WO2013020664A1

WO2013020664A1 - Reaming and/or milling device and reaming and/or milling method for an undercarriage of an aircraft

Info

Publication number: WO2013020664A1
Application number: PCT/EP2012/003255
Authority: WO
Inventors: Michael Kriegel; Mehmet Soylu; Thomas Beckmann
Original assignee: Lufthansa Technik Ag
Priority date: 2011-08-08
Filing date: 2012-07-31
Publication date: 2013-02-14
Also published as: DE102011110530A1; DE102011110530B4

Abstract

The invention relates to a reaming and/or milling device (1, 2) for an undercarriage (3) of an aircraft, wherein the reaming and/or milling device (1, 2) comprises a clamping ring (4) which can be pushed onto the undercarriage (3), and wherein the clamping ring (4) has a plurality of openings (5) and the undercarriage (3) can be machined through at least one of the openings (5).

Description

Friction and / or milling device and method

for a landing gear of an aircraft

The invention relates to a friction and / or milling device for a chassis of an aircraft with the features of the preamble of claim 1 and a corresponding friction and / or milling method having the features of the preamble of claim 11.

Landing gear of aircraft are subject in operation a variety of physical and chemical loads. To ensure that they do not fail during operation, they are - like many other aircraft components - maintained at regular intervals. In the course of maintenance, minor and major signs of wear are treated, so that the chassis then again meets all quality and safety requirements for use. In the course of the suspension maintenance, various friction and milling procedures are performed on the chassis for repair purposes.

In some cases, the landing gear may need to be serviced sooner than expected. For example, when detected in a standard aircraft inspection damaged areas, such as corrosion in holes.

Even minor damage, for example in fastening or bearing points, can cause the landing gear to be removed from the aircraft and to be removed for repair or maintenance, for example in the hold of a ship or aircraft.

CONFIRMATION COPY talking equipped maintenance operation is transported. Due to the high demands made on the machining quality of chassis components, even the processing of small damaged areas, for example by rubbing and / or milling, can not be done without complete removal and transmission of the landing gear.

However, this process can take several days. In the maintenance operation, the landing gear is made airworthy again and then the landing gear is transported back to the aircraft. The costs of an unexpected maintenance case are very high, since in addition to the transport costs incurred often no use of the aircraft in the meantime is possible.

The invention is accordingly based on the object to provide a friction and / or milling device for a chassis of an aircraft and a corresponding method, which allow editing a chassis with high quality and reduced costs, preferably on the aircraft.

The invention solves this problem with the features of the independent claims. To solve the problem, a friction and / or milling device for a landing gear of an aircraft is proposed, wherein the friction and / or milling device comprises a clamping ring which can be pushed onto a part of the chassis and wherein the clamping ring has a plurality of openings, wherein At least one of the openings can be used to process the part.

For example, the clamping ring is pushed onto a cylindrical section of an aircraft landing gear, the so-called "main fitting", and then fixed in its position Even small, imprecise machining operations can sometimes lead to the entire chassis not being usable anymore. The fact that the machining of the chassis is done by at least one opening in the clamping ring, can be worked very precisely. As a result, it is possible to work on a chassis, which may preferably still be on the aircraft. As a result, the transport and breakdown costs of the chassis or the aircraft can be reduced or avoided.

The tools used can additionally be reinforced by the clamping ring and, for example, limited or guided in their movement by the locking pins described in the following and / or the auxiliary positioning device in such a way that meets the high demands on the machining quality.

Advantageously, the clamping ring is pushed onto a part of the chassis while the landing gear is firmly connected to the aircraft.

