DE102004001049A1 - Arrangement for internal insulation of an aircraft fuselage, for retardation of flame propagation into the cabin interior, comprises insulation packages which are covered by a foil with fire resistant properties - Google Patents

Abstract

The arrangement for internal insulation of an aircraft fuselage, for retardation of flame propagation from an external source into the cabin interior, comprises insulation packages which are fastened to fuselage frame elements, and are completely covered by a foil with fire resistant properties.

Description

The The invention relates to an insulating package arrangement for internal insulation an aircraft fuselage according to the claim 1. The insulated package arrangement will fire from outside of the aircraft environment affecting flames of a fire exclude in the cabin space of the aircraft, the construction and the attachment a Isolierpaketes is implemented on the fuselage structure so that the Cabin area of the aircraft from a fire attack from outside the aircraft environment protected and clearly facilitates the evacuation of passengers from the vehicle becomes.

From the aircraft industry conventional insulation systems are known, which, as in an appended 1 shown, consisting essentially of a core and insulating material, which is embedded in a Isolierpaket, and a sheath. The core and insulating material used generally comprises products of the fiber industry, of which in particular glass fiber materials (glass wool) are used. This material will largely meet the requirements for thermal and acoustic insulation. It will by no means be sufficient to cope with the inconvenient situations of an occurring fire whose flames act on the insulating material in this situation and completely burn it. In order to implement mounting (fastening) of the relatively amorphous semi-finished products to (or near) the aircraft fuselage structure, the insulating package (consisting of these semi-finished products) is enclosed by a wrapping film. The ends of the wrapping film will (meaningfully) be made reinforced, so that a sufficient attachment of the (so completed) Isolierpaketes can be done using fasteners on the structural surfaces of the aircraft. In aircraft, the attachment of such Isolierpakete takes place on the frames of the aircraft fuselage structure, wherein fasteners are used, which are usually made of a plastic, for example, a polyamide. Based on the application of such (conventional) insulation systems in aircraft, the following disadvantages can be stated. Conventional insulation systems consisting of glass wool and plain plastic films have (only) a burn through time of less than sixty seconds. In the assumed (and certainly not desired) fire of, for example, on the ground located emergency landed aircraft, in the attached 2 Burning kerosene can cause the aluminum cell of the aircraft structure and also the fuselage insulation (inner liner) of the aircraft to burn through, and corresponding burn through tests with fuselage structures have proven and the unpleasant (n) The fact (s) makes it clear that within ninety seconds both the aluminum skin of the aircraft and the fuselage insulation have completely burned out, so that in such a real conceivable situation, the flame of the fire in the passenger cabin will be unstoppable nevertheless highly precarious situation for the life of the accompanying passengers and the flight crew on board an airplane, since the observer in his thoughts (even with a test) will presuppose their presence on board, because an evacuation of the accident victims and the not injured persons one becomes as very kri have to rate the table.

Farther that observer is not disregarded can let that the conventional Fastenings of insulation made of non-metallic materials (Plastics), the fire in case of disaster, fire safety will not be resisted.

in the Fire disaster will these fortifications, which in given Situation will shrink and burn, a premature fall the burning insulation (insulating packages) hardly prevent it in the interior of the passenger cabin (suddenly) uncontrollable trip paths or other fire hazard points which will probably be the orderly execution of a Evacuation of persons and (possibly) other living beings from one burning aircraft, which has landed, will complicate. These Statement is supplemented so far, that it should be known that the passenger cabin linings) of a conventional Airplane not so is designed (are) a major source of fire longer Time to hold, as these parts of the aircraft in a post-crash fire scenario "fall to the ground will endanger the intended evacuation.

In addition, WO 00/75012 A1 discloses a fuselage insulation for an aircraft fuselage which is disclosed as having a fire retardant. "This document discloses an insulation package which, similar to the previously described arrangement for an" Airbus "product, within a spatial area defined between the fuselage interior trim and the outer hull skin is disposed as primary insulation. In this case, that insulating package is partially protected by a film of fire-retardant material (English fire-blocking material), said fire-retardant film area directly (in the manner of a protective shield against fire) faces the outer skin of the fuselage. Notwithstanding that with this proposal only an unzu sufficient protection of the insulation package and also of the fuselage interior against occurring fire can be granted because during a fire disaster the flames of the fire, which just pass from outside the aircraft through a damaged outer skin and will nourish the inner insulation, so by the (only) Fire-retardant, but not fire-resistant trained film will occur in case of permanent fire stress, no sufficient fire protection safety can be confirmed by the intended regional arrangement of only fire-retardant film against the fuselage interior. In addition, (similar to the Airbus concept above) attachment of the fuselage insulation to the aircraft structure is proposed by means of fasteners, commonly referred to as a plastic attachmant post. Accordingly, therefore, fasteners for fastening the hull insulation are proposed, which are usually made of plastic (s), for example, a polyamide exist. With respect to the application of such (carried out in the plane) insulation systems can be seen in terms of mounting and the construction of insulating insulation used for hull isolation no serious improvements that not only inhibited (hindered) but a spread of fire in a fire disaster event through the fuselage insulation of the aircraft is completely excluded.

