| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Method for monitoring a no-back device of an adjustable horizontal trim actuator, corresponding system and aircraft | US12888965 | 2010-09-23 | US20110127375A1 | 2011-06-02 | Cédric TALLOT; Laura Baxerres; Ivan Ferreol |
| The present invention relates to a method and a system for monitoring of an actuator equipped with a no-back device or no-back brake and in particular an adjustable horizontal trim actuator provided in aircraft.The method comprises the steps consisting in:determining a value representative of the mechanical work produced by the said actuator;comparing the said determined value with ranges of values so as to detect a dysfunctioning of the said no-back device.In the case of an actuator of screw/nut type and a hydraulic motor, the said value representative of the mechanical work is determined from an algebraic velocity of the motor and an algebraic differential of hydraulic pressure at the terminals of the said motor.A negative value corresponding to negative mechanical work then identifies a failure of the no-back device. | ||||||
| 182 | FAULT-TOLERANT ELECTROMECHANICAL ACTUATOR HAVING A TORQUE SENSING CONTROL SYSTEM | US12912218 | 2010-10-26 | US20110089877A1 | 2011-04-21 | David E. Blanding; James Leo Peck, JR. |
| A method for forming an electromechanical actuator that involves using at least one motor module engageable with an output ram for controllably translating the output ram along a linear axis of the output ram. A torque sensing adaptive control (TSAC) system is used for monitoring motor module torque within the motor module and generating a disengagement command signal. The disengagement command signal is used to initiate disengagement of the motor module from the output ram when the torque within the motor module is outside an allowable motor module torque range. | ||||||
| 183 | Fault-tolerant electromechanical actuator having a torque sensing control system | US11291709 | 2005-12-01 | US07834494B2 | 2010-11-16 | David E Blanding; Jim Peck |
| An electromechanical actuator (EMA) is provided. The EMA includes a threaded output ram connectable to a mechanical component and at least one motor module engageable with the output ram for controllably translating the output ram along a linear axis of the output ram. The actuator further includes a torque sensing adaptive control (TSAC) system for monitoring torque within the motor module. The TSAC generates a disengagement command signal when the TSAC system determines torque within the motor module is outside an allowable motor module torque range. The disengagement command signal initiates disengagement of the motor module from the output ram. | ||||||
| 184 | AIRCRAFT ACTUATOR | US12763684 | 2010-04-20 | US20100270426A1 | 2010-10-28 | Makoto SAITO; Chris WORRALL |
| An aircraft actuator is provided that can achieve a significant weight reduction, while securing a sufficient tensile strength and a sufficient buckling strength, even if it is provided with a reaction link in which large bent portions are formed. A reaction link is made of fiber reinforced plastic, and includes a pair of linear portions, a coupling portion, and a pair of bent portions. The cross section at the pair of linear portions, the coupling portion, and the pair of bent portions is formed as a hollow cross section. The outer cross sectional area of the hollow cross section at each of the pair of bent portions is configured to be larger than the outer cross sectional area of the hollow cross section at each of the pair of linear portions. | ||||||
| 185 | FLIGHT CONTROL SYSTEM AND AIRCRAFT COMPRISING IT | US12688268 | 2010-01-15 | US20100222943A1 | 2010-09-02 | Manel SGHAIRI; Patrice Brot; Jean-Jacques Aubert; Agnan De Bonneval; Yves Crouzet |
| The flight control system comprises: at least one actuator (13) for a mobile surface of the said aircraft; a flight control module (12) in communication with the said actuator (13), the said module comprising at least a first and a second computer (14-1, 14-2, 14-3, 15-1, 15-2, 15-3), each computer being adapted for calculating a control command established according to at least one predetermined law for control of the said flight surface; the said actuator (13) comprising logical means (18, 19) adapted for comparing the commands of the said computers (14-1, 14-2, 14-3, 15-1, 15-2, 15-3) and for determining on the basis of these commands the action to be executed on the said mobile surface. The aircraft comprises such a system. | ||||||
| 186 | Mechanical flight control auxiliary power assist system | US11664664 | 2005-10-13 | US07668627B2 | 2010-02-23 | Peter M. Shultz; Carlos A. Fenny; Todd Walker; Sam Arjunan |
| A mechanical flight control system for a rotary-wing aircraft is disclosed. The flight control system comprises an upstream portion, a downstream portion, and a booster means for connecting the upstream portion to the downstream portion. The booster means may comprise dual concentric valve actuators and/or a variety of system load limiting features. | ||||||
| 187 | Method for activating a drive system and drive system | US12215237 | 2008-06-26 | US20100001674A1 | 2010-01-07 | Stefan Hauzenberger; Bernhard Hauber |
