阅读说明：本技术 安装吊挂架及包括其的飞行器 (Installation hanging rack and aircraft comprising same ) 是由 托马斯·德福雷 伯努瓦·奥特乌 奥列弗·格莱兹 于 2019-06-25 设计创作，主要内容包括：本发明涉及一种安装吊挂架(15)及包括其的飞行器,所述安装吊挂架包括结构(100),所述结构包括具有上翼梁(126)、下翼梁(128)、以及侧向侧面(108)的两个C形半结构(102a),并且所述结构包括上面板(110)、下面板(112)、反作用附接点(120)、附接在所述反作用附接点(120)与喷气发动机之间的两个杆件(122)、以及附接至机翼箱盒的前部机翼附接点(124)。所述侧向侧面(108)包括在所述前部机翼附接点(124)与所述反作用附接点(120)之间对齐的托梁(130,132),并且其中,在两个相继的托梁(130,132)之间的角度相等。这种类型的安装吊挂架因此更轻、并且允许沿托梁更好地传递载荷。(The invention relates to a mounting pylon (15) and an aircraft comprising it, comprising a structure (100) which comprises two C-shaped half-structures (102a) with an upper spar (126), a lower spar (128), and lateral sides (108), and which comprises an upper panel (110), a lower panel (112), a reaction attachment point (120), two bars (122) attached between the reaction attachment point (120) and a jet engine, and a front wing attachment point (124) attached to a wing box. The lateral side (108) comprises joists (130, 132) aligned between the front wing attachment point (124) and the reaction attachment point (120), and wherein the angle between two consecutive joists (130, 132) is equal. This type of mounting hanger is therefore lighter and allows better transfer of loads along the joist.)

1. A mounting hanger (15) for mounting a jet engine (14) to a wing box, the mounting hanger (15) comprising a structure (100) comprising:

-a port half-structure (102a) and a starboard half-structure (102b), each in the form of a C-beam open towards the opening of the other half-structure and comprising an upper spar (126), a lower spar (128), and lateral sides (108) extending between the upper spar (126) and the lower spar (128),

an upper panel (110) attached to the upper spar (126),

a lower panel (112) attached to the lower spar (128),

-a reaction attachment point (120) attached below the lower panel (112),

-two rods (122) each having one end attached to the reaction attachment point (120) and the other end configured to be attached to the jet engine (14), and

-a front wing attachment point (124) configured to attach to the wing box,

wherein the lateral side (108) is constructed of an openwork structure and comprises a reaction joist (130) extending in a linear manner between the upper spar (126) and the lower spar (128) and oriented to align between the forward wing attachment point (124) and the reaction attachment point (120), and

wherein the lateral side (108) further comprises a plurality of transfer joists (132) extending in a linear manner between the upper spar (126) and the lower spar (128), wherein the transfer joists (132) are arranged fore and aft behind the reaction joists (130), wherein each transfer joists (132) is oriented to be aligned towards the front wing attachment point (124), and wherein the angle between two consecutive joists (130, 132) is equal,

-an aft wing attachment point (134) arranged aft of the mounting pylon (15) and comprising a base (136) configured to be attached to the wing box by a plurality of bolts and shear pins (142) oriented parallel to a vertical direction Z,

wherein the aft wing attachment point (134) comprises a structural assembly (144) comprising two upper beams (146a-b) and two lower beams (148a-b), wherein the beams (146a-b, 148a-b) are fastened at one end to each other and to the base (136), wherein each upper beam (146a-b) is fastened at the other end to the upper spar (126) on the same side, and wherein each lower beam (148a-b) is fastened at the other end to the lower spar (128) on the same side.

2. A mounting hanger (15) according to claim 1, wherein said beams (146a-b, 148a-b) extend from ends of said spars (126, 128), said ends being shaped to intersect said base (136).

