RU2747889C1 - Method for repairing honeycomb structure of aircraft and steels for implementing the method - Google Patents

Abstract

FIELD: aircraft construction, aircraft repair.SUBSTANCE: invention relates to aircraft construction and aircraft repair. The method of repairing the unit of the honeycomb structure of the aircraft consists in fixing the position of the units of the unit's hinge plate on the mounting plate (2) of the slipway (1) using the base element (4). In the process of assembling the unit, the spar and ribs are attached to the brackets of the clips, after which the brackets of the clips are successively dismantled and replaced with loose crumbs, which are attached to the spar or ribs. Crackers are connected to each other and attached to the mounting plate of the slipway with clamps to form a rigid frame.EFFECT: improves manufacturability of repairing a honeycomb unit.7 cl, 11 dwg

Description

Technology area

The group of inventions relates to the field of aircraft construction and relate to the process of overhauling units of a honeycomb structure, for example, spoilers, and devices designed to carry out such repairs.

State of the art

There is a known method of sealing an assembly of a honeycomb structure of an aircraft (RF patent No. 2159724, IPC B64C 3/26, B64F 5/00, 11/27/2000, analogue), which consists in the fact that after applying a sealing compound to the connecting seams and joints of the unit parts during For 10-15 minutes, air is sucked from the internal cavity of the unit by connecting it to a vacuum pump. Then the unit is disconnected from the vacuum pump and the necessary requirements for drying the sealing compound are met.

The disadvantage of this method is the likelihood of displacement of parts of the unit during vacuum suction of air, which can lead to distortion of the geometry of the unit. In this case, the required compression of the sides of the filler towards each other is not ensured, which reduces the manufacturing quality of the unit of the honeycomb structure of the aircraft.

There is a known method of assembling an assembly of a honeycomb structure of an aircraft (RF patent No. 2544043, IPC B32B 7/12, 04/27/2014, analogue), in which the connection of the sides of the honeycomb filler sectors with stiffening ribs and with each other is carried out using inserts repeating the shape of the honeycomb cells, and clamps installed from the outer and inner sides of the sectors. In this case, the pressing force in the zone of connection of the honeycomb filler with the stiffeners is determined from the condition of equilibrium of the forces acting in the contact zone of the insert, the honeycomb filler and the stiffening rib. The process of creating the force of pressing the sides of the sectors with honeycomb to each other is provided by pressure.

There is a known method of manufacturing an assembly of a honeycomb structure of an aircraft (RF patent No. 1578971, B64C 9/32, B64F 5/00, 03/20/2005, prototype), including molding the outer and inner panels of the panel from a composite material with the subsequent assembly of a three-layer panel with a honeycomb filler, fabrication of the frame, connection of the unit parts with each other and with the hinge unit. Before laying out the composite material of the outer skin of the panel on the tooling in the shape of the skin, lay out the composite material of the insert and lay a separating film between the outer skin and the insert, and after forming the frame, remove the inserts and remove the separating film between the skin and inserts. After that, the upper and lower cladding, frame and assembly units are connected to each other.

The known methods do not provide control and fixation of the geometric parameters of the honeycomb structure unit, as well as the precise positioning of the hinge units relative to the repaired product and the preservation of their position in space, thus the known methods are not applicable for the repair of honeycomb units with different geometry and position of the hinge unit elements.

Known slipway for the assembly of three-dimensional structures of the aircraft, containing columns with plates attached to them, bearing a system of coordinate-base holes; beams attached to the plates with pins-latches using these coordinate-base holes, glasses with latches and forks with lodges and knife switches fixed in them. Glasses are also fixed on the beams along the coordinate-base holes on the beams' slabs. (author's certificate of the USSR No. 184138, B64F 5/00, 11/18/1974, analogue)

The known slipway is limited in use due to the placement of the base elements, lodges and fixators parallel to the main basic axes of the slipway.

Known device for assembling aircraft compartments, containing a frame mounted on wheel bearings made with the ability to adjust their position in height. The frame contains the means that support and fix the units of the unit during the assembly process. To bring the units of the unit to the mounting position, the device is equipped with a drive swivel unit. The device allows assembling the aircraft compartment with the ability to move the compartment in six degrees of freedom. (RF patent No. 65473, IPC B64F 5/00, 10.12.2007, analogue).

