| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 381 | Aerial system utilizing a tethered uni-rotor network of satellite vehicles | US16895361 | 2020-06-08 | US20200361603A1 | 2020-11-19 | Justin M. Selfridge |
| A tethered uni-rotor network of satellite vehicles combines fixed-wing and rotorcraft designs. A central hub with multiple tethers to satellite vehicles radiates outward in a hub-and-spoke arrangement. Satellites have lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The system operates in a persistent state of rotation, driven by satellite propulsion units. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite vehicle and the central hub. As the system rotates, centrifugal forces pull each satellite vehicle outwards, which keeps each tether taught. The tethers are attached at innermost portions of each lifting surface; the energy storage mass is located at the outermost portion; the tension alleviates bending moment common to fixed-wing aircraft, reducing the weight within the structural members, utilize higher aspect ratio wings to reduce induced drag, and thin-thickness high-camber airfoil profiles achieve higher lift-to-drag ratios yield a more aerodynamically efficient aircraft. | ||||||
| 382 | Actuator of an aircraft with an energy-absorbing limit stop with a destructible and detachable bearing surface | US15367286 | 2016-12-02 | US10837530B2 | 2020-11-17 | Nicolas Tilloy; Olivier Brucelle |
| An actuator of an aircraft includes at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20). Each destructible portion of each destructible bearing surface is mounted to be removable with respect to the stop as to be able to be replaced. | ||||||
| 383 | No-back device with energy-dispersing springs | US15480856 | 2017-04-06 | US10655692B2 | 2020-05-19 | Daniel Trybula |
| A no-back device for resisting feedback torque from an actuator. The no-back device comprises: a flange arranged to receive torque via a shaft; a ratchet assembly comprising a ratchet wheel arranged parallel to the flange; and a braking assembly comprising a resistance wheel, which is sandwiched between the flange and the ratchet wheel, and a braking device, which acts on the resistance wheel to generate a resistive angular force reacting against torque exerted on the resistance wheel. The braking device comprises a follower arranged to roll, under bias from a spring in the braking device, on a cam surface extending around a circumferential perimeter of the resistance wheel. Radial displacement of the follower energizes the spring to generate resistive angular force. | ||||||
| 384 | DUCT SUPPORT | US15994518 | 2018-05-31 | US20190368636A1 | 2019-12-05 | Brent Scannell; Thomas Mast; Jon Damon Bennett; Joshua Allan Edler; Jean Pierre Paradis; Keith C. Pedersen |
| One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion. | ||||||
| 385 | Runback control | US15205446 | 2016-07-08 | US10252807B2 | 2019-04-09 | Tommy M. Wilson, Jr. |
| An ice protection system includes an aircraft surface and a gutter defined in the aircraft surface between raised rails. The gutter includes a mouth that narrows into a trailing portion of the gutter. The mouth is configured to channel water runback rivulets into the trailing portion of the gutter. The gutter can be a first gutter of a plurality of side by side gutters, each including a respective mouth narrowing into a respective trailing portion, wherein the gutters are separated from one another by respective rails. | ||||||
| 386 | Aerial system utilizing a tethered uni-rotor network of satellite vehicles. | US15430475 | 2017-02-11 | US20180229838A1 | 2018-08-16 | Justin Selfridge |
| A tethered uni-rotor network of satellite vehicles, is a novel aerial system which combines the best features of both fixed-wing and rotorcraft design methodologies, while minimizing their respective deficiencies. It is made up of a central hub with multiple tethers, where each tether arm radiates outward and attaches to a satellite vehicle; each having lifting airfoil surfaces, stabilizers, control surfaces, fuselages, and propulsion systems. The entire system operates in a state of rotation, which is driven by the propulsion units on each satellite. As the system rotates, centrifugal forces pull the satellite vehicles outward, which maintain tension on the tether arms. As the satellite vehicles move through space, the airfoils generate lift which supports each satellite and a distributed portion of the weight of the central hub. | ||||||
| 387 | Device for protecting the front spar structure of a central casing of an aircraft wing and at least one piece of equipment located in said wing | US14417406 | 2013-06-20 | US09573672B2 | 2017-02-21 | Francis Dazet |
