Aircraft fuel tank aperture sealing

Abstract

A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.

Claims

1. A seal for sealing an aircraft wing rib to a stringer passing through an aperture defined in the rib at a position subject to a tolerance, the seal comprising a first seal part engageable with the rib and a second seal part engageable with the stringer, the first and second seal parts each defining a sealing surface for sealable engagement together upon assembly, wherein the first seal part includes a frame for attachment to the rib around the aperture, said frame comprising a channel disposed about and within an inner periphery of the frame.

2. A seal according to claim 1, in which the first seal part comprises a seal plate having a body slidably engageable with the rib and defining the sealing surface on a flange depending from the body and the second seal part comprises a saddle for fitting over an upstanding part of the stringer and defines an outwardly directed said sealing surface for engagement with the sealing surface of the seal plate.

3. A seal according to claim 2, in which the saddle comprises a pair of downwardly depending legs to engage either side of the stringer and a bridging portion connecting the legs together and is divided into two parts in a region of the bridging portion whereby to accommodate any variation in thickness of the stringer when positioned thereon.

4. A seal according to claim 1, in which the second seal part comprises material with sufficient resilience to absorb any said tolerance between the rib and stringer or in the stringer itself.

5. A seal according to claim 1, wherein said channel comprises a base and a pair of spaced sidewalls depending therefrom and being arranged for engagement with a sealing element of the second seal part upon assembly.

6. A seal according to claim 5, in which said second seal part comprises a saddle shaped sealably to fit over the stringer, said saddle defining an outwardly projecting said sealing element to engage the first seal part within the said channel thereof upon said assembly.

7. A seal according to claim 6, in which the outwardly projecting said sealing element comprises a blade dimensioned to fit within the said channel with a clearance sufficient to absorb any said tolerance.

8. A seal according to claim 7, in which the blade is further dimensioned to allow the use of sealant within the channel.

9. A seal according to claim 7, in which said clearance is formed between the base of the channel and said sealing element to absorb any said tolerance between the channel and sealing element in a direction into or out of said channel.

10. A seal according to claim 7, in which the outwardly projecting sealing element is formed narrower than an internal width of the channel, measured between the two sidewalls thereof, whereby to absorb any said tolerance lengthwise of the stringer, when assembled.

11. A seal according to claim 5, in which the first seal part includes a body to extend across a rib foot between the frame and a web of the rib, when assembled.

12. An aircraft wing rib and stringer sealing assembly including a said wing rib and stringer and a seal according to claim 1.

13. An aircraft wing fuel tank comprising upper and lower wing covers, front and rear spars, and a pair of spaced ribs, said rib being sealably attached to the covers and spars by a seal according to claim 1.

14. An aircraft structural wing box including at least one wing fuel tank according to claim 13.

15. An aircraft wing including a structural wing box according to claim 14.

16. A method of sealing an aperture, said aperture comprising a mousehole aperture defined between an aircraft wing rib comprised in a first part wing box and a stringer comprised in a second part wing box, said first part wing box including a first wing cover, first and second wing spars extending spanwise along the cover and a series of wing ribs spaced spanwise and each extending chordwise between the cover and spars, said second part wing box comprising a second cover stiffened by at least one said stringer, said stringer being positioned to pass through the mousehole aperture upon assembly of the first and second part wing boxes together, the method including the steps of attaching first and second matching seal parts of a seal according to claim 1 to the rib and stringer, respectively, the seal being adapted to absorb any tolerance between the rib and stringer upon said assembly, and assembling together the first and second part wing boxes whereby to bring into sealing engagement the first and second seal parts.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The present invention will now be described, by way of example only, with reference to the following drawings in which:—

(2) FIG. 1 is an orthographic detail view of an aircraft wing rib and first seal part, according to a first embodiment of the invention;

(3) FIG. 2 shows the rib of FIG. 1 assembled with a wing stringer and second seal part to form an aircraft wing rib and stringer sealing assembly according to the invention;

(4) FIG. 3 shows the stringer of FIG. 2 having a second seal part assembled thereon;

(5) FIG. 4 is a detail part sectional side view taken along the line IV-IV of FIG. 2;

(6) FIG. 5 is a detail side sectional view taken, with slight modification, along the line V-V of FIG. 2;

(7) FIG. 6 is an orthographic detail view of an aircraft wing rib for incorporation into a second embodiment of the invention;

(8) FIG. 7 is an orthographic view of a first seal part, according to the second embodiment of the invention;

(9) FIG. 8 shows the rib of FIG. 6 and the first seal part of FIG. 7 assembled together;

(10) FIG. 9 shows a wing stringer and second seal part for assembly to the rib and first seal part of FIG. 8;

(11) FIG. 10 shows the components of FIGS. 8 and 9 being assembled together;

(12) FIG. 11 shows the components of FIG. 10 assembled;

(13) FIGS. 12(a), 12(b), 12(c) and 12(d) show differing horizontal sectional views taken on the line XII-XII of FIG. 11;

(14) FIG. 13 is an orthographic detail view of an aircraft wing rib and stringer for use in a third embodiment of the invention, and