The disadvantage of the known device is the impossibility of using this design for accurate positioning of the product in three-dimensional space

A known slipway for the assembly of three-dimensional structures, consisting of columns on which horizontal beams are installed, having a system of coordinate-base holes for installing lodgments, knife switches and clamps of parts, which are made in the form of swivel fittings that allow installing the forks of the lodgements (knife switches), as well as clamps parts at any required angles and distances to the base axes of the slipway (RF patent No. 69019, IPC B64F 5/00, 10.12.2007, analogue).

The disadvantage of the known building berth is the likelihood of displacement of parts of the unit during thermostating, which can lead to distortion of the geometry of the unit.

The closest in technical essence to the claimed one is a slipway for assembling an aerodynamic control body of an aircraft, including a rectangular mounting frame, a system for basing and fixing the assembled parts of the control body. The basing and fixing system includes a basing unit for a small hinge bracket, a basing unit for a large hinge bracket and means for basing and fixing the aerodynamic body. The bases of the small and large hinge brackets and the locks for the proximal longitudinal edge of the body are located on one side of the frame (base side). Each of the latches includes a base support and means for pressing the housing against this support. (RF patent No. 2509038, IPC B64F 5/00, 03/10/2014, prototype).

The disadvantage of the known device is the impossibility of assembling units having different shapes and configurations, installing fixing and basing units at any required distances and at different angles with respect to the base axes of the slipway.

Disclosure of inventions

The problem to be solved by the invention is to improve the quality of processing of the product during the repair process in order to maintain high performance characteristics of the repaired product.

The technical result consists in ensuring the manufacturability of repairing a honeycomb unit based on maintaining the geometry of the unit at all stages of repair relative to its initial geometric parameters.

The specified technical result is achieved by the proposed method of repairing the unit of the honeycomb structure of the aircraft, including disassembling and flaw detection of the unit parts, and then assembling the unit by connecting the unit parts to each other with the formation of a three-layer panel with honeycomb filler and subsequent fastening of the hinge units. At the same time, before disassembly, the position of the unit's hinge plate is fixed on the mounting plate of the slipway using a base element, the brackets of which are adjusted, ensuring their maximum adherence to the elements of the hinge unit, after which the brackets are fixed to the bar with the formation of a rigid structure. At the same time, before disassembly, the geometric parameters of the honeycomb unit are fixed by fixing the position of the unit on the mounting plate of the slipway with the help of stops and clamps, the brackets of the clamps are adjusted for a snug fit of the pressing end of each bracket to the surfaces of the spar and ribs of the unit and are fixed in the tuning position. In the process of assembling the unit, the spar and ribs are attached to the brackets of the clamps fixed in the tuning position, after which the brackets of the clamps are successively dismantled and replaced with loose breadcrumbs, which are attached to the spar and ribs. Then the crackers are connected to each other and attached to the mounting plate of the slipway with clamps to form a rigid frame.

The specified technical result is achieved when using the proposed slipway for repairing a honeycomb structure unit containing a mounting plate on which an insert is installed, a base element made with the possibility of fixing the position of the unit's hinge plate on the mounting plate, stops and clamps made with the possibility of fixing the position of the unit on the mounting plate. stove. In this case, the locating element and the latches contain brackets mounted on the adapter strips with the possibility of displacement along the strips. The brackets of the clips contain guides and set screws to ensure a snug fit of the clamping ends of the brackets to the surfaces of the ribs and the spar, and the brackets of the base element contain guides and set screws for maximum adhesion to the hinge nodes and fixing their position by fixing the brackets placed on the bar to form a rigid structure. In addition, the construction of the slipway includes crackers installed on the side of the ribs and the spar during assembly and secured with clamps. Inset crackers are designed to fix the geometric parameters of the ribs and spar and to protect the ribs and spar from deformations.

The proposed method and device relate to devices for the repair of honeycomb aggregates designed to create aerodynamic force. These units can have different shapes, sections in planes, angles of inclination of the side surfaces, as well as different locations of the hinge units. The use of brackets installed on the adapter plate in the structures of the base element and retainers makes it possible to repair honeycomb aggregates with different geometries and positions of the hinge assemblies.

During the repair process, the control and fixation of the geometric parameters of the parts of the honeycomb unit are carried out, which are the linear dimensions of the parts, their location in space and relative to each other, control and fixation of angular values, the location of the hinge units.

Due to the precise positioning of the honeycomb unit during the repair process and the control of its geometric parameters, the high performance characteristics of the repaired product are preserved.

In addition, the location of the base element, stops and pile stops on the mounting plate provide unhindered access for the maintenance personnel to the units and parts of the unit.

