| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 201 | Attachment for airships. | US1910579375 | 1910-08-29 | US999125A | 1911-07-25 | SADLER GEORGE P N |
| 202 | Flying-machine. | US1910550962 | 1910-03-22 | US998791A | 1911-07-25 | MCKEETH ALLEN L |
| 203 | Flying-machine. | US1910551972 | 1910-03-28 | US983940A | 1911-02-14 | SHAINLINE JOSEPH B |
| 204 | Flying-machine. | US1910545910 | 1910-02-25 | US970974A | 1910-09-20 | TORBRAND PETER ROBERT |
| 205 | Aerial navigation. | US1909482484 | 1909-03-10 | US943120A | 1909-12-14 | MEANS JAMES |
| 206 | Active Dihedral Control System for a Torsionally Flexible Wing | US15706807 | 2017-09-18 | US20180155005A1 | 2018-06-07 | Greg T. Kendall; Derek L. Lisoski; Walter R. Morgan; John A. Griecci |
| A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied. | ||||||
| 207 | Automatically stabilized aerial platform for carrying liquids | US15391908 | 2016-12-28 | US09963222B2 | 2018-05-08 | Piyush Mishra |
| The present application is at least directed to an automatically stabilized aerial platform. The platform includes one or more containers including one or more liquids. The platform also includes one or more sensors coupled to the one or more liquids. The platform also includes one or more flight controllers operatively coupled to the one or more sensors. The flight controllers are configured to automatically adjust flight control elements in real-time to compensate for sensor values indicating sloshing of the one or more liquids beyond a specified limit. The instant application is also directed to a method of automatic real-time stabilization of an aerial platform carrying at least one liquid. | ||||||
| 208 | Vehicle attitude control using jet paddles and/or movable mass | US14322752 | 2014-07-02 | US09919792B2 | 2018-03-20 | Kevin L Zondervan; Jerome K Fuller |
| Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude. | ||||||
| 209 | Systems and methods for controlling rotorcraft external loads | US15085157 | 2016-03-30 | US09879986B2 | 2018-01-30 | Sean S. Carlson; Cauvin Polycarpe; George N. Loussides; Garrett Pitcher |
| A method of determining cable angle includes acquiring image data of a cable and a load coupled to a rotorcraft using three-dimensional (3D) spatial perception system, constructing an image of the cable and load using the image data, and determining the angle of the cable relative to the external load at an interface of the cable and external load based on the image. | ||||||
| 210 | Flight control for an airborne wind turbine | US14137286 | 2013-12-20 | US09429954B2 | 2016-08-30 | Erik Christopher Chubb; Damon Vander Lind; Brian Hachtmann |
| An example method may include receiving data representing an initial position and an initial attitude of an aircraft. The method further includes determining a change to a first attribute and a second attribute of the position or the attitude of the aircraft to achieve a subsequent position and a subsequent attitude. The method also includes determining a priority sequence for changing the first attribute and the second attribute of the position or the attitude of the aircraft based on a first thrust of the actuator to achieve the change to the first attribute and a second thrust of the actuator to achieve the change to the second attribute. The priority sequence is configured to cause changes to the first attribute before causing changes to the second attribute where the actuator is unable to concurrently provide the first thrust and the second thrust. | ||||||
| 211 | Active Dihedral Control System for a Torsionally Flexible Wing | US14838297 | 2015-08-27 | US20160068252A1 | 2016-03-10 | Greg T. Kendall; Derek L. Lisoski; Walter R. Morgan; John A. Griecci |
| A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied. | ||||||
| 212 | Active dihedral control system for a torisionally flexible wing | US12804988 | 2010-08-02 | US09120555B2 | 2015-09-01 | Greg T. Kendall; Derek L. Lisoski; Walter R. Morgan; John A. Griecci |
| A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied. | ||||||
| 213 | Systems and methods for vertical takeoff and/or landing | US13868539 | 2013-04-23 | US09085354B1 | 2015-07-21 | Eric Peeters; William Graham Patrick |
| Systems and methods for vertical takeoff and/or landing are disclosed herein. An aerial vehicle may include a first propulsion unit and a second propulsion each rotatably connected to a body. The aerial vehicle may include a first wing and a second wing each rotatably connected to the body. And the aerial vehicle may include a control system configured to: position the first propulsion unit, the second propulsion unit, the first wing, and the second wing; operate the first propulsion unit and the second propulsion unit; and rotate the first propulsion unit, the second propulsion unit, the first wing, and the second wing. | ||||||
| 214 | Airframe Stabilization Mechanism for Vertical Takeoff and Landing Transport Plane | US14413117 | 2013-07-10 | US20150191243A1 | 2015-07-09 | Hiromichi Fujimoto |
| A vertical takeoff and landing transport plane is characterized in that a structure formed in the top-bottom direction of an airframe penetrates a rear structure of the vertical takeoff and landing transport plane in order to let a tailwind escape, and characterized by comprising, in the rear structure of the vertical takeoff and landing transport plane, a device for generating thrust rearward behind the rear on the top side of the airframe from the bottom of the airframe. | ||||||
