阅读说明：本技术 具有简化结构的飞行器的前段区域 (Front section region of an aircraft with simplified structure ) 是由 P·贝纳代特 于 2019-09-12 设计创作，主要内容包括：本发明涉及一种飞行器的前段区域,飞行器包括具有框架的机身,前段区域包括驾驶舱和服务区域,驾驶舱部分地布置在前部起落架机构隔室的上方。所述地板包括：-后部主横梁(2),其在位于所述服务区域的框架(20)的平面中延伸并且固定至所述框架(20),-左舷主桁梁(4)和右舷主桁梁(6),其后端部固定至后部主横梁(2),-一个或多个次级横梁,其固定至左舷主桁梁和右舷主桁梁(4,6),以及一个或多个辅助桁梁。减小了横梁/框架附接件的数量。优化了所述地板的主要梁的尺寸；其结果是减轻了重量。(The invention relates to a forward section of an aircraft, the aircraft comprising a fuselage with a frame, the forward section comprising a cockpit and a service area, the cockpit being arranged partly above a forward landing gear compartment. The floor panel includes: -a rear main girder (2) extending in the plane of the frame (20) located in the service area and fixed to the frame (20), -a port main girder (4) and a starboard main girder (6) fixed at their rear ends to the rear main girder (2), -one or more secondary girders fixed to the port and starboard main girders (4, 6), and one or more auxiliary girders. The number of beam/frame attachments is reduced. Optimizing the dimensions of the main beams of the floor; the result is a weight reduction.)

1. A forward section region of an aircraft comprising a fuselage with a frame (20-30), the forward section region housing a cockpit and a service area arranged partly above a forward landing gear mechanism compartment, the forward section region having a floor comprising a cross beam, a truss beam, and one or more floor panels, and characterized in that the floor comprises:

-a rear main beam (2) extending in a plane of a frame (20) located in the service area (32), the rear main beam (2) being fixed to the frame (20),

-a port main girder (4) and a starboard main girder (6), the main girders (4, 6) having rear ends fixed to the rear main beam (2),

-one or more secondary transverse beams (14, 15) fixed to the port and starboard main girders (4, 6), the secondary transverse beams (14, 15) not being fixed to any frame and being carried by the main girders, the floor not comprising any transverse beams fixed to a frame in the cockpit,

-one or more auxiliary girders (16, 17).

2. An anterior section region of the aircraft according to claim 1, wherein the port and starboard main stringers (4, 6) each have a forward end fixed to a structural element (34) of the nose landing gear compartment.

3. An anterior segment region of an aircraft according to claim 2, characterised in that the structural element (34) of the forward landing gear mechanism compartment forms part of a horizontal portion (38) of the top of the mechanism compartment.

4. The forward section area of an aircraft according to one of claims 1 to 3, characterized in that:

-the secondary transverse beams (14, 15) extend only from the port main girder (4) to the starboard main girder (6),

-the one or more floor panels (40, 42) cover the surface laterally delimited by the port and starboard main girders (4, 6) so as to leave two lateral zones (44, 46) free of cross beams and floor panels.

5. The forward section of the aircraft according to one of claims 1 to 4, characterized in that the floor comprises a stiffening cross-member (8) fixed to a frame (22), which is located in the service area in front of the rear main cross-member (2).

6. The aircraft forward section area according to one of claims 1 to 5, characterized in that the floor comprises a port stiffening girder (10) and a starboard stiffening girder (12) each having a rear end fixed to the rear main beam (2).

7. An anterior section region of an aircraft according to claims 2 and 6, characterised in that the port and starboard stiffening girders (10, 12) each have a front end fixed to a structural element (34) of the forward landing gear compartment.

8. Front section region of an aircraft according to one of claims 1 to 7, characterized in that the auxiliary girders (16, 17) do not extend over the entire longitudinal dimension of the front section region.

9. An aircraft, characterized in that the aircraft comprises a forward section area with a floor according to one of the preceding claims.

