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 |
|---|---|---|---|---|---|---|
| 41 | 내부식성 조질강 합금 | KR1020177020384 | 2013-10-24 | KR1020170088439A | 2017-08-01 | 워트데이비드이 |
| 중량% 기준으로하기성분을갖는조질강합금이개시된다. C 0.2-0.5, Mn 0.1-1.0, Si 0.1-1.2, Cr 9-14.5, Ni 3.0-5.5, Mo 1-2, Cu 0-1.0, Co 1-4, W 최대 0.2, V 0.1-1.0, Ti 0.5 이하, Nb 0-0.5, Ta 0-0.5, Al 0-0.25, Ce 0-0.01, La 0-0.01. 합금의나머지는철, 및 0.01% 이하의인, 0.010% 이하의황, 및 0.10% 이하의질소를포함하는, 유사한유사한용도또는서비스용유사한등급의조질강에서발견되는일반적인불순물이다. 이합금으로부터제조된조질강물품도개시된다. 상기강철물품은 290 ksi 이상의인장강도및 65 ksi 이상의파쇄인성(K)을갖는것을특징으로한다. 상기강철물품은염 분무시험(ASTM B117) 에의해측정시일반적인부식에대한양호한내성, 및순환동전위분극방법(ASTM G61 변형)에의해측정시공식에대한양호한내성을갖는것을추가의특징으로한다. | ||||||
| 42 | ブレーキロッド用巻き付け式歪みゲージ | JP2013152960 | 2013-07-23 | JP6336720B2 | 2018-06-06 | ティルマン, ジェームズ エリック |
| 43 | 焼入れ焼戻し耐食合金鋼 | JP2015539774 | 2013-10-24 | JP2016501982A | 2016-01-21 | デイビッド・イー・ワート |
| 重量パーセントで、C:0.2〜0.5、Mn:0.1〜1.0、Si:0.1〜1.2、Cr:9〜14.5、Ni:3.0〜5.5、Mo:1〜2、Cu:0〜1.0、Co:1〜4、W:最大0.2、V:0.1〜1.0、Ti:0.5以下、Nb:0−0.5、Ta:0−0.5、Al:0〜0.25、Ce:0−0.01、La:0−0.01を含む、焼入れ焼戻し合金鋼が開示される。合金鋼の残部は、鉄と同様の用途またはサービスを対象とした同種の焼入れ焼戻し鋼に見られる一般的な不純物であり、0.01%以下のリン、0.010%以下の硫黄ならびに0.10%以下の窒素を含む。この合金から作られた焼入れ焼戻し鋼製品も開示される。鋼製品は、少なくとも290ksiの引張強さおよび少なくとも65ksiの破壊靱性(KIc)を有することを特徴とする。鋼製品は、さらに、塩水噴霧試験(ASTM B117)により測定される、全面腐食に対する優れた耐性を有し、周期状ポテンシオダイナミック分極法(改良したASTM G61)により測定される、孔食に対する優れた耐性を有することを特徴とする。 | ||||||
| 44 | Load indicator | JP2010525431 | 2008-09-19 | JP4873391B2 | 2012-02-08 | マーティン インズ，; スティーヴ スミス， |
| 45 | Overload detection | JP2010525424 | 2008-09-19 | JP2010538917A | 2010-12-16 | イアン ベネット， |
| 過負荷検出アセンブリは、監視されるべき負荷に応じて横方向に曲がるようになっている第１の耐荷重部材（１０）と、通常の負荷状態下で第１の耐荷重部材から離間され、第１の耐荷重部材が負荷限度を超えて負荷を受けるときに第１の耐荷重部材と接触して第１の耐荷重部材によって負荷が与えられる第２の耐荷重部材（１１）とを備える。 第１の耐荷重部材（１０）は、負荷限度を下回る降伏点を有し、降伏点を越えた時点で永久歪みを起こすことが好ましい。 横方向プローブ（１８）は、第１の耐荷重部材が第２の耐荷重部材の方へ移動する際に第１の耐荷重部材と協働してインジケータ部材(２０)を撓ませ、該インジケータ部材は、降伏点を越えるときに永久歪みを起こす。 インジケータ部材の容易な検査は、インジケータ部材が曲げられたか否かを明らかにする。
【選択図】 図２ |
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| 46 | Skid rail for aircraft and method for manufacturing the same | JP2010047000 | 2010-03-03 | JP2010247820A | 2010-11-04 | NAKAZAWA ATSUSHI; AZUMA HIROHIDE |
| <P>PROBLEM TO BE SOLVED: To provide a skid rail for an aircraft excellent in abrasion resistance and machinability, and a method for manufacturing the same. <P>SOLUTION: The skid rail for the aircraft includes (i) a base 2 including a long board 21 joined to the bottom surface of an aircraft fuselage and bosses 22a-22i integrally separated in the longitudinal direction thereof, (ii) cores 3a-3h bonded between the bosses 22a-22i so as to form a rail-shaped integral structure, and (iii) a skin 4 covering the bosses 22a-22i and the cores 3a-3h, the base 2 and the skin 4 being formed by a first fiber-reinforced plastic containing glass fibers and/or a cloth substrate of carbon fibers, the cores 3a-3h being formed by a second fiber-reinforced plastic containing a fabric cloth substrate having the higher abrasion resistance than that of fibers in the first fiber-reinforced plastic. <P>COPYRIGHT: (C)2011,JPO&INPIT | ||||||
| 47 | 焼入れ焼戻し耐食合金鋼 | JP2015539774 | 2013-10-24 | JP6342409B2 | 2018-06-13 | デイビッド・イー・ワート |
| 48 | Overload detection | JP2010525424 | 2008-09-19 | JP4953400B2 | 2012-06-13 | イアン ベネット， |
| 49 | Load indicator | JP2010525431 | 2008-09-19 | JP2010539509A | 2010-12-16 | マーティン インズ，; スティーヴ スミス， |
| 負荷インジケータは、第１及び第２の耐荷重部材（２３、２２）から成る耐荷重アセンブリを備え、第１の耐荷重部材（２３）に加えられる横方向負荷を支持するために前記耐荷重部材が互いに接続され、第１の耐荷重部材は、指標負荷を上回るとそれが脆くなるように第２の耐荷重部材と共にキャビティ（２５）を形成し、キャビティ（２５）は、第１の耐荷重部材が前記負荷によって破断されるとキャビティから漏れる指標液体を収容する。 耐荷重部材（２２、２３）は同軸に配置される円筒部材を備え、その場合、外側部材（２３）は、それを脆くするとともにキャビティ（２５）を形成するために厚みが減少される部分を有する。 キャビティ（２５）は、第２の耐荷重部材（２２）内に内容積を含む。 負荷インジケータは、２つの部品を接続するための耐荷重ピンとして構成されてもよい。
