| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | MULTI-FUSEABLE SHAFT | EP90900454.0 | 1989-11-17 | EP0457763A1 | 1991-11-27 | FULTON, James, W.; WALBORN, Gregory, D. |
| Arbre de torsion à coupe-circuits (32) pour un système de commande de la surface de conduite de vol d'un aéronef (10). L'arbre de torsion à coupe-circuits (32) comprend un tube de cisaillement (50) qui présente des propriétés élastiques de grande résistance pendant le fonctionnement normal jusqu'à un certain niveau de force de torsion. Par la suite, un autre arbre de torsion (52), dont les propriétés plastiques sont moins grandes, peut transmettre un couple pendant une durée de déflexion limitée. | ||||||
| 142 | HIGH LIFT SYSTEM FOR AN AIRCRAFT | PCT/EP2012056350 | 2012-04-05 | WO2012136804A2 | 2012-10-11 | CHRISTMANN MARKUS; GIEBELER CHRISTOPH; RECKSIEK MARTIN; DORR BJOERN |
| The present invention provides a high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor. | ||||||
| 143 | MECHANICAL FLIGHT CONTROL AUXILIARY POWER ASSIST SYSTEM | PCT/US2005036714 | 2005-10-13 | WO2006137908A3 | 2007-04-26 | SHULTZ PETER M; FENNY CARLOS A; WALKER TODD; ARJUNAN SAM |
| A mechanical flight control system for a rotary-wing aircraft is disclosed. The flight control system comprises an upstream portion (113), a downstream portion (1 15) and a booster means (117) for connecting the upstream portion (113) to the downstream portion (115). The booster means (117) may comprise dual concentric value actuators and/or a variety of system load limiting features. | ||||||
| 144 | COMPACT ACTUATOR | PCT/US2005020054 | 2005-06-07 | WO2005124192B1 | 2006-08-17 | LARSON LOWELL V |
| The present invention provides an improved compact actuator (20) for selectively moving an object (27) relative to a support (21). The improved actuator includes a gear reduction unit (24) mounted on the support. The gear reduction unit has a ring gear (25) adapted to be rotated about a longitudinal axis (x-x), and a pinion (26) mounted on the ring gear. All bearings for the output member are physically located within the gear reduction unit. The output member is coupled to the object such that rotation of the output member will move the object relative to the support. | ||||||
| 145 | Linkage and sensor assembly | PCT/US2005005071 | 2005-02-17 | WO2005079460A8 | 2006-06-01 | MAYER EDWARD; HESSE NICHOLAS HELMUT; DEGENHOLTZ ARTHUR |
| A link and sensor (assembly10) includes a first rod (12), a second rod (14) received telescopingly within the first rod, a force sensor attached between the rods and a motion limiter. The force sensor (22) 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. | ||||||
| 146 | CHANGEABLE WING PROFILE | PCT/DE2014000348 | 2014-07-10 | WO2015007259A3 | 2015-03-19 | HASLACH HORST |
| The invention relates to changes to wing profiles. In order to provide an aerodynamic structure that can be adapted and changed in many ways in terms of the wing profile, an aerodynamic structure (10) for a wing device or control surface device of an aircraft according to the invention has a supporting structure (12) and an outer skin (14). The supporting structure has a stationary spar (16) in the longitudinal direction, which spar extends from a root region to an outer end region. The supporting structure also has a plurality of adaptive framework segments (18) in the transverse direction, which each consist of a plurality of triangular compartments (20), which are arranged next to each other and are formed by control elements (22) of stationary length and control elements (24) of adjustable length. The framework segments are connected to the stationary spar. At least some of the triangular compartments have one of the adjustable control elements, at least on one side, such that the framework segments are adjustable in shape. The outer skin is fastened to the framework segments. An outer contour (26) of the aerodynamic structure can be changed at least in the transverse direction by adjusting the shape of the frameworks. | ||||||
| 147 | TRANSLATING CONDUIT APPARATUS FOR AN AIRPLANE OR EQUIPMENT | PCT/US2006024367 | 2006-06-22 | WO2008054345A2 | 2008-05-08 | AMOROSI STEPHEN R; BAUCUM JEFFREY P; CHIN DENNIS |
| An apparatus for an airplane or other equipment is provided. The apparatus may comprise a multitude of connected arms which are adapted to rotate relative to one another. One end of the apparatus may be connected to a fixed wing, while another end of the apparatus may be connected to a moving slat. The apparatus may be used to deliver conduit from the fixed wing to the moving slat. The conduit may comprise one or more of an electrical de-icing wire, a sensor wire, a control wire, a fiber optic line, and a pneumatic line. Within an internal pathway of the apparatus, the conduit may be freely looped around a curved surface at least one-half turn and fixedly secured to a linear surface. Methods of use and assembly are also provided. | ||||||
