| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244990300 |
Linkage
| 75 |
| 244990500 |
Fluid
| 25 |
| 244990400 |
Redundant arrangements
| 10 |
| 244990900 |
Failure tolerant (e.g., jam tolerant, no-back control connection)
| 8 |
| 244990800 |
Actively deformable material (e.g., piezoelectric, shape memory, magnetostrictive, electrostrictive) | 4 |
| 20080272232 | Jet Engine Exhaust Nozzle Flow Effector - A jet engine exhaust nozzle flow effector is a chevron formed with a radius of curvature with surfaces of the flow effector being defined and opposing one another. At least one shape memory alloy (SMA) member is embedded in the chevron closer to one of the chevron's opposing surfaces and substantially spanning from at least a portion of the chevron's root to the chevron's tip. | 11-06-2008 |
| 20090218443 | Magnetorheological fluid elastic lag damper for helicopter rotors - A MagnetoRheolocial Fluid Elastic (MRFE) lag damper system for adaptive lead-lag damping of helicopter main rotors. Embodiments include snubber dampers especially for hingeless helicopter rotors, and concentric bearing dampers. The snubber lag dampers include a flexible snubber body defining a cavity, a flexible or rigid interior (e.g., center) wall subdividing the cavity, and a flow valve in the interior wall or external to the cavity. The flexible snubber body may comprise elastomeric materials and metal rings stacked together to create a sealed MR fluid cavity. The shear deformation of the snubber body induces MR fluid flow through the valve, controlled by a magnetic field in the valve. An MRFE concentric bearing damper is also disclosed, comprising a pair of concentric tubes with elastomeric material injected and cured in an annular gap between the two tubes, and an MR fluid reservoir with piston-mounted MR valve housed inside the innermost tube. | 09-03-2009 |
| 20150129715 | Shape Memory Alloy Rods for Actuation of Continuous Surfaces - A system for connecting two relatively movable structures on an aircraft, comprising: a first rigid structure attached to one of the relatively movable rigid structures; a second rigid structure attached to another of the relatively movable structures; a flexible skin connected to the first and second rigid structures; a sleeve comprising first and second end portions; a first rod comprising a first end portion attached to the first rigid structure, a second end portion slidably coupled to the first end portion of the sleeve, and an intermediate portion made of shape memory alloy; a second rod comprising a first end portion attached to the second rigid structure, a second end portion slidably coupled to the second end portion of the sleeve, and an intermediate portion made of shape memory alloy; and means for heating at least the intermediate portions of the first and second rods. | 05-14-2015 |
| 20160201654 | INTEGRATED HIGH THERMAL CONDUCTIVE FIBER AS COOLING FIN FOR SMA ACTUATOR WITH EXPANDABLE SLEEVE | 07-14-2016 |
| Entries |
| Document | Title | Date |
|---|
| 20080203221 | JAM TOLERANT ELECTROMECHANICAL ACTUATION SYSTEMS AND METHODS OF OPERATION - In a vehicle, having a fixed supporting structure and a load movable relative thereto, a jam tolerant actuating system, a method for controlling this system including: Locating a physical coupling/decoupling mechanism between the load and an actuator assembly as close a practicable to the load; constructing the coupling/uncoupling mechanism to be reversible, and hence testable; and controlling the connection/disconnection via decision making electronics which will detect any system failure by monitoring, at a minimum: actuator main motor load and speed, and actuator output load. Also set forth are specific embodiments of pivotable rotary geared actuators as well as linear ball screw type actuators embodying the coupling/uncoupling mechanisms of this invention. | 08-28-2008 |
| 20080203222 | Yaw Control System and Method - A yaw control system and a method of controlling yaw for an aircraft are provided. The yaw control system includes a first wing set and a second wing set which are rotatable in opposite directions. Each of the wing sets includes at least two wings each including a pivotable flap forming a trailing edge of its respective wing. A flap control assembly controls the pivotable flaps of the first wing set and of the second wing set such that when the pivotable flaps of the first wing set are pivoted in a first direction by a first set angle, the pivotable flaps of the second wing set are simultaneously pivoted by a second set angle in an opposite direction, thereby providing yaw control for the aircraft. | 08-28-2008 |
