Vichniakov
Alexei Vichniakov, Wenzendorf DE
Patent application number | Description | Published |
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20090263676 | Method for Connection At Least Two Pieces of Sheet Material, Particularly At Least Two Metal Sheets for a Lightweight Structure As Well a Joining and Lightweight Structure - A method for connecting at least two sheet-like formations, in particular at least two metal sheets with a thin material thickness for aircraft, comprises establishing butt-joint connections between the sheet-like formations by forming a joining region; mechanical processing of the sheet-like formations and/or of the joining region; mechanical and/or chemical adhesive pre-treatment of the sheet-like formations and/or of the joining region; and pasting-on at least one reinforcement element in the region of the top and/or the bottom of the joining region, wherein for the purpose of forming a second load path the width of the at least one reinforcement element is wider than the width | 10-22-2009 |
20120102869 | LIGHTWEIGHT STRUCTURAL PANEL - What is described is a lightweight structural panel which comprises a planarly extended outer skin of given thickness and stiffening elements which are connected to this outer skin and are arranged at a given distance from one another. According to the invention, the outer skin is formed by component layers which are each extended in the planar direction of the lightweight structural panel and complement one another in the direction of thickness to form the thickness of the outer skin and are interconnected, the stiffening elements being formed in one piece with one of the component layers. | 05-03-2012 |
Alexei Vichniakov, Buxtehude DE
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20130216850 | STRUCTURAL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT - A structural component for an aircraft or spacecraft having an outer skin, comprising at least one former element for reinforcing the outer skin. The former element is arcuately curved in accordance with an inner contour of the outer skin | 08-22-2013 |
Alexei Vichniakov, Hamburg DE
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20130115404 | LIGHTWEIGHT STRUCTURE, PARTICULARLY PRIMARY AIRCRAFT STRUCTURE OR SUBASSEMBLY, AS WELL AS METHOD FOR THE MANUFACTURE THEREOF - A lightweight structure at least sectionally composed of a plurality of connected mosaic elements and/or skin mosaic elements. The lightweight structure allows an essentially load-appropriate arrangement of the mosaic elements and/or the skin mosaic elements including the optional skin. The lightweight structure requires a significantly reduced number of connecting elements, such that the assembly effort can be reduced and an additional weight reduction can be achieved. Also, two variations of a method for manufacturing a lightweight structure are provided. Large-format lightweight structures such as, for example, an aircraft fuselage cell or partial shells thereof can also be manufactured in a reliable and dimensionally accurate fashion because only mosaic elements and skin mosaic elements, with relatively small dimensions, need to be handled. Other applications of the lightweight structure include launch vehicles, rocket stages, space stations, space station modules, satellites and masts or towers of wind power plants. | 05-09-2013 |
20150034764 | AIRCRAFT FUSELAGE STRUCTURE - An aircraft fuselage structure is disclosed having an outer skin, a support structure arrangement with frame elements, and a floor structure arrangement with floor support struts, the floor structure arrangement connected to the support structure arrangement via connection parts. A connection exists between the floor structure arrangement and the support structure arrangement, with a clamping element on the connection part and a locking element on the connection part. The clamping element includes a longitudinal section having a first and a second end. The first end is pivotally attached to the connection part. The second end includes a transverse section, the locking element including at least one locking groove, and the clamping element pivotable between an engagement position in which the transverse section engages the locking groove, and a released position, in which the transverse section is disengaged therefrom. | 02-05-2015 |
Alexi Vichniakov, Hamburg DE
Patent application number | Description | Published |
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20140291447 | AIRCRAFT FUSELAGE STRUCTURE - Provided is an aircraft fuselage structure having an outer skin, a support structure arrangement comprising a multiplicity of frame elements and a floor structure arrangement having a multiplicity of floor support struts. The aircraft fuselage structure provides a connection between the floor structure arrangement and the support structure arrangement which is as simple and quick to produce as possible, while not significantly increasing the weight or weakening the structure. Either the floor structure arrangement or the support structure arrangement can have at a connection there between a male connector element or a female connector element. The male connector element can have a peg which extends in the engagement direction and which has a circumferential outer surface which is provided with a multiplicity of circumferential projections. The female connector element can have a cavity, the inner surface of which is provided with a multiplicity of circumferential tabs. | 10-02-2014 |