FR2463310A1 - PROCESS FOR PROCESSING A RING-LIKE OR SHEATH-CONTAINING ELEMENT FOR FASTENING TUBULAR PIPES OR OTHER SIMILAR ELEMENTS IN MACHINES, APPARATUS OR OTHER ASSEMBLIES, IN PARTICULAR AIRCRAFT; SHEATH OBTAINED ACCORDING TO THE SAID METHOD AND DEVICE FOR IMPLEMENTING SAME - Google Patents

Abstract

PROCESS FOR TREATING AN ELASTIC HOLDING ELEMENT IN THE FORM OF A RING OR SHEATH FOR THE FIXING OF TUBULAR DUCTS OR OTHER SIMILAR ELEMENTS IN MACHINES, APPLIANCES OR OTHER ASSEMBLIES, IN PARTICULAR AIRCRAFT; SHEATH OBTAINED ACCORDING TO THE ABOVE PROCESS AND DEVICE FOR ITS IMPLEMENTATION. BEFORE FITTING, THE HOLDING ELEMENT 5 IS AXIALLY STRETCHED, HAVING THE PROPERTY OF CONTRACTING AXIALLY IN THE EVENT OF HEATING, IT IS HEATED AT THE SAME TIME AND THEN COOLS IT IN STRETCHED CONDITION, WHICH IT WILL THEN KEEP , THEN AFTER THE INSERTION OF THE TUBE 2 TO BE FIXED AND OF THE HOLDING ELEMENT 5 IN THE INTERESTED STRUCTURE 1, WE HEAT THE HOLDING ELEMENT 5, SO IT ALSO CONTRACTS AXIALLY THUS INCREASING THE THICKNESS OF THE WALL . PREFERRED APPLICATION IN AIRCRAFT.

Description

Method of treating a ring-shaped elastic holding member

  or sheath for the fixation of pipes

  tubes or the like in machines,

  similar or other sets, including aircraft.

  The present invention relates to a method of treating an elastic holding member in the form of a sheath, a tube

  or ring possessing the technological property of contracting

  radially in the event of overheating in order to fix tubular conduits, pipe guides or similar machine elements in apparatus, machines or

  vehicles, including aircraft or aircraft cells.

  In the construction of machines and apparatus, sheath-like sheaths are used for coating cables and groups of electric lines, which are particularly useful for preventing lines from mechanical damage. Since moving vehicles are subject to continuous shaking and vibration often causing a "migration" of the protective envelopes out of the area so disturbed if the line groups are placed in space and also given that said envelopes slip during the drawing of the envelopes. lines through them, we have developed so-called contractile sheaths, which have the property of tightly surrounding the bundle of cables by eliminating any possibility of sliding. To mount such contractile sheaths, or they are put on the bundle of cables before its introduction, then heated to about 200-2500C, so that they contract and fix tight assembly on said beam, or we simply put the sheaths on the beam before its mioeen place and we put them in this state at the same time as this

  last to treat them hot only at their final position.

  As already mentioned, these contractile sheaths * offer the advantage of resting without sliding on their support and to protect it from any deterioration; they

  do not fulfill any other purpose.

  In the construction of aircraft, especially in the case of vehicles or aircraft, another problem than that of external mechanical protection of cable bundles lies in the laying of electric lines or flexible fuel lines through more or less extensive areas. of

  the airframe and in their stowage in

  It is difficult to accommodate narrowly restricted spaces and accessibility because of the very different structural or functional arrangements that leave other building elements with only limited heights available for insertion. The arrangement of these areas for laying the aforementioned flexible supply lines

  often by means of guided tubes

  lines or curved in the space which, not only, are of a painful pose during the assembly, but also must be fixed at the cost of a long time to the frames or to other

supports.

  The subject of the invention is therefore a method for

  both to pose and to fix in areas that are difficult to access

  including the internal structure of the airframe of an aircraft, tubular pipes of various types and destinations in a simple manner with regard to mounting and inexpensive with all guarantees of good operation and long-term

of life.

  This process is based on the use of the sheath

  usual tile of the aforementioned kind or sections of such a sheath

  in holding elements for fixing a tubular conduit

  or a guide tube and is characterized in that it is stretched in the axial direction, in particular on a mandrel of corresponding shape, such a holding member before its introduction, it is heated during this operation and then cools it in the stretched state, which it will retain after this cooling, and after the insertion of the machine part or the guide tube to be fixed and the holding element into the machine or the cell of the aircraft in question, said holding element is heated, so that it contracts not only radially inwards, but also, advantageously, simultaneously in the axial direction, which increases its wall thickness by radial direction outwards. If the holding element is arranged in an opening, a structural part, a membrane or a flange fixed in the cell, calibrated so that in case

  heating, the extension in the radial direction towards the ex-

  is greater than the clearance between the outer diameter of the holding member prior to heating and the inner diameter of. the opening of the structural part, the holding element and, with it, the guide tube are clamped in said opening of the part

of structure considered.