| 20090256026 | Tilt Actuation for a Rotorcraft - An aircraft is equipped with hingeless rotors on tilting nacelles, and the tilt angles of the nacelles are controlled using either or both of an actuator and a mast moment generated by a hingeless rotor. An aircraft with two or more rotors on tilting nacelles can achieve control of yaw orientation by differential tilt of its nacelles or masts. Hingeless rotors can be manipulated to control a tilt angle of a mast by changing the rotor blade pitch to produce a mast moment. The rotor and nacelle tilt of a tiltrotor rotorcraft can be controlled and effected in order to manipulate the yaw orientation and flight mode of a rotorcraft such as a tiltrotor. The use of mast moment to control nacelle tilt angle can reduce tilt actuator loads and allows for the control of nacelle tilt even in the event of an actuator failure. | 10-15-2009 |
| 20090302153 | ELECTRICAL SYSTEM AND ELECTRICAL ACCUMULATOR FOR ELECTRICAL ACTUATION AND RELATED METHODS - An electrical system for driving flight control actuators, electrical accumulator, and methods for managing electrical power for an aircraft electrical system and methods of retrofitting an aircraft electrical system with an electrical accumulator are provided. The electrical system can include a bidirectional accumulator positioned in electrical communication with the plurality of flight control actuators to absorb excess electrical power regenerated by the plurality of flight control actuators and to provide supplemental power to the plurality of flight control actuators to thereby satisfy transient power requirements. | 12-10-2009 |
| 20100096498 | AIRCRAFT FLIGHT CONTROL ACTUATION SYSTEM WITH DIRECT ACTING, FORCE LIMITING, ACTUATOR - A direct acting force limiting actuator wherein the actuator output force either directly or indirectly causes significant drag on a rotary input shaft rather than on the translating output member. Consequently, input energy is dissipated before the actuator gear train mechanical advantage amplifies the reaction forces. | 04-22-2010 |
| 20100108803 | FITTING FOR TRIMMING A HORIZONTAL STABILIZER OF AN AIRCRAFT | 05-06-2010 |
| 20100127120 | Aircraft Structure - An aircraft control surface mounting structure comprising a cantilever rib ( | 05-27-2010 |
| 20100170983 | Flight control system for an aircraft - Power takeoff means ( | 07-08-2010 |
| 20100213310 | Shuttle Stop Force Limiter - The present invention provides an actuator characterized by the use of a shuttle that shifts in response to an overload. The shuttle is movable axially relative to a rotary input member by continued rotation of the rotary input member so that a stop on the shuttle moves from an ambush position allowing free rotation of the rotary input member to a blocking position preventing further rotation of the rotary input member. In this way, the shuttle can be used to prevent rotation of a rotary input member during an overload of a control surface, thereby preventing damage to the actuator. | 08-26-2010 |
| 20100282898 | AIRCRAFT STRUCTURE WITH MODIFIED CONTROL DEVICE HINGE LINE - An aircraft structure including a main structure element, a control device, a hinge assembly and an actuator. The hinge assembly includes a spar bracket attached to a rear spar in the main structure element, and a control device bracket attached to control device spar. The hinge assembly is pivotally coupled to the spar bracket about a hinge line, about which the actuator rotates the control device. The actuator is pivotally coupled to the main element at a first pivot point and to the control device at a second pivot point, the length of the actuator between the pivot points being adjustable for rotation of the control device. The hinge line is positioned closer to the rear spar than to the control device spar. A flexible line is fixed to the main structure element, and extends in a span-wise direction along the structure. | 11-11-2010 |
| 20110006154 | Enhanced Lubrication Skewed Roller Clutch Assembly And Actuator Including Same - A roller clutch assembly for use in an actuator is provided that includes a roller cage and at least one roller. A lubricating medium at least partially surrounds the roller cage and the roller. The roller cage includes at least one wiper configured to move the lubricating medium toward its functional location adjacent the rollers. An aircraft actuator for controlling movement of an aircraft flight control surface is also provided that includes a ball nut and a ball screw operatively connected to the flight control surface. A one-way roller clutch is operatively connected to the ball nut and substantially prevents rotation of the ball nut in a first direction in response to a compressive force on the ball screw. A roller clutch assembly according to the present invention is positioned between the ball nut and the one-way roller clutch. | 01-13-2011 |
