CN100430295C - Insulation arrangement for the internal insulation of a vehicle - Google Patents

Abstract

The present invention relates to an insulation structure for the internal insulation of a vehicle. The insulation structure is improved in such a way that using it a fire incursion of the flames of a source of fire acting from outside the vehicle environment into the vehicle interior is excluded as much as possible, an increase of the fire protection safety for separate interior regions lying proximal to a structure external skin being implemented by the type of the film insulation of the insulation package. The insulation structure comprises an insulation package (3), in which an insulation core (1) is embedded, and a film (11). The insulation package (3) is positioned inside an intermediate space which encloses internal paneling and an external skin. It is completely enclosed by the film (11). The film (11) is implemented using a burn-through safe film material, which is an obstruction to a flaming fire, to which a film surface region of this film is subjected during an occurring fire catastrophe.

Description

The isolation structure that is used for the aircraft internal insulation

The cross reference of related application

The application requires the preceence of DE 10 2,004 001 083 that submitted on January 5th, 2004 and the US 60/600,107 that submitted on August 9th, 2004, and be incorporated herein this two as a reference.

Technical field

The present invention relates to such as isolated and/or protection fire.Particularly, the present invention relates to a kind of isolation structure that is used for the internal insulation of aircraft.This isolation structure can be used to protect the interior zone of aircraft to prevent the intrusion from the fire outside the aircraft environment.

Background technology

Conventional isolated system, the isolated system shown in Fig. 1 for example consists essentially of and embeds the core material in the insulation package and seal.Core and isolated material generally include the product of fiber industry, particularly use glass fiber material (glass wool).This material has satisfied about heat insulation and sound-deadened demand.In order to realize that more unbodied half-blank is installed (attached) on Flight Vehicle Structure, utilize wrap film that insulation package (comprising these half-blanks) is sealed.Reinforcement is attached to the end of wrap film so that therefore by means of fastener (therefore being accomplished) insulation package is attached on the body structure surface of aircraft.

Such insulation package utilizes fastener to be attached on the aircraft fuselage structure, described fastener usually by plastics for example polyamide make.The typical isolation system that comprises glass wool and simple plastic film can have about 60 seconds burn through time.

Be parked under the situation that ground aircraft catches fire, promptly " collision postignition situation " (Fig. 2), the kerosene of burning may cause the aluminum cell of aircaft configuration and even the fuselage isolation structure of aircraft (internal insulation structure) to burn.All the time wishing to increase burn through time or increase structure can the flameproof time.

As mentioned above, representative type isolation fastener is made by non-metallic material (plastics), and described material usually can not be anti-over a long time fiery under disaster scenario.Thus, the isolation structure of burning (insulation package) may break, and will (suddenly) uncontrollable obstacle or other fire hazard point occur thus.

WO 00/75012 A 1 discloses the fuselage isolation structure that is used for airframe of a kind of being called " fire blocks ".The disclosure file discloses the main spacer of a kind of conduct and has been positioned an insulation package in the area of space, and described area of space is between fuselage interior panel and exterior fuselage skin.In this case, this insulation package film protection of making by fire-proofing material in a plurality of zones.The direct exterior skin (as fire-proof curtain) in this fireproof membrane zone towards airframe.Ignore and use this scheme to provide inadequate protection to prevent the fact of catching fire insulation package and fuselage interior zone; because during fire; flame may pass impaired exterior skin and may engulf the internal insulation structure from the aircraft outside; promptly will pass (unique) fire-proof curtain; rather than pass fire-resistant film during damage in that permanent catching fire taken place, so only plan fireproof membrane is located the long-term fire savety that may not guarantee about the fuselage interior zone partly.

Summary of the invention

According to exemplary embodiment of the present invention, a kind of isolation structure that is used for the internal insulation of aircraft is provided, described isolation structure is suitable for being arranged in the outside or the intermediate space between the exterior skin of the inside panel of aircraft and aircraft.This isolation structure comprises and has the insulation package of isolating core that described isolation core embeds in the described insulation package.In addition, have the film that is made of anti-film (the burn-through safe film) material that burns, wherein this membraneous material is used to stop catching fire that the film surface zone of this film stands during firing accident.According to an aspect of the present invention, insulation package is basically by this thin film encapsulation.The hose-like end of film is formed on the edge of the outside of the end of described film and thin film encapsulation thereof and insulation package, suppose that the contact position of the membrane wall that hose-like is shaped is shaped as the attachment portion of the film with planar design, wherein said wall is radially relative with half of flexible pipe perimembranous.The attached end of film is according to Z-shaped folding, and one of the film fold domain of attachment portion that will be by folding the film that obtains is stacked on one.