3. The mounting hanger (15) of claim 1 or 2, wherein said base (136) is generally coplanar with said forward wing attachment point (124), wherein said upper beams (146a-b) are generally horizontal, and wherein said lower beams (148a-b) are angled from low to high as they extend from front to back.

4. A mounting hanger (15) according to any one of claims 1 to 3, characterised in that each joist (130, 132) is provided with a rib (150).

5. The mounting hanger (15) according to one of claims 1 to 4, wherein the upper spar (126) and the lower spar (128) are provided with ribs (152, 154).

6. An aircraft (10) comprising a wing box, a jet engine (14), and a mounting pylon (15) according to one of the preceding claims, wherein the mounting pylon (15) is attached to the wing box by the forward wing attachment point (124), and wherein the jet engine (14) is attached to the mounting pylon (15) by the two rods (122).

Technical Field

The invention relates to a mounting pylon for a jet engine under the wing of an aircraft. The invention also relates to an aircraft equipped with a wing box, a jet engine and a mounting pylon of this type.

Background

In existing aircraft, engines such as jet engines are suspended under the wing using complex mounting devices, also known as EMS (engine mounting structure) or mounting hangers. The mounting hangers in normal use have a main structure (also known as a rigid structure) which usually takes the form of a box, i.e. is constructed by assembling an upper spar and a lower spar which are connected to each other by a plurality of transverse stiffening ribs located within the box and at their extremities. The spars are arranged at the lower and upper faces, while the lateral panels close the box to form the sides. Furthermore, a mounting pylon is arranged on top of the engine, between the engine and the wing box. This is referred to as the "12 o' clock" position.

As is known, the main structure of these hangers is designed to allow the transfer to the wing of static and dynamic loads originating from the engine, such as weight, thrust, but also a plurality of different dynamic loads, in particular those associated with fault events such as Blade loss (FBO or "Fan Blade Out"), nose gear collapse, dynamic landing, etc.

In the mounting hangers known from the prior art, as in document FR 2887522, the load transfer between its main structure and the wing box is conventionally ensured by a set of attachment points comprising a front attachment point, a rear attachment point, and an intermediate attachment point intended in particular for absorbing the thrust loads generated by the engine. Conventionally, these attachment points are inserted vertically between the wing box and the main structure to which the suspension pylon is mounted.

While this type of mounting hanger is entirely satisfactory, it is desirable to identify a framework that optimizes the load path between the engine and the wing box.

Disclosure of Invention

One object of the present invention is to propose a mounting hanger for a jet engine under a wing of an aircraft, which mounting hanger provides better load transfer between the jet engine and the wing box.

To this end, proposed is a mounting hanger for mounting a jet engine to a wing box, the mounting hanger comprising a structure comprising:

-a port and a starboard half-structure, each in the form of a C-beam open towards the opening of the other half-structure and comprising an upper spar, a lower spar, and lateral sides extending between the upper and lower spars,

-an upper panel attached to the upper spar,

a lower panel attached to the lower spar,

-a counter-acting attachment point attached below the lower panel,

-two rods each having one end attached to the reaction attachment point and the other end configured to be attached to the jet engine, and

-a front wing attachment point configured to attach to the wing box,

wherein the lateral sides are constructed of openwork structures and include a reaction joist extending linearly between the upper and lower spars and oriented to align between the forward wing attachment point and the reaction attachment point, and

wherein the lateral sides further comprise a plurality of transfer joists extending in a linear manner between the upper spar and the lower spar, wherein the transfer joists are arranged one behind the other behind the reaction joists, wherein each transfer joists is oriented to be aligned towards the front wing attachment point, and wherein the angle between two consecutive joists is equal.

-an aft wing attachment point arranged aft of the mounting pylon and comprising a base configured to be attached to the wing box by a plurality of bolts and shear pins oriented parallel to a vertical direction Z,

wherein the rear wing attachment point comprises a structural assembly comprising two upper beams and two lower beams, wherein the beams are fastened at one end to each other and to the base, wherein each upper beam is fastened at the other end to the upper spar on the same side, and wherein each lower beam is fastened at the other end to the lower spar on the same side.

