Fuselage rear end of an aircraft

Abstract

A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

Claims

1-17. (canceled)

18. A fuselage rear end of an aircraft, comprising: a structural part comprising a skin and longitudinal and transversal reinforcing members, and a fairing, the structural part longitudinally spanning over the whole rear end and comprising a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section, the fairing being located below the second portion of the structural part.

19. The fuselage rear end, according to claim 18, wherein the structural part comprises load transversal reinforcing members configured to attach at least one of a horizontal or a vertical tail plane to the fuselage of the aircraft.

20. The fuselage rear end, according claim 19, wherein the fuselage comprises a cut-out for receiving a vertical tail plane.

21. The fuselage rear end, according to claim 18, wherein the fuselage comprises a cut-out configured to receive a horizontal tail plane.

22. The fuselage rear end, according to claim 21, wherein the fairing longitudinally spans from the fuselage section comprising the front part of the horizontal tail plane cut-out to the rear end of the rear end fuselage.

23. The fuselage rear end, according to claim 21, wherein the fairing longitudinally spans from the fuselage section comprising the front part of the horizontal tail plane cut-out to the fuselage section comprising the rear part of the horizontal tail plane cut-out.

24. The fuselage rear end, according to claim 21, wherein the fairing longitudinally spans from the fuselage section comprising the rear part of the horizontal tail plane cut-out to a rear end of the fuselage rear end.

25. The fuselage rear end, according to claim 18, further comprising a front firewall located in a fuselage section of the fuselage rear end.

26. The fuselage rear end, according to claim 21, further comprising a front firewall located in a fuselage section of the fuselage rear end, wherein the fairing longitudinally spans from the front part of the horizontal tail plane cut-out to the front firewall.

27. The fuselage rear end, according to claim 25, wherein the fairing longitudinally spans from front firewall to the rear end of the fuselage rear end.

28. The fuselage rear end, according to claim 18, further comprising an auxiliary power system at the second portion of the span of the structural part joined through struts to the longitudinal reinforcing members at the point at which the longitudinal reinforcing members are joined to the transversal reinforcing members.

29. The fuselage rear end, according to claim 18, further comprising a fire compartment having a front wall, a rear wall and a lateral firewall located at the second portion of the span, wherein the lateral firewall is attached to the transversal reinforcing members, while in the fairing, the firewall covers the an internal face of the fairing.

30. The fuselage rear end, according to claim 18, wherein in the structural part the skin and the longitudinal reinforcing members are manufactured as a single piece in the same curing cycle.

31. The fuselage rear end, according to claim 18, wherein the structural part further comprises a third portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section, a maintenance door being located below the third portion of the structural part.

32. The fuselage rear end, according to claim 18, wherein the fairing further comprises a maintenance door.

33. An aircraft comprising a fuselage rear end according to claim 18.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0031] To complete the description and in order to provide for a better understanding of the invention, a set of drawings is provided. Said drawings form an integral part of the description and illustrate preferred embodiments of the invention. The drawings comprise the following figures:

[0032] FIG. 1 shows a perspective view of a interface between the main body and the tail cone end of the state of the art.

[0033] FIG. 2 shows a schematic lateral view and a cross-section of a first embodiment of the invention.

[0034] FIG. 3 shows schematic lateral views of different embodiments of the invention.

[0035] FIG. 4 shows a schematic lateral view of another embodiment of the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0036] FIG. 1 shows a known rear end fuselage that is split into two different bodies, a main body (23) and a tail cone end (24) located at the rear part of the main body (23). The interface (20) between the main body (23) and the tail cone end (24) consists in four fittings (21) in both sections (23, 24) and a balancer fitting (22).

[0037] The invention is a carbon fiber reinforced polymer integrated rear fuselage, including a structural part (1) and a lower fairing (5). In this new integrated section, some of the structural elements, for instance skin and some longitudinal structural elements (30) such as stringers and beams, can be continuous from the beginning of the rear fuselage until the end (11) of the tail cone end. Beams are used as longitudinal structural reinforcement means and some of them also have the duty of supporting the auxiliary power system (7) or reinforcing HTP or VTP cut-outs, in the claimed configuration these beams would be extended to the rear fuselage until the end (11) of the tail cone.