Thus, the proposed method and device provide the manufacturability of repairing a honeycomb structure and the ability to repair honeycomb aggregates having different shapes and configurations, installing the hinge assemblies on the aggregates at any required distances and at different angles with respect to the base axes of the slipway.

Brief Description of Drawings

The inventions are explained by the description of a specific example of implementation and the attached graphic materials, where:

figure 1 shows a General view of the slipway;

fig. 2 - fixing the position of the hinge units;

fig. 3 - bracket for the base element of the hinge unit;

fig. 4 - fixing the spatial position of the spar and ribs of the unit;

fig. 5 - spar lock;

fig. 6 - bracket for the side member retainer;

fig. 7 - rib retainer;

fig. 8 - bracket for the rib retainer;

fig. 9 - a set of crackers for the spar;

fig. 10 - a set of rusks for ribs;

fig. 11 - fastening to the spar and ribs of crackers with the formation of a rigid frame during assembly of the unit.

Implementation of the invention

A slipway for repairing a unit of a honeycomb structure 1 of an aircraft contains a mounting (base) plate 2, which serves as the main bearing element of the structure, on which inserts 3, a base element 4, stops 5, clamps 6, clamps of ribs 7 and a spar lock 8 are installed (Fig. one).

To ensure thermal conditions of technological operations, minimize the weight of the structure, ensure the required rigidity and geometry, as well as optimize the manufacturing process using mechanical processing methods, a heat-strengthened wrought aluminum alloy (D16T), which has a chemical composition in accordance with GOST 4784-97, was selected as the material for the execution of mounting plate 2 ... Due to its low heat and electrical conductivity, this material performs well at temperatures above 120 ° C and up to 250 ° C.

Inserts 3 are designed to compensate for the relief of the upper and (or) lower casing 9 of the unit and are made to ensure that the planes of the casing 9 adhere to the mounting plate 2 to prevent warping of the casing during repair. In the inserts 3 and the mounting plate 2, grooves are made for installing thermocouples to control the technological process of gluing with temperature control.

The base element 4 provides the spatial orientation of the hinge assemblies 10 relative to the surface of the unit of the honeycomb structure 1 (Fig. 2), namely, rigid fixation of the position of the hinge assemblies 10 on the mounting plate 2 prior to the start of dismantling works.

In the proposed embodiment, the base element 4 contains at least two brackets 11 (Figs. 2, 3) installed on the adapter plate 12 in accordance with the location of the hinge assemblies 10 by placing the projections of the brackets 11 provided for this in the corresponding tapered holes 13 made according to the entire working surface of the adapter plate 12. The number of brackets 11 presented in the proposed embodiment is not limiting the invention. Evenly made tapered holes 13 allow the brackets 11 to be positioned optimally on the bar, depending on the location of the elements of the attachment assemblies 10 on the unit 1.

The design of each bracket 11 (Figs. 2, 3) ensures accurate positioning of the hinge assemblies 10 relative to the item being repaired and the preservation of their position in space, which makes it possible to orient the remaining parts during the repair process and to identify possible deviations in the overall geometry of the item if they occur. For this, the design of the bracket 11 provides a guide 14, on which the bracket 11 is installed with the possibility of a slight shift along the axis of the adapter plate 12 within the adjacent tapered holes in the bar 12. In addition, the set screws 15 provided for fastening the bracket 11 to the elements of the hinge assemblies 10 are placed in the grooves, which also allows for precise positioning.

On the side of the end stringer 16, ribs 17 and the spar 18 of the unit 1, stops 5 are installed (Figs. 1, 2), which serve to align the unit during the initial installation with respect to the mounting plate 2, as well as to securely fix the location of the unit 1, if it is removed from slipway, and placement of new plating if necessary.

The slipway contains a set of clamps 7 and 8, designed to secure the position of the unit 1 on the mounting plate 2 in order to prevent displacement and rotation during the technological process. Clips 7 and 8 do not carry a power load.

In the proposed embodiment, the latch 8 of the spar 18 contains four brackets 19 (Fig. 4, 5, 6) mounted on the transition strip 20 by placing the projections provided for this on the guide 21 of the bracket 19 in the corresponding tapered holes 22 made over the entire working surface of the transition strips 20. The number of brackets 19, presented in the proposed embodiment, is not limiting the invention, and, if necessary, can be increased or decreased depending on the geometry of the unit being repaired. The guides 21 and set screws 23 of the brackets 19 provide a slight shift of the clamping end of the bracket 19 adjacent to the spar 18 along the longitudinal axis of the strip 20 and directions orthogonal to the longitudinal axis of the strip 20, thereby forming a tight fit of the clamping end of the bracket 19 to the surface of the spar 18 and creating an optimal interface each bracket 19 of the retainer 8 to the surface of the spar 18 to maintain the localization of the spar 18 relative to its original position in the event of its complete replacement.