(15) FIG. 14 shows an aircraft wing rib and stringer sealing assembly, according to the third embodiment of the invention, and

(16) FIG. 15 is an orthographic detail view of an aircraft lower wing cover with ribs attached, according to the prior art.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENT

(17) For ease of understanding, like reference numerals will be used for equivalent features in the drawings. With reference to FIG. 15, according to the prior art and showing the general arrangement of an aircraft wing, a wing lower cover 62 is shown, braced by stringers 14 and ribs 1. Not shown are an upper cover which will be attached to upper edges 63 of the ribs 1 and front and rear spars which will be attached to forward and rear edges of the ribs, respectively. The ribs 1 define “mousehole” apertures 2 therein. The ribs are made of metal but may be made of carbon fibre reinforced composite material. The ribs 1 have rib feet 3a, 3b, and upstanding webs 4.

(18) In FIG. 1, according to the invention, a rib 1 has similar features to those shown in FIG. 15, and in addition two vertical braces 5, 6 and a horizontal brace 7.

(19) Surrounding the aperture 2 is a first seal part in the form of a seal plate 8. The seal plate 8 is here made of fibre reinforced composite material and has a body 9, slots 10, 11 and a flange 12 defining a sealing surface 13 thereon. The seal plate 8 is slidably engageable with the web 4 of the rib 1 to provide sliding adjustment for the seal. In use, sealant is likely to be applied between the body 9 of the seal plate 8 and the web 4 of the rib 1, also onto the sealing surface 13 of the seal plate 8. Sealant may also be required between the saddle 19 and stringer 14.

(20) Shouldered fasteners 41 (see FIG. 4) will be affixed to the rib 1, slidably to secure the seal plate to the rib.

(21) With reference to FIGS. 2 and 3, a stringer 14 is shown assembled (in FIG. 2) with the rib 1. The stringer 14 has a tiered base 15 and an upstanding web 16. The tiered base 15 has an upper tier 17 and a lower tier 18. It will be noted that the web 16 of the stringer 14 is upstanding from the base 15 at an angle which is not a right angle. This is a design feature of a particular section of the wing and must be accommodated in the design of the seal.

(22) Shown sitting on the web 16 of the stringer is a split saddle 19. The saddle 19 is also made of composite material but could be rubber or a polymer and comprises two sections 20, 21. The saddle 19 comprises a backing plate 22 and a saddle portion 23. The saddle portion 23 comprises two downwardly depending legs 24, 25 and a bridging portion 26 connecting them together. The legs 24, 25 and bridging portion 26 define an outwardly directed sealing surface 27 thereon for engagement with the sealing surface 13 of the seal plate 8.

(23) In order to accommodate any variation in the thickness of the stringer web 16, the saddle 19 is split along a line 28 in the bridging portion 26. Any small gap thereby formed will be easily sealed with sealant. Liquid sealant may be used on all sealing surfaces but, between sealing surfaces 13 and 27, a sealant impregnated foam (not separately shown) may be used, likely being applied to the sealing surface 27 of the saddle 19.

(24) Sliding self-adjustment of the seal plate 8 with respect to the rib 1 is accomplished, on assembly, by camming means comprising an inwardly extending taper defined on the sealing surface 27 of the saddle 19. The taper on the sealing surface 27 is slidably engageable with a matching taper on the sealing surface 13 of the seal plate 8. In this way, the seal plate 8 is moved along the slots 10 and 11 and engagement of the sealing surface 27 of the saddle 19 with said matching shape of the sealing surface 13 of the seal plate 8 is facilitated, upon assembly of the stringer to the rib.

(25) It can thus be seen that the invention provides sliding adjustment of the seal and thickness adjustment for the stringer, to accommodate dimensional tolerance in both the positioning of the stringer and of its physical dimensions.

(26) Referring to FIG. 4, a shouldered “sticky” fastener 29 is attached by adhesion of a plate 30 to the rib 1. As an alternative attachment means for the fasteners, a fastener may be riveted on using double countersunk rivets, or bolted on with countersunk rivets. The fastener 29 has a plain portion 31 terminating in a shoulder 32. A threaded portion 33 extends from the shoulder 32 to an end 34 of the fastener.

(27) The plain portion 31 extends through the slot 11 in the seal plate 8. A nut 35 bears against the shoulder 32 via a washer 36. The combined length of the plate and plain portion of the fastener 29 is dimensioned to provide a sliding fit for the seal plate 8 along the slot 11, when bound by the nut 35 and washer 36. The seal plate 8 defines a cutaway 37 therein, co-extending with the slot 11, to receive the plate 30 of the fastener 29.

(28) Referring to FIG. 5, the stringer 14 is shown fully inserted into the aperture 2 in the rib. It can be seen that the bridging portion 26 of the saddle 19 is also of tapered form, with the bridging portion 26 narrowing toward the backing plate 22. When the stringer 14 is moved in the direction of the arrow into full engagement with the saddle 19 and seal plate 8, during assembly, sealant 38, 39 compressed between the stringer and bridging portion 26 and seal plate 8 and bridging portion 26, respectively, will urge the backing plate 22 of the saddle 19 against a rear surface 40 of the rib 1 and thereby form a stronger seal between the stringer 14 and rib 1.

