Method for producing helicopter tail rotor blade from a composite material

FIELD: aviation.

SUBSTANCE: method for producing helicopter tail rotor blade is in cutting prepregs into workpieces in accordance with the cutting map and a given fibrous filler orientation, packages are completed, the packages are spread on the mandrels, packages are vacuum-processed and pre-pressurized in an autoclave on a mandrel. On the pressurized packages the following is installed: centering loads, anti-icing system, lightning protection wire, and balancing weight. Completed packages are placed in the mould on the silicone rubber mandrel, the mould is closed, the temperature is increased stepwise with definite time, the mould is cooled to the ambient temperature, the part is taken out, and the silicone-rubber mandrel is removed. The inner cavity of finished blade shell is filled with polyurethane by casting under pressure with free foaming.

EFFECT: improved production quality of helicopter tail rotor blade due to obtaining stable blade mass-elastic characteristics.

8 dwg

 



 

Same patents:

FIELD: aircraft engineering.

SUBSTANCE: blade comprises regular part of constant weight and geometrical shape and various replaceable end elements. Adapter pins, minor part of the spar, joint point and connector are arranged at blade regular part. Blade root regular part comprises the following elements. Leading multiple section strap, spar of preset stiffness and weight, top and bottom skin, filler of leading part, filler of trailing part, counter flutter weights, end rib with micro switch, electric conductors, connector and weights provoking the flutter. Replaceable end elements represent a structure composed of top and bottom skin, fastening holes for connection with said adapter pins, LEDs, electric conductors, connector, counter flutter weight and light filler. Proposed method consists in the following. Firs, blade root regular part is made with obligatory precise measurement of extending parts, say, adapter pins and spar end part. Results of measurements are used in making of seats in multiple replaceable end elements differing in weight, side, shape and centering. Now, regular parts are assembled with the help of split screw joint.

EFFECT: various aerodynamic characteristics obtained on the basis of one blade, higher reliability, accelerated testing.

10 cl, 14 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft, in particular, to designs and methods of manufacturing of airscrew blades. Blade (10) of propeller for aircraft turbo-propeller engine includes airfoil structure (20) containing at least one fibre reinforcement obtained by means of three-dimensional thread weaving and compressed by matrix, and shaping part (140) of certain form made of rigid cellular material. The mentioned reinforcement contains at least two sections interconnected by means of continuous weaving at the level of propeller blade front edge (20a), herewith both sections enclose the mentioned shaping part (140). The blade contains beam (150) the first portion (151, 152) of which lays inside the structure and is at least partially enclosed by shaping part (140), and the second part (153, 154) passes outside the mentioned structure and contains blade root (30) at its end. The beam (150) is formed of fibre reinforcement compressed by matrix.

EFFECT: lower propeller blade mass while keeping required mechanical properties.

18 cl, 15 dwg

FIELD: aircraft engineering.

SUBSTANCE: blade with flat or cylindrical point of attachment to screw hub has embedded metallic parts for fastening bolts composed by cylindrical sleeves. Reinforcing fibre bundles extend from said point to envelop said sleeves. Blade surface is composed by woven composite and/or composite containing chopped reinforcing fibre. Proposed method consists, first, in fitting expansion sleeves in the mould. Then, blade surface ply is applied on mould surface and composed of reinforcing cloth or chopped reinforcing fibre and synthetic resin. Now, bundles of reinforcing fibre impregnated with synthetic resin are wound around said sleeves and placed in the mould.

EFFECT: decreased weight, sufficient operating performances.

14 cl, 6 dwg

FIELD: transport.

SUBSTANCE: rotorcraft screw blade comprises stiff jointing insert 1 and spar running from blade root to blade free tip. Jointing inset 1 has top, bottom, front, rear left and right side surfaces 2, 3, 4, 5, 6, and 7. Aforesaid spar comprises succession of fiber layers that retain said insert 1 jointed to blade root. Spar is jointed to top, bottom, front, rear and left side surfaces 2, 3, 4, 5, and 7. Proposed method consists in forming blade spar. First support shaft 8 is jointed to stiff jointing insert 1 reversible jointed to holder 20. Fibers are arranged around assembly comprising jointing inserts 1 and holder 20 to make blade spar. First shaft 8 is removed after spar polymerisation.

EFFECT: simplified production.

16 cl, 3 dwg

FIELD: technological processes.

SUBSTANCE: invention is related to manufacture of items from plastics for aircraft equipment. Method of multichannel blade manufacture consists in installation of glass cloth packets soaked with binding agent into mould. In mould partitions and elastic sacks with releasing accessories are installed. Packets are installed with formation of channels, mould is heated, and pressure is supplied into elastic sacks, which is calculated by formulas for the first and second moulds.

EFFECT: provision of manufacturability of items manufacturing from plastics and increase of items strength.

2 dwg

The invention relates to the design of the propeller blades of aircraft, in particular the blades of the tail rotor of the helicopter, made of composite materials

The invention relates to aircraft and, in particular, concerns the creation of the blades of the propellers of composite materials

The invention relates to the field of wind turbines and can be used in the design and manufacture of wind turbines

FIELD: technological processes.

SUBSTANCE: invention is related to manufacture of items from plastics for aircraft equipment. Method of multichannel blade manufacture consists in installation of glass cloth packets soaked with binding agent into mould. In mould partitions and elastic sacks with releasing accessories are installed. Packets are installed with formation of channels, mould is heated, and pressure is supplied into elastic sacks, which is calculated by formulas for the first and second moulds.

EFFECT: provision of manufacturability of items manufacturing from plastics and increase of items strength.

2 dwg

FIELD: transport.

