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公开(公告)号：EP1655223B1
公开(公告)日：2013-01-23
申请号：EP06075319.1
申请日：2000-03-13
发明人： Diverde, Michael B. , Telford, Kenneth N. , Budris, George J. , Gil, Christopher M. , Steinmeyer, John F.
CPC分类号： B64G1/645 , B64G1/002 , B64G1/1085 , B64G1/222 , B64G1/641 , B64G2001/643
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公开(公告)号：EP1655223A2
公开(公告)日：2006-05-10
申请号：EP06075319.1
申请日：2000-03-13
发明人： Diverde, Michael B. , Telford, Kenneth N. , Budris, George J. , Gil, Christopher M. , Steinmeyer, John F.
CPC分类号： B64G1/645 , B64G1/002 , B64G1/1085 , B64G1/222 , B64G1/641 , B64G2001/643
摘要： A satellite dispenser for supporting and deploying a plurality of satellites, and adapted to be carried into the Earth's orbit by a launch vehicle, said satellite dispenser comprising:
a shell including a post portion and a base portion, said structure having a length-wise dimension sufficient to span at least one pair of satellites disposed longitudinally along said post portion;
a frame secured to said shell adapted to assist in supporting at least one of said pair of satellites; and
a separation assembly operably associated with said frame for releasably coupling one of said pair of satellites to said shell and for deploying said one satellite at a desired point of travel of said launch vehicle.摘要翻译： 一种卫星分配器（14），用于支撑和部署多个卫星（18），并且适于由运载火箭运载到地球的轨道中，所述卫星分配器包括：壳体，包括柱部分（22）和基部 所述结构的长度尺寸足以跨越沿着所述柱部分（22）纵向设置的至少一对卫星; 固定到所述外壳的框架（20），其适于辅助支撑所述一对卫星中的至少一个; 以及与所述框架可操作地相关联的分离组件（72），用于将所述一对卫星中的一个可释放地联接到所述壳体并且用于将所述一颗卫星部署在所述运载火箭的所需行进点处。
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公开(公告)号：EP0990130B1
公开(公告)日：2005-10-26
申请号：EP97917803.5
申请日：1997-04-01
发明人： BENNE, Michael , DONOVAN, John , KELBLE, Christopher , KIHLKEN, Thomas , MORRIS, Martin , PAL, Alexander
摘要： A method of determining pressure requires that a three-dimensional surface of an object (14) be covered with a pressure sensitive coating. Next a raw first image (74) is acquired while the object (14) is not under test and a raw second image (74) is acquired while the object is under test. The raw first image (74) and the raw second image (74) are adjusted for a dark image (76) to form an adjusted first image and an adjusted second image. The adjusted first image and the adjusted second image are mapped (78) from a two-dimensional representation onto a three-dimensional model, to form a first model and a second model. A ratio model is formed (80) by taking the ratio of the intensity of the first model and the second model. Finally, a pressure is determined (84) for every surface that forms the three-dimensional model.
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公开(公告)号：EP1405786A2
公开(公告)日：2004-04-07
申请号：EP03078247.8
申请日：1998-12-08
CPC分类号： F16B21/02 , B60N2/015 , B64C1/18 , B64D11/0696 , F16B19/002 , F16B19/1027 , Y02T50/46
摘要： A fastener (78) in an interlocking assembly system for an aircraft cabin comprises
a longitudinally extending shaft (80) having first and second portions (84,86), wherein the first portion (84) is larger in lateral cross-section than the second portion (86), wherein said shaft (80) further includes a first ring (88) proximate an end of the first portion (84) opposite the second portion (86) and a second ring (90) proximate an end of the second portion (86) opposite the first portion (84), and wherein the first ring (88) is larger in lateral cross-section than the first portion (84) and the second ring (90) is larger in lateral cross-section than the second portion (86); and
an annular ferrule (82) defining a lengthwise extending channel extending between opposed first and second ends, wherein said annular ferrule (82) also defines a slit (83) which permits said annular ferrule (82) to elastically deform as said ferrule (82) is advanced over the second ring (90) so as to mount said ferrule (82) upon the second portion (86) of said shaft (80) such that the first end of said ferrule (82) is proximate the first portion (84) of said shaft (80) and the second end of said ferrule (82) is proximate the second ring (90) of said shaft (80), and wherein a portion of the channel adjacent the first end of said ferrule (82) is smaller in lateral cross-section than the first portion (84) and the portion of the channel adjacent the second end of said ferrule (82) is smaller than the second ring (90) such that said ferrule (82) is retained upon the second portion (86) of said shaft (80).摘要翻译： 用于飞机机舱的互锁组件系统中的紧固件（78）包括具有第一和第二部分（84,86）的纵向延伸的轴（80），其中第一部分（84）的横向横截面大于第二部分 其中所述轴（80）还包括靠近所述第一部分（84）的与所述第二部分（86）相对的一端的第一环（88）和靠近所述第二部分（86）的一端的第二环（90） （84）相对的第一部分（86），并且其中第一环（88）的横向横截面大于第一部分（84），并且第二环（90）的横向横截面大于第二部分 部分（86）; （82）限定了在相对的第一端和第二端之间延伸的纵向延伸通道，其中所述环形套圈（82）还限定了允许所述环形套圈（82）随着所述套圈（82）弹性变形的狭缝（83） ）在第二环（90）上推进，以便将所述套箍（82）安装在所述轴（80）的第二部分（86）上，使得所述套箍（82）的第一端靠近第一部分（84 ）并且所述套箍（82）的第二端接近所述轴（80）的第二环（90），并且其中邻近所述套箍（82）的第一端的通道的一部分是 其横向截面小于第一部分（84），并且与所述套管（82）的第二端相邻的通道部分小于第二环（90），使得所述套管（82）保持在第二部分 所述轴（80）的部分（86）。
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5.发明公开Preparation of pre-coated aluminium alloy articles 失效Herstellung von vorbeschichteten Aluminiumlegierungsteilen
公开(公告)号：EP1382705A1
公开(公告)日：2004-01-21
申请号：EP03020302.0
申请日：1996-05-01
发明人： Kreener, Steven G.
