynamic pressure Pd0. | 02-11-2010 |
20100038474 | AIRCRAFT HORIZONTAL STABILIZER - According to the invention, the horizontal stabilizer comprises a fixed intermediate part secured to the structure of said aircraft and at least one mobile edge part able to slide with respect to said fixed intermediate part, transversely to the length thereof. Mobile flaps are able to provide the aerodynamic continuity of the suction face and of the pressure face of said stabilizer when said mobile edge part is deployed. | 02-18-2010 |
20100078518 | HORIZONTAL TAIL LOAD ALLEVIATION SYSTEM - A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit. | 04-01-2010 |
20100084506 | AIRCRAFT RUDDER AUTHORITY CONTROL SYSTEM - A system that acts on a rudder (L) having its stop parts commanded or moved by an actuator (A) is described. The rudder system comprises a reversible mechanical system with movable stop parts working based on control/command signals, having stop parts (M, M′) inside of the field of movement of the actuator (A), interfering in the movement of said actuator; the mentioned control signals are based on informations of the aircraft such as traction of the engines or other signal from each engine (pressure, temperature or axis rotation speed); flight speed (“airspeed”); altitude; skidding angle; aircraft on the ground. The system limits the deflection of the rudder in flight with symmetrical traction, enough for normal maneuvers, and it allows total authority of the rudder (L), allowing a larger movement (larger deflection angle) just when necessary, in other words, when there is a traction asymmetry between the engines and, for aircrafts having wheels mechanically connected to the pedals and rudder, when they are maneuvering on the ground during taxi operations. | 04-08-2010 |
20100096497 | BI-DIRECTIONAL FLIGHT CONTROL SURFACE MECHANISM - A bi-directional flight control surface mechanism comprises a fixed part V of a vertical stabiliser having leading and trailing edges and a rudder having leading and trailing edges. The rudder is mounted relative to the fixed part of the vertical stabiliser so that the trailing edge of the fixed structure is adjacent the leading edge of the rudder. The rudder is movable from a neutral position in which the rudder lies in line with the fixed part of the vertical stabiliser to define a notional centreline to first and second angled positions in which the rudder is angled relative to the fixed part of the vertical stabiliser at a non-zero angle on one or other side of the notional centreline. An actuator is provided to drive the rudder relative to the fixed part of the vertical stabiliser so as to vary the distance between said part of the trailing edge of the fixed part of the vertical stabiliser and the leading edge of the rudder. | 04-22-2010 |
20100116928 | AIRCRAFT - The invention provides an aircraft, comprising a fuselage ( | 05-13-2010 |
20100140393 | RUDDER OF A COMMERICAL AIRCRAFT - A rudder of a commercial aircraft is provided that is divided along its longitudinal direction in at least one region and the parts of the rudder can be spread against the air flow surrounding the aircraft by means of an actuator in order to decelerate the aircraft. | 06-10-2010 |
20100147999 | MOBILE SURFACES FOR AIRCRAFT WITH SEALED SLOTS - A lifting or stabilising component ( | 06-17-2010 |
20100148000 | AIRCRAFT HORIZONTAL STABILIZER SURFACE - Aircraft horizontal stabilizer surface ( | 06-17-2010 |
20100155527 | MONOMOLECULAR CARBON-BASED FILM FOR FORMING LUBRICIOUS SURFACE ON AIRCRAFT PARTS - A monomolecular carbon-based film can be placed on an aircraft part, such as the leading edge designed to directly impinge against air during flight, ascent or descent, in order to form a smooth surface having increased lubricity and reduced air friction. The aircraft part may be in the form of a helicopter rotor, wing, propeller, fin, aileron, nose cone, and the like. The monomolecular carbon-based film can be deposited on the aircraft part, for example, using a reactor that includes a bed of silica and through which emissions from a diesel engine are passed. The monomolecular carbon-based film decreases air friction and increased lift of a modified aircraft that includes an aircraft part treated with the film. | 06-24-2010 |
20100155528 | AIRCRAFT STABILIZER SURFACE TRAILING EDGE - Trailing edge ( | 06-24-2010 |
