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 | Dual tire wheel and brake assembly | US54854966 | 1966-05-09 | US3403875A | 1968-10-01 | FELIX HARTMAN FRANK |
| 102 | Aircraft undercarriages | US15469561 | 1961-11-24 | US3163381A | 1964-12-29 | GEORG PINSKER WERNER JOSEPH |
| 103 | Resilient fairing strip for use in connection with resilient landing gears of aircraft and the like | US2089260 | 1960-04-08 | US3075730A | 1963-01-29 | HALSTEAD JOHN S |
| 104 | Control-augmenting landing gear | US67605657 | 1957-08-05 | US3042345A | 1962-07-03 | HOLLAND JR RAYMOND PRUNTY |
| 105 | Retractable buoyant supporting means for vehicles | US69243557 | 1957-10-25 | US3004737A | 1961-10-17 | BOYLE JAMES F; SUMMER JAMES R; FRAEBEL ROBERT J; LEHBERGER RAYMOND G |
| 106 | Landing gear for airplanes | US63155445 | 1945-11-29 | US2526711A | 1950-10-24 | WILFRED THOMAS |
| 107 | Resilient strut | US69640833 | 1933-11-02 | US2196089A | 1940-04-02 | WALLACE JOHN F |
| 108 | Shock absorber | US5972836 | 1936-01-18 | US2196068A | 1940-04-02 | GREVE LOUIS W |
| 109 | Airplane | US45255630 | 1930-05-15 | US1887738A | 1932-11-15 | SMITH HARRY G |
| 110 | Aircraft-wheel housing | US31415619 | 1919-07-29 | US1446531A | 1923-02-27 | WILLIAMS JR JOHN M |
| 111 | Airplane | US32977519 | 1919-10-10 | US1443812A | 1923-01-30 | CURRAN JOHN J |
| 112 | Aeroplane-undercarriage | US28962519 | 1919-04-12 | US1340483A | 1920-05-18 | LEONIDAS GUILLEMET FRANCOIS |
| 113 | METHOD OF USING A DEVICE CAPABLE OF CONTROLLED FLIGHT | PCT/EP2015060128 | 2015-05-07 | WO2015169931A2 | 2015-11-12 | KOVAC MIRKO; ALHINAI TALIB MUHAMMAD TALIB |
| There is provided a method of using a device capable of controlled flight in a surrounding environment, the device comprising: lifting means for providing lift to the device; object-retaining means for holding an object to be affixed to a target site; and a dispensing assembly for dispensing an adhesive, wherein the method comprises: controlling the lifting means so as to controllably fly the device in the surrounding environment; and using the device to affix an object held by the object-retaining means to a target site in the surrounding environment by dispensing an adhesive from the dispensing assembly. Thus, an aerial device, for example a robotic device, may be used to fly to a desired location and affix an object at the desired location, by dispensing, ejecting or otherwise applying an adhesive. | ||||||
| 114 | ROTATING SEAL FOR ANTI-STICTION OF HYDRAULIC STRUTS | PCT/US2006012011 | 2006-03-30 | WO2006105424A3 | 2007-11-22 | STOCKWELL DANIEL; GONIODSKY IGAR |
| An onboard system for use in measuring, computing and displaying the weight and center-of-gravity for aircraft, while keeping aircraft movement to a minimum. Pressure sensors are mounted in relation to each of the landing gear struts. A motor and rotating seal are configured into each strut and are activated by a computer/controller, while landing gear strut pressures are monitored in the determination of strut stiction. The computer/controller calculates the stiction of each landing gear strut and compensates for the pressure distortions caused by landing gear strut stiction. Additional features include reducing strut stiction, measuring landing gear strut fluid levels, monitoring landing gear strut health, weight adjustments for external ice and de-icing fluids, weight adjustments for wind, monitoring aircraft landing gear strut movement. | ||||||
| 115 | MAGNETIC MEASUREMENT TARGET | US15887840 | 2018-02-02 | US20180224302A1 | 2018-08-09 | Philippe Henrion; Olivier Collet |
| A magnetic measurement target is configured to be positioned inside a vehicle axle and to cooperate with at least two magnetic movement sensors to measure deformation of the axle. The magnetic measurement target includes a body with a fastener end for fastening to one end of the axle and a main portion. The main portion includes a slot formed in an axial direction to separate two longitudinal portions of the body. Each longitudinal portion of the body presents a target surface for which movement can be measured by a magnetic movement sensor. | ||||||
| 116 | SYSTEM AND METHOD FOR SIMPLIFIED AIRCRAFT BRAKE DISTANCE ESTIMATION | US15852913 | 2017-12-22 | US20180208165A1 | 2018-07-26 | Andrew Brett Slatkin |