SUBSTANCE: rotorcraft screw blade comprises stiff jointing insert 1 and spar running from blade root to blade free tip. Jointing inset 1 has top, bottom, front, rear left and right side surfaces 2, 3, 4, 5, 6, and 7. Aforesaid spar comprises succession of fiber layers that retain said insert 1 jointed to blade root. Spar is jointed to top, bottom, front, rear and left side surfaces 2, 3, 4, 5, and 7. Proposed method consists in forming blade spar. First support shaft 8 is jointed to stiff jointing insert 1 reversible jointed to holder 20. Fibers are arranged around assembly comprising jointing inserts 1 and holder 20 to make blade spar. First shaft 8 is removed after spar polymerisation.

EFFECT: simplified production.

16 cl, 3 dwg

FIELD: aircraft engineering.

SUBSTANCE: blade with flat or cylindrical point of attachment to screw hub has embedded metallic parts for fastening bolts composed by cylindrical sleeves. Reinforcing fibre bundles extend from said point to envelop said sleeves. Blade surface is composed by woven composite and/or composite containing chopped reinforcing fibre. Proposed method consists, first, in fitting expansion sleeves in the mould. Then, blade surface ply is applied on mould surface and composed of reinforcing cloth or chopped reinforcing fibre and synthetic resin. Now, bundles of reinforcing fibre impregnated with synthetic resin are wound around said sleeves and placed in the mould.

EFFECT: decreased weight, sufficient operating performances.

14 cl, 6 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft, in particular, to designs and methods of manufacturing of airscrew blades. Blade (10) of propeller for aircraft turbo-propeller engine includes airfoil structure (20) containing at least one fibre reinforcement obtained by means of three-dimensional thread weaving and compressed by matrix, and shaping part (140) of certain form made of rigid cellular material. The mentioned reinforcement contains at least two sections interconnected by means of continuous weaving at the level of propeller blade front edge (20a), herewith both sections enclose the mentioned shaping part (140). The blade contains beam (150) the first portion (151, 152) of which lays inside the structure and is at least partially enclosed by shaping part (140), and the second part (153, 154) passes outside the mentioned structure and contains blade root (30) at its end. The beam (150) is formed of fibre reinforcement compressed by matrix.

EFFECT: lower propeller blade mass while keeping required mechanical properties.

18 cl, 15 dwg

FIELD: aircraft engineering.

SUBSTANCE: blade comprises regular part of constant weight and geometrical shape and various replaceable end elements. Adapter pins, minor part of the spar, joint point and connector are arranged at blade regular part. Blade root regular part comprises the following elements. Leading multiple section strap, spar of preset stiffness and weight, top and bottom skin, filler of leading part, filler of trailing part, counter flutter weights, end rib with micro switch, electric conductors, connector and weights provoking the flutter. Replaceable end elements represent a structure composed of top and bottom skin, fastening holes for connection with said adapter pins, LEDs, electric conductors, connector, counter flutter weight and light filler. Proposed method consists in the following. Firs, blade root regular part is made with obligatory precise measurement of extending parts, say, adapter pins and spar end part. Results of measurements are used in making of seats in multiple replaceable end elements differing in weight, side, shape and centering. Now, regular parts are assembled with the help of split screw joint.

EFFECT: various aerodynamic characteristics obtained on the basis of one blade, higher reliability, accelerated testing.

10 cl, 14 dwg

FIELD: aircraft engineering.

SUBSTANCE: blade of composites is moulded in die to full profile of its outer surfaces. It comprises high-strength structural elements, filler if inner cavities of light materials, balancing weights, heating strap, abrasion-proof binding, fastening elements, aerodynamic cowls and trimmers. Blade features frame-less configuration. Blade structural carcass over its entire length consists of high-strength shell composed by lengthwise stacks of fibrous composite sheets. Blade all inner cavities house fillers composed by inserts of porous materials fitted over its entire length. Inner inserts and abrasion-proof binding arranged on the blade leading edge acts as both structural elements and as temporary elements in fabrication.

EFFECT: simplified design of the blade, minimised tooling, maximum precision of the blade outer geometry.

10 cl, 12 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to turboprops and propellers. Blade (10) comprises structure with aerofoil (20) with two opposite skins (21, 22) produced by 3D braiding of fibrous reinforcing material (100), spar (30) containing fibrous reinforcing material produced by 3D braiding and compacted by female die. Said spar comprises first part (31) extending beyond said structure with aerofoil and can be engaged with driven hub at blade revolution, and second part located inside said structure between two skins (21, 22). Spar (30) second part (32) features depth, in fact, similar to that of skins (21, 22). Fibrous reinforcing material of spar (30) second part (32) has the same braided reinforcement like that of skins (21, 22). Method of blade fabrication comprises making of the first blank of skins and second fibrous spar blank by 3D braiding of threads. Second blank comprises first and second sections. Note here that second section features depth, in fact, equal to that of first blank skin and reinforcement identical to skin.

EFFECT: higher mechanical properties of blades composed of two parts.

18 cl, 20 dwg

FIELD: aviation.

SUBSTANCE: method for producing helicopter tail rotor blade is in cutting prepregs into workpieces in accordance with the cutting map and a given fibrous filler orientation, packages are completed, the packages are spread on the mandrels, packages are vacuum-processed and pre-pressurized in an autoclave on a mandrel. On the pressurized packages the following is installed: centering loads, anti-icing system, lightning protection wire, and balancing weight. Completed packages are placed in the mould on the silicone rubber mandrel, the mould is closed, the temperature is increased stepwise with definite time, the mould is cooled to the ambient temperature, the part is taken out, and the silicone-rubber mandrel is removed. The inner cavity of finished blade shell is filled with polyurethane by casting under pressure with free foaming.

EFFECT: improved production quality of helicopter tail rotor blade due to obtaining stable blade mass-elastic characteristics.

8 dwg

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