| 148 | ACTUATOR AND FLAP ARRANGEMENT WITH ACTUATOR INTERCONNECTION | PCT/US2007069257 | 2007-05-18 | WO2007140147A2 | 2007-12-06 | DEGENHOLTZ ARTHUR; MAYER EDWARD; VAGHELA NARESH P |
| An actuator and flap arrangement includes a flap, movable relative to a support structure, and two actuators. Each actuator has a portion fixed relative to the support structure, a portion movable relative to the fixed portion and connected to the flap for transfer of motor force to flap upon movement of the movable portion, and a motor for moving the movable portion relative to the fixed portion. The arrangement also includes a device interconnecting the two actuators for transferring motive force between the two actuators. | ||||||
| 149 | AIRFOIL FOR AN AIRCRAFT AND AIRCRAFT | PCT/EP2006070273 | 2006-12-29 | WO2007074173A3 | 2007-08-16 | POHL ULRICH |
| The invention relates to the monitoring of the landing flaps on an airfoil (2) for an aircraft (1), and to an aircraft (1) having such an airfoil (2). The airfoil (2) has a wingbox (3), a support (5) which is mounted relative to the wingbox (3) such that it can rotate with respect to a flap rotation axis (7), a flap (4) which is attached to the support (5) and rotates with respect to the flap rotation axis (7) during rotation of the support (5) relative to the wingbox (3), a movement mechanism (8) which is coupled to the support (5) in order to set an angle position of the flap (4) with respect to the wingbox (3) and a measurement apparatus (18) for detection of the angle position of the flap (4). The measurement apparatus (18) has a rotation sensor (19), which is arranged on the support (5), and a four-element coupling transmission (22, 24, 26, 27) which couples the rotation sensor (19) to the movement mechanism (8). | ||||||
| 150 | TORQUE LIMITTING DEVICE USING DETENT MEMBERS RESPONSIVE TO RADIAL FORCE | PCT/US2005042598 | 2005-11-22 | WO2006093543A3 | 2006-10-19 | BAE KWAN-HO |
| 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. | ||||||
| 151 | LINKAGE AND SENSOR ASSEMBLY | PCT/US2005005071 | 2005-02-17 | WO2005079460A3 | 2006-03-02 | MAYER EDWARD; HESSE NICHOLAS HELMUT; DEGENHOLTZ ARTHUR |
| A link and sensor (assembly10) includes a first rod (12), a second rod (14) received telescopingly within the first rod, a force sensor attached between the rods and a motion limiter. The force sensor (22) 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. | ||||||
| 152 | Rudder control method and system for an aircraft | US14966170 | 2015-12-11 | US10054955B2 | 2018-08-21 | Patrice Brot; Sylvain Devineau |
| The system includes a rudder bar configured to be able to be actuated by a pilot of the aircraft, a unit for automatically detecting a position value corresponding to a position of the rudder bar, an auxiliary unit for generating a trim value, a computation unit configured to generate a control value as a function of the position value of the rudder bar and of the trim value. The computation unit is configured to generate the control value according to a nonlinear kinematic relative to the position value of the rudder bar. | ||||||
| 153 | FIBRE-OPTIC COMMUNICATION SYSTEM AND AN AIRCRAFT | US15819319 | 2017-11-21 | US20180145751A1 | 2018-05-24 | Kayvon BARAD; Alessio CIPULLO |
| A fibre-optic communication system for an aircraft including: a light source operable to generate light; a transceiver in optical communication with the light source, the transceiver including a control input and a reflector; an optical fibre in optical communication with the transceiver; and a light detector in optical communication with the optical fibre. The transceiver is operable to generate an amplitude modulated light signal by selectively reflecting the light received from the light source into the optical fibre using the reflector according to information received at the control input. The light detector is operable to receive the amplitude modulated light signal from the optical fibre and to detect an amplitude of the amplitude modulated light signal to extract the information. | ||||||
| 154 | Aerial vehicle with deployable components | US15388396 | 2016-12-22 | US09902488B2 | 2018-02-27 | Nicholas Robert Alley; Joshua Lemming Steele; Jesse Owen Williams; Daniel Kuehme; Jonathan Caleb Phillips |
| An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. | ||||||
