Wing and fin panel or operation of air vehicle from layer composite materials

FIELD: aviation.

SUBSTANCE: panel contains a skin with a smooth flat outer surface of geometric shape and a framework attached to it in the form of a system of criss-crossing ribs consisting of layers fastened with a polymeric binder, unidirectional high-strength and/or high-modulus yarns and/or fabrics. And in the space between the ribs porous material is located, with formation with the latter of equidistantly outer surface of the skin of a continuous smooth surface on which strips of woven material, with perpendicular to the surface flanges, that are fastened with it by adhesive or polymeric binder in the longitudinal direction of panel between the longitudinal ribs impregnated with the binder, space between which is filled with an impregnated polymeric binder, oriented in the direction of strips arrangement, unidirectional reinforcing material with formation of power stringers coated by woven fabric material, constituting integrally with framework longitudinal ribs.

EFFECT: increasing the strength and reliability of the skin connection with power stringer, simplifying the manufacturing.

8 cl, 1 dwg

 



 

Same patents:

FIELD: aircraft engineering.

SUBSTANCE: integral panel comprises skin, stringers and transverse belts made integral with said skin. Said skin is composed of three-ply panel including outer and inner linings of reinforcing material. Cellular plastic filler with conical holes is arranged between said linings to allow for direct contact between said inner and outer skins. This panel is equipped with reinforcements built in panel edges and stringers integrated in said panel. Stringers are composed of cellular plastic core with cavity reinforced by inner shell and furnished with the stack of flanges and outer shell arranged at cellular plastic core. Transverse belt is composed of U-shape-section grooves.

EFFECT: stiff shell resisting the compression, shear and crosswise stresses.

5 dwg

FIELD: transport.

SUBSTANCE: invention relates to structural elements of wings, particularly, to aircraft wing torsion box made of composites. Wing torsion box comprises top and bottom stringer panels, front and rear spars and ribs dividing torsion box inner space into compartments. Stringers are arranged at skin outer side, feature U-like cross-section with outrigger flange and are arranged with isolation clearance to prevent transfer of strain between stringers and penetration of skin damaging matters. Stringer flange outer surfaces are coated with composite ply making an extra thin-wall outer skin. Stringers are composed of flanges and walls. Walls consist of separate thin-wall posts that lose stability under transverse strains originating at dangerous impacts and can be removed via clearances between stringer flanges.

EFFECT: higher safety of panels, simplified design and repair.

5 cl, 2 dwg

FIELD: transport.

SUBSTANCE: invention relates to structural elements of wings, particularly, to aircraft wing torsion box made of composites. Wing torsion box comprises top and bottom stringer panels. Front and rear spars and ribs of said panels divide torsion box inner space into compartments. Stringers are arranged in panel from the skin outer side and feature cross-section with the outrigger flange and set at spacing approximating to flange width. Stringers outer surfaces are coated with a thin layer of composite to make the panel outer skin. Stringer walls can plastically deform at impact loads.

EFFECT: higher safety of panels, simplified design and repair.

3 cl, 2 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to streamlined structures of composites, particularly, aircraft wings. Aircraft wing of polymer composites has lining, spars and stiffness ribs, inner ribs based on glass and coal clothes (coal tapes). Lining comprises top and bottom shells and consists of outer glass and coal cloth-based plies and inner layer of foam filler arranged there between. Wing top and bottom lining shells changing at wing root and end parts into ribs and spars made by infusion of binder with material polymerisation in appropriate dies with interconnection of shells nearby wing leading and trailing edges by glue film applied on both sides of connection surfaces. Wing mid part connection of top and bottom shells is made with the help of twin moulded angle pieces of coal cloth with binder and pre-installed via glue film at inner surfaces of said top and bottom shells connected to ribs by similar flue film. Inner ribs are made by infusion of binder and connected to top and bottom shells and ribs via glue film fed between connection surfaces.

EFFECT: higher surface quality, reliability and strength, decreased weight.

5 cl, 5 dwg

FIELD: transport.