In the proposed embodiment, each retainer 7 of the ribs 17 contains at least two brackets 24 (Fig. 4, 7, 8) mounted on the adapter plate 25 by placing the projections provided for this on the guide 26 of the bracket 24 in the corresponding tapered holes 27 made along the entire working surface of the transition bar 25. The number of brackets 24, presented in the proposed embodiment, is not limiting the invention, and, if necessary, can be increased depending on the geometry of the unit being repaired. The guides 26 and set screws 28 of the brackets 24 provide a slight shift adjacent to the rib 17 of the end of the bracket 24 along the longitudinal axis of the bar 25, in directions orthogonal to the longitudinal axis of the bar 25, as well as rotation around the central set screw 29 of the bracket, thereby forming a tight fit of the end surface bracket 24 to the surface of the rib 17 at a certain angle, thereby achieving optimal coupling of each bracket 24 of the fixator 8 to the surface of the rib 17 and maintaining the localization of ribs 17 relative to the original position in the event of their complete replacement.

The slipway contains a set of crackers 30 and 31 for ribs 17 and spar 18, respectively (Fig. 9, 10), installed on the side of ribs 17 and spar 18 and protecting them from deformation during gluing using thermostatting.

To fix the position of the unit 1 on the mounting plate 2 and to eliminate the likelihood of its accidental displacement, clamps 6 are used, evenly located on the horizontal flanges of the spar and ribs of the unit 1 on the sides of the ribs 17 and the spar 18. In this case, the mentioned crackers 30 and 31 of the ribs 17 and the spar 18 serve, inter alia, as a supporting surface for the clamps 6 (Fig. 11).

The number of brackets 11, 19 and 24, stops 5 and clamps 6 is determined taking into account the geometry of the unit being repaired 1.

Mounting plate 2 of the slipway at the time of locksmith operations is installed along the technological holes on the assembly table. If necessary, during dismantling and installation operations, power fastening is provided by means of clamps 6.

Before the initial installation of the unit on the slipway, rivets are removed from the side of the outer skin, as well as all other fasteners and hardware. From the side of the upper casing, dismantle all fasteners of the hitch assemblies.

Initially, the unit 1 is placed on the mounting plate 2 on the upper skin 9 (Fig. 2). Before placing the unit 1, insert 3 is installed on the mounting plate 2, the size of which is determined depending on the supporting surface of the unit. On the side of the end stringer 16, stops 5 are placed on the mounting plate 2, along which the likelihood of displacement of the product is limited. After placing the unit 1 on the mounting plate 2, stops 5 are also installed on the sides of the ribs 17 and the spar 18, fixing the position of the edges. After installing and securing the stops 5, the unit 1 is pressed with the clamps 6 to the mounting plate 2 to eliminate the likelihood of its accidental displacement.

From the side of the hinge unit 10, a base element 4 is installed on the mounting plate 2, the brackets 11 of which are adjusted for each hinge unit 10 to ensure maximum adherence to the elements of the hinge unit 10. The position of the unit hinge unit 10 of the unit is fixed by fixing the brackets 11 placed on the strip to form a rigid constructions. The fixation of the hinge nodes 10 is carried out in accordance with the fundamental rules of basing - the presence of a base point and a force closure along each of the spatial axes for each detail of the node. The base element 4, together with the elements of the hinge assemblies 10 fixed on it, is dismantled from the mounting plate 2, marked and removed from the working area.

On the side of the spar 18, a retainer 8 is installed (Fig. 4), the brackets 19 of which are adjusted for a snug fit of the pressing end of each bracket 19 to the surface of the spar 18, which is fixed with a screw connection through the technological holes.

On the side of the ribs 17, a clamp 7 is installed, the brackets 24 of which are adjusted for a snug fit of the pressing end of each bracket 24 to the surface of the ribs 17. The fit is fixed with a screw connection through the technological holes.

Brackets 19 and 24 of the clips 8 and 7 of the positions of the spar 18 and ribs 17 and are fixed in the tuning position using the set screws 23, 28, 29. After that, the adjusting screws that secure the brackets 19 and 24 to the spar 18 and the ribs 17 are removed. 7 are dismantled from the mounting plate 2, marked and removed from the working area.