【選択図】 図３ |
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| 50 | A method and apparatus for supporting a cause take-off of aircraft | JP2008516215 | 2006-06-13 | JP2008543638A | 2008-12-04 | アンドレ アンゲル; ウォルフラム シェーン |
| 【課題】本発明は、航空機の離陸引き起こしを支持する方法および装置である。
【解決手段】前記航空機が、縦に並んで配置され、少なくとも２つの主着陸装置ユニット（１０，２０）を両側に有し、主着陸装置ユニット（１０，２０）がホイール（１１，１２，１３，２１，２２，２３）を備えている。 本発明によれば、離陸引き起こしを支持するために、主着陸装置ユニット（１０，２０）の少なくとも後部対（２０）において、後部主着陸装置ユニット（２０）の地面上を転動するホイール（２１，２２，２３） と胴体６０との間の距離を能動的に短縮する。 【選択図】 図２ |
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| 51 | JPH01503530A - | JP50637487 | 1987-04-29 | JPH01503530A | 1989-11-30 | |
| 52 | Supporting of aeroplane and landing gear system | JP14560277 | 1977-12-02 | JPS5373799A | 1978-06-30 | CHIYAARUZU FUREDORITSUKU NIIBA; SUTEIIBUN AAREN KURASUMAN; AAUIN JIEFURII KENIGUSUBAAGU |
| 53 | 내부식성 조질강 합금 | KR1020157008878 | 2013-10-24 | KR1020150048889A | 2015-05-07 | 워트데이비드이 |
| 중량% 기준으로하기성분을갖는조질강합금이개시된다. C 0.2-0.5, Mn 0.1-1.0, Si 0.1-1.2, Cr 9-14.5, Ni 3.0-5.5, Mo 1-2, Cu 0-1.0, Co 1-4, W 최대 0.2, V 0.1-1.0, Ti 0.5 이하, Nb 0-0.5, Ta 0-0.5, Al 0-0.25, Ce 0-0.01, La 0-0.01. 합금의나머지는철, 및 0.01% 이하의인, 0.010% 이하의황, 및 0.10% 이하의질소를포함하는, 유사한유사한용도또는서비스용유사한등급의조질강에서발견되는일반적인불순물이다. 이합금으로부터제조된조질강물품도개시된다. 상기강철물품은 290 ksi 이상의인장강도및 65 ksi 이상의파쇄인성(K)을갖는것을특징으로한다. 상기강철물품은염 분무시험(ASTM B117) 에의해측정시일반적인부식에대한양호한내성, 및순환동전위분극방법(ASTM G61 변형)에의해측정시공식에대한양호한내성을갖는것을추가의특징으로한다. | ||||||
| 54 | 기수측 보조 착륙장치, 힘 전달 구조체, 및 회전익 항공기 | KR1020060036386 | 2006-04-21 | KR100790530B1 | 2008-01-02 | 비에텐하데르,끌로드 |
| 본 발명은 회전익 항공기용의 조향가능한 기수측 보조 착륙장치(2)를 제공하고, 이 착륙장치(2)는 후방으로 철회 가능하다. 이 착륙장치(2)에서, 진동 시스템(13)이 충격 흡수 스트로크(59)보다 큰, 그의 힌지식 연결 전방 단부(52)를 중심으로 한 상승 스트로크(58)를 제공하고, 충격 흡수 액추에이터(9)는 진동 시스템(13)의 상부 접촉 위치를 지나는 철회 수단을 가짐으로써, 진동 시스템(13)과 충격 흡수 액추에이터(9)가 충격 흡수 기능과 착륙장치 철회 기능 모두를 제공한다. | ||||||
| 55 | 기수측 보조 착륙장치, 힘 전달 구조체, 및 회전익 항공기 | KR1020060036386 | 2006-04-21 | KR1020060111410A | 2006-10-27 | 비에텐하데르,끌로드 |
| An auxiliary nose undercarriage, a force transmission structure, and a rotary wing aircraft are provided to lower the aerodynamic resistance and to stabilize the takeoff and landing operation of the aircraft. An auxiliary nose undercarriage(2) can be contracted to the rear side. A vibrator system(13) shows a lift stroke(58) about a hinge front surface end(52) larger than an impact absorption stroke(59). An impact absorbing actuator(9) has a contracting unit passing through an upper bonding position. The vibrator system and the impact absorbing actuator provides both an impact absorbing function and an auxiliary nose undercarriage contracting function. | ||||||
| 56 | Systems and methods for detecting landing gear ground loads | US13267561 | 2011-10-06 | US10131419B2 | 2018-11-20 | Bradley W. Baird |
| There is provided a system for predicting loading of a landing gear including, a plurality sensors positioned proximate to the landing gear. The plurality of sensors measure strain applied to the landing gear, and each sensor yielding strain data. The system further includes a processor that receives the strain data from the plurality of sensors and predicts at least one ground load based on strain data. There is further provided a method for predicting loading of a landing gear. The method includes powering a plurality of sensors located proximate to a landing gear structure, interrogating the plurality of sensors via data acquisition circuitry to yield strain data, instructing the data acquisition circuitry as to a sampling rate and data resolution to be used for the interrogating, and, finally, processing the strain data to predict a ground load. | ||||||
