阅读说明：本技术 用于飞行器的组件和推进组件及飞行器 (Assembly and propulsion assembly for aircraft and aircraft ) 是由 托马斯·德福雷 雅基·皮埃什 于 2019-06-24 设计创作，主要内容包括：本发明涉及用于飞行器的组件和推进组件及飞行器,组件包括：吊挂架,吊挂架具有安装板,安装板具有前部面和后部面,在前部面与后部面之间至少一个中心孔穿过安装板；前部发动机安装件,前部发动机安装件包括翼梁,翼梁具有顶接抵靠安装板的前部面的后部面,对于每个中心孔,翼梁具有与中心孔对准的互补中心孔；以及每个中心孔的安装系统。安装系统包括：剪切销,剪切销从后部面插入到中心孔和互补中心孔中,剪切销具有顶接抵靠后部面的凸缘；支撑件,支撑件具有中心孔,中心孔的直径大于凸缘的直径,支撑件固定至后部面；盖体,盖体固定至支撑件,盖体封闭中心孔顶接抵靠剪切销。因此,这样的组装系统可以仅从一个侧部装配,即使另一侧不可触及。(The invention relates to an assembly for an aircraft, a propulsion assembly and an aircraft, the assembly comprising: a hanger having a mounting plate with a front face and a rear face, at least one central aperture passing through the mounting plate between the front face and the rear face; a front engine mount comprising a spar having an aft face abutting against the forward face of the mounting plate, the spar having, for each central aperture, a complementary central aperture aligned with the central aperture; and a mounting system for each central aperture. The mounting system includes: a shear pin inserted into the central bore and the complementary central bore from the rear face, the shear pin having a flange abutting against the rear face; a support having a central bore with a diameter greater than a diameter of the flange, the support secured to the rear face; the cover body is fixed to the supporting piece, and the cover body seals the center hole and abuts against the shearing pin in a butting mode. Thus, such an assembly system can be fitted from only one side, even if the other side is not accessible.)

1. An assembly (200) for an aircraft (10) and comprising:

-a hanger (102) having a mounting plate (212) with a front face (230) and a rear face (232), and through which passes at least one central aperture (214a-b) between the front face (230) and the rear face (232),

-a front engine mount (202) comprising a spar (204) having an aft face abutting against a forward face (230) of the mounting plate (212), and, for each central aperture (214a-b), having a complementary central aperture (224) aligned with the central aperture (214a-b), and

-a mounting system (300) for each central hole (214a-b), the mounting system comprising:

-a shear pin (402) inserted into the central hole (214b) and the respective complementary central hole (224) from the rear face (232) of the mounting plate (212) and having a flange (404) abutting against the rear face (232) of the mounting plate (212),

-a support (308) having a central hole (310) with a diameter larger than the diameter of the flange (404) and fixed to the rear face (232) of the mounting plate (212) so as to be aligned with the central hole (310) and the central hole (214b), and

-a cap (406) fixed to the support (308), the cap closing the central hole (310) and abutting against the shear pin (402).

2. The assembly (200) of claim 1, wherein said mounting plate (212) has at least one peripheral aperture (216a-d) therethrough between said front face (230) and said rear face (232), characterized in that, for each peripheral hole (216a-d), the spar (204) has a complementary peripheral hole (226a-b) aligned with the peripheral hole (216a-d) and a nut (228a-b) fixed in the region of the complementary peripheral hole (226a-b), and in that, for each peripheral hole (216a-d), the mounting system (300) includes a tension bolt (502), the tension bolt is threaded into the nut (228a-b) from a rear face (232) of the mounting plate (212) by passing through the perimeter holes (216a-d) and the complementary perimeter holes (226 a-b).

3. The assembly (200) of claim 2, wherein the head of each tension bolt (502) has a unique shape (510), and wherein the assembly (200) comprises an anti-rotation system (500) comprising:

-a mounting plate (504) fixed between a rear face (232) of the mounting plate (212) and the support (308), having an opening (504) aligned with the central hole (214b) and having a diameter larger than the diameter of the flange (404) of the shear pin (402), and having a wing (506) through which a locking hole (508) passes,

-a locking plate (512) having a unique inverse shape, wherein the unique shape (510) and the unique inverse shape cooperate to lock the locking plate (512) against rotation about the axis of the tension bolt (502), and the locking plate has a locking opening (514) aligned with the locking hole (508), and

-a pin fitting into the locking opening (514) and the locking hole (508).