As a result, the invention has the object, a known Isolierpaket arrangement an aircraft, which is used for internal insulation, in such a way to improve that with her a fire attack from outside of the aircraft environment affecting flames of a fire in the cabin space of the (emergency landed) aircraft excluded becomes. The structure of the insulating package and its attachment to the Hull structure will be appropriate, increasing the fire safety for severed and near a structural skin implement lying interior areas.

These The object is achieved by the measures specified in claim 1 solved. In the other claims Be suitable embodiments and Further developments of these measures specified.

The Invention is in one embodiment with the attached Drawings closer described ben. Show it

1 a conventional hull insulation of a commercial aircraft;

2 a (so-called) post-crash fire scenario on a parked airliner;

3 a Isolierpaket arrangement for the inner insulation of an aircraft fuselage with a burn-through film envelope of the insulating package;

4 the detail "x" after the 4 depicting the attachment of the insulating end sections of two hull insulation packages to a frame;

5 the representation of a trained as Isolierstift first fastener;

5a the representation of a longitudinal section of the insulating pin after the 5 ;

6 the side view of a designed as a truncated cage-like cage body second fastener;

6a the top view of the frustoconical cage body according to the 6 ;

7 the representation of a Stringer attached to the structure holder with rivet fastening of the insulating sections of the hull insulation packages;

7a the representation of the attachment of the insulating sections on a frame-extended bulkhead.

To the representation after the 1 for a viewer more comprehensible), in which a fuselage insulation is presented, with which all aircraft of the type: "Airbus" are traditionally equipped, it is also mentioned in the introduction that in the strength of the fuselage, the latter, in addition to stringers 31 , with which all outer skin fields of an outer skin 33 an aircraft fuselage structure are stiffened, several frames 32 which is perpendicular to the aircraft's longitudinal axis 9 (approximately) arranged at a distance c and the stringer 31 are attached. These frames 32 is at the non-attached end of a (so-called) former beam 40 integrated, which is parallel to the aircraft's longitudinal axis 9 is continued, with the (not attached free) end of the bulkhead support 40 (according to this embodiment) perpendicular to the aircraft's longitudinal axis 9 is angled.

On the isolation of the known (a person skilled) hull insulation is the beginning of the description already received, the representation of the 1 the viewer an impression of the location of a (generally quantified) insulating package 3 (the hull insulation) on the (nearby) outer skin 33 of the aircraft will be. This insulation package 3 is each with a so-called Feldisolierpaket 17 and a so-called frame insulation package 16 Traditionally both are laid separately and close to the outer skin 33 respectively resting a Stringerauflagefläche 31a the stringer 31 (So a defined structural area of the aircraft fuselage structure) are attached. That's why the 1 be taken that intermediate the arranged at a distance c (two) frames 32 close to (an) an inner surface area of an outer skin field of the outer skin 33 a field insulation package 17 is located and also the bulk carrier 40 a frame insulation package 16 is applied, the two-sided fitting the frame longitudinal sides 41 is performed, wherein the Spantisolierpaket 16 (from the field of view of the side view after the 3 considered) once at a so-called front (right) frame longitudinal side 41 and on the other hand on a so-called back (left) frame longitudinal side 41 to be led.

These two (traditionally used) insulation packages are completely encased in a flammable plastic film. They are within one (in the 1 unrecognizable) intermediate space, the inner lining of the aircraft and the outer skin panels of the outer skin 33 include, arranged.

To meet the urgent need for an increase in fire safety safety for partitioning room areas, with a gap to the outer skin 33 and a latter parallel in (transverse to the fuselage longitudinal axis 9 Include - defined (defined)) arranged interior trim of the aircraft cabin, to clarify (here, with reference to the 2 A deliberately thought-provoking presentation of the "fire catastrophic situation" mentioned at the beginning of an emergency-landed passenger plane, bearing in mind the (only assumed) fire situation which is described as a "post-crash-fire scenario". 7 is designated that in a (from outside the fuselage) damaged aircraft structure 8th (with a defective outer skin 33 ) will cause a state of emergency for passengers and aircrew due to leading external mechanical impact and a subsequent fire impact on the illustrated aircraft areas due to leaked and inflamed kerosene in the fuselage or cabin inside, then the viewer is clear that fire protection measures must be provided, If you want the (possibly also accident) passengers and the flight crew completely from the passenger resp. Cabin area on the emergency slide evacuate as quickly as possible, so still with enough available period to the outside of the aircraft. Consequently, there is a need that the recognized disadvantages (fire hazards) inherent in and also referred to in the traditionally installed solution should be remedied by improvements. In the following, corresponding improvements are proposed with which, on the model of 3 and id F. the 4 . 4a . 5 . 5a . 6 That need can be satisfied.