SUBSTANCE: invention relates to production of structures including butt joints of panels from polymer composites, particularly, to jointing of structural aircraft parts (torsion boxes, wing, stabilisers) from said polymer composites. Said butt joint comprises two connectable panels, each including lining and stiffness elements. Said panels are partially overlapped by composite butt strap, its one side being connected with first panel and another one with second panel. Said strap overlaps partially the ends of aforesaid stiffness elements. Said butt joint comprises extra three metal plates rigidly butted to comprises butt strap and two panels. Area of larger metal plate corresponds to that of composite butt strap to equal the sum of smaller metal plates. Metal needles are rigidly secured at one surface of said metal plates and inserted therein. Metal sleeves are fitted in the plates. Metal plate smooth surface are tightly pressed together, butted and bolted together, said bolts passing through bores made in panels and sleeves fitted plates.

EFFECT: efficient transfer of forces via mated elements, high bearing capacity, lower weight, simple fabrication and multiple assembly/disassembly.

6 cl, 5 dwg

FIELD: process engineering.

SUBSTANCE: invention relates to production of laminar boards and shells with light fillers, particularly, to stepped laminar board and method of its production. Proposed board comprises top and bottom shells with folding four-beam filler from sheet blank consisting of elementary modules, each being formed by two beams of sawtooth and zigzag beams. Filler is made stepped from signal blank and comprises inclined folded flat sections in its final transformed state. Inclination of one section allows varying between sawtooth and zigzag beams. Proposed method consists in marking and bending sheet blanks along marked lines, transforming sheet blank into relief state, making n-quantity of stages on filler zigzag and sawtooth lines to be transformed into preset width and height described by mathematical expressions.

EFFECT: better manufacturability.

2 cl, 4 dwg

FIELD: transport.

SUBSTANCE: invention relates to method for covering light airplanes with polyester sheathing fabric, as well as to dispersive hot-gluing glue and its application for covering. For covering, polyester sheathing fabric with longitudinal shrinkage of 7% and transversal shrinkage of 5% at 160-180°C is used. In the process of covering light airplanes and/or their parts consisting of frame system, sheathing fabric in the area of its overhangs and frame parts is covered by dispersive hot-gluing glue and wrapped around longeron part of frame so that when connection between sheathing fabric and frame produced by glue is destructed the fabric could be held on frame carcass. Dispersive hot-gluing glue contains 80-88% of adhesive, 12-15% of hardener and 0.15-0.3% thickener, and the glue is polymerised at temperatures >40°C. The hardener contains 54-60% of solvent, 0.35-0.5% of naphthalensulfonic acid sodium salt-based stabiliser, 0.25-0.35% of propoxylated spirit-based emulsifier, 1.7-1.9% of polyetheramines-based hardener, 37-41% of polyisocyanate.

EFFECT: reliability and durability of light airplanes and/or their parts covering.

15 cl, 3 dwg

Aircraft assembly // 2448875

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft fuselage and wing equipped with lightning protection. Proposed assembly comprises skin 10, structural element 11 and fastener 1 to joint them together. The main component of proposed skin 10 is made up of layer 12 of plastic reinforced by carbon fiber CFRP. Outer surface of skin 10 is coated by copper foil 13. Layer of copper paint 19 based on phenol resin and copper powder is applied on the surface of foil 13. End section 2a of fastener 1 is provided with sleeve 17 (nut) with its surface coated by insulation material to lock skin 10 with structural element 11 via insulation washer 21. Insulation coat of insulation washer 21 consists of polymer containing aluminium powder. Insulation gasket 22 is arranged between said washer 21 and structural element 11. Insulation gasket 22 comprises several laminated polyimide films.

EFFECT: higher reliability and resistance.

5 cl, 5 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to flight vehicles heavier than air with soft wing. Soft two-skin wing with stiffeners made up of rods articulated with wing top and bottom surfaces and one with another to form, in the filled wing, the pyramid-like figures with jointed together by base ribs that make wing bottom surface. Strips are secured to vertices of aforesaid pyramids.

EFFECT: better structural and aerodynamic characteristics.

6 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft prefabricated wing skin panel and to method of its production. Proposed panel comprises skin panel with aerodynamic profile surface on one side and, on the other side, it has attachment surface to accommodate fasteners for wing structural elements. Said attachment surface is provided with two opposed ledges to make mounting channel. Wing structural element has first and second flanges to be clamped in said mounting channels by aforesaid opposed ledges. Said wing structural element is mounted in aforesaid channel by cold interference fit.

EFFECT: lower weight at sufficient wing strength.

18 cl, 5 dwg

FIELD: transport.