| This invention discloses a method for activating a drive system for control surfaces or working systems of an aircraft, wherein the speed of a drive unit of the drive system is regulated, and after a starting operation the maximum driving power available during the further operation for speed regulation of the drive unit is reduced. Likewise, this invention comprises a drive system for control surfaces or working systems of an aircraft, comprising a drive unit with speed regulation and a corresponding control. | ||||||
| 188 | BREAKABLE COUPLING DEVICE, AND AN ASSOCIATED TRIM ACTUATOR | US12468285 | 2009-05-19 | US20090283642A1 | 2009-11-19 | Bernard Gemmati; Philippe Vincent; Romuald Biest |
| A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque. | ||||||
| 189 | ACTUATOR SYSTEMS AND ASSOCIATED METHODS FOR UNMANNED AIR VEHICLES AND OTHER APPLICATIONS | US11750133 | 2007-05-17 | US20090212167A1 | 2009-08-27 | Peter Kunz |
| Actuator systems and associated methods are disclosed herein. One aspect of the disclosure is directed toward an actuator system that includes a first structure and a second structure movable relative to the first structure. The system further includes an actuator apparatus and an actuator device coupled in series between the first structure and the second structure. The system can still further include a controller operably coupled to the actuator apparatus and the actuator device. The controller can be programmed with instructions to automatically actuate the actuator apparatus and the actuator device so that a position of the first structure relative to the second structure after the actuator apparatus and the actuator device have been actuated is at least approximately the same as a position of the first structure relative to the second structure before the actuator apparatus and the actuator device have been actuated. | ||||||
| 190 | Rotorcraft control system with stepped mixing linkage | US10528906 | 2003-09-19 | US07461812B2 | 2008-12-09 | Carlos A. Fenny; Duane Hicks |
| A control system for a rotorcraft is disclosed. The control system includes a stepped mixing linkage, such that a selected amount of right-left lateral cyclic output is generated for certain amounts of forward-aft cyclic input. The stepped mixing linkage includes two supporting links and a floating link pivotally coupled between the two supporting links. The ratio of the lengths of the two supporting links to the length of the floating link is small, thereby generating a selected lateral sinusoidal output, a selected rotation of the sinusoidal output, and a selected ramped output in response to each forward-aft pilot input command. | ||||||
| 191 | Techniques for controlling transfer of torque using detent members responsive to radial force | US10996171 | 2004-11-23 | US07367891B2 | 2008-05-06 | Kwan-Ho Bae |
| A torque limiting device includes a base configured to reside in a fixed position relative to a drive unit, an input shaft assembly configured to receive a torque load from the drive unit, and an output shaft assembly which is capable of rotating about an axis. The torque limiting device further includes detent members disposed adjacent to the input shaft assembly and the output shaft assembly. The detent members are configured to transition the torque limiting device between (i) a drive state in which the input shaft assembly rotates the output shaft assembly about the axis and (ii) a tripped state in which the input shaft assembly does not rotate the output shaft assembly about the axis depending on forces provided to the detent members, by the input shaft assembly, in respective radial directions away from the axis and toward the base. | ||||||
| 192 | Disengage device for aircraft control | US11038725 | 2005-01-19 | US07316373B2 | 2008-01-08 | Takashi Nagayama; Hiroshi Yoneda; Kenshi Miyata |
| A disengage device in an aircraft, which prevents a driving force of a drive unit from transmitting to a control surface, having:a first rod having one end portion connected to the drive unit, the other end portion, and a hollow portion formed to have a predetermined length and open at the other end portion;a branch pipe which is connected to a side wall of the first rod and communicates with the hollow portion;a second rod having one end portion connected to the push-pull rod, the other end portion, and a recess portion formed in a part of a side wall of a portion which extends a predetermined length from the other end portion to the one end portion side and is inserted in the hollow portion; andan engaging member arranged to be freely movable in the branch pipe, which is engagable with the recess portion. | ||||||
| 193 | Linkage and sensor assembly | US11059718 | 2005-02-16 | US07296487B2 | 2007-11-20 | Edward Mayer; Nicholas Helmut Hesse; Arthur Degenholtz |
| A link and sensor assembly includes a first rod, a second rod received telescopingly within the first rod, a force sensor attached between the rods and a motion limiter. The force sensor has a longitudinal range of motion. The limiter limits longitudinal motion between the rods to the range of motion and limits angular motion between the rods. | ||||||
| 194 | Aircraft high-lift system with overload protection | US10788160 | 2004-02-26 | US07195209B2 | 2007-03-27 | Bernd Schievelbusch |
| The invention concerns an aircraft high-lift system with a drive system, components for transmitting the drive energy over the entire wing span to drive stations of individual segments of landing flap/slat flap systems, and with overload protection. According to the invention, the overload protection consists of electrical load sensors positioned at the drive-energy in-take points of the individual power trains on the flaps. | ||||||