Background

The floor of the front section of an aircraft usually comprises transverse beams, which are supported by the frames of the fuselage, stringers, which are supported by the transverse beams, and panels, which cover the entire surface defined by the lattice of said transverse beams and stringers.

The cross beams thus constitute the main beams of the floor. A cross beam is provided at each frame of the fuselage and each cross beam is directly fixed to the frame at both its ends, which results in a large number of ties between the cross beam and the frame. In the vicinity of the tie of the cross beam on the frame, there must also be provided a fixing of the top of the nose landing gear mechanism compartment, which is located partly below the cockpit.

The invention aims to propose a simplified structure for the floor of the front section area, in which the number of cross beam/frame fixtures is reduced.

Disclosure of Invention

To this end, the invention proposes a forward section of an aircraft comprising a fuselage with a frame, which forward section accommodates a cockpit and a service area, the cockpit being arranged partly above a front landing gear compartment, the forward section having a floor comprising a cross beam, a truss and one or more floor panels. The floor according to the invention comprises:

-a rear main beam extending in the plane of a frame located in the service area, the rear main beam being fixed to the frame,

-a port main girder and a starboard main girder, the main girders having rear ends fixed to the rear main beam,

-one or more secondary transverse beams fixed to the port and starboard main girders, said secondary transverse beams not being fixed to any frame and being carried by said main girders, the floor not comprising any transverse beams fixed to a frame in the cockpit,

-one or more auxiliary girders.

Thus, according to the invention, the main beams are not cross beams (except for the rear main cross beam), but are girders, in particular port and starboard main girders.

This is advantageous in a number of ways. First, because the secondary beam is not fixed to the frame, the number of beam/frame ties is significantly reduced.

Secondly, it should be noted that the dimension of the cabin (and even the forward section area) in the transverse direction is larger than the dimension of the cabin in the longitudinal direction. The main beams (girders) in the floor according to the invention are therefore shorter than those of the known front-end floor. Thus, they may be less thick (and lighter) for the same cockpit and service area loads to be supported. In other words, the dimensions of the main beams of the floor are optimized by means of the invention.

According to a possible feature of the invention, the port and starboard main girders each have a front end fixed to a structural element of the forward landing gear compartment, the structural element used advantageously being located in front of the cockpit.

It is possible to already provide, like the rear main beam, a front main beam fixed to the frame, so as to take up the load of the main girder; such a front main beam would add weight to the aircraft and increase the number of beam/frame ties. The present invention takes advantage of the proximity between the floor of the cockpit at the front of the cockpit and the structure of the forward landing gear mechanism compartment by using structural elements of the compartment rather than additional cross beams to support the main stringers at their forward ends.

In the absence of structural elements of the compartment at the front end of the cabin, which can take the load of the floor according to the invention, additional structural elements are provided. This additional structural element may be a front main beam fixed to the frame or a linking element between the floor according to the invention and the front sealing nose cone of the aircraft. This arrangement is less advantageous but still possible.

Possible embodiments of the front section area floor according to the invention:

the secondary cross-beam does not extend over the entire transverse dimension of the front section region; for example, the secondary transverse beams extend only from the port main girder to the starboard main girder,

-the one or more floor panels cover a surface laterally bounded by the port and starboard main girders. Obviously, this surface corresponds at least to the "walking surface" of the crewmember for the aircraft (the area over which the crewmember needs to pass and therefore requires them to walk). Preferably, the surface extends longitudinally at least between the two secondary beams.

In this embodiment, the secondary transverse beams extend at most only from the port to starboard main girders, these secondary transverse beams not extending to the fuselage; similarly, the one or more floor panels do not extend laterally beyond (toward the fuselage) the port and starboard main stringers. This arrangement therefore leaves lateral zones on each side of the cockpit that are free of cross beams and panels. In prior art aircraft, the multiple cross beams in the forward section are many obstacles to the system extending through the floor. The presence of two lateral zones without cross beams and panels greatly facilitates the extension of the system.

