| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Flow Body For An Aircraft For Passive Boundary Layer Suction | US15413836 | 2017-01-24 | US20170217568A1 | 2017-08-03 | Gerd Heller |
| An aircraft flow body includes a flow surface exposed to an airstream during flight, at least one structural component attached to an interior of the flow surface, at least one perforated area having a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings and upstream of the at least one structural component, and at least one suction duct having a first end in communication with the manifold and a second end placed exterior to the flow surface downstream of the structural component. The at least one suction duct includes a suction opening facing away from the first end and adapted for inducing a suction force into the at least one suction duct when the flow surface is exposed to the airstream during flight, thereby inducing a flow of air from through the openings to the suction opening. | ||||||
| 122 | Aircraft with forward sweeping T-tail | US14440753 | 2013-03-14 | US09637218B2 | 2017-05-02 | Gabriel L. Suciu; Jesse M. Chandler |
| An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft portion of the fuselage is angled forward away from the aft portion and out of the discharge of airflow from the thrust reverser. | ||||||
| 123 | Aircraft having an aircraft fuselage and an air sucking fuselage component | US13850353 | 2013-03-26 | US09623959B2 | 2017-04-18 | 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. | ||||||
| 124 | Gyroscopic Orbiter with Vertical Takeoff and Vertical Landing Capabilities | US15184186 | 2016-06-16 | US20170088291A1 | 2017-03-30 | Thomas Norman Hesse |
| A gyroscopic orbiter with vertical takeoff and vertical landing capabilities can transition between different functional modes while in-flight. The orbiter typically includes a fuselage, a front boom, a front propulsion unit, a rear boom, and a rear propulsion unit. The front boom is mounted at two pivot points to a bow of the fuselage by the front boom. The rear boom is mounted at two pivot points to a stern of the fuselage by the rear boom. One functional mode is the vertical takeoff and landing mode, wherein the propulsion units are oriented parallel to each other and are directed upward. Another functional mode is the shuttle mode, wherein the propulsion units are oriented at an angle with each other, and the front propulsion unit is directed forward. Another functional mode is the high speed mode, wherein the propulsion units are oriented collinear with a roll axis of the fuselage. | ||||||
| 125 | AIRCRAFT REAR PORTION COMPRISING A VERTICAL STABILIZER HAVING A BOX-SECTION STRUCTURE INCLUDING A LOWER PORTION ACCOMMODATED IN THE FUSELAGE | US15259585 | 2016-09-08 | US20170066518A1 | 2017-03-09 | Guillaume Gallant; Jose Luis Martinez Munoz |
| To optimize the structure of an aircraft tail section, an aircraft rear section comprises a fuselage section, a tail section, and a vertical stabilizer comprising a box-section structure which comprises a box-section upper part extending on the outside of the tail section, and a box-section lower part housed inside the tail section, such that the tail section is wholly supported by the box-section structure. | ||||||
| 126 | Box wing with angled gas turbine engine cores | US14440895 | 2013-03-14 | US09567062B2 | 2017-02-14 | Jesse M. Chandler; Gabriel L. Suciu |
| An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft includes a box wing extending from the aft portion of the fuselage to a forward portion of the fuselage that is disposed outside of the burst zone. | ||||||
| 127 | Aircraft fuselages | US14976988 | 2015-12-21 | US09505481B2 | 2016-11-29 | 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. | ||||||
| 128 | Bonded and Tailorable Composite Assembly | US15191527 | 2016-06-24 | US20160297512A1 | 2016-10-13 | 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. | ||||||
| 129 | AIRCRAFT REAR STRUCTURE | US15089675 | 2016-04-04 | US20160297510A1 | 2016-10-13 | Diego Folch Cortes; Esteban Martino Gonzalez; Jose Antonio Mariblanca Lopez; Lionel Diochon |
| An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone. | ||||||
| 130 | METHOD FOR MANUFACTURING A NACELLE STRAKE | US14626694 | 2015-02-19 | US20160243806A1 | 2016-08-25 | Juddson Frost |
| A method for manufacturing a strake is provided. The method includes: providing a first thermoplastic laminate panel; providing a second thermoplastic laminate panel; attaching the first thermoplastic laminate panel to the second thermoplastic laminate panel such that at least a portion of the attachment surface of the first thermoplastic laminate panel is attached to the attachment surface of a portion of the second thermoplastic laminate panel, which attached portions form a body of the strake; forming a first flange from a portion of the first thermoplastic laminate panel; and forming a second flange from a portion of the second thermoplastic laminate panel. | ||||||
| 131 | METHODS AND APPARATUS TO CONTROL AIRCRAFT HORIZONTAL STABILIZERS | US14539789 | 2014-11-12 | US20160200419A1 | 2016-07-14 | Jonathan Kyle Moore; Brian Charles Bock; Edward E. Coleman |