IPC分类号： C22F1/04
CPC分类号： C22F1/04 , B05D3/0254 , B05D7/14 , B05D7/51 , B05D2202/25 , B05D2258/00 , B05D2701/00 , B21K1/58 , C21D9/0093 , C25D11/18 , C25D21/18
摘要： An aluminum-alloy article such as a fastener or rivet (40) is prepared by providing an aluminum-alloy article precursor that is not in its final heat-treated state, and in one form is in its solution treated/annealed state. A curable organic coating material is also provided. The method includes anodizing the article precursor, preferably in chromic acid solution and without chemical sealing during anodizing, applying the organic coating material to the aluminum-alloy article precursor, and precipitation heat-treating the coated aluminum article precursor to its final heat-treated state, thereby simultaneously curing the organic coating. If the aluminum alloy temper is of the naturally aging type, it is optionally lightly deformed prior to precipitation treatment aging. The approach may also be applied to articles that are not solution treated/annealed and aged, by first overly deforming the article precursor so that the curing treatment of the coating also partially anneals the article precursor to the final desired deformation state.
摘要翻译： 通过提供不属于其最终热处理状态的铝合金制品前体，并且以一种形式处于其溶液处理/退火状态，制备诸如紧固件或铆钉（40）的铝合金制品。 还提供了可固化的有机涂层材料。 该方法包括阳极氧化制品前体，优选在铬酸溶液中，并且在阳极氧化期间没有化学密封，将有机涂料施加到铝合金制品前体，并将涂覆的铝制品前体沉淀热处理至其最终热处理状态 从而同时固化有机涂层。 如果铝合金回火是天然老化型，则在沉淀处理老化之前任选轻度变形。 该方法也可以应用于不经过溶液处理/退火和老化的制品，首先使制品前体过度变形，使得涂层的固化处理也部分地将制品前体退火到最终期望的变形状态。
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6.发明授权
公开(公告)号：EP1042099B1
公开(公告)日：2003-05-07
申请号：EP98966749.8
申请日：1998-12-23
IPC分类号： B23K20/12
CPC分类号： B23K20/1265 , Y10T428/1234 , Y10T428/12375 , Y10T428/12764
摘要： The machined-sandwich structural assembly has two components joined together with a joint of substantially the same strength as the weakest base material. More specifically, the structural assembly includes a first structural member and a second structural member. The first structural member is spaced from the second structural member through a plurality of intermediate members which extend between the first structural member and the second structural member. The plurality of intermediate members are friction stir welded to the first structural member. The resultant assembly requires less stock material, takes less time to machine and has a jint of improved strength.
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公开(公告)号：EP0915802B1
公开(公告)日：2002-11-06
申请号：EP96927369.7
申请日：1996-08-09
IPC分类号： B64D1/04
CPC分类号： B64D1/04
摘要： A renewable energy source ejector rack (10) for retaining and releasing stores on an aircraft, which has on-board pressurization capability, employs a single pressurization system for two or more release mechanisms (64, 66), and uses air or other clean non-pyrotechnic pressurized gases both as the energy source and as the transfer medium. The aircraft contains a miniature compressor (36) and purification system. Ambient air is filtered, dried and stored as an energy medium. Since the compressor system is onboard, the pressure can be constantly maintained regardless of temperature change. Using purified air eliminates the excessive cleaning burden imposed when using state-of-the-art pyrotechnics, and eliminates the sealing problems associated with hydraulics.
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公开(公告)号：EP0958999A3
公开(公告)日：2001-08-29
申请号：EP99303952.8
申请日：1999-05-21
IPC分类号： B64C3/48
CPC分类号： B64C3/48
摘要： An aerofoil having a body (62) and an edge which comprises a tip (52) and at least one working surface, characterised in that said at least one working surface is formed by an elastomeric member (54,56).
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公开(公告)号：EP1038772A3
公开(公告)日：2001-07-18
申请号：EP00200898.5
申请日：2000-03-13
CPC分类号： B64G1/645 , B64G1/002 , B64G1/1085 , B64G1/222 , B64G1/641 , B64G2001/643
摘要： A satellite dispenser (300) adapted to be coupled to a launch vehicle. The dispenser (300) includes a single-piece, integrally formed tubular shell (302) for supporting a plurality of independent satellites (340) thereon. The tubular shell (302) is significantly lighter than multi-piece dispenser shells that require a connecting ring for coupling the post portion and base portion of the shell together. The single piece shell (302) also significantly reduces the cost and simplifies the manufacture of the dispenser shell. The dispenser shell (302), in certain preferred embodiments, includes a tapered post portion (304) which enables satellites (340) being carried on the upper portion of the post portion to extend further into a fairing (342) disposed over the satellites (340) and dispenser shell (302) during flight, thus making more efficient use of the envelope defined by the interior area of the fairing (342). A frusto-conical base portion (306) integrally formed with the post portion (304) enables the load supported by the dispenser shell (302) to be evenly distributed throughout the base portion (306). The single-piece design also significantly improves the bending stress resistance of the dispenser and its overall structural rigidity. The various preferred embodiments each include a plurality of circular frames which are secured to an interior surface of the dispenser shell. A plurality of interface fittings are secured to an exterior surface of the dispenser shell and support a plurality of satellites thereon.
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