| 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 | Vertical takeoff and landing unmanned aerial vehicle | US15132107 | 2016-04-18 | US09694906B1 | 2017-07-04 | Shereef Aly Sadek |
| The vertical takeoff and landing unmanned aerial vehicle includes a pair of selectively rotatable ducted fans and a selectively rotatable thrust vectoring nozzle providing vertical takeoff and landing for an unmanned aerial vehicle or a similar type of aircraft. A pair of fixed forward-swept wings are mounted on a rear portion of a fuselage, and a pair of canards are mounted on a top end of a forward portion of the fuselage. The pair of ducted fans are respectively mounted on free ends of the pair of canards, and are selectively rotatable about an axis parallel to a pitch axis of the fuselage. An engine is mounted in the rear portion of the fuselage, and a thrust vectoring nozzle is mounted on the rear portion of the fuselage for directing thrust exhaust from the engine. The thrust vectoring nozzle is selectively rotatable about an axis parallel to the pitch axis. | ||||||
| 182 | A ROTORCRAFT TAIL BOOM, AND A ROTORCRAFT | US15318536 | 2015-06-04 | US20170121010A1 | 2017-05-04 | Debbie LEUSINK; David ALFANO |
| A tail boom having a structure and a protuberance, the protuberance being secure with the structure. In each section of the tail boom, the protuberance extends in elevation over an extension height (Hext) and it extends laterally over an extension thickness (EPext), the extension height (Hext) lying in the range 0.05 times the maximum thickness (EPmax) of the structure, included, to 0.5 times the maximum thickness (EPmax), included, of the section, the extension thickness (EPext) lying in the range 0 to 0.4 times the maximum thickness (EPmax), included, of the section. | ||||||
| 183 | Method of inspecting impacts observed in fan casings | US14007269 | 2012-03-15 | US09494486B2 | 2016-11-15 | Julien Tran; Richard Lavignotte |
| A method for inspecting impacts present on an internal face of a fan casing, the method including: spotting a first impact present on the internal face of the fan casing; delimiting an inspection area containing the first impact; spotting the various impacts present in the delimited inspection area, the various spotted impacts forming a set of impacts to be considered; measuring, for each impact that is to be considered, the depth of length of the impact; for each impact to be considered, determining a harmfulness value, using at least one chart relating the depth and length of each impact to be considered to a level of harmfulness; determining, for the inspection area containing the first impact, a total harmfulness value by adding together the harmfulness level determined for each impact to be considered. | ||||||
| 184 | HAND-LAUNCHED, SOLAR-POWERED AIRCRAFT | US14474221 | 2014-09-01 | US20160257417A1 | 2016-09-08 | Timothy J. CURLEY; Gordon Paul BRADLEY |
| Embodiments of a hand-launched solar-powered aircraft are disclosed. In addition, embodiments of kits are disclosed for the construction of a hand-launched solar-powered aircraft. Further, embodiments of methods of making a hand-launched aircraft are disclosed. In some embodiments, the hand-launched aircraft is solar-powered. Still further, embodiments of an educational kit for a hand-launched, solar-powered aircraft are disclosed. In various embodiments, the educational kit comprises educational material on one or more science and technology learning topics, which educational material is relevant to and supplemented by the assembly and/or operation of the aircraft. The education material can relate to, for example, one or more of flying techniques, aeronautics, renewable energy, electronics, mechanical engineering, and/or climatology. | ||||||
| 185 | AIRFRAME-INTEGRATED PROPELLER-DRIVEN PROPULSION SYSTEMS | US14631423 | 2015-02-25 | US20160244150A1 | 2016-08-25 | Helio HIRANO; Luis Gustavo TRAPP |
| Propeller-driven craft (e.g., aircraft) are provided with at least one propulsion system having at least one engine and at least one aerial tractor propeller which generates a propeller propwash airflow when driven by the engine. At least one airfoil is disposed in the propeller propwash airflow of the at least one aerial tractor propeller. The airfoil is contoured and oriented relative to a swirl rotation angle (ω) of the propeller propwash airflow in order to induce a forward force component on the craft in response to the propeller propwash airflow over the at least one airfoil, thus improving the craft's performance and/or reducing fuel consumption. | ||||||
| 186 | Bonded and tailorable composite assembly | US14098131 | 2013-12-05 | US09415858B2 | 2016-08-16 | Eugene A. Dan-Jumbo |
| 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. | ||||||
| 187 | Aircraft comprising a device for influencing the directional stability of the aircraft, and a method for influencing the directional stability of the aircraft | US13255246 | 2010-03-17 | US09315255B2 | 2016-04-19 | Carsten Weber; Markus Fischer; Arnaud Namer |
| An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps. | ||||||
| 188 | Rudder system for an aircraft | US13891345 | 2013-05-10 | US09284039B2 | 2016-03-15 | Christian Maenz |
| A rudder system for an aircraft includes a center box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the center 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 center 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. | ||||||
| 189 | Apparatus and methods to operate laminar flow control doors | US14036992 | 2013-09-25 | US09272773B2 | 2016-03-01 | Rick A. Biedscheid |