4. A propulsion assembly for an aircraft (10), comprising an engine (150) and an assembly (100) according to one of the preceding claims.

5. An aircraft (10) comprising at least one propulsion assembly according to the preceding claim.

Technical Field

The present invention relates to an assembly for an aircraft, comprising a pylon and a forward engine mount, to a propulsion assembly for an aircraft comprising such an assembly, and to an aircraft comprising at least one such propulsion assembly.

Background

Aircraft conventionally comprise a wing, below which a pylon is mounted, on which the engine is mounted. The engine is fixed to the pylon via a mount system consisting of, among other things, an engine mount at the front and a rear engine mount at the rear.

With the forward engine mount positioned against the forward edge of the pylon, mounting is provided by tension bolts, and the shear pins are perpendicular to the forward edge, i.e. generally horizontal.

The engine is first secured to the front engine mount and, because of its structure, it obstructs access to the front face of the front engine mount.

The positioning of the front engine mount against the leading edge of the pylon is then performed by lifting vertically. When the front engine mount is in place, the shear pins and tension bolts are assembled.

Assembling the shear pin and tension bolt is difficult because the front face of the front engine mount is difficult to access.

Disclosure of Invention

The object of the present invention is to propose an assembly for an aircraft comprising a pylon and a forward engine mount comprising means for easier fitting and fixing of a shear pin.

To this end, the invention proposes an assembly for an aircraft, said assembly comprising:

-a hanger frame having a mounting plate with a front face and a rear face and at least one central aperture passing through the mounting plate between the front face and the rear face;

-a front engine mount comprising a spar having an aft face abutting against the forward face of the mounting plate, and, for each central bore, the spar having a complementary central bore aligned with the central bore; and

-a mounting system for each central hole, the mounting system comprising:

-a shear pin inserted into the central bore and the respective complementary central bore from a rear face of the mounting plate and having a flange abutting against the rear face of the mounting plate,

-a support having a central bore of a diameter greater than the diameter of the flange and secured to the rear face of the mounting plate so as to be aligned with the central bore and the central bore, an

-a cap secured to the support, the cap closing the central bore and abutting against the shear pin.

Thus, such an assembly system can be fitted on one side only, even if the other side is not accessible.

Advantageously, the mounting plate has at least one peripheral hole therethrough between the front face and the rear face, the spar has, for each peripheral hole, a complementary peripheral hole aligned with the peripheral hole and a nut fixed in the region of the complementary peripheral hole, and the mounting system includes, for each peripheral hole, a tension bolt screwed into the nut from the rear face of the mounting plate by passing through the peripheral hole and the complementary peripheral hole.

Advantageously, the head of each tension bolt has a unique shape and the assembly comprises an anti-rotation system comprising:

-a mounting plate fixed between a rear face of the mounting plate and the support, having an opening aligned with the central hole and having a diameter larger than the diameter of the flange of the shear pin, and having a wing through which a locking hole extends,

-a locking plate having a unique inverse shape, wherein the unique shape and the unique inverse shape cooperate to lock the locking plate against rotation about an axis of the tension bolt, and the locking plate has a locking opening aligned with the locking hole, an

-a pin fitting into the locking opening and the locking hole.

The invention also proposes a propulsion assembly for an aircraft comprising an engine and an assembly according to one of the above alternatives.

The invention also proposes an aircraft comprising at least one propulsion assembly according to the above alternative.

Drawings

The above and other features of the present invention will become more apparent upon reading the following description of an exemplary embodiment, which is given with reference to the accompanying drawings, in which:

figure 1 is a side view of an aircraft with at least one assembly according to the invention,

figure 2 is a perspective view of an assembly according to the invention before assembly,

figure 3 is a perspective and exploded view of a mounting system according to the present invention,

FIG. 4 is a cross-sectional view of an assembly according to the invention in an assembled position, and

fig. 5 is a perspective view of the assembly in an assembled position.