| A braking system and method utilizing a simplified estimate of a distance between two locations on the earth based on spherical geometry. A braking system utilizing the aforementioned simplified estimate does not require computationally intensive calculations and is more efficient and better equipped to handle real-time generation of distance estimates for braking needs and variable conditions. In the present invention, geodesics evaluations are not used; rather, a modified Haversine formula that simplifies computations is used, including a one-time computation of the cosine of latitude coordinate. | ||||||
| 117 | HYBRID METALLIC/COMPOSITE JOINT WITH ENHANCED STRENGTH | US15286062 | 2016-10-05 | US20180094663A1 | 2018-04-05 | Mark R. Gurvich; Rony Giovanni Ganis; Virginia H. Faustino |
| A metallic/composite joint may comprise a composite member extending along a centerline axis and a metallic member. The composite member may comprise a cylinder having a flared end. An outer surface of the flared end may be oriented at a first angle relative to the centerline axis. An inner surface of the metallic member may be oriented at a second angle relative to the centerline axis. The inner surface of the metallic member and the outer surface of the composite member may be separated by a first gap at a first location and may be separated by a second gap at a second location.In various embodiments, the composite member may comprise a cylinder having an angled end, an inner surface of the angled end oriented at the first angle and an insert having an outer surface oriented at the second angle. | ||||||
| 118 | Oval Lifting-Body Airplane | US15268059 | 2016-09-16 | US20180079505A1 | 2018-03-22 | Laszlo Molnar |
| An oval lifting-body airplane may generate lift without wings. It may be propelled by a pivoting propulsion engine attached to an upper surface, allowing it to fly substantially parallel to the oval's major axis or the oval's minor axis, allowing different configurations for landing and takeoff than for cruising. | ||||||
| 119 | METHOD OF REFURBISHING HIGH VALUE ARTICLES | US15677807 | 2017-08-15 | US20170342545A1 | 2017-11-30 | Benjamin C. Opfermann; Craig P. Pessetto; Douglas K. Wiser |
| A system and method for refurbishing an internal surface of an article of manufacture includes a sputtering unit. The internal surface of the article of manufacture defines an internal cavity. The sputtering unit includes an electrode assembly coupled to a sealing portion. The refurbishing method begins with preparing the internal surface to remove physical damage and contamination. Next, the sputtering unit is interfaced with the article by extending the electrode assembly into the cavity and sealing the sputtering unit to the article with the sealing portion. The internal surface of the article then defines a boundary of a sputtering chamber. A dimensional value is provided that is related to an internal dimension of the cavity. Finally the sputtering unit is operated to deposit material onto the internal surface based upon the provided dimensional value. | ||||||
| 120 | Method and system for determining friction coefficient μ for an aircraft landing event | US14005500 | 2012-03-16 | US09798838B2 | 2017-10-24 | Laura Collett; Kyle R. Schmidt; Pia Sartor |
| Method and system of determining ground-to-tire friction coefficient for an aircraft landing event. The method uses an aircraft computational model to repeatedly model the landing event, varying one or more initial conditions of the aircraft model until a best match between a modelled value and a provided value of aircraft vertical acceleration is determined. The method uses initial conditions associated with the best match of modelled and provided vertical acceleration values and a strain value from a sensor on the aircraft landing gear, with the ground-to-tire friction coefficient is a variable. The method models the landing gear to generate a modelled strain value and compares this with the measured strain value, and repeats the landing gear modelling step with a different value for the ground-to-tire friction coefficient until a best match between the modelled strain value and the measured strain value is determined and outputting the respective friction coefficient value. | ||||||
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