| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | COUPLING | EP15804200.2 | 2015-11-25 | EP3224137A1 | 2017-10-04 | INGLETON, Martyn |
| A coupling comprising a brake plate (70); a first friction pad (64) operable to be selectively biased against the brake plate (70). In a first mode of operation the first friction pad (64) is biased against the brake plate (70) by a first force. In a second mode of operation the first friction pad (64) is biased against the brake plate (70) by a second force. The second force is substantially greater than the first force. | ||||||
| 22 | Procédé et dispositif pour l'optimisation du braquage des volets déporteurs d'un aéronef en vol | EP05290161.8 | 2005-01-25 | EP1568605B1 | 2006-06-28 | Seve, Philippe |
| 23 | Procédé et dispositif pour l'optimisation du braquage des volets déporteurs d'un aéronef en vol | EP05290161.8 | 2005-01-25 | EP1568605A1 | 2005-08-31 | Seve, Philippe |
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| 24 | Collective control system for a helicopter | EP87630165.6 | 1987-09-01 | EP0261056A3 | 1989-08-30 | Wright, Stuart Cammett; Stiles, Lorren, Jr.; Adams, Don Luis |
Pilot workload is reduced in a helicopter having a force-type, multi-axis sidearm control stick by providing a displacement-type control stick for collective blade pitch control. Either stick may be used by the pilot. When the force-type stick is employed, a trim system causes the displacement-stick to track a collective position command signal which is provided to the blade actuators. Changeover of control to the displacement-type control stick is accomplished either with a switch, or by moving the collective-type control stick. The signals associated with each control stick are alternately faded in and out to assure a smooth transition when collective control is switched over from one to the other. |
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| 25 | RECONFIGURABLE UNMANNED AIRCRAFT SYSTEM | EP15864636 | 2015-12-01 | EP3227181A4 | 2018-05-16 | CHAN ALISTAIR K; CHEATHAM JESSE R III; CHIN HON WAH; DUNCAN WILLIAM DAVID; HYDE RODERICK A; ISHIKAWA MURIEL Y; KARE JORDIN T; PAN TONY S; PETROSKI ROBERT C; TEGREENE CLARENCE T; TUCKERMAN DAVID B; WEAVER THOMAS ALLAN; WOOD LOWELL L JR |
| A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base. A method of configuring an aircraft having a set of rotors on a mission to carry a payload comprises the steps of determining properties of the payload including at least mass properties, determining the manner in which the payload will be coupled to the aircraft, determining configuration for each of the rotors in the set of rotors at least partially in consideration of the properties of the payload, and positioning the set of rotors in the configuration for the aircraft to perform the mission. | ||||||
| 26 | VORTEX GENERATORS RESPONSIVE TO AMBIENT CONDITIONS | EP15185618.4 | 2015-09-17 | EP2998219A1 | 2016-03-23 | BORDOLEY, Anat; TILLOTSON, Brian J; WANG, Michael Chih-Huan; CLINGMAN, Dan J |
A deployable vortex generator 100/700 attached to a lifting surface 20 includes a vane moveable relative to the lifting surface. The vane 106/406 moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity.