| 20110215194 | ELECTRONIC POWER MODULE FOR AN AIRCRAFT ACTUATOR - An electronic power module, in particular an all-electric actuator for an aircraft, comprising a support having electronic components mounted thereon together with a package covering and surrounding the components and fastened on the support, the package having walls fastened on corresponding faces of an intermediate part that is fastened to the support inside the package. | 09-08-2011 |
| 20110220760 | Actuation System for a Lift Assisting Device and Roller Bearings Used Therein - An actuation system for deploying and retracting a lift assisting device of a wing of an aircraft, is presented. The actuation system includes a track pivotally coupled to the lift assisting device, a shaft rotating in response to flight control signals to deploy or retract the lift assisting device, means for actuating the lift assisting device between a retracted position and a deployed position along an arcuate path, a plurality of track roller bearings and a plurality of side roller bearings. The roller bearings rotatably contact the track to guide the track along the arcuate path. The track roller bearings are comprised of an outer ring, a split inner ring and liners disposed between bearing surfaces of the outer and the inner rings. The split inner ring is configured for accommodating deflection and bending of a mounting pin coupling the track roller bearing in proximity to the track. | 09-15-2011 |
| 20110272521 | FLIGHT UNIT CONTROL SYSTEM, FLIGHT CONTROL DEVICE INCLUDING SUCH A SYSTEM, AND USE OF SUCH A SYSTEM - The present invention relates to a flight unit control system (S), comprising at least one instrumented fastening bolt ( | 11-10-2011 |
| 20120018578 | NEAR SYNCHRONOUS CONTROLLED INDUCTION MOTOR DRIVE ACTUATION SYSTEM - A distributed electromechanical actuation system including multiple electromechanical actuators intended to operate together in a synchronous (or near synchronous) manner. Each individual actuator is powered by one or more induction motors or other appropriate motor such as a stepper motor. The induction motors are designed to have a very high pullout torque with very low slippage to the pull out point. The group of actuators is controlled from a single controller (e.g., an induction motor controller) that utilizes a Volts per Hertz type of open loop control where the bus voltage and frequency are controlled to assure that the motors always operate on the low slip side of the pull out point performance curve. | 01-26-2012 |
| 20140021294 | MEASUREMENT OF THE INERTIAL PROPERTIES OF AN AIRCRAFT MOVABLE CONTROL SURFACE - A method for obtaining the inertial properties of a movable rotating around a hinge line in an aircraft control surface. The method includes the steps of removing the mechanical connections of the actuators from the movable, leaving the movable free to rotate around its hinge line, further balancing the movable and calculating in a first approach its coarse static momentum. The method includes refining the coarse static momentum and obtaining simultaneously a frictional momentum of the movable; incorporating an elastic element on the control surface and configuring a second order mechanical system; inducing forced oscillations on the movable at a certain frequency, this frequency being increased until it is sensibly close to the resonance frequency of the movable to produce a wave response; calculating, from the wave response, the momentum of inertia of the movable. | 01-23-2014 |
| 20140097292 | AIRCRAFT - The present invention relates to an aircraft having at least one landing flap arranged at the wing of the aircraft and having at least one drive unit for actuating the landing flap, wherein the aircraft furthermore has at least one control unit which controls the aileron function of the aircraft, wherein the control unit is connected to the named drive unit or units for adjusting the landing flap(s) and is configured such that it carries out the aileron function of the aircraft in at least one flight mode only or also by the operation of the named drive unit(s) and thus by the adjustment of the landing flap(s). | 04-10-2014 |
| 20140110525 | System and Method for Providing for Collective Control in an Aircraft - In accordance with one embodiment of the present disclosure, a trunnion includes a first portion and a second portion. The first portion is capable of coupling directly to a drive tube of an aircraft, wherein the drive tube is capable of rotating around a first axis. The second portion is capable of coupling to a swash plate of the aircraft, wherein the swash plate is capable of causing the pitch of at least one of a plurality of aircraft blades to change. | 04-24-2014 |
| 20140374536 | AIRCRAFT WING - A wing including a spar, a box shaped sleeve in the spar running substantially the entire length of the wing, a skin affixed to spar and to the corners of the sleeve and shaped to from a leading edge and trailing edge of the wing, a spoiler affixed to an upper surface of the trailing edge of the spar, a vent affixed to the lower surface of the trailing edge of the spar below the spoiler. | 12-25-2014 |