In order to implement (satisfy) this aspect (that need), that is to increase the fire safety safety for separated and close to an outer skin 33 The interior of the aircraft fuselage (cabin areas), for example, a passenger plane, aims, is also mentioned at this point that a burn-through film 11 is proposed from a fire-resistant film material, which is modeled on the 3 a hull insulation paucet 19 Wrapped in the interior insulation of an aircraft fuselage. A fire-retardant film material will not suffice. Through the complete foil wrapping of the hull insulation package 19 One will be able to counter the threatening dangers in the (unpredictable and unwanted) fire-emergency catastrophe of an aircraft - for whatever cause (fatal) reasons - in order to counter the threatening dangers of a fire catastrophe.

In the 3 Now the viewer is presented with the presentation of an advanced hull insulation. Very vividly, the arrangement of the fuselage insulation is conveyed to the fuselage structure of an aircraft fuselage, which consists of several in the direction of the aircraft's longitudinal axis 9 arranged hull insulation packages 19 . 20 . 21 . 22 is integrated with elongated stretched package.

In this respect, there is a single hull insulation package 19 to 22 from the merger of one (with regard to 1 featured) field and a Spantisolierpaketes 17 . 18 to one (individual) core insulation package 19 to 22 , Its arrangement on the fuselage structure of the fuselage largely with the location of the individual field and Spantisolierpaketes 17 . 18 after 1 matches. The merger will increase the frequency of (in 1 shown) separation points (interruptions) of the hull insulation (compared to the traditional installation of such Isolierpakete 3 ) Minimized, at least halved, whereby the attacking fire less fire safety weaknesses are offered in the field of attachment points of the hull insulation.

In contrast to those field and frame insulation packages 17 . 18 whose isolation is only relatively amorphous Semi-finished products, for example glass fiber materials, used that will satisfy the requirements of thermal and acoustic insulation, which is enveloped by a combustible plastic film, takes into account the structure of a single proposed hull insulation package 19 to 22 a fireproof insulation of larger cross-section or a fireproof barrier layer of smaller cross-section or otherwise both burn-through insulating, ie either individually (alone) or with each other in combination within the relevant fuselage insulation package 19 to 22 are arranged. One of the two burn-through-proof insulating means is either close or adjacent to an inner wall region of the foil wall (the foil 11 ). Otherwise, it would be conceivable that the burn-through insulation or the barrier layer also outside and adjacent to the circumference of the film 11 of the individual hull insulation package 19 to 22 is guided by adhesive bonding to a Stringerauflagefläche 31a the stringer 31 and on the circumference of the film 11 is attached.

In the 4 , which will be considered in more detail later, a detail "x" is shown, which in the 3 is specified. There, a fire-proof insulation with a (in comparison of a barrier layer) larger cross-section more clearly visible), which within the trunk insulation package concerned 19 to 22 is arranged and the end of the film 11 emerging from the latter as a shallow (executed with the strength of the burn-through insulation) insulating section 12 led out. A detailed technology, which the sealing of the film finish at the exit point of the insulating section 12 is not considered in more detail.

This flat insulating section 12 , the single hull insulation package 19 to 22 , which has a longitudinally elongated package shape, lengthened outward to the outside, becomes the terminal attachment of the hull insulation packages 19 to 22 on the relevant frame 32a . 32b . 32c be used, with the attachment based on the 4 is explained.

Coming back to the 3 you will also be able to see that, for example, a first hull insulation package 20 adjacent a stringer pad 31a of the (relevant) stringer 31 between a (so figured) third bulkhead 32c and a first frame 32a , which occupy a defined distance c, is arranged.

It is also shown that this first hull insulation package 20 front and back each sideways to (two) frame longitudinal sides 41a . 41b a so-called first spantes 32a is guided, the exiting insulating section 12 together with that of a (hereinafter referred to) second hull insulation package 21 (after the model of 4 ) on the first frame 32a is attached.

Likewise - after the same technology - the second hull insulation package 21 adjacent the stringer pad 31a the stringer 31 between the first frame 32a and a second frame 32b , which occupy those defined distance c, arranged, the exiting insulating section 12 together with that of a fourth (hereinafter indicated and numbered) fourth core insulation package 22 (after the model of 4 ) on the second frame 32b is attached.

This is supplemented, including a third hull insulation package 19 - according to the described technology - adjacent a stringer pad 31a of the (relevant) stringer 31 between the mentioned third frame 32c and a latter arranged at a distance c upstream bulkhead, whose exiting insulating section 12 together with that of the first hull insulation package 20 (after the model of 4 ) on the third frame 32c is attached. In addition, the installation is a fourth hull insulation package 22 recognizable, its exiting insulating section 12 together with that of the second hull insulation package 21 (after the model of 4 ) on the second frame 32b is attached.

For fastening burn-proof fasteners 4 . 13 used, whose shape and structure from the 5 . 5a . 6 . 6a and the arrangement thereof (in connection with that representation of the attachment of the exiting insulating sections 12 on the frames 32a to 32c ) from the 4 becomes clear.