This type of mounting hanger is therefore lighter and allows better transfer of loads along the joist.

Advantageously, the base is generally coplanar with the forward wing attachment point, the upper spar is generally horizontal and slopes from low to high as the lower spar extends from front to rear.

Advantageously, each joist is provided with ribs.

Advantageously, the upper spar and the lower spar are provided with ribs.

The invention also proposes an aircraft comprising a wing box, a jet engine, and a mounting pylon according to one of the preceding variants, wherein the mounting pylon is attached to the wing box by means of the front wing attachment point, and wherein the jet engine is attached to the mounting pylon by means of the two rods.

Drawings

The above-mentioned features of the invention, as well as others, 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 shows a side view of an aircraft according to the invention,

figure 2 shows a side view of a mounting hanger according to the present invention,

fig. 3 shows a perspective view of the rear of the mounting hanger according to the invention, viewed according to arrow III of fig. 2,

FIG. 4 shows a perspective side view of a mounting hanger according to the present invention, and

figure 5 shows a perspective view of a region where a hanger according to the present invention is installed.

Detailed Description

Fig. 1 shows an aircraft 10 having a wing 12 comprising a wing box and below which is attached a mounting hanger 15 according to the invention and which in turn supports a jet engine 14.

By convention, X denotes the longitudinal direction of the jet engine 14, this direction X being parallel to the longitudinal axis of the aircraft 10. Further, Y represents the lateral direction of the jet engine 14, which is horizontal when the aircraft is on the ground, and Z represents the vertical direction or vertical height when the aircraft is on the ground, these three directions X, Y and Z being orthogonal to each other.

Fig. 2 shows a mounting hanger 15 having a structure 100. Fig. 3 shows a rear portion of the structure 100, fig. 4 shows the structure 100 with a portion of the structure omitted for internal visibility, and fig. 5 shows details of the structure 100.

The structure 100 includes a port side half structure 102a and a starboard side half structure 102 b.

Each half-structure 102a-b is in the form of a C-beam that opens to the opening of the other half-structure 102b-a, as shown more clearly in fig. 3. Each half structure 102a-b includes an upper spar 126 in the form of an upper flange 104 and a lower spar 128 in the form of a lower flange 106 oriented generally in the transverse Y-direction, and lateral sides 108 extending in a generally vertical plane between the upper spar 126 and the lower spar 128.

In fig. 4, the port half-structure 102a has been removed.

The structure 100 also includes an upper panel 110 that is attached to the upper spar 126, for example by bolts or by welding.

The structure 100 also includes a lower panel 112 that is attached to the lower beam 128, for example by bolts or by welding.

The upper spar 126 follows the upper panel 110 and the lower spar 128 follows the lower panel 112.

The assembly of the half structures 102a-b, the upper panel 110 and the lower panel 112 forms a box that is empty and therefore lighter than prior art mounting hangers.

The structure 100 also includes a nose 114 that is disposed inside and at the front of the resulting box. Thus, the nose 114 is attached between the half structures 102a-b and between the panel 110 and the panel 112.

The structure 100 includes a forward engine attachment point 116 at the front of the nose 114 for attaching the jet engine 14, and more specifically for attaching the fan casing. This front engine attachment point 116 will be known to those skilled in the art.

The structure 100 further comprises an rear engine attachment point 118 attached below the lower panel 112 at a general level of a middle region of the structure 100 as seen from the longitudinal direction X. The aft engine attachment point 118 is attached to the jet engine 14, and more specifically to the center housing. This rear engine attachment point 118 will be known to those skilled in the art and is for example in the form of two female clevises.

The structure 100 also includes a reaction attachment point 120 attached below the lower panel 112 at the general level of the middle region, forward of the rear engine attachment point 118.