Preferably, the friction and / or milling device Absteckbolzen and the clamping ring a plurality of circular openings running, the circular openings are positioned over holes in the chassis and by inserting the Absteckbolzen through the circular openings in the clamping ring in the holes in the chassis fixing the clamping ring the suspension is possible. The openings in the clamping ring are thus preferably adapted to the holes in the chassis. The locking pins are inserted through preferably three holes in the clamping ring in three holes in the chassis, so that the clamping ring is firmly connected to the chassis and is fixed. Through another hole in the clamping ring can be a precise machining of the chassis, especially a hole in the chassis done. Preferably, the clamping ring comprises at least three circular openings, which lie in a first component plane, and additionally at least three further circular openings, which are arranged in an overlying or underlying second component level. Through the circular openings of the clamping ring - as already described - be fixed, while three fixing points are advantageous in order to avoid blurring or slipping during processing. The second row of holes allows the clamping ring to be compatible with different spacing holes in the chassis, therefore, at least some of the holes in the second component plane are offset from the holes of the first component plane. This is due to the fact that there are typically different hole configurations or spacings at different locations of the chassis. The holes of each component plane thus form the individual holes in the part of the chassis to be machined, wherein the holes can be used, if necessary, to different hole configurations of two different parts of the chassis.

Preferably, the plurality of openings in the clamping ring is arranged such that four of the openings can be positioned simultaneously via four holes in the chassis. A positionability of four holes is advantageous because the clamping ring can be fixed by three holes with Absteckbolzen and through the fourth hole in the clamping ring, the underlying hole in the chassis can be edited.

Preferably, the friction and / or milling device has an auxiliary positioning, which is firmly connected or connectable to the clamping ring and fixed by the used friction or milling equipment for use on the chassis and / or can be positioned. The auxiliary positioning device can be, for example, a holding guide, which makes it possible to protect an inserted reamer from wobbling or tilting. The holding guide is therefore preferably placed at the opening in the clamping ring, which is located above a hole to be machined in the chassis. For example, by means of an inserted reamer through the opening in

Clamping a hole in the chassis are machined, the reamer is guided by the holding guide and centered.

Preferably, four openings in the clamping ring are simultaneously positioned over four holes in the chassis when the clamping ring is pushed rotated by 180 °, said 180 ° rotation is a rotation about an axis perpendicular to the central axis of the clamping ring. After rotation, the tension ring is pushed "head over", ie, with its other face first, The positionability of four openings in the tension ring over four holes in the landing gear in "overhead" pushed tension ring is advantageous because it allows each the four holes of different hole configurations of two different parts of the chassis in the chassis can be edited without a further clamping ring is required.

Otherwise, not every hole may be processed with the same quality. For example, if the holes in the chassis do not have the same distance from each other, a sufficient fixation of the clamping ring is difficult. It could happen in this case that in addition to the hole to be machined only one or two other holes in the clamping ring can be positioned over holes in the chassis and thus only one or two Absteckbolzen could be used for fixation. Accordingly, it is advantageous if the clamping ring so is designed so that always four holes in the clamping ring can be positioned over four holes in the chassis. By means of the "overhead" installation, holes can be worked on in some suspensions, which would otherwise require a further clamping ring with a different hole spacing be used.

Preferably, the clamping ring comprises four circular openings, each of the four openings being at a distance of about 85 ° to another of the four openings. Preferably, the clamping ring comprises four further circular openings in a second component level, wherein each of the four further openings to another of the four further openings has a distance of about 85 °. This particular distance of the openings is suitable for the hole spacing of certain suspensions. With reference to the figures 8 to 11 further preferred hole spacings will be explained later.

For some applications, it may be advantageous if the clamping ring is formed by two interconnected half-rings.

To solve the problem, a friction and / or milling method is proposed on a landing gear of an aircraft, wherein the method comprises at least the following steps: a) pushing a clamping ring on the chassis and then fixing the clamping ring on the chassis; b) Performing a friction and / or a milling treatment on the chassis, wherein the machining of the chassis is performed by at least one opening in the clamping ring; c) Loosening and removing the clamping ring from the chassis.

The steps a), b) and / or c) are advantageously carried out while the landing gear is firmly connected to the aircraft.

Due to the fixation by the clamping ring and the machining of the chassis through an opening in the clamping ring, the friction and / or milling method can be performed directly on the part of the chassis, preferably without this has to be separated from the aircraft.