| 20150021432 | CONTROL BOX - The invention provides a control box for selectively delivering orders to receivers ( | 01-22-2015 |
| 20150060601 | AIRCRAFT ELECTRIC ACTUATOR DRIVE APPARATUS - An aircraft electric actuator drive apparatus has an electric actuator and a secondary power supply device. The electric actuator is driven using electric power from a main power unit provided in an aircraft. The secondary power supply device can temporarily supply electric power to the electric actuator while electric power from the main power unit is applied to the electric actuator. | 03-05-2015 |
| 20150083850 | SYSTEM AND METHOD FOR OPTIMIZING PERFORMANCE OF AN AIRCRAFT - A system for optimizing performance of an aircraft may include a flight control computer for computing an optimum flap setting based on aircraft data. The system may further include a flap control system having a flap control device. The system may additionally include a flap actuation system coupled to the flap control system for positioning the trailing edge device at the optimum flap setting. | 03-26-2015 |
| 20150083851 | LEADING AND TRAILNG EDGE DEVICE DEFLECTIONS DURING DESCENT OF AN AIRCRAFT - An system for increasing the descent rate of an aircraft may include a flight control computer, an edge control system, and a speedbrake control device. The flight control computer may be configured to compute a first setting for a leading edge device and/or a trailing edge device of an aircraft wing. The edge control system may be communicatively coupled to the flight control computer and may include an edge control device having a plurality of control device positions including a cruise position. The speedbrake control device may include a plurality of speedbrake detents including a flight detent. The edge control system may be configured to automatically command the leading edge device, the trailing edge device, or both, to a deflection angle corresponding to the first setting if the edge control device is in the cruise position and the speedbrake control device is in the flight detent. | 03-26-2015 |
| 20150129714 | CONNECTION DEVICE FOR MEANS OF AIRPLANE - The disclosure disclosed a connection device for connecting first means of the airplane to second means of the airplane. The first means and the second means are provided with connection regions, which lengthwise extend in a first direction and are connected with each other, respectively. A plurality of finger-like grooves, which are parallel with each other and extend respectively in a second direction inclined relative to the first direction in which the connection region extends, are provided respectively on a connection face of the connection region of the first means and a connection face of the connection region of the second means. Wherein the plurality of finger-like grooves are formed in such a manner that a finger-like protrusion is formed between adjacent finger-like grooves, when fitted, the finger-like protrusions of one of the first means and the second means is inserted into the corresponding finger-like grooves of the other one of the first means and the second means, thereby the first means and the second means are fixedly connected. | 05-14-2015 |
| 20150360768 | Mounting assembly for fully automatic slat - A slat mounting assembly comprising brackets specifically positioned at opposing points, respectively on the main spar and the slat spar on a center line connecting the slat and main spar combined with design and structure of the brackets that maintains a parallel relationship between pairs of axles in a unit such that the slat deploys and retracts automatically, freely, without binding and is securely attached to the wing. | 12-17-2015 |
| 20160129990 | ROTARY ACTUATOR FOR CONTROLLING A FLIGHT CONTROL SURFACE - A rotary actuator for controlling a flight control surface and a flight control surface actuation assembly including the rotary actuator. The actuator comprises a rotary output shaft for driving a flight control surface, a locking mechanism for selectively preventing rotation of the rotary output shaft and a torque limiter for allowing the locking mechanism to be bypassed upon the locking mechanism experiencing a torque above a predetermined limit. | 05-12-2016 |
| 20160152322 | MULTI-SLICE ROTARY ELECTROMECHANICAL ACTUATOR | 06-02-2016 |
| 20160167766 | TRACK CONTAINER | 06-16-2016 |
| 20160167768 | AIRCRAFT, CONTROL SURFACE ARRANGEMENTS, AND METHODS OF ASSEMBLING AN AIRCRAFT | 06-16-2016 |
| 20160200437 | Tethered Flight Control System for Small Unmanned Aircraft | 07-14-2016 |
| 20170233107 | AIRCRAFT HIGH-LIFT DEVICE EQUIPPED WITH AT LEAST ONE DIFFERENTIATED COUPLING SYSTEM | 08-17-2017 |
