83 results about "Aeronautical industry" patented technology

The invention relates to a wrought product such as an extruded, rolled and / or forged aluminum alloy-based product comprising, in weight %: Cu: 3.0-3.9; Li: 0.8-1.3; Mg; 0.6-1.0; Zr: 0.05-0.18; Ag: 0.0-0.05; Mn: 0.0-0.5; Fe+Si≦0.20; Zn≦0.15; at least one element from among: Ti: 0.01-0.15; Sc: 0.05-0.3; Cr: 0.05-0.3; Hf: 0.05-0.5; other elements ≦0.05 each and ≦0.15 total, remainders aluminum. The invention also relates to the process for producing said product. The products according to the invention are particularly useful in the production of thick aluminum products intended for producing structural elements in the aeronautical industry.

A right angle light diverter includes a hexagonal tube that is bent at a right angle that is coated with a highly reflective coating on the inside surface. An incoming light beam may be homogenized upon entering an input port of the hexagonal tube and may be evenly diverted at a right angle at a reflection section while the homogenized profile may be maintained. A right angle optical splitter may include at least one additional output section. An incoming light beam may be homogenized and may be split into at least two outgoing beams that may be diverted at right angles at reflection sections. The right angle light diverter and the right angle optical splitter may be suitable for, but not limited to, applications in aircraft industry, both military and commercial. They may be used, for example, in connection with airborne laser programs, in commercial airplanes, and in military jets.

The invention relates to a stringer (11, 21, 31) which is made from a composite material and which is used to stiffen composite panels, particularly those used in the aeronautical industry. The inventive stringer is formed by a base (15) which is used to join same to the panel and a structural element (13, 23, 33) which is equipped with a structural reinforcement (17, 27, 37) at the end opposite the base (15), said structural reinforcement being made from high-modulus unidirectional fibres of the same material as the stringer or another compatible material. The invention also relates to a method of producing said stringer.

The invention discloses a low-crackle type high speed steel roll and its centrifugal casting method, wherein the steel comprises the following chemical constituents (by weight percent): C 1.5-2.0%, W 3.0-6.0%, Mo 1.5-3.0%, V 3.0-10.0%, Cr 3.0-10.0%, Ni 1.5-3.0%, Mn<1.5%, Si<1.5%, RE 0.08-0.20%, K 0.05-0.15%, Mg 0.04-0.10%, wherein 0.20 B22D 13 / 12 C22C 38 / 18 1 13 2 2006 / 1 / 19 1803339 2006 / 7 / 19 1331626 2007 / 8 / 15 2007 / 8 / 15 2007 / 8 / 15 Zhengzhou Institute of Aeronautical Industry Management Henan 450005 Fu Hanguang Jiang Zhiqiang Shi Jinfa li zhengjian 61200 The Patent Agency of Xi'an University of Communications No.28, Xianning, Road, the City of Xi'an, Shanxi Province 710049

The invention belongs to the technical field of turbine blade performance detection in the aviation industry, in particular to a simulation test method of thermal fatigue failure of a blade with thermal barrier coating. The method can simulate the thermal fatigue work environment of temperature alternating circulation of various blades in an aircraft engine with high performance, and simultaneously tests and analyzes data, such as temperature, temperature gradient, surface topography image evolution, three dimensional deformation field, three dimensional displacement field, interface oxidation layer and thickening rule thereof, thermal fatigue flaw initiation and expansion, cooling airflow and the like of a blade sample with a thermal barrier coating, thus realizing real-time monitoring of three dimensional thermal strain and stress of the blade in the process of thermal fatigue experiments, and providing an important means for predicting thermal fatigue damaging position and invalidation time of the blade. The experimental data obtained by the method can provide important experiment basis for effectively evaluating the failure mechanism of the aircraft engine blade in the environment of high-temperature gas and predicting ceramic coating dropping position, dropping time and service life.

The invention relates in particular to an unprocessed extruded product for manufacturing a machined extruded product for the aeronautical industry, made of an Al-Cu-Li alloy with the following composition, as weight percentages: Cu: 2.0 - 6.0; Li: 0.5 - 2.0; Mg: 0 - 1.0; Ag: 0 - 0.7; Zn 0 - 1.0; and at least one element selected among Zr, Mn, Cr, Se, Hf and Ti, the amount of said element, if chosen, being 0.05 to 0.20 wt % for Zr, 0.05 to 0.8 wt % for Mn, 0.05 to 0.3 wt % for Cr and for Se, 0.05 to 0.5 wt % for Hf and 0.01 to 0.15 wt % for Ti, Si <= 0.1; Fe <= 0.1; others <= 0.05 each and <= 0.15 in total, the balance being aluminium, having an unprocessed core (21) with an aspect ratio of at least 5 and at least one unprocessed flank (22) with an aspect ratio of less than 4 and in which the length direction is substantially perpendicular to the lengthwise direction of the core, characterized in that a portion of the unprocessed flank (22) connecting the unprocessed flank to the unprocessed core has decreasing thickness and in that the ratio of the thickness of said unprocessed flank (22) at the end of said unprocessed flank connected to the web (E221) to that at the end thereof opposite the core (E222) - i.e. E221 / E222 - is less than 0.8, thus defining two substantially symmetrical concave areas.; The invention also relates to the method for manufacturing a machined extruded product and to the corresponding machined extruded product. The products according to the invention are useful in particular for manufacturing floor beams and girders.