Preferably, the steps a), b) and c) are performed at least twice in succession, wherein the clamping ring for the second implementation is rotated by 180 °, and wherein this 180 ° rotation is a rotation about an axis perpendicular to the central axis of the clamping ring. As already described, it may be necessary for certain suspensions, postpone the clamping ring "over head ^M , so that enough circular openings can be positioned in the clamping ring via corresponding holes in the chassis. In this way it is possible, for example, to move an auxiliary positioner fixedly connected to the clamping ring into the desired position, so that, for example, damaged areas on all holes in the chassis can be repaired. The circular openings of the first component plane are at least partially offset from the circular openings of the second component plane. Preferably, in the course of step b), first a manual friction method using a reamer on a hole in the chassis and then a manual milling method, in which a preferably 45 ° bevel is milled at the hole. This procedure is particularly well suited to remove unwanted corrosion from holes in the chassis, as described in detail in the following embodiment.

The invention will be explained below with reference to preferred embodiments with reference to the accompanying figures. Showing:

1 shows a friction device in an isometric view, FIG. 2 shows the friction device in a plan view, FIG. 3 shows a sectional view of the friction device, FIG. 4 shows a milling device in an isometric view, FIG. 5 shows the milling device in a plan view, FIG FIG. 7 a side view of the milling device, FIG.

8 is a sectional view of the friction device in a first component level,

Fig. 9 is a sectional view of the friction device in a second component level, 10 is a sectional view of the milling device in a first component level,

11 is a sectional view of the milling device in a second component level.

Figures 1 to 3 show a friction device 1, which is pushed onto a part of a chassis 3 - the so-called "main fitting" - in this example it is a nose landing gear of an aircraft type A 330 or A 340.

The friction device 1 comprises a clamping ring 4, whose inner diameter is slightly larger than the outer diameter of the chassis 3 and which can be firmly connected by means of Absteckbolzen 7 with the chassis 3. The friction device 1 also includes an auxiliary positioning device 10, which is designed as a holding guide 11 in this embodiment.

In the holding guide 11, a reamer 9 is arranged displaceably, which is guided by the holding guide 11 and with a hole 6 in the chassis 3 is processed. In this embodiment, a plurality of holes 6 of the chassis 3 corrosion, which should be removed by rubbing and milling or turning.

FIGS. 4 to 7 show a milling device 2 which, as a rule, is pushed onto the same chassis 3 following the rubbing operation which is carried out with the friction device 1. It is fixed in the same way with Absteckbolzen 7, which are inserted through openings 5 in the clamping ring 4 in holes 6 in the chassis 3. Both the friction and the milling device 1,2 are fixed with three Absteckbolzen 7 on the chassis 3. A fourth hole 6 in the chassis 3 is through edited the associated opening 5 in the clamping ring 4. In order to machine further holes 6, the clamping ring 4 is rotated about its central axis 8 - or, if necessary, pulled off and pushed back "upside down." Due to the arrangement of the openings 5 in the clamping ring 4 described later, it is thus possible for chassis types With a corresponding hole configuration, a precise machining of all holes 6 is made possible.

The milling device 2 comprises in this embodiment, a clamping device 15 which is installed within the chassis 3. By the clamping device 15, which is supported on the inside of the chassis 3, and through the hole to be machined 6, a pilot 14 is inserted, on which in turn a rotary device 13 is attached. The pilot 14 serves to center the rotary device 13. The pilot 14 rotates around

Cutting tool and thus allows the material removal. After cocking the pilot 14, the rotary device is placed over the pilot 14. In the rotating device 13, the cutting tool is screwed. The cutting tool defines the clamping height of the rotating device 13 above the hole 6. The rotating device 13 is additionally guided by an additional auxiliary positioning device 10, which is designed here as a rotary device holder 12. The rotating device 13 allows a cutting material removal by rotation of the cutting tool.