20100163672 | FAIRING SYSTEM FOR A HORIZONTAL STABILISER OF AN AIRCRAFT AND PROCESS FOR INSTALLING SAID SYSTEM - The invention relates to a fairing system for a horizontal stabiliser of an aircraft and to a process for installing said system, such that the fairing system for the sealing of the horizontal stabiliser ( | 07-01-2010 |
20110095128 | AIRCRAFT WITH AT LEAST TWO RUDDER UNITS IN A NON CENTRAL ARRANGEMENT - An aircraft has at least two rudder units in a non-central arrangement. The rudder units have a profile and are rigidly secured to the aircraft. The profile is adjusted in such a way as to yield an inflow at a positive geometric angle of incidence, so that the profile generates a lift force having a component pointing in the flight direction. This makes it possible to offset a portion of the aircraft drag. | 04-28-2011 |
20110147517 | PIVOTING STABILISING SURFACE FOR AIRCRAFT - An aircraft ( | 06-23-2011 |
20110174921 | FLIGHT CONTROL SYSTEM FOR AN AIRCRAFT - The invention relates to a flight control system for an aircraft comprising control surfaces ( | 07-21-2011 |
20120025013 | AEROSPACE VEHICLE YAW GENERATING TAIL SECTION - A tail section for an aerospace vehicle is provided. The tail section comprises a rudder which is movable about an axis to generate a yawing moment on the aerospace vehicle. The tail section further comprises a thruster having, in flow series, an air intake, an electrically powered device for accelerating the air received through the intake, and an air outlet which directs the accelerated air to increase the yawing moment generated by the rudder. | 02-02-2012 |
20120091266 | Active Flow Control on a Vertical Stabilizer and Rudder - Systems and methods described herein provide for the control of airflow over a vertical control surface of an aircraft to enhance the forces produced by the surface. According to one aspect of the disclosure provided herein, the vertical control surface of the aircraft is engaged by active flow control actuators that interact with the ambient airflow to alter one or more characteristics of the airflow. An actuator control system detects a flow control event, and in response, activates the active flow control actuators to alter the airflow. According to various aspects, the flow control event is associated with a separation of the airflow, which is corrected through the activation of the appropriate active flow control actuators, increasing the forces produced by the vertical control surface of the aircraft. | 04-19-2012 |
20120091267 | ADAPTIVE TAIL ASSEMBLY FOR SOLAR AIRCRAFT - An adaptive aircraft tail assembly includes a tail boom, and a tail structure. The tail structure has a plurality of control surfaces configured to alter or maintain flight characteristics of the aircraft. The tail structure also has at least (i) one or more photovoltaic cells, or (ii) at least one or more solar thermal collection cells, or (iii) both photovoltaic cells and solar thermal collection cells. The tail structure also includes a rotational pivot configured to rotationally attach the tail structure to the tail boom. Preferably, the plurality of control surfaces are configured so as to be manipulatable to rotate the tail structure about a central axis of the tail boom via the rotational pivot. | 04-19-2012 |
20120111997 | ROTORCRAFT EMPENNAGE - An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. The rudder may mount to a first vertical stabilizer extending between the horizontal stabilizers. The horizontal stabilizers may be secured to second and third vertical stabilizers to form a duct having the rudder positioned within the duct. Additional rudders may mount to the second and third vertical stabilizers. | 05-10-2012 |
20120138738 | SYSTEM FOR INCREASING CONTROLLABILITY FOR AN AIRCRAFT - The system includes deflection transmission means ( | 06-07-2012 |
20120138739 | AIRCRAFT PROVIDED WITH A TAIL PLANE INCLUDING MEANS FOR COMBATING FLUTTER - An aircraft ( | 06-07-2012 |
20120168559 | Removable Horizontal Stabilizer for Helicopter - An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, the spar being located transversely through a tailboom opening and configured to provide structural support for at least a first horizontal airfoil and a second horizontal airfoil. The first and second horizontal airfoils are configured to fittingly receive the spar so that the spar fits at least partially inside the first and second horizontal airfoils. The first and second horizontal air-foils extend outboard from the tailboom to provide aerodynamic pitch stability. | 07-05-2012 |
