| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Aircraft System for Reduced Observer Visibility | US15870467 | 2018-01-12 | US20180222570A1 | 2018-08-09 | 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. | ||||||
| 62 | Gyroscopic orbiter with vertical takeoff and vertical landing capabilities | US15184186 | 2016-06-16 | US10017278B2 | 2018-07-10 | 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. | ||||||
| 63 | FAIRING FOR AN AIRCRAFT | US15801536 | 2017-11-02 | US20180118328A1 | 2018-05-03 | Wolfgang EILKEN; Memis TIRYAKI; Klaus-Peter SANMANN; Ghasem MOUSSAVI |
| A fairing for an aircraft is disclosed in which the fairing comprises a first fairing portion configured to be fixedly attached to a first structural component and having a first edge; a second fairing portion configured to be fixedly attached to a second structural component and having a second edge, wherein the first edge and the second edge define an interface configured to enable relative movement between the first fairing portion and the second fairing portion. | ||||||
| 64 | AIRCRAFT EXHIBITING INDEPENDENT ELEVATORS | US15618294 | 2017-06-09 | US20170361917A1 | 2017-12-21 | Frédéric Sauvinet |
| An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced. | ||||||
| 65 | STRUCTURAL COMPONENT OF AIRCRAFT WING BODY AND AIRCRAFT INCLUDING THE STRUCTURAL COMPONENT | US15601473 | 2017-05-22 | US20170341774A1 | 2017-11-30 | Mei DING |
| The present disclosure relates to a structural component of an aircraft wing body and an aircraft including the structural component. According to an aspect of the present disclosure, a structural component of an aircraft wing body is provided. The structural component includes a body part and a profile. The body part includes an edge portion formed by end portions of a first skin and a second skin of the body part superposed together. The profile is attached to the edge portion. The profile has an outer profile conforming to an outer profile of the body part such that the structural component, as a whole, exhibits an aerodynamic outer profile after the profile is attached to the edge portion. The profile is attached to the edge portion via a plurality of separate intermediate members or by contacting the edge portion. | ||||||
| 66 | BODY TAB YAW DEFLECTOR | US15479654 | 2017-04-05 | US20170341730A1 | 2017-11-30 | Kenneth Merle Dorsett |
| In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft. | ||||||
| 67 | Aircraft fuselages | US15361943 | 2016-11-28 | US09828085B2 | 2017-11-28 | 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. | ||||||
| 68 | Clocked thrust reversers | US14440718 | 2013-03-14 | US09663239B2 | 2017-05-30 | 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. | ||||||
| 69 | VORTEX GENERATOR ARRANGEMENT, FLOW CONTROL SYSTEM AND METHOD FOR CONTROLLING A FLOW ON A RUDDER SURFACE | US15274197 | 2016-09-23 | US20170096214A1 | 2017-04-06 | Bruno Stefes; Wolfgang Eilken; Erich Paul |
| A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed. | ||||||
| 70 | Use of auxiliary rudders for yaw control at low speed | US14618072 | 2015-02-10 | US09611037B1 | 2017-04-04 | 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. | ||||||
| 71 | AIRCRAFT FUSELAGES | US15361943 | 2016-11-28 | US20170073061A1 | 2017-03-16 | 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. | ||||||
| 72 | CONTROL SURFACE FOR AN AIRCRAFT | US15223258 | 2016-07-29 | US20170029090A1 | 2017-02-02 | Robert NORTHAM; James CHU |
| The present application relates to a control surface for an aircraft. The control surface has a leading edge, a trailing edge, and a chord-line defined between the leading edge and the trailing edge. A first aerodynamic surface is between the leading and trailing edges and a second surface is between the leading and trailing edges. The leading edge is formed by a nose, the nose having a hinge axis about which the control surface is deflectable. A maximum thickness of the control surface perpendicular to the chord-line between the first aerodynamic surface and the second surface is located aft of the hinge axis. The present application also relates to a control surface for an aircraft having a maximum curvature of the first aerodynamic surface of the control surface located aft of the hinge axis. The present application also relates to an aircraft or part of an aircraft comprising a fixed section and a control surface. | ||||||
| 73 | Modular aircraft system | US15096216 | 2016-04-11 | US09505484B1 | 2016-11-29 | Nasser M. Al-Sabah |
| The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle. | ||||||
| 74 | AIRCRAFT FUSELAGES | US14976988 | 2015-12-21 | US20160107741A1 | 2016-04-21 | 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. | ||||||
| 75 | SYSTEMS AND METHODS COUNTERING AN UNMANNED AIR VEHICLE | US14801479 | 2015-07-16 | US20160023760A1 | 2016-01-28 | Wayne Goodrich |
| Systems and methods for countering an unmanned air vehicle are disclosed. Representative methods include directing an interceptor UAV toward a target UAV, and directing the interceptor UAV back to ground along a controlled flight path, for example, in response to an instruction not to engage with the target UAV, and/or in response to an unsuccessful engagement. Another representative method includes disabling the target UAV by deploying a disabling element (e.g., a net) from the interceptor UAV to contact the target UAV. Representative systems include a target acquisition system, a launch control system, and an engagement system carried by the interceptor UAV. In particular embodiments, the interceptor UAV can have a generally cylindrical fuselage, one or more fins carried by the fuselage, counter-rotating propellers carried by the fuselage, and a disabling system that is configured to disable the target UAV. | ||||||
| 76 | Aircraft fuselages | US13659180 | 2012-10-24 | US09216807B2 | 2015-12-22 | 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. | ||||||
| 77 | LEADING EDGE NOSE STRUCTURE ON THE VERTICAL STABILIZER OF AN AIRCRAFT | US14729632 | 2015-06-03 | US20150360766A1 | 2015-12-17 | Martin Gerber |
| An aircraft with a fuselage, wings, horizontal stabilizers and a vertical stabilizer, wherein on a front portion of the vertical stabilizer an elongated one-piece nose element is mounted which forms lateral air guide surfaces. To the front end of the nose element a perforated metal plate nose member is attached. The front end of the nose element being closed and between this closed front end and the nose member an elongated air channel is formed. | ||||||
| 78 | BOX WING WITH ANGLED GAS TURBINE ENGINE CORES | US14440895 | 2013-03-14 | US20150336655A1 | 2015-11-26 | 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. | ||||||
| 79 | AIRCRAFT WITH FORWARD SWEEPING T-TAIL | US14440753 | 2013-03-14 | US20150298794A1 | 2015-10-22 | 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. | ||||||
| 80 | Aerospace vehicle yaw generating tail section | US13176516 | 2011-07-05 | US08960599B2 | 2015-02-24 | Huw L. Edwards; Stephen M. Husband; Paul Fletcher |
| A tail section for an aerospace vehicle is provided. The tail section comprises a rudder which is movable about an axis to generate a yawing moment on the aerospace vehicle. The tail section further comprises a thruster having, in flow series, an air intake, an electrically powered device for accelerating the air received through the intake, and an air outlet which directs the accelerated air to increase the yawing moment generated by the rudder. | ||||||
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