By the described milling arrangement, a hole 6 can be machined with sufficient precision, for example, a hole 6 is then provided to the rubbing with a preferably 45 ° chamfer, the chamfer preferably by hand as described above, in particular by means of the rotary device 13 is milled. FIGS. 8 to 11 show sections through in each case two component planes of the friction device 1 (FIGS. 8 and 9) and the milling device 2 (FIGS. 10 and 11). The clamping ring 4 has a flattening 17 for both the friction device 1 and the Fräsvorrich device 2. Through the opening 5 at this flattening 17, the machining of the chassis 3 takes place. In both cases, the processing unit is attached to this side. Accordingly, since the processing apparatus can be used only at one of the many openings 5 in this embodiment, the clamping ring 4 must be rotated when a hole 6 at this hole is to be processed. This would be easily possible if the hole spacing in the chassis 3 and in the clamping ring 4 regularly, for example, always 90 °, would be. In cases where this is not the case, the clamping ring 4 can not be simply rotated around its own central axis 8, otherwise no more at least three openings 5 could be placed over holes 6 in the chassis 3 and fixed with Absteckbolzen 7.

Without the three pin 7 but editing is not guaranteed with sufficient precision. For such cases, a second component level is arranged above or below the first component level with openings 5, which in turn has a plurality of openings 5. If the clamping ring is installed "overhead", that is pushed through 180 °, this 180 ° rotation is a rotation about an axis perpendicular to the central axis 8 of the clamping ring 4, by using the openings 5 from the second component level, the same device for machining - at least in the case of the example described in this embodiment A 330 / A 340 chassis - all relevant holes 6 of the main fittings are used.

The hole spacing of the openings 5, through which a machining of the chassis 3 takes place or by the Absteckbolzen 7 can be plugged is entered in Figures 8 to 11 with degrees without brackets. The distances in brackets denote the distance between other openings 5 in the clamping ring, which are usually not used for fixing or processing, but serve to save weight.

In the figures 10 and 11 holes 16 are shown, through which the auxiliary positioning device 10 can be firmly connected to the clamping ring 4.

Performing a corrosion removal on a landing gear hole preferably proceeds as follows:

First, the component, connections or the like are removed from the chassis 3, which would prevent a postponement of the clamping ring 4. Subsequently, the clamping ring 4 of the friction device 1 with holding guide 11 on the chassis, for example, on the main fitting, postponed.

Subsequently, the clamping ring 4 is aligned so that four circular openings 5 are placed as precisely as possible over four holes 6 in the chassis. The opening 5, on which the holding guide is located, is positioned over the hole 6 to be processed. If necessary, the clamping ring 4 must be installed "over head." Then three locking pins 7 are inserted through three openings 5 in three holes 6. If a hole has already been processed, the hole 6 must be provided with a corresponding sleeve.

Subsequently, the reaming tools are attached and adjusted, for example, a reamer 9 is set to the preferred friction range of 29.00 mm to 30.02 mm. The delivery is 0.1 mm. Preferably, a reamer 9 inserted through the holding guide 11 and rotated by a tap wrench in a clockwise direction. The diameter of the hole 6 is measured after each rubbing operation, in addition it is examined whether the corrosion is removed. After the corrosion is removed, the friction device 1 can be removed carefully from the chassis 3.

The friction process is followed by a milling process. For this purpose, first the clamping device 15 is installed in the chassis 3. The clamping device 15 has two clamping jaws, which are arranged displaceably in a linear direction. A jaw has a sleeve which is positioned centrally of the corroded bore. Subsequently, the clamping ring 4 of the milling device 2 is pushed onto the chassis 3.

The clamping ring 4 is aligned so that it can be fixed with three Absteckbolzen 7. Subsequently, the pilot 14 is positioned in the sleeve of the jaw. On the pilot 14, a rotary device 13 is plugged, which is guided by the rotary device holder 12. By a manual turning operation, the hole 6 is provided with a chamfer. For this purpose, the device has a hand crank. When turning the hand crank takes the chip removal. The chamfer is preferably 2.4 mm to 2.6 mm deep and preferably has an angle of 45 °.