Structure 100 also includes two rods 122, one end of each rod 122 attached to reaction attachment point 120. The rods 122 are arranged on either side of the longitudinal mid-XY plane of the mounting hanger 15. Each rod 122 is attached at one end to the reaction attachment point 120 and at the other end to the front of the central casing of the jet engine 14. The rods 122 are used, among other things, to react to thrust loads generated by the jet engine 14.

The structure 100 also includes a front wing attachment point 124, which in this case is an integral part of the upper panel 110, and by which the structure 100 can be attached to the wing box.

Each lateral side 108 is constructed of an openwork structure and it includes a reaction joist 130 extending in a linear fashion between the upper spar 126 and the lower spar 128 and oriented to align between the forward wing attachment point 124 and the reaction attachment point 120. The load transferred by the rod 122 is divided into a component in the lower spar 128 and a component in the reaction joist 130.

The lateral side 108 also includes a plurality of transfer joists 132 (in this case three transfer joists) that extend in a linear fashion between the upper and lower spars 126, 128. The transfer joists 132 are arranged behind the reaction joists 130 and back and forth in the plane of the lateral sides 108. Each transfer joist 132 is oriented to align toward the front wing attachment point 124 and the angle between two successive joists 130 and 132 is equal.

In other words, the angle between the reaction joist 130 and the immediately following first transfer joist 132 in the plane of the lateral side 108 is equal to a. The angle between the first transfer joist 132 and the immediately subsequent second transfer joist 132 is equal to a.

These angles are considered equal if they are within +/-10% of the average angle, preferably between 28 ° and 32 °.

These angles are measured relative to the centerline of each joist 130 and 132.

Arranging the joists 130 and 132 to be radii provides good load strength and reduces the weight of the mounting hanger 15. Load is transferred through each of the joists 130 and 132.

The structure 100 also includes an aft wing attachment point 134 arranged aft of the mounting pylon 15 and by which the structure 100 can be attached to the wing box.

The aft wing attachment point 134 includes a base 136 that is attached to the wing box by a plurality of bolts (four bolts in this case) oriented parallel in the vertical direction Z. Each bolt is secured in a hole 138 through the base 136.

The aft wing attachment point 134 also includes a shear pin 142 (or "nipple") arranged between the base 136 and the wing box and oriented parallel to the vertical direction Z. A shear pin 142 is secured in a hole 140 through the base 136. The shear pin 142 transfers shear loads from the mounting hanger 15 to the wing box.

The aft wing attachment point 134 also includes a structural assembly 144 that includes two upper spars 146a-b and two lower spars 148 a-b. Two upper beams 146a-b are arranged on either side of the XZ mid-plane and two lower beams 148a-b are arranged on either side of the XZ mid-plane.

One end of each beam 146a-b, 148a-b is secured to the base 136. At one end, beams 146a-b and beams 148a-b are thus secured to each other and to base 136.

The other end of each upper beam 146a-b is secured to the upper spar 126 of the same side half 102 a-b.

The other end of each lower beam 148a-b is secured to the lower spar 128 of the same side half structure 102 a-b.

The beams 146a-b and 148a-b may be secured to the respective spars 126 and 128 by any suitable means (e.g., by splice plates, by welding, etc.). According to another embodiment, beams 146a-b and 148a-b extend from ends of spar 128 of spar 126 that are shaped to intersect with base 136.

The loads transferred in the lower spar 128 are then transferred in the base 136 through the intermediary of the lower beams 148 a-b.

This type of aft wing attachment point 134 makes it possible to react to shear loads and replace the solid side panels of the prior art by splitting the loads between spars 146a-b and spars 148 a-b.

Base 136 is generally coplanar with forward wing attachment point 124, and upper spars 146a-b are then generally horizontal, and lower spars 148a-b are sloped from low to high as they extend forward to aft.

To increase the stiffness of each of the semi-structures 102a-b, each joist 130, 132 is provided with a rib 150. Similarly, the upper spar 126 and the lower spar 128 are also provided with ribs 152, 154.