82 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.

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 relates to a plate metal special-shaped piece processing method, in particular to a titanium alloy volute casing piece forming method, which comprises the following steps that: the size of an outer circle and an inner circle of a preform body is calculated according to a design drawing of a volute casing piece; the material is fed; the size of mould cavity is reduced by 3 to 7 percent when designing a mould, the processing method adopts a numeric-control processing center to process, and the hardness of the mould is more than or equal to HRC45; the formation is carried out in a multi-pass hot-drawing way; and finally the metal volute casing piece is obtained through the mechanical processing and the surface treatment. The titanium alloy volute casing piece is processed through the multi-pass hot-drawing formation technology; the high-temperature-resistant anti-oxidation coat is used for coating the surface of a titanium alloy sheet so as to realize that the titanium material can be heated inside an ordinary resistance furnace; the size reduction range of the mould cavity is found when designing the mould; technological seams are arranged on local part of the preform body so as to prevent local part from being cracked during the formation process; and the industrialized small mass production of the titanium alloy volute casing piece is realized, the quality of the product reaches the level of the similar product in overseas developed countries, and the urgent need of the aviation industry is solved.

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 renovation technology of a carbon / carbon aviation brake disc which reaches the service life, and a process thereof. The process comprises the following eight procedures: determining whether the carbon / carbon aviation brake disc which reaches the service life can be repaired by detecting various indexes of the brake disc, and determining the modification indexes; cutting off the worm surface of the brake disc to expose the new internal surface; pulling out a tooth-shape groove on the surface of the brake disc, and meshing two or more brake blades by the tooth-shape groove; macroscopically combining the brake disc by a special high-temperature bonding agent; machining and shaping the bonded brake disc and causing the brake disc to be close to the size of a finished product; performing a chemical vapor deposition process on the bonded brake disc, and causing the spliced brake disc to be connected microscopically; machining and shaping the brake disc treated by the chemical vapor deposition again to meet the requirement of the design size; and finally coating an oxidation resistant coating on a shaped semi-finished product to obtain a renovated finished product. By the technology and the process, about 40% of the carbon / carbon aviation brake discs which reach the service life can be renovated and reutilized, thus saving raw materials, reducing the great expenditure of the astronautical and aeronautical industries, and having environmental protection value.

Disclosed is an adapter device D, T that, when installed on the division / break area of fixation tracks in an aircraft, it allows installation and / or positioning of passenger's seat in that area; the device D, T is composed by a main body 1 having two portions 9, 10; the end of the portion 9 is integrated to a part 2 having a fork shape configuring a half-opening 3; close to the end of the portion 10 there is a pair of half-tabs 5, one half-tab 5 symmetrically disposed in relation to the other, on each side of the body 1, on the main body 1, there is a pair of semi-circular tabs 4; on the portion 10, between the pairs of half-tabs 5 and tabs 4, there is one more pair of tabs, 4′, one tab 4′ symmetrically disposed in relation to the other, on each side of the body 1; there is two threaded pass-through holes 11, 11′ located on the portion 10; disc parts 6, 6′ which are actually screws heads are disposed on the portion 10, said screws being installed in the threaded holes 11, 11′. Considering the standardization of seats tracks and fasteners existent in the aeronautical industry, the adapting devices D and T can be used with several types of passengers' seats and tracks, and said devices can be adapted without adversely modifying installation characteristics; as the use of the adapting devices D and T is very simple, thus not demanding any modification or disassembly of the seats and, this way, it does not affect the pre-qualification of such seats.

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 provides a high-transparence toughened PA12 / PA56 alloy material. The high-transparence toughened PA12 / PA56 alloy material can be used in the field of special industries with high transparence requirement. The formula of the material comprises 10-30 wt% of PA12 resin, 55-86.9 wt% of PA56 resin, 2-8 wt% of a flexibilizer, 0.2-2 wt% of light guiding powder, 0.2-1 wt% of an antioxidant, 0.5-2 wt% of a lubricant and 0.2-2 wt% of a nucleation inhibitor. A preparation method of the material comprises the following steps: uniformly stirring all component raw materials through a high mixer, adding the stirred raw materials to a double screw extruder, carrying out melt extrusion, cooling the extruded material, air-drying the cooled material, granulating the air-dried material, and strongly magnetizing obtained granules to obtain the material. The material has high toughness, has the transparence comparable to common nylon, and can be used in the fields of the aviation industry, automobile manufacturing, the electric appliance industry, image, medical science and food packaging.

The present invention relates to a body-separated type one-way bolt fastener, belonging to the field of mechanical assembly technology. Said bolt body is composed of three portions, including two side bar bodies and one intermediate bar body, said three portions can be combined into a bolt whole body. The outer profile of cross-section of main body portion of every side bar body is equipped with a section of minor arc, said curved face has screw threads. Said intermediate bar body is mainly used for preventing side bar body from falling and has anti-drawing measure. When two side bar bodies and intermediate bar body are combined together, the cross-section of combined bolt whole body is circular, and its curved surface has screw threads, so that when said three portions are combined into a bolt whole body, said bolt whole body can be fixed by using general nut.

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 provides a high damping composite plate. The composite plate comprises a restraint layer and damping layers. Multiple damping layers are laminated and adhered on one surface of the restraint layer. The provided high damping composite plate is a novel whole resin system dedicatedly developed for the aviation industry, does not contain any asphalt or harmful volatile, is flame retardant, has the advantages of wide frequency range and wide temperature range, and solves the problems that conventional damping plates in the aviation industry are not environment-friendly, and the damping efficiency is low.

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.