(29) Referring to FIGS. 6 to 11 of the drawings, in a second embodiment, a rib 1 has an upstanding web 4, rib feet 3a, 3b, a horizontal brace 7 and vertical braces 5, 6. A mousehole aperture 2 is defined between the braces 5, 6 and 7. Attached by adhesive to the vertical braces 5, 6 are “sticky” studs 41, 42.

(30) Referring to FIG. 7, a first seal part in the form of a frame 43 is shown for attachment to the rib 1 around the aperture 2, the frame 43 defines an inwardly directed channel 44 therearound with the channel comprising a base 45 and a pair of spaced sidewalls 46, 47 depending from the base 45. An interior of the channel 44 defines a sealing surface for the first seal part. A pair of slotted brackets 48, 49 engage with the sticky studs 41, 42, respectively, sealably to secure the frame 43 against a sealing face 50 of the rib 1, as shown in FIG. 8. Sealant may be applied to the sealing face 50 to ensure that a seal is formed.

(31) Referring to FIGS. 9 and 10, a second seal part in the form of a second saddle 51 has a sealing element in the form of an outwardly projecting blade 52. The blade 52 defines opposed sealing surfaces 60, 61 (see FIG. 12c)). As shown in FIGS. 10 and 11, upon assembly of the stringer 14 into the aperture 2, the blade 52 of the second seal part moves progressively into engagement with the channel 44 in the frame 43.

(32) A width of the second saddle 51, taken at an outer extremity of the blade 52, measured across the stringer 14, will normally be less than a distance between opposed bases 45 of the channel 44, thereby giving a degree of relative freedom of movement, laterally of the stringer 14 and in the direction of the arrows shown in FIG. 10, between the blade 52 and channel 44 of the first and second seal parts. This freedom of movement therefore allows the seal to absorb any lateral positional tolerance between the first and second seal parts.

(33) Additionally, an upper extremity 53 of the blade, when fully inserted into the channel 44 of the frame 43, as shown in FIG. 11, is designed not to reach the base 45 of the channel 44 in upper region 54 of the frame. Thus, any dimensional tolerance in height of the stringer 14 can be accommodated by the seal of this embodiment of the invention.

(34) It will be appreciated that the channel 44 will normally be filled with sealant, before assembly, whereupon insertion of the blade 52 into the channel 44 will displace unwanted sealant, leaving the blade 52 sealed to the channel 44. Instead, if it is required only to absorb dimensional tolerance laterally of the stringer rather than longitudinally, a thickness of the blade 52 may be dimensioned to be a close sliding fit between sidewalls 56, 47 of the channel 44 and the use of sealant within the channel may be avoided. It should be noted, however, that sealant will almost certainly be required, for example to seal the frame 43 to the sealing face 50 of the rib 1 or to seal the second saddle 51 to the web of the stringer 14. Thus it is unlikely that sealant would not be used in the channel 44 as well.

(35) Referring now to FIG. 12, FIG. 12a) shows the assembly with the blade 52 of the second saddle 51 positioned nearer to the rib web 4, within the channel 44. This corresponds to the second saddle 51 being positioned on the stringer 14 within tolerance but slightly nearer the rib web 4.

(36) FIG. 12c) shows the blade 52 positioned further from the rib web 4, within the channel 44. This corresponds to the second saddle being positioned within tolerance but slightly further away from the web 4.

(37) FIG. 12b) shows the blade 52 positioned at an angle, across the channel 44. This corresponds to the stringer 14 passing through the aperture 2 at a slight angle to the rib 1.

(38) FIG. 12d) shows the blade 52 positioned both nearer to the web 4 and also nearer to one side of the aperture 2 than the other, within the channel 44. This corresponds to the stringer 14 passing through the aperture 2 slightly off-centre and with the second saddle 51 being slightly nearer the web 4.

(39) The rib configuration so far discussed, with stiffeners around the mousehole, is not universal. FIGS. 13 and 14 show an alternative configuration with no rib mousehole stiffeners. Here, a modified first seal part 54 has a body 55 to extend between a channel 56 and a web 4 of the rib 1 to move the channel 56 away from the web 4 so that the channel 56 is clear of the rib foot 3a, 3b and can contact and be sealed directly to stringer base 57.

(40) In this embodiment, the modified first seal part 54 is fastened to the rib web 4 by fasteners 59. The modified first seal part 54 seals against the second saddle 51, the rib web 4 with a relatively large surface area, also along the rib foot 3a, 3b, against an edge 58 of the rib foot 3a, 3b and against the stringer base 57. Sealant is applied to sealing surfaces as required.

(41) The embodiments described herein are respective non-limiting examples of how the present invention, and aspects of the present invention, may be implemented. Any feature described in relation to any one embodiment may be used alone, or in combination with other features described, and may also be used in combination with one or more features of any other of the embodiments, or any combination of any other of the embodiments. Furthermore, equivalents and modifications not described above may also be employed without departing from the scope of the invention, which is defined by the accompanying claims.

(42) The word “or” as used herein is to be taken to mean “and/or” unless explicitly stated otherwise.