| Methods and apparatus to control aircraft horizontal stabilizers are described herein. One described method includes calculating, using a processor, a desired movement of a horizontal stabilizer of an aircraft to counteract a pitching moment of the aircraft, and controlling the horizontal stabilizer based on the desired movement. | ||||||
| 132 | Very low-power actuation devices | US13542635 | 2012-07-05 | US09228815B2 | 2016-01-05 | Jahangir S. Rastegar; Jacques Fischer |
| An actuator including: a housing; a piston movably disposed in the housing, the piston being movable between an extended and retracted position; a plurality of gas generation charges generating a gas in fluid communication with the housing; and an exhaust port for exhausting gas from the cylinder generated by the plurality of gas generation charges; wherein activation of each of the plurality of gas generation charges results in an increase in pressure in the housing causing the piston to move in the housing from the refracted to the extended position. The actuator can further include a return spring for biasing the piston in the retracted position and the plurality of gas generation charges can be disposed in the housing. | ||||||
| 133 | CLOCKED THRUST REVERSERS | US14440718 | 2013-03-14 | US20150298814A1 | 2015-10-22 | Gabriel L. Suciu; Jesse M. Chandler |
| An aircraft includes a fuselage including a propulsion system supported within an aft portion. A thrust reverser is mounted proximate to the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser directs thrust at an angle relative to a vertical plane to reduce interference on control surfaces and reduce generation of underbody lift. | ||||||
| 134 | STABILIZER WITH STRUCTURAL BOX AND SACRIFICIAL SURFACES | US14440995 | 2013-10-17 | US20150284067A1 | 2015-10-08 | Gabriel L. Suciu; Jesse M. Chandler |
| An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at least one primary control surface. The primary control surfaces maintain aircraft controllability in the event that the sacrificial control surface becomes inoperable. | ||||||
| 135 | Supplementary control surface structure for airplanes | US14503345 | 2014-09-30 | US09090325B1 | 2015-07-28 | Ahmad Abdullah Al-Jassem Qanaei |
| A supplementary control surface structure for airplanes is installed atop the fuselage of an airplane to enhance the roll rate of the airplane and thereby assists in reducing bending loads on the wings by enabling a smaller aileron deflection for a given roll rate. The supplementary control surface structure desirably includes a moveable vertically oriented roll control surface member desirably installed in a vertically oriented fin or strake that extends atop the fuselage from the flight deck to the vertically oriented tail fin. The supplementary control surface structure is desirably interconnected with the conventional aileron controls of the airplane in order to operate in concert with the ailerons. The supplementary control surface structure is also adaptable to other roll control systems, such as spoilers and wing warping. | ||||||
| 136 | Use of auxiliary rudders for yaw control at low speed | US13282985 | 2011-10-27 | US08960594B2 | 2015-02-24 | David L. Groen |
| Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | ||||||
| 137 | Aircraft System for Reduced Observer Visibility | US14184542 | 2014-02-19 | US20140312169A1 | 2014-10-23 | Christopher Eugene Fisher; Steven Bradley Chambers; Pavil Belik; Austin Craig Gunder; John Peter Zwaan |
| An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom. | ||||||
| 138 | Device for boundary layer suction and composite component therefor | US13435078 | 2012-03-30 | US08800915B2 | 2014-08-12 | Martin Gerber |
| A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place. | ||||||
| 139 | Strut system for the stabilization of the shell of an aerodynamic aircraft component for a commercial aircraft | US13019612 | 2011-02-02 | US08678315B2 | 2014-03-25 | Bernd Tomschke; Pasquale Basso |
| The invention relates to a strut system for the stabilization of the shell (2) of an aerodynamic aircraft component in a commercial aircraft, comprising a pair of connection supports (4a, 4b) connected on the inside to the shell (2) and opposing each other, between which connection supports (4a, 4b) several struts (5) extend to form a latticework structure (3), which struts (5) in nodal points (6a, 6b) arranged on the ends are non-detachably connected to the connection supports (4a, 4b), wherein the area extension of the latticework structure (3) is aligned in such a manner relative to a middle plane of symmetry (11) that the struts (5), formed with an open symmetrical cross section, as well as the cross section of the connection supports (4a, 4b), are arranged so as to be symmetrical to the aforesaid. | ||||||
| 140 | Framework wing box for a wing | US11990578 | 2006-08-17 | US08602356B2 | 2013-12-10 | Christian Maenz |
| A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework. | ||||||
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