SUBSTANCE: invention relates to structure of composite with holes, particularly, to aircraft wing and fuselage. This structure extending in wing direction comprises multiple holes and is composed of plastic reinforced with fibre and to be subjected to compressive and/or extending load in lengthwise direction. Stiffness at lengthwise expansion/compression in peripheral edge area around the hole is smaller than that at compression is lengthwise direction in the other area around peripheral edge area. Every hole makes an access hole made in aircraft wing lower surface outer skin. Besides, lengthwise direction can be lengthwise direction of aircraft. Note here that every hole makes the illuminator opening made in aircraft fuselage outer skin.

EFFECT: ruled out strain concentration at peripheral edges of openings, decreased weight.

8 cl, 10 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to streamlined structures of composites, particularly, aircraft wings. Aircraft wing of polymer composites has lining, spars and stiffness ribs, inner ribs based on glass and coal clothes (coal tapes). Lining comprises top and bottom shells and consists of outer glass and coal cloth-based plies and inner layer of foam filler arranged there between. Wing top and bottom lining shells changing at wing root and end parts into ribs and spars made by infusion of binder with material polymerisation in appropriate dies with interconnection of shells nearby wing leading and trailing edges by glue film applied on both sides of connection surfaces. Wing mid part connection of top and bottom shells is made with the help of twin moulded angle pieces of coal cloth with binder and pre-installed via glue film at inner surfaces of said top and bottom shells connected to ribs by similar flue film. Inner ribs are made by infusion of binder and connected to top and bottom shells and ribs via glue film fed between connection surfaces.

EFFECT: higher surface quality, reliability and strength, decreased weight.

5 cl, 5 dwg

FIELD: aircraft engineering.

SUBSTANCE: stringer panel forming the skin and stringers from alternating monolayers of composite arranged in lengthwise direction along said stringers. Stringer cross-section features wavy shape. Stringer is divided into first part starting in skin depth and formed by extra lengthwise monolayers, second part with shin transverse monolayers are laid in separate strips, and third part formed by lengthwise and crosswise stringer monolayers above the last top layer of the skin. Crosswise monolayers extend to wave edges to overlap underlying crosswise monolayers Layers at stringer cross-section mid part can be made horizontal so that wave top has smooth horizontal section.

EFFECT: reliable joint between stringer and skin.

2 dwg

FIELD: transport.

SUBSTANCE: invention relates to structure made of composite material (CM) with a hole made in it and concerns aircraft (AC) wing and body. Structure made of CM is bottom skin of AC main wing. The structure contains structural element (SE) with holes and adjacent SE. The holes are access holes. Main wing bottom skin is formed by SE with holes and adjacent SE having separation surfaces passing in longitudinal direction of the main wing and connecting SE with holes with adjacent SE. Adjacent SE is connected with side section of SE with holes. SE with holes and adjacent SE are made so that they take up tensile load and/or compression load acting in longitudinal direction of a wing. Full rigidity of SE with holes under tension and/or compression in longitudinal direction of AC wing is less than Full rigidity of adjacent SE under tension and/or compression in longitudinal direction. Also, structure made of CM can be AC body skin. Body skin is formed by SE with holes and adjacent SE having separation surfaces passing in longitudinal direction of body and connecting SE with holes with adjacent SE. In this case, the holes are holes used as windows into which window material is set.

EFFECT: lower weight of CM structure, lower concentration of stresses occurring at peripheral edge of holes, simpler design of hole edge reinforcement.

8 cl, 18 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed panel comprises skin with smooth flat geometrical shape of outer surface secured to frame structures. The latter are composed of a system of crossed ribs secured to said skin. Said system of ribs consists of unidirectional high-strength (high modulus) threads and/or fabric secured by polymer binder and oriented along geodesic lines on the skin inner surface. Thickness and height of said ribs differ.

EFFECT: decreased weight, higher rigidity and stability in operation.

5 cl, 2 dwg

FIELD: mechanical engineering; manufacture of aircraft structures.

SUBSTANCE: proposed method of manufacture of airframe components of aircraft (1) from polymer composite materials consists in placing the parting layer (3) on mandrel (2) and winding the spiral and circular layers of load-bearing components crimping the facing made from thermally shrinkable material. Parting layer is laid section by section; sections (10) of parting layer are made from anti-adhesion elastic material and are provided with slits. Sections (10) are laid in such manner that they form spiral grooves (12) and circular grooves (13)over entire parting layer. Sections (10) are oriented and secured on mandrel (2) by means of fasteners (15). Grooves (12 and 13) are filled with polymer composite material. Mandrel (2) is provided with parting layer (3) made from separate sections (10) secured on mandrel with the aid of fasteners (15); detents are mounted at intersection of spiral axes of spiral grooves (12). Airframe members are made from many crossing spiral and circular stiffeners of both directions.