Subsequently, the milling device 2 is dismantled and the chassis 3 can be used again after removal of the initially removed components. List of reference numbers:

1 friction device

2 milling device

3 landing gear

4 clamping ring

5 opening

6 holes

7 locking pins

8 central axis

9 reamer

10 auxiliary positioning device

11 holding guide

12 turntable holder

13 rotary device

14 pilot

15 clamping device

16 holes

17 flattening

Claims

Friction and/or milling device (1,2) for a landing gear (3) of an aircraft, characterized in that the friction and/or milling device (1,2) comprises a clamping ring (4) which is mounted on a part of the landing gear ( 3) can be pushed on and wherein the clamping ring (4) has a plurality of openings (5) and the part can be processed through at least one of the openings (5).

Reaming and/or milling device (1,

2) according to claim 1, characterized in that the clamping ring (4) can be pushed onto a part of the chassis (3) while the chassis

(3) is firmly connected to the aircraft.

Reaming and/or milling device (1,2) according to one of the preceding claims, characterized in that the reaming and/or milling device (1,2) has locking pins (7) and the clamping ring

(4) comprises a plurality of circular openings (5), the circular openings

(5) about holes

(6) can be positioned in the chassis (3) and through a

Inserting the locking bolts (7) through the circular openings (5) in the clamping ring (4) into the holes (6) in the chassis (3) fixes the clamping ring (4) on the chassis

(3) is possible.

Reaming and/or milling device (1,2) according to one of the preceding claims, characterized in that the clamping ring (4) comprises at least three circular openings (5) which lie in a first component plane and additionally at least three further circular openings (5 ), which are arranged in a second component level above or below. Reaming and/or milling device (1,2) according to one of the preceding claims, characterized in that the plurality of openings (5) in the clamping ring (4) is arranged in such a way that four of the openings (5) simultaneously have four holes (6 ) can be positioned in the chassis (3).

Reaming and/or milling device (1,2) according to claim 5, characterized in that four openings (5) in the clamping ring (4) can also be positioned simultaneously via four holes (6) in the chassis (3) when the clamping ring (4 ) is pushed on rotated by 180 °, this 180 ° rotation being a rotation about an axis perpendicular to the central axis (8) of the clamping ring (4).

Reaming and/or milling device (1,2) according to one of the preceding claims, characterized in that the reaming and/or milling device (1,2) has an auxiliary positioning device (10) which is fixed to the clamping ring (4). is connected and through which the reaming or milling devices used can be fixed and/or positioned for use on the chassis (3).

Reaming and/or milling device (1,2) according to one of the preceding claims, characterized in that the clamping ring (4) comprises four circular openings (5), each of the four openings (5) facing a different one of the four openings (5 ) has a distance of approximately 85°.

Reaming and/or milling device (1,2) according to claim 8, characterized in that the clamping ring (4) comprises four further circular openings (5) in a second component level, each of the four further openings (5) being a The other of the four further openings (5) is at a distance of approximately 85°.

Reaming and/or milling device (1,2), according to one of the preceding claims, characterized in that the clamping ring (4) is formed by two half rings that can be connected to one another.

Reaming and/or milling process on a landing gear (3) of an aircraft, characterized in that the method comprises at least the following steps: a) pushing a clamping ring (4) onto the landing gear (3) and then fixing the clamping ring (4). the chassis (3); b) carrying out a friction and/or milling treatment on the chassis (3), the machining of the chassis (3) being carried out through at least one opening (5) in the clamping ring (4); c) Remove the clamping ring (4) from the chassis (3).

Reaming and/or milling method according to claim 11, wherein steps a), b) and/or c) are carried out while the landing gear (3) is firmly connected to the aircraft.

Reaming and/or milling process on a landing gear (3) of an aircraft according to claim 11 or 12, characterized in that steps a), b) and c) are carried out at least twice in succession and the clamping ring (4) for the second implementation rotated 180°, where- This 180° rotation is a rotation about an axis perpendicular to the central axis (8) of the clamping ring (4). Reaming and/or milling process on a landing gear (3) of an aircraft according to claim 13, characterized in that in the course of step b) first a manual reaming process using a reamer (9) is carried out on a hole (6) in the landing gear (3). takes place and then a manual milling process is carried out, in which a preferably 45 ° chamfer is milled on the hole (6).