20120256047 | Method For Improving The Aerodynamic Efficiency Of The Vertical Tail Of An Aircraft - According to the invention, the thickness (EP | 10-11-2012 |
20120298795 | AIRCRAFT WITH A PIVOTABLE REAR PORTION - The invention relates to an aircraft the fuselage ( | 11-29-2012 |
20130119193 | METHOD AND DEVICE FOR THE LATERAL STABILIZATION OF AN AIRCRAFT - The stabilizing device ( | 05-16-2013 |
20130320137 | RUDDER SYSTEM FOR AN AIRCRAFT - A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a centre box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses. | 12-05-2013 |
20140077029 | REMOVABLE HORIZONTAL STABILIZER FOR HELICOPTER - An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, the spar being located transversely through a tailboom opening and configured to provide structural support for at least a first horizontal airfoil and a second horizontal airfoil. The first and second horizontal airfoils are configured to fittingly receive the spar so that the spar fits at least partially inside the first and second horizontal airfoils. The first and second horizontal airfoils extend outboard from the tailboom to provide aerodynamic pitch stability. | 03-20-2014 |
20150360766 | LEADING EDGE NOSE STRUCTURE ON THE VERTICAL STABILIZER OF AN AIRCRAFT - An aircraft with a fuselage, wings, horizontal stabilizers and a vertical stabilizer, wherein on a front portion of the vertical stabilizer an elongated one-piece nose element is mounted which forms lateral air guide surfaces. To the front end of the nose element a perforated metal plate nose member is attached. The front end of the nose element being closed and between this closed front end and the nose member an elongated air channel is formed. | 12-17-2015 |
20160046361 | Bonded and Tailorable Composite Assembly - An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment. | 02-18-2016 |
20160107741 | AIRCRAFT FUSELAGES - Aircraft fuselages are disclosed herein. An example apparatus includes a fuselage of an aircraft having a first section and a second section to which a tail assembly is to be coupled. The second section is aft of the first section and is to extend to at least a trailing edge of a horizontal stabilizer of the tail assembly. A first width of the first section decreases from a front to a rear of the first section, and a second width of the second section is substantially constant. | 04-21-2016 |
20160122002 | Actuating device for displacing a part of the empennage of a helicopter - An actuating device is proposed to displace a part of an empennage of a helicopter, the device comprising:
| 05-05-2016 |
20160137287 | Structural Arrangement and Method of Fabricating A Composite Trailing Edge Control Surface - The present disclosure is generally directed to a composite trailing edge control surface including a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through. | 05-19-2016 |
20160159466 | LOW DRAG SKIN HEAT EXCHANGER - The present invention provides a heat exchanger including a heat exchange panel configured to form an exterior surface of the vehicle (e.g. an aircraft), the heat exchange panel having at least a portion made of a thermally conductive material, and one or more vortex generators protruding from the exterior surface and configured to direct airflow to particular areas on the aircraft, which may then prevent large scale airflow separation. The vortex generator also improves the surface mixing of air flowing over the exterior surface of the heat exchange panel. | 06-09-2016 |
20160176505 | TAILPLANE WITH POSITIVE CAMBER | 06-23-2016 |
244089000 | Elevators both front and rear | 3 |
20120091268 | Structural Dynamic Stability For An Aircraft - An improvement and method for improved structural dynamic stability for 20 and 30 Series Learjets are disclosed. The improvement includes a redistribution of the elevator mass balance to uncouple the elevator rotational motion from the stabilizer translation motion for the higher order horizontal frequencies having node lines in the proximity of the mass outboard counterbalance weights. The original tail section includes a rudder, and a horizontal stabilizer supporting an elevator mounted adjacent the rudder. The elevator includes a proximal end adjacent the rudder and a distal end that includes a counterbalance portion. The improvement includes replacement of an original mass counterbalance weight from within the counterbalance portion with a new mass counterbalance weight of less mass, and the inclusion of additional mass counterbalance weights disposed within the elevator and interposed between the proximal end and the counterbalance portion. | 04-19-2012 |