EFFECT: high manufacturability; enhanced operational reliability of airframe members.

4 cl, 13 dwg

The invention relates to a technology of manufacturing of geometrically-complex products made of composite materials by the method of continuous automated winding, mostly asymmetric aerodynamic force structure elements type of airplane wings, helicopter blades, air and water propellers, power pumps, compressors, fans, control surfaces, etc. and can be used in aviation, shipbuilding, automotive and other modern industries

FIELD: chemistry.

SUBSTANCE: invention relates to constructive composite materials and can be used in construction, and in aerospace equipment. A solidified prepreg includes a structural layer of electrically conductive fibres and the first external layer of thermoactive resin, with the resin layer including thermoplastic particles and glassy carbon particles.

EFFECT: prepreg provides higher electrical conductivity, mechanical properties and resistance to damage, caused by strikes of lightning.

31 cl, 3 dwg, 2 tbl

FIELD: machine building.

SUBSTANCE: invention relates to manufacture of structural members exposed during operation to high temperatures, and concerns a detail from composite material with ceramic matrix and method of its manufacture. It contains a fibre frame packed with a matrix, formed by multiple layers from ceramics with inclusion of the matrix phase boundary layer deflecting cracks between two adjoining ceramic layers of the matrix. The phase boundary layer includes the first phase from the material capable to promote to deflection of crack, which reached the phase boundary layer according to the first type of propagation in a transverse direction through one of two ceramic layers of the matrix, adjoining with a phase boundary layer, in such a manner that the crack propagation proceeds according to the second type of propagation along the phase boundary layer, and the second phase formed by discrete contact sections, distributed in the phase boundary layer and capable to promote to deflection of the crack, spreading along the phase boundary layer according to the second type of propagation, in such a manner that the crack propagation is deflected and continues according to the first type of propagation in transversal direction through another ceramic layer of the matrix, adjoining with the phase boundary layer.

EFFECT: invention ensures the creation of the detail from composite material with the ceramic matrix with increased life expectancy at high temperatures in corrosive medium.

15 cl, 19 dwg, 2 ex

FIELD: textiles, paper.

SUBSTANCE: fibrous absorber of electromagnetic radiation comprises two inner layers of a mixture of dielectric and electrically conducting carbon fibers which are mechanically fastened to each other by needling. Manufacturing of the absorber is carried out from the mixture of dielectric and electrically conducting carbon fibers, in which carbon fiber is used as electrically conducting carbon fibers. Carbon fiber is used with specific insulation resistance from 1.5·10-3 to 1.0 Ohm cm, and the deviation from the average value of content of carbon fiber in 1 g of the mixture does not exceed 5% by weight. The absorber additionally comprises two outer layers of rubberised fabric. The absorber has the structure of the inner layers of a mixture of dielectric and electrically conducting carbon fibers fixed by piercing with needles with a density of piercing from above of 5÷20 cm-2, from below of 20÷100 cm-2. The absorber layers are made of rubberised fabric, on the edges they are tightly stuck to each other or connected by double-faced adhesive tape.

EFFECT: improving hygienic indicators of garments with volumetric unconnected heat retainers, change in thickness of adequately to change in conditions of the ambient environment, and reduction of specific consumption of valuable heat retainer to obtain the specified thermal insulation properties.

3 cl, 2 dwg, 1 tbl, 3 ex

FIELD: textile, paper.

SUBSTANCE: covering includes a textile element of surface 2 and a layer 1, which on the surface and at least partially is connected to this textile element of the surface. The layer 1 contains a viscoelastic polymer foam. The textile element of the surface 2 has a module of elasticity, the value of which makes from ≥0.5 N/mm2 to ≤2.5 N/mm2. In the layer 1 the viscoelastic polymer foam has deposition hardness, the value of which at 40% of compression makes from ≥1 kPa to ≤10 kPa. In the layer 1 the viscoelastic polymer foam has hysteresis, the value of which at the deposition hardness determination of 40% makes ≥20% to ≤70%.

EFFECT: method of manufacturing includes a foaming operation of the back side of the textile element of surface with the help of a reaction mixture, forming a polymer foam of the layer.

13 cl, 8 dwg

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