Detailed Description

In the following description, the terms relating to position are referred to with reference to a normal forward-traveling aircraft, i.e. as depicted in fig. 1.

Fig. 1 shows an aircraft 10 that includes a fuselage 12 having wings 14 on each side.

A pylon 102 is mounted below each wing 14 and an engine 150 is mounted on the pylon 102. The engine 150 is, for example, a turbojet engine, and comprises, among other things, a structural casing fixed to the suspension pylon 102, and a nacelle 152 constituting an aerodynamic deflector of the engine 150, which is fixed to the structural casing and to the suspension pylon 102.

Throughout the following description, and by convention, direction X corresponds to the longitudinal direction of engine 150, which is parallel to the longitudinal axis of engine 150. In addition, direction Y corresponds to a direction oriented laterally with respect to engine 150, and direction Z corresponds to a vertical or elevation direction, with these three directions X, Y, Z being orthogonal to one another.

Fig. 2 shows an assembly 200 including the hanger 102 and a forward engine mount 202. For simplicity, the structural housing is not depicted, but is fixed to the front engine mount 202 and has a portion that is forward of and obstructs access to the front engine mount 202.

The forward engine mount 202, which is fixed between the pylon 102 and the structural shell, thus comprises a spar 204 fixed to the pylon 102 and two gussets 206 (only one of which is visible in fig. 2) positioned on each side of the mid-plane XZ of the engine 150. Each gusset 206 is secured between the spar 204 and the structural shell.

For each gusset 206, spar 204 and structural shell have a clevis 208 into which one end of gusset 206 is inserted and secured by a mounting system 210 of the assembly nut type.

The front edge of the hanger 102 has a mounting plate 212 that is generally vertical and has a forward facing front face 230 and a rearward facing rear face 232.

The mounting plate 212 has at least one central aperture 214a-b therethrough between a front face 230 and a rear face 232.

In the embodiment of the invention described herein, there are two central apertures 214 a-b. The axis of each central aperture 214a-b is generally horizontal and parallel to the longitudinal direction X.

Each central bore 214a-b is intended to receive a shear pin.

For each central bore 214a-b, spar 204 has a complementary central bore 224 that is aligned with the respective central bore 214 a-b.

The assembly of spar 204 against mounting plate 212 is performed by vertical lifting F until each complementary central aperture 224 is aligned with a respective central aperture 214a-b of mounting plate 212. During assembly, the forward face 230 positions itself against the aft face of the spar 204.

Fig. 3 and 4 show the mounting system 300 assembled for each of the central apertures 214 a-b.

The mounting system 300 includes a shear pin 402 having a flange 404. The shear pin 402 is inserted into the central apertures 214a-b and corresponding complementary central apertures 224 from the rear face 232 of the mounting plate 212 and its flange 404 abuts against the rear face 232 of the mounting plate 212. The shear pin 402 is long enough so that it is located in the central bore 214b and the corresponding complementary central bore 224 of the beam wing 204.

The mounting system 300 includes a support 308 having a central bore 310 with a diameter greater than a diameter of a flange 404. The support 308 is secured to the rear face 232 of the mounting plate 212 in alignment with the central aperture 310 and the central aperture 214 b. In this case, the support 308 is fixed in position by three screws 312 which are screwed into nuts attached to the support 308 while passing through the mounting plate 212 from the front face 230 to the rear face 232 through bores made for this purpose. This attachment pattern does not require the bore to be tapped, but any other attachment pattern is equally possible, such as tapping the bore and threading the screw 312 from the rear face 232.

The mounting system 300 includes a cover 406 that is removably attached to the support 308 and closes the central bore 310 and abuts against the shear pin 402.

Here, the attachment of the cover 406 is performed using screws 408 which are screwed from the rear face 232 into nuts attached to the support 308.

The mounting system 300 is assembled by securing the support 308 to the rear face 232. Once spar 204 is facing mounting plate 212, shear pins 402 are assembled from aft face 232, and finally caps 406 are secured to supports 308 from aft face 232.

Thus, access to the front of the spar 204 is not required to assemble the shear pin 402 after the spar 204 has been positioned.

In the embodiment of the invention set forth herein, the mounting system 300 includes an anti-friction ring 304 received in the central bore 214 b. Shear pin 402 is thus pushed into anti-friction ring 304.