20120205490 | AIRCRAFT HORIZONTAL STABILISER FITTED WITH LEADING-EDGE STRAKE - An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root. | 08-16-2012 |
20140312169 | Aircraft System for Reduced Observer Visibility - An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom. | 10-23-2014 |
244090000 | Ailerons and other roll control devices | 11 |
20090127406 | AILERON ACTUATOR BRACKET - An aircraft wing comprising: a trailing edge cove extending in a span-wise direction along a trailing edge of the wing, the trailing edge cove having a front face, a top face and a bottom face; an actuator bracket which is mounted to the front and top faces of the trailing edge cove, but not to its bottom face; an aileron actuator coupled at one end to an aileron and at the other end to the actuator bracket, the aileron actuator being adjustable from a retracted position to a deployed position to deploy the aileron; and a channel extending in a span-wise direction along the wing and positioned below the actuator bracket. | 05-21-2009 |
20090218450 | FITTING FOR PIVOTALLY CONNECTING AERODYNAMIC CONTROL ELEMENT TO AIRCRAFT STRUCTURE - A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge. | 09-03-2009 |
20090230253 | METHOD AND DEVICE FOR PILOTING AN AIRCRAFT OPTIMIZING THE CONTROL OF THE AILERONS IN AN ENHANCED-LIFT CONFIGURATION - In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b | 09-17-2009 |
20110303796 | MORPHING CONTROL SURFACE TRANSITION - A transition section forms a continuous contour across a gap between a pair of structures. The transition section comprises at least one rib mounted within the gap and being pivotable relative to the structures. A tip may be mounted to an aft end of the rib and may be rotatable about a tip axis. A skin panel may extend between the structures and may at least partially cover the tip. The skin panel may be deformable during pivoting of the rib such that the tip may rotate into substantial alignment with the skin panel. | 12-15-2011 |
20120074265 | NANO-REINFORCED RADIUS FILLER FOR AN AIRCRAFT STRUCTURE AND A METHOD OF PRODUCING AN AIRCRAFT STRUCTURE COMPRISING SUCH FILLER - A composite radius filler for use in an aircraft structure. The aircraft structure includes structural composite parts assembled together to form the aircraft structure. The composite radius filler is arranged between rounded sections of the structural composite parts for filling a gap formed between the structural composite parts. The composite radius filler is made structural by a nanostructure arranged within the composite radius filler for the reinforcement of the interface between the radius filler and the structural composite part. A method for producing an aircraft structure including a nano-reinforced radius filler. | 03-29-2012 |
20120145834 | Aircraft Attitude Control Configuration - Control surfaces in an aircraft attitude control configuration provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes thrusters mounted to an aircraft, a first control surface kinematically coupled to the aircraft downstream of a first thruster to enable a first vector force to be generated by a portion of thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft of a second thruster. The control surfaces are displaced symmetrically a longitudinal axis of the aircraft. The control surfaces are independently and differentially movable with respect to each other to enable generation of a second vector force by a portion of thrusted air from the second thruster on the second control surface. | 06-14-2012 |
20130146718 | ELEVON CONTROL SYSTEM - A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements. | 06-13-2013 |
20140284431 | AIRCRAFT STRUCTURE WITH STRUCTURAL NON-FIBER REINFORCING BONDING RESIN LAYER - The present invention regards an aircraft structure comprising an aerodynamic composite shell ( | 09-25-2014 |