| 155 | Aerial vehicle with deployable components | US15388478 | 2016-12-22 | US09902487B2 | 2018-02-27 | Nicholas Robert Alley; Joshua Lemming Steele; Jesse Owen Williams; Daniel Kuehme; Jonathan Caleb Phillips |
| An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. | ||||||
| 156 | Kite configuration and flight strategy for flight in high wind speeds | US14584536 | 2014-12-29 | US09896201B2 | 2018-02-20 | Damon Vander Lind |
| An airborne tethered flight system including a base unit, a tether having a first end attached to the base unit and a second end attached to a kite, wherein the kite comprises a main wing, a tail wing, and a tail boom attached to said main wing on a first end, said tail boom coupled to said tail wing on a second end, a plurality of vertical pylons attached to the main wing, said pylons comprising vertical airfoils adapted to provide lift, turbine driven generators mounted on the vertical airfoils attached to the main wing, and an additional vertical airfoil extending between the tail boom and tail wing. | ||||||
| 157 | Load sensing system | US14666955 | 2015-03-24 | US09891122B2 | 2018-02-13 | Laurent Schwartz; Arnaud de la Chevasnerie |
| An actuator including a pair of load sensors arranged in the load path through the actuator. The load sensors are antagonistically preloaded and their outputs electrically connected to a processor for calculating a load in the actuator from the difference in loads measured by the respective load sensors. | ||||||
| 158 | Controlled flight of a multicopter experiencing a failure affecting an effector | US14893874 | 2014-06-05 | US09856016B2 | 2018-01-02 | Mark W. Mueller; Sergei Lupashin; Raffaello D'Andrea; Markus Waibel |
| According to a first aspect of the invention, there is provided a method for operating a multicopter experiencing a failure during flight, the multicopter comprising a body, and at least four effectors attached to the body, each operable to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing said failure. The method may comprise the step of identifying a failure wherein the failure affects the torque and/or thrust force produced by an effector, and in response to identifying a failure carrying out the following steps, (1) computing an estimate of the orientation of a primary axis of said body with respect to a predefined reference frame, wherein said primary axis is an axis about which said multicopter rotates when flying, (2) computing an estimate of the angular velocity of said multicopter, (3) controlling one or more of said at least four effectors based on said estimate of the orientation of the primary axis of said body with respect to said predefined reference frame and said estimate of the angular velocity of the multicopter. The step of controlling one or more of said at least four effectors may be performed such that (a) said one or more effectors collectively produce a torque along said primary axis and a torque perpendicular to said primary axis, wherein (i) the torque along said primary axis causes said multicopter to rotate about said primary axis, and (ii) the torque perpendicular to said primary axis causes said multicopter to move such that the orientation of said primary axis converges to a target orientation with respect to said predefined reference frame, and (b) such that said one or more effectors individually produce a thrust force along said primary axis. | ||||||
| 159 | AUTOMATIC FLIGHT CONTROL ACTUATOR SYSTEMS | US15171733 | 2016-06-02 | US20170350491A1 | 2017-12-07 | Dean Wilkens |
| An automatic actuator system is provided. The automatic actuator system includes an input linkage that receives an input and an output linkage adapted to control a flight surface actuator. The automatic actuator system includes a first strain wave gear having a first circular spline coupled to the input linkage and a first flex spline rotatably coupled to the first circular spline. The automatic actuator system includes a second strain wave gear having a second circular spline coupled to the first flex spline. The second strain wave gear includes a second flex spline, and the second flex spline is coupled to the output linkage such that at least a portion of the input from the input linkage is transferred to the output linkage via the first strain wave gear and the second strain wave gear. | ||||||
| 160 | AERIAL VEHICLE WITH DEPLOYABLE COMPONENTS | US15388396 | 2016-12-22 | US20170291685A1 | 2017-10-12 | Nicholas Robert Alley; Joshua Lemming Steele; Jesse Owen Williams; Daniel Kuehme; Jonathan Caleb Phillips |
| An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. | ||||||
QQ群二维码
意见反馈
意见反馈