| A device for protecting a front spar structure of a central casing -of an aircraft wing and at least one item of equipment situated in the wing, comprising: a shielding surface extending in front of the front spar of the central casing, from a surface of an intersection between the wing and the fuselage delimited by the root of the wing, transversely to the surface of intersection, to a first rib of the central casing partially surrounding at least one item of equipment; and means -for fixing the shielding surface to the central casing producing an isostatic link. | ||||||
| 388 | Component having a box structure for an airplane airfoil | US14361453 | 2011-11-30 | US09434466B2 | 2016-09-06 | Jun Li |
| The present invention relates to a panel, especially for a component having a box structure in an airplane airfoil, comprising a surface shaped body and grid-like reinforcement bars protruding from the body on one side of the body, and the body and the grid-like reinforcement bars are integral molded. Since the body and the grid-like reinforcement bars of the panel are integral molded, no additional connecting process is required, so that the disconnection phenomenon as happened between the skin and the stiffener or stringer of the prior art would not occur, and the assembly complexity can be decreased. | ||||||
| 389 | Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface | US14086424 | 2013-11-21 | US09381991B2 | 2016-07-05 | Enrique Guinaldo Fernandez; Francisco Cruz Dominguez; Francisco Javier Honorato Ruiz; Paula Más Más; Iker Vélez De Mendizábal Alonso; Carlos Garcia Nieto |
| An aircraft lifting surface with a monolithic main supporting structure of a composite material including an upper skin having at least a part of the upper aerodynamic profile of the leading edge and/or of the trailing edge, a lower skin, a front spar, a rear spar, and leading edge ribs and/or a trailing edge ribs. The main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. | ||||||
| 390 | AIRCRAFT REAR STRUCTURE | US14983468 | 2015-12-29 | US20160185439A1 | 2016-06-30 | Esteban Martino Gonzalez; Diego Folch Cortes; Pablo Goya Abaurrea; Sandra Linares Mendoza |
| An aircraft rear structure that comprises a rear pressure bulkhead, and a lifting surface located at both sides of the fuselage of the aircraft. The lifting surface comprises spars extending in the longitudinal direction of the lifting surface. The pressure bulkhead is aligned with one of the spars of the lifting surface. | ||||||
| 391 | Method and apparatus for fabricating large scale integrated airfoils | US13324254 | 2011-12-13 | US09017510B2 | 2015-04-28 | Martin Wayne Hansen |
| An airfoil is fabricated by assembling cured skins with spars having cured spar webs and uncured spar chords. The skins are bonded to the spars by curing the spar chords. | ||||||
| 392 | Inflatable airfoil system having reduced radar and infrared observability | US12633272 | 2009-12-08 | US08727280B1 | 2014-05-20 | Kevin Reed Lutke; Aaron Jonathan Kutzmann |
| A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section. | ||||||
| 393 | Wing load alleviation structure | US12139363 | 2008-06-13 | US08720822B2 | 2014-05-13 | Thomas Vaneck; Robert Parks |
| A wing load alleviation structure for use on an aircraft, comprising a front spar, wherein the front spar includes a plurality of alternating rigid spar structures and inflatable spar structures; and a rear spar, wherein the rear spar includes a plurality of alternating rigid spar structures and pivot joints, such that when a load is applied to the front and rear spars, deflection of each of the front and rear spars continues at a first rate until a critical load is reached, and then as the loading increases, deflection of each of the front and rear spars continues at a second rate. | ||||||
| 394 | PITCHING STABILIZATION MEANS AND A ROTARY WING AIRCRAFT INCLUDING SUCH MEANS | US13890385 | 2013-05-09 | US20130313355A1 | 2013-11-28 | Jean-Loup Gatti; Remy-Elian Arnaud |
| A pitching stabilization means (10) having at least one stationary stabilization surface (20) extending in a thickness direction from a bottom face (21) to a top face (22) and in a transverse direction from a leading edge (23) towards a trailing edge (24). The stabilization surface (20) has at least one slot (30) passing through said thickness of the stabilization surface (20) from said top face (22) to said bottom face (21), said slot (30) being arranged within the stabilization surface (20) between said leading edge (23) and said trailing edge (24) so as to allow a flow of air coming from a rotor to pass from said top face (22) towards said bottom face (21). | ||||||