Next, disassembly and flaw detection of unit 1 parts are carried out. Thanks to the system of stops 5 and clamps 7 and 8, unit 1 at the stage of disassembly and flaw detection can be removed from the slipway without losing information about its basic location.

The assembly of the unit 1 is performed in the reverse order: along the stops 5 on the mounting plate 2, the casing 9 is placed (Fig. 4). The spar 18 and ribs 17 are fastened with screw connections through the technological holes to the brackets 19 and 24 of the clamps 7 and 8. The brackets 19, 24 are dismantled one at a time, as the brackets are removed, each of them is replaced with an insert cracker 31, 30 (Fig. 11). Crackers 31, 30 are attached to the spar 18 and ribs 17 with a screw connection through the technological holes, interconnected and fastened to the mounting plate 2 with clamps 6. When the crackers are fastened, a rigid frame is formed to prevent displacement of parts of the unit 1 or their deformation during thermostating when connecting parts unit between each other.

After complete fixation of the assembled product, glue and a foaming adhesive composition are applied to the joints of the spar 18, ribs 17 and upper skin 9, honeycomb filler is placed, then the process of honeycomb filler gluing is carried out. After gluing, the honeycomb core is machined to fit the sheathing plane.

Then the lower casing and the reinforcement are installed on the product, covering the joints of the parts with glue, and the gluing process is repeated with thermostatting on the ACR-3 HotBonder equipment. After that, the elements of the hinge assemblies 10 are fixed by bolting and riveting in accordance with the spatial geometric information about their location. Rivets are installed at the joints of the power elements and the rivet joint is sealed. The finished product is primed and painted.

Thus, the slipway proposed for protection ensures the achievement of the claimed technical result - ensuring the manufacturability of the repair of the honeycomb structure unit.

Claims (7)

1. A method of repairing a unit of a honeycomb structure of an aircraft, including disassembling and flaw detection of unit parts, and then assembling the unit by connecting the unit parts to each other with the formation of a three-layer panel with a honeycomb filler and subsequent fastening of the hinge units, characterized in that before disassembly, the position of the units is fixed hinging the unit on the mounting plate of the slipway using a base element, the brackets of which are adjusted, ensuring their maximum adhesion to the elements of the hinge units, after which the brackets are fixed to the bar with the formation of a rigid structure; before disassembly, the geometrical parameters of the honeycomb unit are fixed by fixing the position of the unit on the mounting plate of the slipway with the help of stops and clamps, while the brackets of the clamps are adjusted for a snug fit of the clamping end of each bracket to the surfaces of the spar and ribs of the unit and are fixed in the tuning position during the assembly process of the unit, the spar and ribs are attached to the brackets of the clamps fixed in the tuning position, after which the brackets of the clamps are sequentially dismantled and replaced with loose crumbs, which are attached to the spar or ribs, then the crackers are connected together and fixed to the mounting plate of the slipway with clamps to form a rigid frame. 2. A repair method according to claim 1, characterized in that the number of brackets, stops and clamps is determined taking into account the geometry of the unit being repaired. 3. A slipway for repairing an aggregate of a honeycomb structure, containing a mounting plate on which an insert is installed, a base element made with the possibility of fixing the position of the unit hinge of the unit on the mounting plate, stops and clamps made with the possibility of fixing the position of the unit on the mounting plate, characterized in that which contains crackers installed on the side of the ribs and the spar and fixed with clamps, designed to fix the geometric parameters of the ribs and the spar and protect the ribs and the spar from deformations, while the base element and clamps contain brackets installed on transition strips with the possibility of displacement along the strips, brackets retainers contain guides and set screws to ensure a snug fit of the clamping ends of the brackets to the surfaces of the ribs and the spar, and the brackets of the base element contain guides and set screws for maximum adhesion to the hinge nodes and fixing their position by fixing the brackets placed on the strip with the formation of a rigid structure. 4. A slipway according to claim 3, characterized in that the brackets are installed on the transition bars by placing the projections of the brackets in the tapered holes made on the working surface of each transition bar. 5. A slipway according to claim 3, characterized in that the inserts are made to ensure that the sheathing planes adhere to the mounting plate. 6. A slipway according to claim 3, characterized in that grooves are made in the inserts and the mounting plate for installing thermocouples. 7. A slipway according to claim 3, characterized in that the mounting panel is made of heat-strengthened deformable aluminum alloy D16T.

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