20150048215 | EFFICIENT CONTROL AND STALL PREVENTION IN ADVANCED CONFIGURATION AIRCRAFT - An apparatus forming an aircraft which is designed for flight by movement through the air, the aircraft has a front and rear portions and a center of mass, with left and right sides when divided by a central plane of reference. The aircraft has inboard portions closer to said central plane of reference and outboard portions farther from said central plane of reference. Further, the aircraft contains at least one positive lifting aerodynamic surface configured to affect the flow of air near said at least one positive lifting aerodynamic surface when said aircraft is appropriately moving forward, and at least one elevon structure configured to create negative aerodynamic force when said aircraft is appropriately moving forward. The elevon structure is constructed so as to have outboard portions thereof positioned outward of said central plane of reference to a distance at least three-fourths of the distance from said central plane of reference to a tip end of said at least one wing. | 02-19-2015 |
20090250558 | AERODYNAMIC SURFACE ASSEMBLY FOR AIRCRAFT - Set of aerodynamic surfaces for an aircraft. | 10-08-2009 |
20130320152 | SLAT SUPPORT ASSEMBLYA HINGE ASSEMBLY FOR ROTATABLY MOUNTING A CONTROL SURFACE ON AN AIRCRAFT - A hinge assembly for rotatably mounting a control surface on an aircraft comprising an actuating shaft, a support element configured to mount the actuating shaft to a first component of an aircraft and a hinge element configured to mount the actuating shaft to a second component of an aircraft, wherein the actuating shaft is slidably mounted to the support element and configured to slide along its longitudinal axis relative to the support element, and the hinge element engages with the actuating shaft so that the actuating shaft and the hinge element are urged to rotate relative to each other about the longitudinal axis of the actuating shaft when the actuating shaft is urged to slide along its longitudinal axis, such that one of said first and second components is urged to rotate relative to the other said component about the longitudinal axis. | 12-05-2013 |
244090000 | Roll control spoilers | 1 |
20090127406 | AILERON ACTUATOR BRACKET - An aircraft wing comprising: a trailing edge cove extending in a span-wise direction along a trailing edge of the wing, the trailing edge cove having a front face, a top face and a bottom face; an actuator bracket which is mounted to the front and top faces of the trailing edge cove, but not to its bottom face; an aileron actuator coupled at one end to an aileron and at the other end to the actuator bracket, the aileron actuator being adjustable from a retracted position to a deployed position to deploy the aileron; and a channel extending in a span-wise direction along the wing and positioned below the actuator bracket. | 05-21-2009 |
20090218450 | FITTING FOR PIVOTALLY CONNECTING AERODYNAMIC CONTROL ELEMENT TO AIRCRAFT STRUCTURE - A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge. | 09-03-2009 |
20090230253 | METHOD AND DEVICE FOR PILOTING AN AIRCRAFT OPTIMIZING THE CONTROL OF THE AILERONS IN AN ENHANCED-LIFT CONFIGURATION - In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b | 09-17-2009 |
20110303796 | MORPHING CONTROL SURFACE TRANSITION - A transition section forms a continuous contour across a gap between a pair of structures. The transition section comprises at least one rib mounted within the gap and being pivotable relative to the structures. A tip may be mounted to an aft end of the rib and may be rotatable about a tip axis. A skin panel may extend between the structures and may at least partially cover the tip. The skin panel may be deformable during pivoting of the rib such that the tip may rotate into substantial alignment with the skin panel. | 12-15-2011 |
20120074265 | NANO-REINFORCED RADIUS FILLER FOR AN AIRCRAFT STRUCTURE AND A METHOD OF PRODUCING AN AIRCRAFT STRUCTURE COMPRISING SUCH FILLER - A composite radius filler for use in an aircraft structure. The aircraft structure includes structural composite parts assembled together to form the aircraft structure. The composite radius filler is arranged between rounded sections of the structural composite parts for filling a gap formed between the structural composite parts. The composite radius filler is made structural by a nanostructure arranged within the composite radius filler for the reinforcement of the interface between the radius filler and the structural composite part. A method for producing an aircraft structure including a nano-reinforced radius filler. | 03-29-2012 |