[0038] These elements can be manufactured in a single part for the whole length, which implies reduction of manufacturing processes/operations and assembly savings due to joint parts removal.

[0039] Regarding FIG. 2, the longitudinal (30) and transversal (31) reinforcing members comprise means for attaching an auxiliary power system (7) at the second portion (3) of the span of the structural part (1) in which the transversal reinforcing members (31) occupy only a portion of the perimeter of the fuselage. The auxiliary power system (7) is joined through struts (15) to the longitudinal reinforcing members (30) at the point at which they cross with the transversal reinforcing members (31) so that the struts (15) are joined to a strong point.

[0040] The second portion (3) of the span of the structural part (1) also comprises means for attaching a the APU compartment (8) that has to be fireproof. The fireproof compartment (8) comprises a front wall (6), a rear wall (13) and a lateral firewall (16). The lateral firewall (16) is attached to the transversal reinforcing members (31) and the skin and it also covers the internal face of the fairing (5) as depicted in FIG. 2b.

[0041] Finally, the second portion (3) of the span of the structural part (1) also comprises means for attaching the above referenced fairing (5) as depicted in FIGS. 2a and 2b.

[0042] The structural part (1) shown in FIG. 2a also comprises a cut-out (9) for attaching a horizontal tail plane.

[0043] Depending on the aircraft configuration, namely HTP mounted on fuselage or T-tail, the position of the lower fairing (5) could have different embodiments as depicted in FIG. 3.

[0044] Additionally, different configurations address the HTP disassembly/assembly process that can be made in different ways, vertically or in the flight direction. Also, depending on the extension of the lower fairing (5) with respect to the front firewall (6), there may be different embodiments.

[0045] FIGS. 3a to 3d show embodiments wherein the HTP can be assembled and disassembled from the bottom.

[0046] FIG. 3a shows an embodiment wherein the lower fairing (5) longitudinally extends from the fuselage section comprising the front part of the HTP cut-out (10) to the rear end (11) of the tail cone end (1). The HTP can also be assembled from the rear part.

[0047] FIG. 3b shows an embodiment wherein the lower fairing (5) longitudinally extends from the fuselage section comprising the front part of the HTP cut-out (10) to the fuselage section comprising the rear part of the HTP cut-out (12).

[0048] FIGS. 3c and 3d show an embodiment wherein the lower fairing (5) longitudinally extends from the fuselage section comprising the front part of the HTP cut-out (10) to the front firewall (6).

[0049] FIG. 3e shows an embodiment wherein the lower fairing (5) longitudinally extends from the fuselage section comprising the rear part of the HTP cut-out (12) to the rear end (11).

[0050] The lower fairings (5) shown in the embodiments of FIGS. 3a and 3e have advantages over the other embodiments regarding damages during manufacturing and handling operations, since the lower rear area is sometimes damaged. The fairing (5) is joined to the upper part of the structure by removable attachment means and therefore, said fairing (5) would be replaced in case of damage instead of the whole tail cone end. All these embodiments are applicable for conventional and T-tail configurations.

[0051] FIG. 4 shows an embodiment for a T-tail configuration wherein the lower fairing (5) longitudinally extends from the front firewall (6) to the rear end (11). In a T-tail configuration, the lower fairing (5) could be bigger than in an HTP configuration since no HTP is located inside the structural part (1). Additionally, the front firewall (6) could be moved forward increasing the space for systems and maintenance tasks in the tail cone end since there are not limitations because HTP is not mounted on the fuselage.

[0052] The fairing would extend up to the front firewall (6) or the interface between the first and second portion of the structural part.

[0053] The rear end of the fuselage comprises maintenance doors (17) to gain access to the APS compartment (8) and to the HTP cut-out (9) to inspect and maintain actuator and the pivot point of the HTP. Depending on the configuration, said maintenance doors (17) can be located in the lower fairing (5) or adjacent to a third portion (4) of the structural part (1) in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section, being the maintenance door (17) located below the third portion (4) of the structural part.

[0054] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.