According to a possible feature, the front section floor according to the invention comprises a cross beam, called a stiffening cross beam, which is fixed to the frame of the aircraft in the service area, in front of the rear main cross beam. The stiffening cross-member is located, for example, at a junction between the cabin and the service area, while the rear main cross-member is located at a rear end of the service area, for example, at a junction between the service area and the passenger compartment. The stiffening cross-member may be secured to the frame forward of the frame to which the rear main cross-member is secured.

In other words, in this embodiment, the floor finally comprises two beams fixed to the frame, both beams being located in the service area, which is the point where the front section supports the heaviest load. The other cross-beams located in front of the reinforcing cross-beam are not fixed to the frame and are described in this respect as secondary cross-beams.

Likewise, according to a possible feature of the invention, the forepart zone floor comprises a port and a starboard stiffening girder, each having a rear end fixed to the rear main beam and a front end preferably fixed to the structural elements of the forward landing gear mechanism compartment, like the port and starboard main girders.

According to a possible feature of the invention, the structural elements of the forward landing gear mechanism compartment that fix the forward ends of the port and starboard main girders, and if appropriate the forward ends of the port and starboard stiffening girders, form part of the horizontal portion of the top of the mechanism compartment.

The invention extends to an aircraft equipped with a forepart zone floor according to the invention.

Further details and advantages of the invention will emerge from a reading of the following description of a preferred embodiment, with reference to the attached schematic drawings and related to the one provided as a non-limiting example.

Drawings

- [ FIG. 1 ]: fig. 1 is a perspective schematic view from above and behind of a front section area floor according to the invention, wherein the floor panel is not shown.

- [ FIG. 2 ]: fig. 2 is a perspective schematic view from above and in front of the floor mounted in the aircraft fuselage of fig. 1, and with a floor panel thereof.

- [ FIG. 3 ]: figure 3 is a schematic outline view of an aircraft equipped with a forward pushed forward mechanism compartment (so described due to its location) and a floor according to the invention.

Detailed Description

Fig. 1 shows the "skeleton" of the floor of the forepart area of a passenger aircraft, which comprises a section 30 for receiving a cockpit and a section 32 for receiving a service area with a galley and a lavatory (not shown).

Below this floor, from the front to the rear of the aircraft, there is a forward landing gear mechanism compartment (hereinafter simply referred to as "forward mechanism compartment") and a technical bay which extends below the cockpit and below the service area. The technical cabin is open in the upper part and pressurized like a cockpit.

There are mainly two types of frontal mechanism compartments: a so-called "conventional" forward mechanism compartment, which extends substantially under the cockpit, or even only in a central or rear portion of the cockpit, so that there is a pressurized space between the forward mechanism compartment and the sealed nose cone of the aircraft; and a so-called "push-forward" forward mechanism compartment (such as that shown in fig. 3) that extends to the sealed nose cone 33 of the aircraft. The front mechanism compartment 31, visible at the top in fig. 1 and 2, is a "push-forward" compartment. The invention is applicable to aircraft provided with a forward-pushing mechanism compartment and aircraft provided with a conventional mechanism compartment. However, it is more advantageous in the case of a push-forward compartment, where the absence of free space (pressurized) between the sealing nose cone and the mechanism compartment complicates the extension of the system to the cockpit.

The top of the (pushed forward) front mechanism compartment visible in fig. 1 comprises a horizontal part 38 and an inclined part 39.

The floor of the front section illustrated in fig. 1 and 2 comprises a rear main cross member 2 which is fastened to and supported by a frame 20 of the fuselage of the aircraft and which is located in the service area. The securing of the rear main beam 2 to the frame 20 may be accomplished using ties 36 as known in the prior art floor.

The front section area floor according to the invention illustrated in fig. 1 and 2 further comprises port and starboard main girders 4, 6, the rear ends of which are fixed to and supported by the rear main beam 2 and the front ends of which are fixed to and supported by a structural element 34 forming part of a horizontal portion 38 of the top of the forward mechanism compartment.