| 215 | Fluid-based orientation control system | US14058486 | 2013-10-21 | US08965674B1 | 2015-02-24 | Stephen D. Russell |
| A system includes a fluid reservoir containing a first fluid, a pair of fluidic channels in fluidic connection with the fluid reservoir, a counter-fluid reservoir having a second fluid that is non-miscible with the first fluid, and a pump connected to the fluid reservoir. The pump is configured to pump the first fluid from the fluid reservoir into the pair of fluidic channels. When contained in a vehicle, the system allows for control of the vehicle's orientation. The system may use sensor input to determine when to actuate the pump. Each fluidic channel may have a cross-section that varies along its length. The fluidic channels may be geometrically symmetric about the fluid reservoir. The system may be incorporated into a vehicle to control the vehicle's orientation. | ||||||
| 216 | Method of assisted piloting of a rotary wing aircraft having at least one propulsion propeller, an assisted piloting device, and an aircraft | US13676299 | 2012-11-14 | US08788123B2 | 2014-07-22 | Marc Salesse-Lavergne; Nicholas Queiras; Paul Eglin |
| A device (10) for assisted piloting of an aircraft having a rotary wing with a plurality of second blades (3′) and a propulsion unit with a plurality of first blades (2′). The device includes control means (30, 40) for delivering a movement order (O) for moving in a direction, said device (10) having a processor unit (20) for transforming said order (O) into an acceleration setpoint (C) along said direction, and then for transforming said acceleration setpoint (C) into at least one required longitudinal attitude setpoint (θ*) that is transmitted to a first automatic system (26) for maintaining longitudinal attitude by controlling a longitudinal cyclic pitch of the second blades (3′), and into a first required load factor setpoint (Nx*) in a longitudinal direction that is transmitted to a second automatic system (25) for maintaining load factor by controlling the collective pitch of the first blades. | ||||||
| 217 | Aircraft comprising fairings for correcting its dissymmetry or lateral asymmetry | US13793222 | 2013-03-11 | US20130240667A1 | 2013-09-19 | Cyril Guichot; Fabien Latourelle |
| An aircraft having an asymmetry or a lateral geometric dissymmetry and comprising at least one pair of wings to each of which are fixed at least one fairing, each fairing comprising a surface connected to the lower surface of the wing and extending longitudinally in the direction of a longitudinal axis of the fuselage. The surface of at least one of the fairings has at least one local geometric deformation which is suitable for producing a corrective rolling moment to compensate for the undesirable rolling moment produced by the asymmetry or the lateral dissymmetry of the aircraft. | ||||||
| 218 | STEERING OF VEHICLES THROUGH BOUNDARY LAYER CONTROL | US11909515 | 2006-03-23 | US20090065649A1 | 2009-03-12 | Holger Babinsky; Geoffrey Hatton; Simon McIntosh |
| In aeronautical devices where a fluid such as air flows over a surface (1) to create lift or thrust, improved performance can be obtained by energising a so-called 5 “boundary layer” (10) of the fluid flow close to the surface. This is known to help prevent separation of the fluid flow stream from the surface thereby maximising the lift or thrust achieved. The invention provides a facility (7A) for controlling the mechanisms (7) used for energising the boundary layer so as to selectively increase or decrease the effect 10 in different areas. When this is done for example on different sides of an air vehicle, it provides an effective mechanism for steering the vehicle. | ||||||
| 219 | Aircraft control system | US11732109 | 2007-04-02 | US20080001028A1 | 2008-01-03 | Greg Kendall; Derek Lisoski; Walter Morgan; John Griecci |
| A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied. | ||||||
| 220 | Method and device for checking plane's entry into a dive and anti-dive devices for planes using the same | US11202571 | 2005-08-12 | US20070026757A1 | 2007-02-01 | Yu Tian; Wenyan Jiang |
| The present invention relates to a method of checking model planes entering into a dive and an anti-dive method. Operating model planes necessitates a certain kind of skills. As regards a beginner, plane crashes often occur due to improper operations. The present invention provides a method of checking planes entering into a dive, comprising steps of: installation of a first optical sensor in the upper part of the plane, with its installation angle upwardly intersecting with the forward direction of the plane as α degrees that checks light intensity and outputs a first checked optical signal; installation of a second optical sensor in the bottom part of the plane, with its installation angle downwardly intersecting with the backward direction of the plane as β degrees which checks light intensity and outputs a second checked optical signal; comparison of the first checked optical signal with the second checked optical signal, and when the difference between the light intensity represented by the first checked optical signal and that represented by the second checked optical signal is smaller than a threshold of light intensity differences, a warning signal to the effect that the plane has entered into a dive is sent out. Moreover, an anti-dive method and device for planes are also provided. | ||||||
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