20120145834 | Aircraft Attitude Control Configuration - Control surfaces in an aircraft attitude control configuration provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes thrusters mounted to an aircraft, a first control surface kinematically coupled to the aircraft downstream of a first thruster to enable a first vector force to be generated by a portion of thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft of a second thruster. The control surfaces are displaced symmetrically a longitudinal axis of the aircraft. The control surfaces are independently and differentially movable with respect to each other to enable generation of a second vector force by a portion of thrusted air from the second thruster on the second control surface. | 06-14-2012 |
20130146718 | ELEVON CONTROL SYSTEM - A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements. | 06-13-2013 |
20140284431 | AIRCRAFT STRUCTURE WITH STRUCTURAL NON-FIBER REINFORCING BONDING RESIN LAYER - The present invention regards an aircraft structure comprising an aerodynamic composite shell ( | 09-25-2014 |
20150048215 | EFFICIENT CONTROL AND STALL PREVENTION IN ADVANCED CONFIGURATION AIRCRAFT - An apparatus forming an aircraft which is designed for flight by movement through the air, the aircraft has a front and rear portions and a center of mass, with left and right sides when divided by a central plane of reference. The aircraft has inboard portions closer to said central plane of reference and outboard portions farther from said central plane of reference. Further, the aircraft contains at least one positive lifting aerodynamic surface configured to affect the flow of air near said at least one positive lifting aerodynamic surface when said aircraft is appropriately moving forward, and at least one elevon structure configured to create negative aerodynamic force when said aircraft is appropriately moving forward. The elevon structure is constructed so as to have outboard portions thereof positioned outward of said central plane of reference to a distance at least three-fourths of the distance from said central plane of reference to a tip end of said at least one wing. | 02-19-2015 |
20090250558 | AERODYNAMIC SURFACE ASSEMBLY FOR AIRCRAFT - Set of aerodynamic surfaces for an aircraft. | 10-08-2009 |
20130320152 | SLAT SUPPORT ASSEMBLYA HINGE ASSEMBLY FOR ROTATABLY MOUNTING A CONTROL SURFACE ON AN AIRCRAFT - A hinge assembly for rotatably mounting a control surface on an aircraft comprising an actuating shaft, a support element configured to mount the actuating shaft to a first component of an aircraft and a hinge element configured to mount the actuating shaft to a second component of an aircraft, wherein the actuating shaft is slidably mounted to the support element and configured to slide along its longitudinal axis relative to the support element, and the hinge element engages with the actuating shaft so that the actuating shaft and the hinge element are urged to rotate relative to each other about the longitudinal axis of the actuating shaft when the actuating shaft is urged to slide along its longitudinal axis, such that one of said first and second components is urged to rotate relative to the other said component about the longitudinal axis. | 12-05-2013 |
244090000 | Balanced air pressure | 1 |
20090127406 | AILERON ACTUATOR BRACKET - An aircraft wing comprising: a trailing edge cove extending in a span-wise direction along a trailing edge of the wing, the trailing edge cove having a front face, a top face and a bottom face; an actuator bracket which is mounted to the front and top faces of the trailing edge cove, but not to its bottom face; an aileron actuator coupled at one end to an aileron and at the other end to the actuator bracket, the aileron actuator being adjustable from a retracted position to a deployed position to deploy the aileron; and a channel extending in a span-wise direction along the wing and positioned below the actuator bracket. | 05-21-2009 |
20090218450 | FITTING FOR PIVOTALLY CONNECTING AERODYNAMIC CONTROL ELEMENT TO AIRCRAFT STRUCTURE - A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge. | 09-03-2009 |
20090230253 | METHOD AND DEVICE FOR PILOTING AN AIRCRAFT OPTIMIZING THE CONTROL OF THE AILERONS IN AN ENHANCED-LIFT CONFIGURATION - In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b | 09-17-2009 |