It is added to the preceding remarks that one embodiment which involves the laying of one of the hull insulation packages 19 to 22 concerns, which could be applied to an inner surface area of an outer skin panel, is not considered closer; although this type of transfer would theoretically be conceivable. Insofar, it is only to the extent that a laying of the individual hull insulation packages below the intended Stringer contact surface 31a and on the outer skin 33 located similar to the pre-installed installation. The attachment could also be on the given frame longitudinal sides 41a . 41b a single Spantes done.

In the 4 now becomes the attachment of the first and second hull insulation package 20 . 21 at the first frame 32a illustrated, this embodiment of the attachment, as previously indicated, equally at all in the direction of the aircraft's longitudinal axis 9 arranged frames 32a . 32b . 32c (up to an nth bulkhead) with two serial stringer pad 31a overlying hull ice lierpaketen 20 . 21 , that of the frame-bound stringer support surface 31a rest, is technologically implemented. It is assumed that (in the context of upstream work) the Spantenbefestigungsbereich 15 a through hole 24 is bored.

In addition, a defined package area of the individual hull insulation package 19 to 22 , the to the frame system at the back (laterally right) positioned first frame longitudinal side 41a of the (here) first frame 32a is provided, except for a so-called hole-like implementation.

The downstream package area of the relevant core isolation package 19 to 22 , who (after the model of the 1 ) resting on the former 40 and laterally adjacent the angled end of the bulkhead support 40 is continued, the end of the film sets up to a first flat Isolierendabschnitt 12a of the (for example, first) core insulation package 20 away, the other side (left side) of a front side positioned second frame longitudinal side 41b of the first frame 32a is fitting. That first flat insulating section 12a is a so-called hole-like recess recessed. Since it is provided that a second flat insulating section 12b at the end of the film termination of the adjacent (serially arranged) second core insulation package 21 is continued, on or lying under the bearing surface of the first insulating section 12a is arranged, is that insulating end portion 12b also excluded a so-called hole-like recess. If the hole-like passage, the through hole and those two hole-like recesses are arranged congruent, can be burned through trained Isolierstift of the first fastener through the holes that defined package area of the first fuselage insulation package 20 , the through hole of the frame mounting portion 15 and those of the two flat insulating sections 12a . 12b to lead.

The structure of the Isolierstiftes is after the 5 . 5a with a cylindrical core element 25 and a cylinder-like plastic-like sheath 28 realized, the core element 25 near the ends of the pencil 27 each a flange-like increase 26 is scheduled. The core element 25 whose shape can be seen from the longitudinal section after the 5a is in that plastic-like sheath 28 (one bedded, about the middle of the shroud 28 is a kind of ring) flange 29 taken out, from which - inserting on the cylinder size of a casing 28 and parallel to a pin axis 43 of the first fastening element 4 (the insulating pin) distributed over its extended length - several fir-shaped elevations 30 are positioned, which are arranged at a distance a from each other. The fir-shaped elevations 30 are comparable to a kind of staircase gradation whose gradation 44 is conical, with the beginning of the gradation 44 on the circumference of the casing 28 and their descending conical shape with a conical decrease in the circumference of the shell 28 is realized. The end area of the casing 28 is realized dome-shaped, which is designed as Rezess. The outer shape of that end region is similar to the shape of a paraboloid, which is comparable to the course of a parabolic rotating body whose longitudinal section is realized with a parabolic shape, wherein at the branch end of the parabola each one to the pin axis 43 vertically drawn staircase-like gradation 44 is continued. The core element 25 is made of metals, which consists of a steel, preferably a stainless steel. The sheathing, however, is realized with a thermally poorly conductive plastic.

The structure of the second fastening element 13 is after the 6 . 6a realized with a so-called truncated cone body in the manner of a truncated cone-like cage body. The ground and top surface 46 . 47 is realized with burn-trained insulating or ring elements, on the outer periphery of a burn-through trained insulating jacket 50 is attached, the randseitlich the element of the base and the element of the top surface is mechanically connected.

The truncated cone body could be made such that the top surface 46 is realized with a first insulating, the center of the disc is excluded a hole. The hole diameter of this hole should be smaller than the outside diameter of the end portion realized with the shape of a paraboloid 42 the dome-shaped casing 28 be such that the hole wall of this running with a plastic insulating disc taut over the branch end of the parabola of the parabolic end portion 42 the sheath 28 lead. Without anticipating the further remarks, it is intended that the first insulating disk designed with a plastic, although on the dome-shaped sheathing because of the conceded compliance of the plastic 28 of the first fastening element 4 the insulating pin (taut) will move, whereas in the reverse direction of the insulating this latter only with mechanical effort on the dome-shaped shell 28 lead. Because this design also has a footprint 46 of the truncated cone body forming the second plastic insulating disk will be considered, the disc center is except a hole, the hole diameter of this hole is equal to or slightly larger than the outer diameter of that dome-shaped shell 28 of the first fastening element 4 be the insulating pin so that this second insulating over that dome-shaped sheathing 28 the Isolierstif let it lead. Coming back to the presentation of the 3 and 4 This makes it clear that ultimately a so executed second fastener 13 the flat Isolierierendabschnitte to be fixed and fastened 12 . 12a . 12b on the frame longitudinal sides 41 . 41a . 41b the frame 32 . 32a . 32b . 32c should be suitable.

