子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Systems and methods for mounting landing gear strain sensors | US12839170 | 2010-07-19 | US08359932B2 | 2013-01-29 | Odd Harald Steen Eriksen; Shuwen Guo; Chuang-Chia Lin; Lawrence Joseph Stang |
| A strain sensor device for measuring loads on aircraft landing gear. This is done by measuring strains in the lower end of the strut, by which we infer the loading in the entire landing gear structure. These strains can be very large (as high as 10,000 microstrain) and can be imposed in numerous random directions and levels. The present invention includes a removable sensor assembly. An electromechanical means is presented that can accommodate large strains, be firmly attached to the strut, and provide good accuracy and resolution. | ||||||
| 102 | Pin bearing arrangement for aircraft landing gear | US12869309 | 2010-08-26 | US08359930B2 | 2013-01-29 | Angel Manuel Gago Tripero; José Luis López Arévalo |
| Pin bearing arrangement (10) for measuring loads in an aircraft landing gear (1), comprising a trailing arm (2), connected to at least one of the aircraft wheels (3), and a shock absorber (4), connected to the aircraft, whereby load (11) is transferred from the trailing arm (2) to the shock absorber (4), the trailing arm (2) being rotatable with respect to the shock absorber (4), the pin bearing arrangement (10) comprising at least one strain measuring element (12) attached to the pin bearing arrangement (10) in predetermined positions, these positions being selected such that the strain measuring element (12) gives at least a minimum detectable signal when the load (11) transferred is over a first threshold value, for any value of the angle (5) adopted by the trailing arm (2) with respect to the shock absorber (4). The invention also refers to a method for providing an indication of the on-ground condition of an aircraft, using a pin bearing arrangement (10) as the one described, and to a method for determining the positioning of the at least one strain measuring element (12) in such a pin bearing arrangement (10). | ||||||
| 103 | Aircraft Landing Gear Including a Fairing | US13509676 | 2010-04-30 | US20120292442A1 | 2012-11-22 | Yann Simonneaux |
| An aircraft landing gear including a fairing (12) arranged to be moveable between first and second configurations, wherein in the first configuration the fairing shields an element of the landing gear from an incident airflow, the fairing being arranged to be in the first configuration when the landing gear is deployed but unloaded, and wherein in the second configuration the fairing exposes the landing gear element to the incident airflow, the fairing being arranged to be in the second configuration when the landing gear is deployed and loaded. | ||||||
| 104 | PANEL MADE OF COMPOSITE MATERIAL | US13508323 | 2010-11-17 | US20120282441A1 | 2012-11-08 | Romain Lefrancois; Georges Filippi; Mathieu Hottin; François Lemoine |
| A panel is made of composite material comprising a skin made of composite material and having two opposite general sides, and first stiffeners extending over one of the sides of the skin. It is characterised in that it comprises additional stiffeners that are arranged on the side of the skin opposite that bearing the first stiffeners, and which extend in a direction distinct from that of the first stiffeners. The skin and the stiffeners arranged on each side are preferably made integral by co-moulding. | ||||||
| 105 | Aircraft noise reduction apparatus | US12153493 | 2008-05-20 | US08302906B2 | 2012-11-06 | Leung Choi Chow; Christopher Neil Wood; Philip Campbell |
| The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear. | ||||||
| 106 | Weight-on-gear sensor | US12640064 | 2009-12-17 | US08226030B2 | 2012-07-24 | James Grant Mast; Charles Eric Covington; Paul Eugene Darden; William L. McKeown |
| A weight-on-gear sensor for use on an aircraft with landing skids having a bracket and a displacement sensor attached to the bracket is disclosed. The bracket has a center member connecting a first end member to a second end member. The center member has a centerline and the end members extend from the centerline of the center member. Mounting members extend along the centerline of the center member to facilitate attachment of the bracket to a cross tube. The displacement sensor connects the first end member to the second end member. The displacement sensor is parallel to, and offset from, the centerline of the center member so that when a bending moment is applied to the center member the first displacement sensor is either elongated or shortened. | ||||||
| 107 | LANDING GEAR AXLE NUT SAFETY SOCKET | US13191241 | 2011-07-26 | US20120167374A1 | 2012-07-05 | Douglas Manke |
| A socket and a method for tightening a nut on an axle are disclosed. The socket includes a socket body having a first end and a second end. The first end of the socket body has a rotatable gear hub. The second end is configured to accommodate the nut. The socket includes a socket body insert fixed substantially within the socket body. The socket also includes a trigger movable between a triggered position and a non-triggered position, wherein the trigger is configured to move to the triggered position when a distance between the axle and nut is different than a predetermined trigger distance. The socket further includes a reset pin operably connected to the trigger to reset the trigger to the non-triggered position when depressed. The socket also includes a reset spring positioned between the reset pin and the gear hub to bias the reset pin towards the second end. | ||||||