20110303796 | MORPHING CONTROL SURFACE TRANSITION - A transition section forms a continuous contour across a gap between a pair of structures. The transition section comprises at least one rib mounted within the gap and being pivotable relative to the structures. A tip may be mounted to an aft end of the rib and may be rotatable about a tip axis. A skin panel may extend between the structures and may at least partially cover the tip. The skin panel may be deformable during pivoting of the rib such that the tip may rotate into substantial alignment with the skin panel. | 12-15-2011 |
20120074265 | NANO-REINFORCED RADIUS FILLER FOR AN AIRCRAFT STRUCTURE AND A METHOD OF PRODUCING AN AIRCRAFT STRUCTURE COMPRISING SUCH FILLER - A composite radius filler for use in an aircraft structure. The aircraft structure includes structural composite parts assembled together to form the aircraft structure. The composite radius filler is arranged between rounded sections of the structural composite parts for filling a gap formed between the structural composite parts. The composite radius filler is made structural by a nanostructure arranged within the composite radius filler for the reinforcement of the interface between the radius filler and the structural composite part. A method for producing an aircraft structure including a nano-reinforced radius filler. | 03-29-2012 |
20120145834 | Aircraft Attitude Control Configuration - Control surfaces in an aircraft attitude control configuration provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes thrusters mounted to an aircraft, a first control surface kinematically coupled to the aircraft downstream of a first thruster to enable a first vector force to be generated by a portion of thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft of a second thruster. The control surfaces are displaced symmetrically a longitudinal axis of the aircraft. The control surfaces are independently and differentially movable with respect to each other to enable generation of a second vector force by a portion of thrusted air from the second thruster on the second control surface. | 06-14-2012 |
20130146718 | ELEVON CONTROL SYSTEM - A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements. | 06-13-2013 |
20140284431 | AIRCRAFT STRUCTURE WITH STRUCTURAL NON-FIBER REINFORCING BONDING RESIN LAYER - The present invention regards an aircraft structure comprising an aerodynamic composite shell ( | 09-25-2014 |
20150048215 | EFFICIENT CONTROL AND STALL PREVENTION IN ADVANCED CONFIGURATION AIRCRAFT - An apparatus forming an aircraft which is designed for flight by movement through the air, the aircraft has a front and rear portions and a center of mass, with left and right sides when divided by a central plane of reference. The aircraft has inboard portions closer to said central plane of reference and outboard portions farther from said central plane of reference. Further, the aircraft contains at least one positive lifting aerodynamic surface configured to affect the flow of air near said at least one positive lifting aerodynamic surface when said aircraft is appropriately moving forward, and at least one elevon structure configured to create negative aerodynamic force when said aircraft is appropriately moving forward. The elevon structure is constructed so as to have outboard portions thereof positioned outward of said central plane of reference to a distance at least three-fourths of the distance from said central plane of reference to a tip end of said at least one wing. | 02-19-2015 |
20090250558 | AERODYNAMIC SURFACE ASSEMBLY FOR AIRCRAFT - Set of aerodynamic surfaces for an aircraft. | 10-08-2009 |
20130320152 | SLAT SUPPORT ASSEMBLYA HINGE ASSEMBLY FOR ROTATABLY MOUNTING A CONTROL SURFACE ON AN AIRCRAFT - A hinge assembly for rotatably mounting a control surface on an aircraft comprising an actuating shaft, a support element configured to mount the actuating shaft to a first component of an aircraft and a hinge element configured to mount the actuating shaft to a second component of an aircraft, wherein the actuating shaft is slidably mounted to the support element and configured to slide along its longitudinal axis relative to the support element, and the hinge element engages with the actuating shaft so that the actuating shaft and the hinge element are urged to rotate relative to each other about the longitudinal axis of the actuating shaft when the actuating shaft is urged to slide along its longitudinal axis, such that one of said first and second components is urged to rotate relative to the other said component about the longitudinal axis. | 12-05-2013 |