Otherwise, a trained as a truncated cone body second fastener 18 with a first plastic-like insulating ring 48 larger ring circumference and a second plastic-like insulating ring 49 realized smaller ring circumference, thereby framed the first insulating ring 48 circumferentially the top surface 47 the truncated cone body of that second fastener 13 , whereas the second insulating ring 49 circumferentially the base area 46 the truncated cone body of that second fastener 13 border. It is conceivable that on the inner ring diameter of the first and the second insulating ring 48 . 49 a plurality of spaced at the ring circumference insulating struts 51 are fixed, which are arranged vertically standing distributed on the circumference of the ring. But it is sufficient that these Isolierstreben 51 only the ring circumference of the second insulating ring 49 with the outer periphery of a disk-shaped core element 52 , wherein the outer diameter of the core element 52 (substantially) smaller than the inner ring diameter of the second insulating ring 49 is. The core element 52 and the second insulating ring 49 lie plan in a plane, being the core element 52 perforated disc center punched and embedded in a plastic-like sheath.

It should be noted that the hole diameter of the second insulating ring 49 smaller than the outer diameter of the end portion realized with the shape of a paraboloid 42 the dome-shaped casing 48 be executed; namely from the above with regard to the preceding hole formation of the first insulating of the aforementioned embodiment reasons. The disc-shaped core element 42 is made of metal. It consists of a steel, preferably a stainless steel. The mentioned sheath of the core element 2 is realized with a thermally poorly conductive plastic.

The completeness is mentioned that the insulating washers and the insulating rings, with which the second fastener 13 is constructed, are arranged parallel to each other, wherein the base 46 forming element, so the second insulating ring 49 to the top surface 47 forming element, ie the first insulating ring 48 , in the ring spacing b (height distance of the rings) is arranged. The scope of these elements is that of insulating 50 wrapped around the outside of the rings is attached.

It is added that the second fastener 13 can also be compared with the shape of a so-called truncated cone-like cage body, because at its base and top surface 46 . 47 Randseitlich several burn-through trained Isolierstreben 51 In this case, the circumferentially distributed insulating struts are arranged 51 ringrandseitlich the second insulating ring 49 larger ring circumference and the first insulating ring 48 attached, support the two rings like a cage. Otherwise, it would be conceivable that these Isolierstreben 51 against one (the base area 46 forming) second insulating and against a (the top surface 47 forming) first insulating support, which the ends of the insulating struts 51 angeibenseitseitlich are attached.

Also, it must not go unmentioned that several hull insulation packages 19 to 22 inside one of frames 32 . 32a . 32b . 32c limited trunk area of the fuselage structure are positioned on the inner fuselage structure of the fuselage. It is provided that the hole-like recess of the flat Isolierendabschnitte 12 . 12a . 12b that (at least two) hull insulation packages 19 to 22 , which each one side of a long side 41 . 41a . 41b of the spantes 32 . 32a . 32b . 32c an insulating section is continued, designed as a burn-through insulating insulating first fastener 4 is transferred, whereby on the relevant frame longitudinal side 41 . 41a . 41b . 41c a so-called overlap of Isolierendierendabschnitte 12 . 12a . 12b is formed, whose attachment to the frame longitudinal side 41 . 41a . 41b . 41c with the formed as an insulating disc or ring member second fastener 13 on the first fastening element ( 4 ) is secured.

Ultimately, in the 7 a structure holder 53 shown, for example, a stringer 31 , on the outer skin 33 [(and possibly) attached to the contact surface of the respective stringer attachment is attached. This structure holder 53 but also on the frame 32 . 32a . 32b . 32c or the unattached end of a spider 32 . 32a . 32b . 32c be attached to the (extended) bulkhead. From this representation, it can be seen that there is quite a possibility of those shallow insulating sections 12 . 12a . 12b holding a hull insulation package 19 to 22 are continued, intermediate the bearing surfaces of the structure holder 53 and a (here angled) support element by riveting or screwing the element assembly to secure with another burn-resistant fastener. That other fastener is provided with a rivet made of steel or titanium, or with a screw and nut made of steel or titanium or plastic. The screw connection element may consist of aramid or of a CFRP material.

The presentation of the 7a provides that rivet attachment or attachment of the insulation end sections 12 . 12a . 12b on the frame-extended structure holder 53 , that of the bulkhead of the (without beam carrier 40 executed) Spantes 32 . 32a . 32b . 32c by means of a screw on the frame-extended free end of the relevant Spantes 32 . 32a . 32b . 32c is secured with that burn-through fastener by rivets or screws.