One exemplary embodiment of the present invention can be allowed a kind of derivative aircraft isolation structure, and described structure is used for internal insulation, invade the inside of aircraft so that can prevent or postpone the flame of the burning things which may cause a fire disaster that the outside causes around the aircraft.In addition, can believe the increase of isolating the fire savety of each separation interior zone that just can realize the close structure external skin in position by the film of such insulation package.

Description of drawings

According to the following drawings, reference example embodiment, the present invention will be described in more detail.

Fig. 1 shows the known fuselage isolation structure of commercial aircraft;

Fig. 2 shows the scene of the commercial aircraft collision postignition of parking;

Fig. 3 shows a kind of isolation structure that is used for the commercial aircraft internal insulation according to an exemplary embodiment of the present invention, and the insulation package of described isolation structure has the anti-thin film encapsulation that burns;

Fig. 4 shows a kind of isolation structure shown in Fig. 3 according to an exemplary embodiment of the present invention, and described isolation structure has the anti-film reinforcement that burns thin film encapsulation formation by layering;

Fig. 5 shows a kind of remodeling of the isolation structure shown in Fig. 4 according to an exemplary embodiment of the present invention, wherein shows by another anti-partial thin film that burns thin film encapsulation formation to seal;

Fig. 6 shows a kind of remodeling of the isolation structure shown in Fig. 4 according to an exemplary embodiment of the present invention, wherein shows single anti-Z-shaped folding (in the example) that burns film;

Fig. 6 a shows the diagram of the local B shown in Fig. 6.

The specific embodiment

For Fig. 1 is made an explanation, also will point out for the purpose of introducing, in the intensity stay of airframe, except the stringer 31 of all exterior skin plates of being used to strengthen aircraft fuselage structure, airframe also comprises a plurality of frameworks 32, and these frameworks separate the interval c that necessarily (is similar to) perpendicular to aircraft longitudinal axis (not shown) and place and/or be attached on the stringer 31.The Vierendeel girder 40 that is parallel to the extension of aircraft longitudinal axis is integrated on the not attached end of these frameworks 32, and (not attached freedom) end of Vierendeel girder 40 is perpendicular to the longitudinal axis bevel (in this embodiment) of aircraft.

The viewer that is illustrated as among Fig. 1 provides about the impression of (totally having numbered) insulation package 3 in (nearside) outside or the position on the exterior skin 33 of aircraft.This insulation package 3 is under each situation, all be embodied as and have plate insulation package 17 and framework insulation package 16, both (in the zone of the common structural support member that uses) placed apart also is attached to aircraft fuselage structure (near the zone of exterior skin).From Fig. 1, it can also be seen that, plate insulation package 17 spaced-apart interval c are positioned between (two) framework 32, inner surface area near the exterior skin plate of exterior skin 33, framework insulation package 16 is positioned on the Vierendeel girder 40, its from the vertical side of framework 41 along extending laterally (and in a side pressure on the vertical side 41 of framework).These two insulation package are sealed fully by film 2.They are arranged in intermediate space (Fig. 1 can not find out) inside, and described intermediate space is sealing the inside panel of aircraft and the exterior skin plate of exterior skin 33.

In order to illustrate the fire savety that utilizes the attainable improvement of exemplary embodiment of the present invention and the improvement of the area of space that is separated out, wherein said area of space comprises intermediate space, exterior skin 33, and the position is parallel with latter's (limit and be provided with perpendicular to the fuselage longitudinal axis) and the inside panel of isolated aircraft cabin, referring to the diagram among Fig. 2, the fire condition in the passenger plane of considering to park.In being called " collision postignition situation " 7 in the case of fire (Fig. 2) of simulation as can be seen, under the situation that causes breakdown plane structure 8 (exterior skin 33) owing to external mechanical influence, and/or overflow and/or light and cause under this aircraft zone catches fire result's situation simultaneously owing to the kerosene of fuselage and/or engine room inside, emergency situation may take place in passenger and aircrew.Therefore, need all the time to improve isolation structure or setting, prolong flameproof time or long-term maintenance isolation so that allow.