The mounting plate 212 has a recess 302 on its front face 230 surrounding the central aperture 214b and in the embodiment of the invention described herein, an anti-friction ring 304 has a flange 306 that fits into the recess 302. In this case, therefore, anti-friction ring 304 is assembled from front face 230.

It may also be provided that the recess is located on the rear face 232 side, and that the anti-friction ring 304 is thus fitted thereto from the rear face 232.

In the embodiment of the invention described herein, the mounting plate 212 also has four perimeter holes 216 a-d. The axis of each peripheral hole 216a-d is generally horizontal and parallel to the longitudinal direction X. Here, the mounting plate 212 has one central hole 214a-b and two peripheral holes 216a-d on each side of the mid-plane XZ, wherein one peripheral hole 216a, 216c is located above the central hole 214a-b and wherein one peripheral hole 216b, 216d is located below the central hole 214 a-b. Of course, the number of central apertures 214a-b and perimeter apertures 216a-d may vary.

Each peripheral hole 216a-d is intended to receive a tension bolt 502 and opens onto the front face 230 and the rear face 232.

For each peripheral hole 216a-d, spar 204 has a complementary peripheral hole 226a-b aligned with the respective peripheral hole 216 a-d.

For each peripheral hole 216a-d, spar 204 includes a nut 228a-b that is secured in the region of a corresponding complementary peripheral hole 226a-b to allow a tension bolt 502 of mounting system 300 to be screwed in.

Each aperture 216a-d is aligned with a corresponding complementary peripheral aperture 226a-b when spar 204 is assembled against mounting plate 212.

Tension bolts 502 are also assembled from the aft face 232 of the mounting plate 212 and are threaded into nuts 228a-b of the spar 204 provided for this purpose by passing through the perimeter holes 216a-d and complementary perimeter holes 226 a-b.

The mounting plate 212 protrudes beyond the body of the hanger 102 at the sides so that the central apertures 214a-b and the perimeter apertures 216a-d are accessible from the rear face 232.

In the embodiment of the invention described herein, mounting system 300 includes an additional anti-friction ring 410 that is received in a complementary central bore 224 of spar 204 that is aligned with central bore 214b of mounting plate 212. An additional anti-friction ring 410 has a flange that fits into a recess around the complementary hole 224 on the rear face of the spar 204. The shear pin 402 is thus pushed into the additional anti-friction ring 410.

For each tension bolt 502, the mounting system 300 also includes an anti-rotation system 500 that prevents rotation of the tension bolt 502.

Anti-rotation system 500 includes a mounting plate 504 secured between aft face 232 of mounting plate 212 and supports 308. The mounting plate 504 has an opening 504 that is aligned with the central bore 214b and has a diameter that is larger than the diameter of the flange 404 of the shear pin 402 to allow the shear pin to be mounted from the rear face 232.

In the embodiment of the invention described herein, the mounting plate 504 has holes for the passage of screws 312.

For each adjoining tension bolt 502 of the mounting plate 504, this mounting plate has a wing 506 extending towards the tension bolt 502 and through which a locking hole 508 extends.

The head of each tension bolt 502 has a unique shape 510, and the anti-rotation system 500 includes a locking plate 512 having a unique inverse shape, wherein the unique shape 510 and the unique inverse shape cooperate with each other to lock the locking plate 512 against rotation about the axis of the tension bolt 502.

In the embodiment of the invention described herein, unique shape 510 is a unique star-shaped convex form and the unique opposite shape is a star-shaped concave form.

The locking plate 512 has a locking opening 514 (in this case oval shaped) that is aligned with the locking hole 508.

The anti-rotation system 500 also includes a pin that is positioned and fitted into the locking opening 514 and the locking hole 508 to prevent rotation of the locking plate 512, and thus the tension bolt 502.

In the embodiment of the invention depicted in fig. 3 and 4, the mounting system 300 further includes a collar 314 that fits into the bottom of the recess 302 and includes a counter bore to receive the head of the screw 312.

Thus, for the aircraft 10, a propulsion assembly according to the present invention includes an engine 150, an assembly 100 having a pylon 102 and a forward engine mount 202.