With these measures after the 7 and 7a Ensures that it is also in the range of system arrangements, which riveted to the structure or bolted structure holder 53 Breaching the flames of a fire (penetrating from outside the aircraft environment) is prevented. This so-called "fire barrier" is screwed or riveted between these precautions and the aircraft structure.

Finally, it is added that the hull insulation package, which in terms of 1 is considered, nor a conventional glass fiber (glass wool) existing insulation package 3 is. The core material of that insulating package is sufficient 3 only the requirements of thermal and acoustic insulation.

They are (also here) mostly fiber products, mainly using fiberglass materials. That, due to a (clearly) existing risk of fire for passengers) and flight crew by this conventionally used construction of the insulating package 3 , in the future, even improvements to the latter will be necessary, one wants the fire safety of that known Isolierpaketes 3 continue to expand, is likely the example of 2 have become clear.

In order to meet the requirements of a fire protection safety with respect to the overall arrangement of the inner insulation of the fuselage at least halfway, the core material (the glass fibers) of the respect 3 mentioned hull insulation packages 19 to 22 (up to a nth core insulation package) completely from the mentioned burn-through-proof film 11 envelops. The foil 11 for wrapping the relevant hull insulation package 19 to 22 is proposed, with a burn-through material, ie with a film material which is resistant to burn through the film wall due to permanent action of the flames (in the 2 shown) fire 7 on the outer surface of the film 11 respectively their film material is safe realized. This foil material becomes for a flaming fire 7 to which a film surface area of this film 11 during a fire disaster that took place in the 2 being exposed is an absolute obstacle.

Since the phrase "burn-through-resistant" strongly correlates with the statement "fire-resistant", where "fire-resistant" means "resistant to fire", therefore, the film becomes 11 be realized with a material of high and durable fire resistance, which is designed to be sufficiently resistant. The amount of this resistance to fire correlates 7 with the type of film used and the film wall thickness used; wherein the durability of the resistance with a period of use of the film 11 which is regarded as a very long period of time, and then over a (finite) running time of longer time interval (from the start of use of the film 11 expected) will run; For example, until the expiration of a time at which the film material for reasons of film aging its resistance to fire 7 will lose or be expected that this resistance to fire 7 will subside.

Indication: insensitive "do not be sensitive" (here) against the flame exposure of the fire 7 on the film material ahead. As other sensitivities of the film material, for example against the outside of the insulating package 3 on the film material acting ambient conditions at the site of the film 11 , it would be conceivable, the statement: "burn-through" in the main with the statement: insensitive "against occurring fire 7 The film material used may well be insensitive to other influences, for example against contamination and other chemical influences in the air, against the influence of electrical hazards, against the influence of the ambient air pressure, etc., and should (in aircraft construction).

The slides 11 should therefore be realized with a material of high and durable fire resistance, which is resistant and / or insensitive to fire occurring 7 is formed, which is why the burning of a film wall by the influence of the flaming fire 7 even if permanently exposed to the surface of the film surface, there is no propagation and the fire flaming against the surface of the film surface is spread 7 is prevented.

1

insulating material

2

wrapping foil

3

insulation package

4

first Fastener; insulated pin

7

Post-crash fire scenario; Fire

8th

aircraft structure

9

aircraft longitudinal axis

11

by fireproof foil

12

flat Isolierendabschnitt

12a

first Isolierendabschnitt

12b

second Isolierendabschnitt

13

second Fastener, truncated cone body

15

Spantenbefestigungsbereich

17

Feldisolierpaket

18

Spantisolierpaket

19

Rumpfisolierpaket, third

20

Rumpfisolierpaket, first

21

Rumpfisolierpaket, second

22

Rumpfisolierpaket, fourth

24

Through hole; drilling

25

Core element (of the first fastener 4 ), cylindrical

26

Elevation (of the core element 25 ), flange-like

27

Pin end (of the core element 25 )

28

jacket

29

flange

30

survey fir-like

31

Stringer

31a

Stringerauflagefläche

32

rib

32a

first rib

32b

second rib

32c

third rib

33

shell

33a

inner surface area (of an outer skin field of the outer skin 33 )

40

rib carrier

40a

End (of the bulkhead 40 )

41

Frame longitudinal side

41a

first Frame longitudinal side; on the back (left), sideways

41b

second Frame longitudinal side; front (right), sideways

42

end

43

Pin axis (of the first fastener 4 )

44

gradation

46

Base (the second fastener 13 )

47

Covering surface (of the second fastening element 13 )

48

first insulating ring

49

second insulating ring

50

insulating

51

Isolierstrebe

52

Core element disk-like

53

Structure Holder

a

Distance (the fir-like elevations 30 )

b

Distance (the insulating rings 48 . 49 )

c

Distance (the rib 32 . 32a . 32b . 32c )

Claims (22)