Now, improve near for example this needs of the fire savety that separates interior zone of the structure external skin of passenger plane in order to implement, for instance, the anti-film of being made by fire-resistant membraneous material 11 that burns is adopted in suggestion, and described film 11 is being sealed the insulation package 3 of the internal insulation that is used for airframe traditionally fully according to the pattern among Fig. 3.As long as by insulation package 3 is encapsulated in the film; can be no matter (unpredictable and do not wish occur) fire of the aircraft (being typically aircraft) what initial (destructions) reason causes prevents potential danger in protecting, so that overcome the shortcoming of pointing out in the beginning.Preferably can adopt completely and seal.

Another kind of consider to comprise the have glass fibre typical isolation packaging part 3 of (glass wool), isolate core 1 and embed in the insulation package 3.In this case, core material satisfies about heat insulation and sound-deadened demand.This (even at this) is the product of fiber industry normally, mainly uses glass fiber material.Below discuss the connection type situation of thin film encapsulation formula insulation package 3 and the use of respective fastener in more detail, so that satisfy situation to small part about the fire safety sexual needs of the overall setting of the internal insulation of airframe.

Recommendation is used to seal the film 11 (for predetermined purpose) of insulation package 3 will seal insulation package 3 fully.This anti-burns material by using, and promptly uses membraneous material to realize, described material is avoided by membrane wall because fiery 7 flame dauer effect on the outside face of film 11 and/or its membraneous material causes the risk of burning.Therefore, this membraneous material is the absolute obstacle to burning fire 7, and during the fire shown in Fig. 2, the surf zone of this film 11 will suffer this burning fire 7.

" anti-burning " and word " fire-resistant " height correlation because word, " fire-resistant " is similar to " back-fire relief " to a certain extent, so film 11 uses and have material high, lasting refractory ability and implement, and is implemented as to have enough refractory abilities.In this case, the level of this resistivity to fiery 7 is relevant with the type and the employed membrane wall thickness of employed membraneous material, resistance is relevant with the used life of film 11, so the used life of film 11 is considered very long period and will effectively uses the long time limit (limited) life-span (bringing into use calculating from film 11); For example, until membraneous material 11 will lose owing to film is aging its to the resistibility of fire 7 or the lowered time of resistibility that can expect to fire 7 till.

Word " insensitive " (herein) supposition is insensitive to fire 7 combustions that act on the membraneous material 7.Owing to can expect other sensivity of membraneous material, for example to from the sensivity in the environmental conditions of the use location of film 11 of insulation package 3 external actions on membraneous material, so word " anti-burning " mainly comprises the meaning to the fire 7 " insensitive " that takes place, employed membraneous material can also influence insensitive certainly to other, for example airborne dirt and other chemical affect, to the influence of electrical hazard, to the influence of environmental air pressure, or the like.

Correspondingly, film 11 uses have the material of height, lasting refractory ability and implement, it is implemented as fire 7 that opposing takes place and/or insensitive to it, even therefore be subjected to the dauer effect of fire in the film surface zone, membrane wall can not burnt owing to burning fire 7 yet, and can prevent or hinder burning fire 7 and spread the film surface zone.

For example, another embodiment that is installed on the isolation structure that is used for internal insulation on the commercial aircraft has been shown among Fig. 4.Correspondingly,---according to the pattern among Fig. 3---(only) utilizes single (first) to prevent burning this insulation package 3 that film 11 is sealed fully at first, utilizes another (second) of being layered on the first film 11 to prevent that burning film 11a seals it.In this case, whether comprise that for two films 11,11a the membraneous material of same type do not impose.Importantly all to use anti-(fire-resistant) membraneous material that burns in both cases.

Even afterwards, shown in (using arrow) among Fig. 5, (by for example two-layerly anti-burn film 11,11a forms) the film zone A that limits of film reinforcement is embodied as by means of the 3rd anti-film 11b (by this film is laid on the second film 11a) that burns and carries out the film enhancing, also be to be understood that on the meaning of this qualification, can have for example be layered on second or half of the film surface zone of the first film 11,11a on thin layer.To can not be disengaged sealing fully of film assembly 3, and/or will be counted as realizing by first and/or second film 11, the 11a that seal fully on the insulation package 3.Use the 3rd anti-film 11b that burns to strengthen very meaningful to this film that qualification film zone A carries out; because the 3rd other film 11b will provide other anti-fire action, for example described the 3rd film 11b will cover fully towards the film surface zone of (as shown in fig. 1) exterior skin 33 (as other protection barrier).In addition, for instance, film end 33a, the 33b that the bilateral of the second and the 3rd film 11a, 11b exists be overmolded on also already present two film ends of the first film 11 (may by exert pressure and heat simultaneously film to be connected bring in carry out).