| 108 | AERO-ACOUSTIC OPTIMISATION METHOD FOR COMPLEX-SECTION MECHANICAL PARTS AND CORRESPONDING MECHANICAL PART AND LANDING GEAR | US13163895 | 2011-06-20 | US20110309193A1 | 2011-12-22 | Christelle Seror Goguet |
| The invention is intended to reduce the drag caused by a complex-section part in an airflow, for example the landing gear of an aircraft, making it possible to optimise the lift/drag ratio and to reduce the aerodynamic noise by reducing the local noise source combined with a global optimisation of the aeroplane related to the reduction in drag. To do so, the invention provides for the shaping of the complex part, masking its form with a special casing.According to one embodiment, the aero-acoustically optimised complex-section metal mechanical part is fitted with an aerodynamically shaped cover made of several longitudinal parts articulated with hinges to facilitate their installation. This cover is attached to at least two supports placed away from one another along the axis of the part, each support is bolted to the cover and mates with the section of the part. The external face of the cover is cylindrical and its internal face bears against the supports. The cover advantageously has a translucent part beside the walls of a remaining opaque part. Stops are provided on the part to limit the translational movement of the cover. | ||||||
| 109 | PIN BEARING ARRANGEMENT FOR AIRCRAFT LANDING GEAR | US12869309 | 2010-08-26 | US20110303788A1 | 2011-12-15 | Angel Manuel GAGO TRIPERO; Jos+e,acu e+ee Luis L+e,acu o+ee pez Ar+e,acu e+ee valo |
| Pin bearing arrangement (10) for measuring loads in an aircraft landing gear (1), comprising a trailing arm (2), connected to at least one of the aircraft wheels (3), and a shock absorber (4), connected to the aircraft, whereby load (11) is transferred from the trailing arm (2) to the shock absorber (4), the trailing arm (2) being rotatable with respect to the shock absorber (4), the pin bearing arrangement (10) comprising at least one strain measuring element (12) attached to the pin bearing arrangement (10) in predetermined positions, these positions being selected such that the strain measuring element (12) gives at least a minimum detectable signal when the load (11) transferred is over a first threshold value, for any value of the angle (5) adopted by the trailing arm (2) with respect to the shock absorber (4). The invention also refers to a method for providing an indication of the on-ground condition of an aircraft, using a pin bearing arrangement (10) as the one described, and to a method for determining the positioning of the at least one strain measuring element (12) in such a pin bearing arrangement (10). | ||||||
| 110 | Landing gear strut extender | US11717904 | 2007-03-13 | US20100133379A1 | 2010-06-03 | Garrett H. DeVlieg |
| A mechanism for increasing the ride height of aircraft by selectively increasing the hydraulic fluid content within landing gear struts. By increasing the hydraulic fluid volume within a strut, the strut is lengthened without adversely affecting its spring rate while the ability to withdraw fluid from a strut maintains the ability of the strut to absorb the impact of landing. The mechanism is readily retrofitable to existing landing gear systems to accommodate more efficient under the wing intake designs and to reduce the likelihood of FOD during taxiing at minimal cost and with very a minimal increase in the aircraft weight. | ||||||
| 111 | Weight-on-Gear Sensor | US12640064 | 2009-12-17 | US20100095788A1 | 2010-04-22 | James Grant Mast; Charles Eric Covington; Paul Eugene Darden; William L. McKeown |
| A weight-on-gear sensor for use on an aircraft with landing skids having a bracket and a displacement sensor attached to the bracket is disclosed. The bracket has a center member connecting a first end member to a second end member. The center member has a centerline and the end members extend from the centerline of the center member. Mounting members extend along the centerline of the center member to facilitate attachment of the bracket to a cross tube. The displacement sensor connects the first end member to the second end member. The displacement sensor is parallel to, and offset from, the centerline of the center member so that when a bending moment is applied to the center member the first displacement sensor is either elongated or shortened. | ||||||
| 112 | Weight-on-gear sensor | US11659748 | 2004-08-10 | US07637459B2 | 2009-12-29 | James Grant Mast; Charles Eric Covington; Paul Eugene Darden; William L. McKeown |
| A weight-on-gear sensor for use on an aircraft with landing skids having a bracket and a displacement sensor attached to the bracket is disclosed. The bracket has a center member connecting a first end member to a second end member. The center member has a centerline and the end members extend from the centerline of the center member. Mounting members extend along the centerline of the center member to facilitate attachment of the bracket to a cross tube. The displacement sensor connects the first end member to the second end member. The displacement sensor is parallel to, and offset from, the centerline of the center member so that when a bending moment is applied to the center member the first displacement sensor is either elongated or shortened. | ||||||
| 113 | System and method for determining aircraft hard landing events from inertial and aircraft reference frame data | US11423529 | 2006-06-12 | US07589645B2 | 2009-09-15 | R. Kyle Schmidt |
| This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation. | ||||||
| 114 | Motor for driving aircraft, located adjacent to undercarriage wheel | US12291257 | 2008-11-06 | US20090114765A1 | 2009-05-07 | Isaiah Watas Cox; Hans Juergen Walitzki; Jonathan Sidney Edelson |