Isolierpaket-arrangement for the inner insulation of an aircraft fuselage whose strength composite in addition to stringers ( 31 ), with which all outer skin fields of an outer skin ( 33 ) of an aircraft fuselage structure, a plurality of ribs ( 32 ), which is perpendicular to the aircraft longitudinal axis ( 9 ) are arranged at a defined distance (c) and at the stringer ( 31 ), to which at the non-attached end a former support ( 40 ), which is parallel to the aircraft longitudinal axis ( 9 ) in which a plurality of core insulation packages ( 19 to 22 ), which have an elongated elongated packet shape, in the direction of the aircraft longitudinal axis ( 9 ) are located on the aircraft fuselage structure, the longitudinally adjacent a Stringerauflagefläche ( 31a ) the stringer ( 31 ) attached to the aircraft fuselage, or which lie longitudinally adjacent an inner surface area ( 33a ) of an outer skin panel, and these core insulation packages ( 19 to 22 ) on a longitudinal side of the frame ( 41 . 41a . 41b ) of the frames ( 32 . 32a . 32b . 32c ), which are also completely covered by a foil ( 11 ) and encased within a space including an interior trim and the skin panels, the structure thereof having a larger cross section fireproof insulation and / or a lower cross section fireproof barrier layer, either singly or in combination within the fuselage insulation package (US Pat. 19 to 22 ), in which the insulation or the barrier layer is guided close or adjacent to an inner wall region of the film wall or only the insulation outside and adjacent to the circumference of the film ( 11 ) of the hull insulation package ( 19 to 22 ), the length end side of the hull insulation package ( 19 to 22 ) to the outside with a flat Isolierendierendabschnitt ( 12 . 12a . 12b ), which corresponds to a frame attachment area ( 15 ), which below the frame longitudinal sides ( 41 . 41a . 41b ) of a spider ( 32 . 32a . 32b . 32c ) and nearby the Stringer ( 31 ), with fire-resistant fasteners ( 4 . 13 ) on the frame ( 32 . 32a . 32b . 32c ) is attached. Insulating package arrangement according to claim 1, characterized in that the frame mounting area ( 15 ) a through hole ( 24 ) and a package area of the hull insulation package ( 19 to 22 ), the one side of a front or rear side disposed longitudinal side of the frame ( 41a . 41b ) is present, ausgenom a hole-like implementation men as well as the continued isolation section ( 12 . 12a . 12b ), the other side of a front or rear side disposed longitudinal side panel ( 41a . 41b ) is fitted, a hole-like recess is recessed. Isolierpaket arrangement according to claims 1 and 2, characterized in that a first fastening element ( 4 ), which is realized with a burn-through insulating pin, is guided through the hole-like passage, the through hole and the hole-like recess, provided that the latter are arranged congruently. Isolierpakelsanordnung according to claim 3, characterized in that the structure of the insulating pin with a cylindrical core element ( 25 ) near the end of the foundation ( 27 ) a flange-like elevation ( 26 ) is attached, and a cylindrical plastic-like sheath ( 28 ) is realized. Insulating package arrangement according to claim 4, characterized in that the core element ( 25 ) in the plastic-like sheath ( 28 ) is bedded. Isolierpaket arrangement according to claim 4, characterized in that approximately centrally of the sheath ( 28 ) a flange ( 29 ) is led out, starting from the cylinder circumference of the casing ( 28 ) and parallel to the core element ( 25 ) over its extended length several fir-shaped elevations ( 30 ) are positioned, which are spaced from each other. Isolierpaket arrangement according to claim 6, characterized in that the fir-shaped elevations ( 30 ) are comparable to a stepped graduation whose graduation ( 44 ) is tapered, the beginning of the gradation ( 44 ) at the circumference of the casing ( 28 ) and their descending conical shape with a conical decrease of the circumference of the casing ( 28 ) is realized. Insulating package arrangement according to claim 4, characterized in that the end region ( 42 ) of the sheath ( 28 ) is realized dome-shaped, which is designed as a recess, wherein the outer shape of the end region ( 42 ) is realized with the shape of a paraboloid, which is comparable to the course of a parabolic rotating body whose longitudinal section is realized with a parabolic shape, wherein at the branch end of the parabola each one to the pin axis ( 43 ) vertically drawn step-like graduation ( 44 ) is continued. Insulating package arrangement according to claim 4, characterized in that the core element ( 25 ) is made of metal, which is made of a steel, preferably a stainless steel, and the sheath ( 28 ) is realized with a thermally poorly conductive plastic. Insulating package arrangement according to claims 1 and 8, characterized in that a second fastening element ( 13 ) is realized with the shape of a truncated cone body (truncated cone-like cage body), at its base and top surface ( 46 . 