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| 27 | PROCEDE ET DISPOSITIF POUR LA CONDUITE D'UN AERONEF ROULANT SUR LE SOL | EP06764770.1 | 2006-06-12 | EP1890935B1 | 2009-07-29 | BELLOUARD, Rémi; MULLER, Jean |
| The inventive method consists in forming a difference (D1) between left and right braking commands (FG, FD), in converting said difference (D1) into an additional control command (D2) for a rudder (16) and for a steerable nose gear (4) and in applying said additional control command (D2) to said rudder (16) and steerable nose gear (4) according to both following conditions: the difference (D1) is greater than a first threshold and the combined control command transmitted to the rudder and steerable nose gear (4) by a rudder bar is less than a second threshold. | ||||||
| 28 | Display system for a vehicle | EP04012067.7 | 2004-05-21 | EP1491444B1 | 2006-08-16 | Stickels, Keith David |
| 29 | Collective control system for a helicopter | EP87630165.6 | 1987-09-01 | EP0261056B1 | 1993-07-28 | Wright, Stuart Cammett; Stiles, Lorren, Jr.; Adams, Don Luis |
| 30 | Collective control system for a helicopter | EP87630165.6 | 1987-09-01 | EP0261056A2 | 1988-03-23 | Wright, Stuart Cammett; Stiles, Lorren, Jr.; Adams, Don Luis |
Pilot workload is reduced in a helicopter having a force-type, multi-axis sidearm control stick by providing a displacement-type control stick for collective blade pitch control. Either stick may be used by the pilot. When the force-type stick is employed, a trim system causes the displacement-stick to track a collective position command signal which is provided to the blade actuators. Changeover of control to the displacement-type control stick is accomplished either with a switch, or by moving the collective-type control stick. The signals associated with each control stick are alternately faded in and out to assure a smooth transition when collective control is switched over from one to the other. |
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| 31 | VORTEX GENERATORS RESPONSIVE TO AMBIENT CONDITIONS | US15783742 | 2017-10-13 | US20180118332A1 | 2018-05-03 | Anat BORDOLEY; Brian J. TILLOTSON; Michael Chih-Huan WANG; Dan J. CLINGMAN |
| A deployable vortex generator attached to a lifting surface includes a vane moveable relative to the lifting surface. The vane moves from a deployed position to a retracted position in response to a change in ambient conditions. In the deployed position, the vane acts on the air flow to create vortices. In the retracted position, the vane is closely aligned with the free stream velocity. | ||||||
| 32 | Air vehicle control system and method | US13911160 | 2013-06-06 | US09037315B2 | 2015-05-19 | Richard E Hindman |
| A control actuation system (CAS) for positioning control effectors of an air vehicle, for steering the air vehicle, includes application of a control allocation matrix to measured positions of the control effectors or their actuators, as part of a feedback mechanism. The output from the control allocation matrix is used as an input for one or more controllers, the output of which is passed through an inverse control allocation matrix, to produce signals that are sent to control actuators to position the control effectors. The controller may use different gains for different of its inputs, for example applying a lower gain for a brake signal than for one or more of a pitch signal, a roll signal, and a yaw signal. The control actuation may make for a control system that is able to better withstand impaired performance or non-performance of some the control effectors. | ||||||
| 33 | Display System | US14148816 | 2014-01-07 | US20140365038A1 | 2014-12-11 | Keith David STICKELS |
| A display system for displaying a layout of controls in a simulator including at least one of an information display, a switch such as a toggle or push-button switch, and a monitoring device such as an indicator, or a gauge, for a vehicle, the display system including a touch sensitive screen which is generally transparent over a significant portion of its area, and a plurality of projectors which project onto a back of the screen, images of the vehicle controls, the projectors each being operatively connected to a computer controller which responds to the front of the screen being touched where a depicted control is displayed, to change the display in a manner to mimic the result of a corresponding actual vehicle control being operated. | ||||||
| 34 | AIR VEHICLE CONTROL SYSTEM AND METHOD | US13911160 | 2013-06-06 | US20140365035A1 | 2014-12-11 | Richard E Hindman |
| A control actuation system (CAS) for positioning control effectors of an air vehicle, for steering the air vehicle, includes application of a control allocation matrix to measured positions of the control effectors or their actuators, as part of a feedback mechanism. The output from the control allocation matrix is used as an input for one or more controllers, the output of which is passed through an inverse control allocation matrix, to produce signals that are sent to control actuators to position the control effectors. The controller may use different gains for different of its inputs, for example applying a lower gain for a brake signal than for one or more of a pitch signal, a roll signal, and a yaw signal. The control actuation may make for a control system that is able to better withstand impaired performance or non-performance of some the control effectors. | ||||||