It should be noted that the top of the forward mechanism compartment is dimensioned to be able to withstand a significant pressure difference, since it is exposed on one side (above the compartment) to the pressure prevailing in the cockpit and on the other side to the pressure outside the aircraft. The top of the compartment thus comprises structural elements capable of taking up significant loads, for example beams 34 in the rear part of the horizontal part 38 of the top. The present invention advantageously utilizes this feature herein.

The front section area floor according to the invention shown in fig. 1 and 2 also comprises a stiffening cross-beam 8, as well as port and starboard stiffening girders 10, 12.

The stiffening cross-member 8 is fixed to the frame 22 of the fuselage. The frame 22 is a frame in front of the frame 20, that is, a frame located directly in front of the frame 20 to which the rear main cross member 2 is fixed. The stiffening girders 10 and 12 are fixed in the same way as the main girders 4 and 6, that is to say they are fixed by their rear ends to the rear main girder 2 and by their front ends to the structural elements 34 of the front mechanism compartment.

It should be noted that the port and starboard main girders 4 and 6, as well as the stiffening girders 10 and 12, are also supported by the stiffening cross-members 8.

The front section area floor according to the invention illustrated in fig. 1 and 2 also comprises two secondary cross beams 14, 15 extending only from the port main girder 4 to the starboard main girder 6. These secondary transverse beams are fixed to and supported by the main girders 4 and 6 and the reinforcing girders 10 and 12. The floor may include other secondary beams or, conversely, may include a single secondary beam.

The front section area floor according to the invention shown in fig. 1 and 2 also comprises auxiliary girders 16, 17, 18, 19. From the stiffening cross-beam 8, auxiliary girders 16, 17 extend to the secondary cross-beam 14, which are fixed to the stiffening cross-beam and the secondary cross-beam. The auxiliary girders 18, 19 extend from the secondary crossbeam 14 to the structural element 34 of the front mechanism compartment, to which they are fixed.

The network of beams and auxiliary girders is not limited to that shown in the drawings. The distribution of the beams and the auxiliary girders can vary and the positioning of a number of different auxiliary girders and secondary girders should be determined according to the mechanical loads that the floor must withstand. By way of example, the pilot and copilot seats have a base, and for reasons of structural efficiency it is preferable to locate the intersection of the cross-member with the auxiliary girder in line with the mountings of these mounts. Outside this logic, for example, when the grid size is too large to ensure the rigidity of the walking area of the floor, beams and/or auxiliary girders may be added.

The front section area floor according to the invention finally comprises a floor panel. As a variant, a single floor panel 40 is provided, which covers the entire crewmember walking surface, this surface including all the service areas and only a part of the cockpit. In the example shown, this (single) panel is perforated, holes 42 being provided in positions to reduce the weight of the floor, while ensuring resistance to the overall mechanical load to which the floor is subjected. The holes may be plugged by lighter plates in order to ensure the placement of the floor covering (suitable carpet type) and to withstand the loads of the crew walking.

As can be seen in fig. 2, the frames 24, 26, 28 before the frame 22 to which the reinforcing beam 8 is fixed do not support any beam. There is no beam blockage in the space 44 (lateral zone) extending transversely between the port main spar 4 and the fuselage, as is the space 46 (lateral zone) extending transversely between the starboard main spar 6 and the fuselage. These two lateral zones are not the areas where the crew walks but the areas that primarily receive navigation tools or other equipment, even lost areas that are not used in the cockpit floor. Thus, it is advantageous that the lateral zones 44 and 46 may be free of floor panels (as illustrated in fig. 2). These lateral zones are therefore devoid of any structural floor elements (neither cross beams nor floor panels). This means that there are no obstacles in the lateral zones 44 and 46 between the cockpit and the technical cabin that prevent the system from extending vertically.

The invention extends to any variant available to those skilled in the art, which is intended to fall within the scope defined by the appended claims.