47 ), which are realized with burn-trained insulating or ring elements, Scheibenibenrandseitlich or ringrandseitlich a disc or a ring larger outer periphery a burn-through trained insulating jacket ( 50 ) is set. Isolierpaket arrangement according to claims 8 and 10, characterized in that the top surface of the truncated cone body is realized with a first insulating, which is executed perforated disc center whose hole diameter is smaller or almost equal to the outer diameter of the realized with the shape of a paraboloid end region ( 42 ) of the dome-shaped casing ( 28 ) is such that the hole wall of the insulating washer (due to the compliance of the plastic) tautly over the branch end of the parabolic end portion ( 42 ) of the sheath ( 28 ). Isolierpaket arrangement according to claim 10, characterized in that the cover surface ( 47 ) of the truncated cone body with a first plastic-like insulating ring ( 51 ) larger ring circumference and a second plastic-like insulating ring ( 49 ) smaller ring circumference is realized, wherein at the inner ring diameter of the first insulating ring ( 48 ) and on the outer ring diameter of the second insulating ring ( 49 ) a plurality of spaced at the ring circumference insulating struts ( 51 ) are fixed, which are arranged vertically standing distributed on the circumference of the ring. Insulating package arrangement according to claims 4, 8, 10 and 12, characterized in that the structure of the second insulating ring ( 49 ) with a disk-shaped core element ( 52 ), which is executed perforated disc center, the hole diameter is smaller or almost equal to the outer diameter of realized with the shape of a paraboloid end region ( 42 ) of the dome-shaped casing ( 48 ), and a plastic-like sheathing is realized. Isolierpaket arrangement according to claim 13, characterized in that the disc-shaped core element ( 42 ) is embedded in the plastic-like sheath. Isolierpaket arrangement according to claim 13, characterized in that the disc-shaped core element ( 42 ) is carried out of metals, the egg steel, preferably a stainless steel, and the sheathing of the core element ( 42 ) is realized with a thermally poorly conductive plastic. Isolierpaket arrangement according to claim 10, characterized in that the second fastening element ( 13 ) is realized with the shape of a truncated cone-like cage body, at its base and top surface ( 46 . 47 ) Scheibenibenseitseitlich a disc larger disc circumference or marginal margin of the ring of a larger ring circumference several burn-trained Isolierstreben ( 51 ), which a second insulating disk of the base ( 46 ) against a first insulating disk or the first insulating ring ( 48 ) of the top surface ( 47 ) is supported, are attached. Insulating package arrangement according to claims 1 to 3 and 10, characterized in that a plurality of core insulation packages ( 19 to 22 ), which are inside one of frames ( 32 . 32a . 32b . 32c ) are positioned on the inner fuselage structure of the fuselage, and the hole-like recess of the flat insulation end sections ( 12 . 12a . 12b ) of those (at least two) hull insulation packages ( 19 to 22 ), each on one side of a longitudinal side (( 41 . 41a . 41b ) of the spider ( 32 . 32a . 32b . 32c ) an insulating section is continued, designed as a burn-through insulated insulating first fastener ( 4 ) is transferred, characterized on the relevant frame longitudinal side ( 41 . 41a . 41b . 41c ) an overlap of the insulating end sections ( 12 . 12a . 12b ) is formed, whose attachment to the frame longitudinal side ( 41 . 41a . 41b . 41c ) formed with the insulating or ring member second fastener ( 13 ) on the first fastening element ( 4 ) is secured. Isolierpaket arrangement according to claim 1, characterized in that the structure and the position of the individual hull insulation package ( 19 to 22 ) with that of a traditionally used Feldisolierpaketes, in the direction of the aircraft axis ( 9 ) on the aircraft fuselage structure or close to the latter and longitudinally adjacent to that stringer bearing surface ( 31a ) of the stringer ( 31 ) is located at a defined distance (c), and a traditionally used Spantisolierpaketes, the longitudinal fitting the division longitudinal sides ( 41 . 41a . 41b ) and the former ( 40 ) of the individual spantes ( 32 . 32a . 32b . 32c ), is consistent, in each case from a merger of the individual field and Spantisolierpaketes that completely by a burn-through film ( 11 ) and / or is provided with a burn-through-proof insulation and / or with a sag-proof barrier layer, the burn-through-proof elements of the relevant field and frame insulation package being connected to the merged core insulation package ( 19 to 22 ) are continued without interruption. Insulating package arrangement according to claim 1, characterized in that the flat Isolierierendabschnitte ( 12 . 12a . 12b ), which is a hull insulation package ( 19 to 22 ), a structure holder ( 53 ), which protrudes the stringer ( 31 ) on the outer skin ( 33 ), or at the bulkhead of the individual frame ( 32 . 32a . 32b . 32c ), the unattached end of the frame ( 32 . 32a . 32b . 32c ), or at the beam carrier ( 40 ), which, with another fireproof fastening element, hold the structure holder ( 53 ) are screwed or riveted. Insulating package arrangement according to claim 19, characterized in that, in the area of system arrangements which relate to the structure holder ( 53 ) and a holding separate support element, the insulation ( 1 ) and the film ( 11 ) and / or the insulating sections ( 12a . 12b ) of the hull insulation packages ( 19 to 22 ), which are designed as Fire Barrier, screwed and riveted. Insulating package arrangement according to claim 1, characterized characterized in that the further fastening element is a steel or titanium rivet or steel or titanium or plastic existing screw connection element. Insulating package arrangement according to claim 21, characterized in that the screw connection element is made of aramid or made of a CFK material screw together with nut is.