| 57 | HYBRID METALLIC/COMPOSITE JOINT WITH ENHANCED PERFORMANCE | US15285973 | 2016-10-05 | US20180093422A1 | 2018-04-05 | Mark R. Gurvich; Rony Giovanni Ganis; Virginia H. Faustino |
| A metallic/composite joint may comprise a composite member having a flared end or an angled end, a liner perimetrically surrounding the composite member, and a metallic member perimetrically surrounding the liner. A first side of the liner contacts the composite member and a second side of the liner contacts the metallic member. The liner perimetrically surrounds at least a portion of the flared end. A through-thickness compressive stiffness of the liner may be less than a similar stiffness of the composite member. | ||||||
| 58 | METALLIC COMPOSITE JOINT | US15190978 | 2016-06-23 | US20170369157A1 | 2017-12-28 | Mark R. Gurvich; Rony Giovanni Ganis |
| A composite metallic joint assembly may include a composite metal rod having a metal liner and a composite material disposed around the metal liner. A first portion of the composite metal rod may comprise the composite material and the metal liner and a second portion of the composite metal rod may comprise the metal liner exposed at a radially outer surface of the composite metal rod. The metal liner may have a first radial thickness at a first axial position corresponding to the first portion of the composite metal rod and a second radial thickness at a second axial position corresponding to the second portion of the composite metal rod. The second thickness may be greater than the first thickness. | ||||||
| 59 | Systems and methods for landing identification | US13312073 | 2011-12-06 | US09688388B2 | 2017-06-27 | Eric D. Cahill; Michael Shaw |
| Systems and methods disclosed herein may be useful for use in landing identification. In this regard, a method is provided comprising receiving pulse information over a first time period, wherein the pulse information is indicative of an angular distance traveled by a first wheel, comparing the pulse information to a threshold value, and determining a likelihood of a landing event based upon the comparison. In various embodiments, a system is provided comprising a monstable multivibrator in electrical communication with a metal-oxide-semiconductor field-effect transistor (MOSFET), a resistor-capacitor network in electrical communication with the MOSFET, and a comparator that receives a voltage from the resistor-capacitor network and a reference voltage. | ||||||
| 60 | QUENCH AND TEMPER CORROSION RESISTANT STEEL ALLOY | US15235226 | 2016-08-12 | US20170002447A1 | 2017-01-05 | David E. Wert |
| A quench and temper steel alloy is disclosed having the following composition in weight percent. C0.2-0.5 Mn0.1-1.0 Si0.1-1.2 Cr 9-14.5 Ni2.0-5.5 Mo1-2 Cu 0-1.0 Co1-4 W0.2 max. V0.1-1.0 Tiup to 0.5 Nb 0-0.5 Ta 0-0.5 Al 0-0.25 Ce 0-0.01 La 0-0.01 The balance of the alloy is iron and the usual impurities including not more than about 0.01% phosphorus, not more than about 0.010% sulful, and not more than about 0.10% nitrogen. A quenched and tempered steel article made from this alloy is also disclosed. The steel article is characterized by a tensile strength of at least about 290 ksi, a fracture toughness (kIc) of at least about 65 ksi, good resistance to general corrosion, and good resistance to pitting corrosion. | ||||||
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