| 195 | Device with remote motor for controlling an aerodynamic control surface of a missile | US11176303 | 2005-07-08 | US20060289695A1 | 2006-12-28 | Georges Bois; Rinaldo Rossi |
| An aircraft comprising at least one aerodynamic control surface (26) controlled using a remote motor (4), through a transmission comprising a linear device (7) rigid in torsion but flexible in bending and in tension and compression, to absorb thermomechanical deformations. This transmission comprises small clearances, good flexibility, does not require any additional support and makes favourable use of a reduction gear (9) located near the control surface (26) rather than near the motor (4). | ||||||
| 196 | System for safely disabling and re-enabling the manual vehicle control input of aircraft and other vehicles | US10913729 | 2004-08-09 | US20060041345A1 | 2006-02-23 | Darrell Metcalf |
| The invention pertains to the field of security for aircraft and other vehicles, and more particularly to systems for preventing the hijacking, commandeering or suicide bombing of aircraft, or other vehicle(s). Aircraft system and vehicle system embodiments of the invention have one or more kinds of automating computers capable of safely controlling either an aircraft or vehicle in one or more types of common, well-proven, or yet-to-be-developed, computer-automated modes. The system provides mechanical control linkage disabling means interfaced with control signal receiving means responsive to wireless, or hard-wired, transmitted security-related control signal(s). Control linkage disabling means are located within a series of physical control linkage components of a vehicle at a point subsequent to where manual control input is initiated and prior to where computer automated control is provided. The disabling means renders ineffectual the mechanical control needed for one or more humans to control or direct a vehicle. | ||||||
| 197 | Aircraft wing | US11198641 | 2005-08-05 | US20060038088A1 | 2006-02-23 | Robert Dodson |
| An aircraft wing (12) comprising a fixed wing (14), a slat (16) movable relative to the fixed wing (14) between a retracted position and an extended position, electrical lines (36, 38) extending between the fixed wing (14) and an electrical system (34) on the slat (16), and a linkage (40). The linkage (40) houses the electrical lines (36, 38) and is convertible between a retracted condition when the slat (16) is in the retracted position and an extended condition when the slat (16) is in the extended position. | ||||||
| 198 | System for setting the span load distribution of a wing | US11206313 | 2005-08-17 | US20060038086A1 | 2006-02-23 | Daniel Reckzeh |
| A system for setting a span load distribution of a wing of an aircraft with a base flap system comprises at least one inboard flap element and one outboard flap element, which elements in the direction of the span are arranged on the trailing edge of the wing, and can be positioned relative to the span direction of the wing. The flap elements are not mechanically coupled with each other and are controlled independently of each other for the purpose of setting the span load distribution. | ||||||
| 199 | Flap interconnection system for aircraft | US11187334 | 2005-07-22 | US20060022093A1 | 2006-02-02 | Bernd Poppe; Kurt Auhagen |
| Described is an interconnection system, in particular for flaps which are located side-by-side, on an aircraft wing, for example landing flaps or high-lift flaps. The interconnection system is in particular characterised in that it comprises a correspondingly guided compensating profile for a gap between the flaps, which gap changes when the flaps are moved. Preferably, the interconnection system is combined with a failsafe device for adjacent flaps in the form of a longitudinally adjustable interconnection strut which is connected to the adjacent flaps by way of corresponding load introduction fittings. The interconnection system is in particular suitable for large aircraft in which the gap between adjacent flaps, due to the relatively large lateral movement of the flaps during retraction and extension, becomes relatively wide, and the forces acting on the flaps are relatively great. | ||||||
| 200 | Disengage device | US11038725 | 2005-01-19 | US20050178926A1 | 2005-08-18 | Takashi Nagayama; Hiroshi Yoneda; Kenshi Miyata |
| A disengage device in an aircraft, which prevents a driving force of a drive unit from transmitting to a control surface, having: a first rod having one end portion connected to the drive unit, the other end portion, and a hollow portion formed to have a predetermined length and open at the other end portion; a branch pipe which is connected to a side wall of the first rod and communicates with the hollow portion; a second rod having one end portion connected to the push-pull rod, the other end portion, and a recess portion formed in a part of a side wall of a portion which extends a predetermined length from the other end portion to the one end portion side and is inserted in the hollow portion; and an engaging member arranged to be freely movable in the branch pipe, which is engagable with the recess portion. | ||||||
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