| 35 | DISPLAY SYSTEM | US13606801 | 2012-09-07 | US20130211629A1 | 2013-08-15 | Keith David STICKELS |
| A display system for displaying a layout of controls in a simulator including at least one of an information display, a switch such as a toggle or push-button switch, and a monitoring device such as an indicator, or a gauge, for a vehicle, the display system including a touch sensitive screen which is generally transparent over a significant portion of its area, and a plurality of projectors which project onto a back of the screen, images of the vehicle controls, the projectors each being operatively connected to a computer controller which responds to the front of the screen being touched where a depicted control is displayed, to change the display in a manner to mimic the result of a corresponding actual vehicle control being operated. | ||||||
| 36 | Method and device for driving an aircraft during the ground run thereof | US11917304 | 2006-06-12 | US07967247B2 | 2011-06-28 | Rémi Bellouard; Jean Muller |
| The method of the invention includes forming a difference between left and right braking commands, by converting the difference into an additional control command for rudder and for a steerable nose gear, and applying the additional control command to the rudder and steerable nose gear according to both of the following conditions: the difference is greater than a first threshold and the combined control command transmitted to the rudder and steerable nose gear by a rudder bar is less than a second threshold. | ||||||
| 37 | Method and Device for Driving an Aircraft During the Ground Run Thereof | US11917304 | 2006-06-12 | US20080197239A1 | 2008-08-21 | Rémi Bellouard; Jean Muller |
| The inventive method consists in forming a difference (D1) between left and right braking commands (FG, FD), in converting said difference (D1) into an additional control command (D2) for rudder (16) and for a steerable nose gear (4) and in applying said additional control command (D2) to said rudder (16) and steerable nose gear (4) according to both following conditions: the difference (D1) is greater than a first threshold and the combined control command transmitted to the rudder and steerable nose gear (4) by a rudder bar is less than a second threshold. | ||||||
| 38 | Modulating vernier flap control system | US866144 | 1977-12-30 | US4154415A | 1979-05-15 | Charles V. Harris; George A. Schlanert |
| A slat and modulatable flap control system for an aircraft having slats in the leading edge of the wing and having flaps in the trailing edge of the wing. A detent pin on a control handle, and any one of four detent slots on a detent crank, can be engaged to selectively, and automatically, set the flaps and the slats (because of the cooperative action of other constituent components of the control system) in optimum positional relationship for takeoff/"go-around," cruising, approach, and landing of aircraft. The control system is ideally suited for aircraft used in "short takeoff-and-landing" situations. | ||||||
| 39 | Ratio select mechanism | US830185 | 1977-09-02 | US4132126A | 1979-01-02 | David C. Hussey |
| A ratio select mechanism including a supporting structure, first and second rotary input members mounted on the supporting structure, and a connecting lever extending between the rotary input members. An output member is coupled to the connecting lever. The opposite ends of the connecting lever are mounted for movement on the rotary input members, respectively, along radially extending paths. By adjusting the relative radial positions of the end portions of the connecting lever, the authority which each of the rotary input members has over the output member can be adjusted. | ||||||
| 40 | Control stick transducer | US3676818D | 1971-05-10 | US3676818A | 1972-07-11 | OLIVER KENNETH L |
| A transducer for monitoring forces applied to an aircraft control stick includes a spring flexure which acts as a primary restraint to loads applied to the control stick. The spring flexure is secured to the transducer housing and disposed in a horizontal plane. The control stick handgrip is supported above the spring flexure by means of a vertical member passing through a central hub of the spring flexure so that the flexure provides a resilient mounting responsive to forces applied to the handgrip in any horizontal direction. A counterbalance suspended from the same hub of the flexure cancels the effect of any acceleration forces parallel to the spring flexure that may be induced in the mass of the handgrip and its mounting. Cantilevered load beams are arranged to deflect in response to loads applied to the handgrip in excess of an adjustable threshold value. Strain gauges are used to measure the deflection of the load beams and thus provide electrical output signals indicative of the amount of command force applied to the handgrip. Stop members limit the deflection of the spring flexure to values suitable for use with the strain gauges.
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