  The method according to the invention therefore gives the known contractile sheath holding element a new dimension of use with regard to its technical function of fixing and is of a safe and easy to apply operation.

as for the assembly.

  It is particularly economical to treat a relatively long section of sheath according to the invention, that is to say to stretch it axially on a corresponding mandrel by heating it at the same time and to let it cool down to the state stretched, then divide the section thus treated into other shortened sections to the extent appropriate to be

  used as holding elements in the sense of the invention.

  The treatment temperature is advantageously set between 200 and 2500 ° C. and the drawing is approximately 50% of the length.

initial material.

  The invention will be better understood by means of the description

  DETAILED DESCRIPTION OF AN EMBODIMENT TAKEN AS NON-LIMITING EXAMPLE AND SHOWN IN THE APPENDIX BRIEFLY, FIG. 1 is an elevational view of a guide tube fastened according to said invention by holding elements in fixed parts of 'a cell; Figure 2 is a plan view of the same guide tube; Figure 3 is a sectional view along the line III-III of Figure 1; FIG. 4 is a sectional view according to FIG. IV-IV of FIG.

Figure 3.

  It is proposed to arrange and fix inside a hard to reach area of an aircraft cell structure 1 a guide tube 2 curved in space. This tube passes through, as seen in particular in Figure 3, openings 3 of corresponding dimensions formed in elements, or flanges, fixed to the cell. An element of

  previously treated according to the process according to the invention.

  The outer circumference of the guide tube is inserted between the outer periphery of the guide tube and the inner periphery of each opening 3. The holding elements 5 are heated into these openings 3.

  and they then contract, both radially towards the

  than axially, hence a strengthening of their wall thickness and an increase in their diameter in the radial direction towards the outside. It can also be formed, during the contraction in the axial direction of the holding element, as seen in FIG. 4, with a bead on each side, which also results in an assembly of shapes in the axial direction. . By the radially extending extension the clearance chosen between the outside diameter of the holding element introduced and the inside diameter of the opening 3, a secure and firm base of the holding elements 5 is obtained, and consequently also guide tubes 2 inside the cell structure. The holding elements 5 can be mounted on the guide tube 2 before the introduction of the latter, but they can also, according to the given conditions of this implementation, be slipped or threaded onto said tube of guidance 2 only after mounting inside the

structure. -

  As can be seen in FIG. 4, the openings 3 may, according to another characteristic of the invention, be provided with a coating that protects the holding elements 5, or with a protective edge 6 that preserves mechanical deterioration. the holding elements 5, during the contraction of said holding elements, by an increase in their bearing surface. This edge protection only becomes imperative

  if the openings 3 are in sheet metal parts

  flanges, gussets, etc.- of relatively small thickness.

2 463310

Claims (2)

  1. A method of treating an elastic holding member   in the form of sheath, tube or ring possessing the technological property   to shrink radially in the event of heating in order to fix tubular conduits, pipe guides or similar machine elements in apparatus, machines or vehicles, especially aircraft, characterized in that the the holding element (5) is stretched axially, in particular on a mandrel of corresponding shape, before it is put in place, heated during this operation and then cooled in the stretched state, which it will retain. after this cooling, and then after the insertion of the machine part or guide tube (2) to be fixed and the holding element (5) in the machine or the aircraft cell (1) in question , heating said element   maintaining (5), so that at the same time it also contracts   axial rection, which increases its radial wall thickness. * 2. Process according to Claim 1, characterized in that the treatment temperature of the holding element (5) or the sheath is adjusted to approximately 200-2500 ° C and the drawing in the axial direction to approximately 50%. the initial length of the holding member (5). 3. Sheath cooled in the stretched state, possessing the properties   of the holding element according to the preamble of the   - claim 1 and obtained according to the method of one of the claims   1 or 2, characterized by the fact that before it is put in place it has a length that is multiple to that of a holding element (5) to be used and that it is divided into several sections of a corresponding length   to that of the holding elements (5) to be used.   4. Arrangement of the holding element according to claim 1, characterized in that the openings (3) in the housing of the machine or in the airframe (1), if any in relatively thin sheets, comprise, for the support elements (5), a coating or a ring edge protection (6).