| Apparatus and methods to operate laminar flow control system doors are described. One described example apparatus includes an outboard structure of an aircraft, a first door assembly on a first side of the outboard structure having a first door defining a first opening and a second door assembly on a second side of the outboard structure having a second door defining a second opening. The example apparatus also includes a perforated surface proximate a leading edge of the outboard structure and an actuator disposed in the aircraft. The actuator drives first and second linkages that couple the first and second doors to the actuator. The first and second linkages are to operate the first and second doors, respectively, in an open mode in which the first and second openings create an airflow path between the perforated surface and the first and second openings. | ||||||
| 190 | Bonded and Tailorable Composite Assembly | US14098131 | 2013-12-05 | US20160046361A1 | 2016-02-18 | Eugene A. Dan-Jumbo |
| 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. | ||||||
| 191 | Active flow control on a vertical stabilizer and rudder | US12903720 | 2010-10-13 | US09090326B2 | 2015-07-28 | Edward A. Whalen; Mark I. Goldhammer |
| 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. | ||||||
| 192 | FLOW BODY, METHOD FOR MANUFACTURING A FLOW BODY AND AIRCRAFT HAVING SUCH A FLOW BODY | US14574876 | 2014-12-18 | US20150183513A1 | 2015-07-02 | Martin GERBER |
| An flow body comprises a curved suction skin having a first perforation, a leading edge and two skin sections extending therefrom, wherein each skin section has an outer end facing away from the leading edge, an interior suction duct having a second perforation and extending through an inside of the curved suction skin in a distance from the leading edge, and two sidewall members, connected to the outer ends, wherein the sidewall members are made of a composite material. The suction skin comprises a profiled contour shape, which determines a pressure distribution over at least one of the two skin sections when air flows over the curved suction skin, wherein the pressure distribution comprises a stagnation point, a suction peak and a subsequent local pressure maximum downstream of the suction peak, wherein the first perforation extends from a stagnation point on the suction skin to the local pressure maximum. | ||||||
| 193 | SURVEILLANCE SYSTEM | US14370178 | 2012-12-05 | US20150142210A1 | 2015-05-21 | Clyde Warsop; Andrew Julian Press; Alan Geraint Davies |
| The invention relates to a launched aerial surveillance vehicle, more specifically to a grenade or under-slung grenade launcher (UGL) aerial surveillance vehicle, a surveillance system and methods of providing rapid aerial surveillance.The vehicle once deployed is capable of autonomous flight paths, with basic inputs to change the circular flight paths, so as to build up surveillance for an area of interest. The vehicle comprises at least on optical sensor, which may be IR or visible range, to survey the area of interest, and feed the images back to at least one remote user. | ||||||
| 194 | APPARATUS AND METHODS TO OPERATE LAMINAR FLOW CONTROL DOORS | US14036992 | 2013-09-25 | US20150083866A1 | 2015-03-26 | Rick A. Biedscheid |
| Apparatus and methods to operate laminar flow control system doors with improved reliability and serviceability are described herein. One described example apparatus includes a fin of an aircraft, a door assembly on a first side of the fin having a first door defining a first opening and second door defining a second opening. The example apparatus also includes a perforated surface proximate a leading edge of the fin and an actuator disposed in the aircraft. The actuator drives a linkage that couples the door to the actuator. The linkage is to operate the door in a first open mode in which the first opening faces in a first direction to create a suction airflow path between the perforated surface and the first opening, and a second open mode in which the second opening faces in a second direction to create a purge airflow path between the second opening and the perforated surface. | ||||||
| 195 | Rotorcraft empennage mounting system | US13605951 | 2012-09-06 | US08944366B2 | 2015-02-03 | Jacob Johannes van der Westhuizen |
| 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. A bulkhead is positioned rearwardly from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof. | ||||||
| 196 | Tail capable of improving anti-bird strike performance of aircraft | US13630654 | 2012-09-28 | US08746619B2 | 2014-06-10 | Yulong Li; Jun Liu; Tao Suo; Zhongbin Tang; Jun Lv; Liangdao Zhou; Guangrong Zhu; Hao Cong; Zhengli Zhang |
| The present invention relates to a tail for improving anti-bird strike performance of an aircraft. A leading edge reinforcement having a shape of an isosceles triangle is located inside a tail leading edge. The leading edge reinforcement is spanwisely fixed in sections between respective spans formed by the wing rib inside the tail leading edge along the tail of the aircraft. An apex angle of the leading edge reinforcement is the same as an apex angle or arc transition of the tail leading edge skin. The leading edge reinforcement is fixedly connected with the small front beam by a leading edge reinforcement fixed surface. The present invention additionally installs a leading edge reinforcement in the original tail of the aircraft. | ||||||
| 197 | AIRCRAFT FUSELAGES | US13659180 | 2012-10-24 | US20140110528A1 | 2014-04-24 | Bruce Raymond Detert |
| 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. | ||||||
| 198 | Airplane with a tailcoat tail assembly and rear engine | US13255720 | 2010-03-12 | US08651414B2 | 2014-02-18 | Olivier Cazals; Jaime Genty De La Sagne |
| An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage. | ||||||
| 199 | AIRCRAFT HAVING AN AIRCRAFT FUSELAGE AND AN AIR SUCKING FUSELAGE COMPONENT | US13850353 | 2013-03-26 | US20130270390A1 | 2013-10-17 | Géza Schrauf; Hubert Stuke |
| An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices. | ||||||
| 200 | Aircraft with at least two rudder units in a non central arrangement | US12913466 | 2010-10-27 | US08439302B2 | 2013-05-14 | Malte Schwarze; Andreas Westenberger |
| 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. | ||||||
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