| 395 | Structural dynamic stability for an aircraft | US13323471 | 2011-12-12 | US08376270B2 | 2013-02-19 | John Baker |
| 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. | ||||||
| 396 | Method and apparatus for hurricane surveillance from the eye | US11937053 | 2007-11-08 | US08210467B2 | 2012-07-03 | Wesley H. Hubbell; Victor G. Nastasi |
| Methods and apparatus to provide an aerial vehicle having an eyewall sensor to enable the aerial vehicle to stay within the eye of a hurricane and transmit weather information to a remote location. In one embodiment, the aerial vehicle is an unmanned aerial vehicle (UAV) launched into the eye of the hurricane. | ||||||
| 397 | OPTIMIZATION OF STRUCTURES SUBJECTED TO HOT GAS STREAMS | US13091202 | 2011-04-21 | US20120153083A1 | 2012-06-21 | José Javier Almendros Gómez; Yolanda De Gregorio Hurtado |
| Optimisation of structures subjected to hot gas streams. The invention refers to a fairing (10) for aircraft horizontal stabilizer (3) comprising a front part (11) and a rear part (12), the front part (11) covering a limited extent of the fairing (10) surface, which is the part of the fairing (10) receiving hot air stream (6) coming from the aircraft engines (4), this front part (11) being made of an anti-erosion material, the rear part (12) covering the rest of the surface of the fairing (10), this rear part (12) being made of a material resisting the aerodynamic loads existing on the fairing (10). The invention also refers to an aircraft comprising a horizontal stabilizer (3) with a fairing (10) such as the one described. | ||||||
| 398 | Method and apparatus for welding of polymer composite components | US11534397 | 2006-09-22 | US07921893B2 | 2011-04-12 | Andrew Beehag; Kenneth Douglas Horton; Bruce Cartwright |
| A method and apparatus is disclosed for joining of composites with thermoplastic surfaces. The process includes the location of the said components within a load bearing frame, and bringing the thermoplastic surfaces to be joined into contact. Pressure application devices, in the form of fluid filled bladders, are also located within the frame, and are located such that pressure is applied evenly to said thermoplastic surfaces. Where components have a high level of curve or twist, form blocks that have the approximate shape of the component surface are located between the frame and bladders. Pressure and heat are applied to the joint area, and heat removed while the joint area is maintained under some pressure. A feature of the present invention is the option of using opposing pressure application devices, reducing the need for substantial tooling in order to maintain component location accuracy. A distinct advantage of this invention is the flexibility to join curved or twisted components, or complete the welding of closed assemblies such as wing boxes. | ||||||
| 399 | System and method for deployment and actuation | US11942099 | 2007-11-19 | US07906749B2 | 2011-03-15 | Erik A. Fjerstad |
| A mechanical deployment and actuation system may comprise a rotation module, a pinion module, a rack module, and a bevel module. The rotation module may be configured to couple to a housing and rotate about the principal axis of the rotation module relative to the housing. The pinion module may be configured to couple to the rotation module and selectively rotate about the principal axis of the pinion module relative to the rotation module. The rack module may be configured to dynamically couple to the pinion module and translate along the principal axis of the rack module in response to rotation of the pinion module. The bevel module may be configured to couple to the rotation module and selectively rotate the rotation module, wherein rotation of the rotation module rotates about the principal axis of the rotation module, the rack module, and the pinion module. | ||||||
| 400 | Aircraft stabilizer system and methods of using the same | US12152661 | 2008-05-14 | US20090008498A1 | 2009-01-08 | Robert J. Desroche |
| An aircraft can include a tail section and a stabilizing system coupled to the tail section. The stabilizing system has a vertical stabilizer and at least one strake that cooperate to generate forces that compensate for a reaction torque generated by a main lifting rotor that produces lifting forces when the aircraft is in flight. Methods for improving aircraft performance include installing the at least one strake and retrofitting of a vertical stabilizer to increase thrust forces produced by a tail rotor. | ||||||
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