| The invention disclosed is a self-propelled aircraft undercarriage for driving an aircraft on the ground, comprising: an axle; a strut supporting said axle; at least one wheel rotatably mounted on said axle; and drive means for driving said at least one wheel; characterized in that said drive means is disk shaped and is external to said wheel. In one embodiment of the invention, said drive means is mounted on said axle between said strut and said wheel. In a second embodiment, said drive means is mounted on said axle, on the side of said wheel furthest from said strut. | ||||||
| 115 | Method and apparatus suitable for measuring the displacement or load on an aircraft component | US10569668 | 2004-08-26 | US07506549B2 | 2009-03-24 | Alessandro Riccardo Britannico Giazotto |
| The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system. The system includes a control unit a controllable microwave emitter of electromagnetic radiation and a microwave detector comprising a plurality of antennae. When the aircraft component is subjected to a load relative movement of the emitter and detector is caused. The detector generates in response to microwave radiation received from the focused beam of radiation emitted by the emitter a signal that is received by a signal processor of the control unit. The signal received by the control unit depends on the relative positions of the emitter and detector. The control unit is arranged to provide an output signal representative of the load sustained by the aircraft component. The system may be used to control braking in dependence on the output signal so as to maximize braking efficiency without overloading the landing gear leg. | ||||||
| 116 | PROCESS FOR LANDING A TAILLESS AIRCRAFT | US11165018 | 2005-06-23 | US20070145185A1 | 2007-06-28 | Walter Clark |
| The invention is a process for landing a tailless or flying wing type aircraft having a nose and wings that produce lift. The process includes the step of allowing the nose of the aircraft to stay lower upon touchdown such that lift from the wings is reduced. | ||||||
| 117 | System And Method For Determining Aircraft Hard Landing Events From Inertial And Aircraft Reference Frame Data | US11423529 | 2006-06-12 | US20070008187A1 | 2007-01-11 | R. Schmidt |
| This invention allows for the precise determination of an aircraft's landing conditions and whether an aircraft has experienced a hard landing that exceeds the allowable design loads of the aircraft's landing gear. The system comprises a computer that measures signals from an inertial measurement unit (IMU) at high data rates (e.g. 100 Hz) and also records signals from the aircraft avionics data bus. The computer compares the output from the inertial measurement unit's accelerometers against at least one predetermined threshold parameter to determine whether the aircraft's three dimensional landing deceleration is safely within the design allowances or other regulatory limitations, or whether the landing event needs further investigation. | ||||||
| 118 | Landing arrangement for an aircraft | US11028535 | 2005-01-05 | US07143975B2 | 2006-12-05 | Kenneth F Udall |
| A landing arrangement for an aircraft comprises an aircraft support assembly (22) to support the aircraft (10) when the aircraft is on the ground. The aircraft support assembly (2) is movable between a first ground engaging condition (22b) in which the aircraft nose (24) is spaced above the ground by a first distance (X) and a second ground engaging condition (22C) in which the aircraft nose (24) is spaced above the ground by a second distance (Y). The second distance (Y) is less than the first distance (X). | ||||||
| 119 | Retractable landing gear for aircraft | US10880466 | 2004-07-01 | US07007891B2 | 2006-03-07 | Dominique Ducos; Jean-François Locufier |
| Retractable landing gear for an aircraft, the landing gear being of the type that is raised vertically, and comprising a plurality of independent legs, each leg comprising a structural part rigidly secured to a structure of the aircraft, a pivoting rocker beam supporting a pair of wheels, and a shock absorber. In accordance with the invention, the shock absorber of each leg is extended by a positioning portion enabling the total length of the extended shock absorber to be shortened in order to collapse the leg, and each leg further comprises a positioning actuator connected in hinged manner to the extended shock absorber and arranged to lengthen relative to a normal use position in order to lengthen the corresponding leg. This makes it possible to shorten and/or lengthen one or another of the legs of the landing gear while the aircraft is stationary or taxiing slowly. | ||||||
| 120 | Aeroplane provided with noise-reducing means, as well as a landing gear and blowing means | US10621362 | 2003-07-18 | US20040104301A1 | 2004-06-03 | Jasper Jan Wickerhoff; Tjaard Sijpkes |
| An aeroplane provided with noise-reducing means for reducing the noise level that is produced during a flight, in particular during the landing stage of the aeroplane, due to the presence of the landing gear of the aeroplane, said sound-reducing means comprising deflection means for deflecting an air flow away from the landing gear or at least from components thereof, characterized in that the deflection means comprise blowing means provided with a blowing element having at least one blowing nozzle for creating an air screen at the front side of the landing gear, or at least components thereof, from said at least one blowing nozzle. | ||||||
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