In Fig. 6 (in Figure 4 and 5), show by laying two one decks and be layered on the anti-this film reinforcement that burns film 11,11a (complete closed film assembly 3) on another layer, it is contemplated that at least in theory use a plurality of anti-burn film 11,11a, 11b ..., 11z _nThe film reinforcement of implementing.As preamble about Fig. 5 pointed, the film reinforcement is implemented at the peripheral of second (herein) film 11a by means of the 3rd film 11b once more.

Yet, opposite with Fig. 5, can see following variation.In the example of the first film 11, (in the framework of last working cycle) hose-like end of film 11 is formed on the edge of the outside of end, thin film encapsulation of film 11 and insulation package 3.If the membrane wall that (the hose-like end of the first film 11) hose-like is shaped is layered on another along their rectangle width and one of rectangle length, wherein width is with the flexible pipe circumference half be corresponding, and the development length of the hose-like zone of length and the first film 11 (as thin film encapsulation) is corresponding, and then this hose-like end is shaped as the have rectangular appearance attachment portion 50 of this film 11 of (in birds-eye view).

The length and width limit of the end of the attached end 50 of Cheng Xinging has straight design (in lateral plan) in this manner.

The final condition of the Z-shaped folding attachment portion of the first film 11 can be approx inferred according to the detail drawing B of Fig. 6 a, perhaps clear at least flat attached end 50 is this Z-shaped folding along its spread length, therefore, after folding, end 50 will have the rectangle mating surfaces the attached end B11 of three independent flat parts, C11, D11---according to pattern of Fig. 6 a---they in the final position one be stacked on another.The hose-like end of the second and the 3rd film 11a, 11b also can form among corresponding flat attached end 50a, the 50b in this manner and be folded into Z-shaped subsequently.It is also conceivable that by applying pressure and heat (by means of suitable instrument) will (because Z-shaped folding) be stacked in the attached end 50 on, the attached end of flat part of 50a, 50b is configured as the compacting end body portion of film 11,11a, 11b.

In the attached end of part of attached end 33,33a, 33b and/or compacting end body portion, make through hole perpendicular to mating surfaces, for example the fastener of screw-like Connection Element and so on is guided through described through hole, and uses described fastener that attached end 50,50a, 50b and/or compacting end body portion are attached on the aircaft configuration that provided afterwards.

Also to point out, also consider to use and prevent burning film 11,11a, 11b as fire-proof curtain or jointly as fire-proof curtain.

To point out that also this anti-film 11 that burns utilizes carrier thin film to implement, with the fiber applications of fire-proof curtain on described carrier thin film.The fiber of fire-proof curtain uses ceramic-fibre to implement.Correspondingly, there is the anti-possibility that film 11 or film reinforcement are formed by ceramic-fibre of burning, this film reinforcement has strengthened a qualification film zone A of film 11 at least, otherwise will use multilayer film 11 that are stacked on another to implement.

Reference list

1 core material

2 wrap films

3 insulation package

4,13 securing members

7 collision postignition situations; Fire

8 aircaft configurations

11, the anti-film that burns of 11a, 11b

17 plate insulation package

18 framework insulation package

21 holes

31 stringers

32 frameworks

33 exterior skins

40 Vierendeel girders

The long side of 41 frameworks

The attached end of 50 (films 11)

The attached end of 50a (film 11a's)

The attached end of 50b (film 11b's)

The film zone that A limits

B11, C11, the local attached end of D11 (film 11)

C (framework 32) at interval

Claims (8)

1, a kind of isolation structure that is used for the aircraft internal insulation, described isolation structure are arranged in the intermediate space between the exterior skin of the inside panel of aircraft and aircraft, and this isolation structure comprises:

Insulation package (3);

Wherein isolating core (1) is embedded in the described insulation package;

By preventing burning the film (11) that membraneous material constitutes;

Wherein said membraneous material is used to stop the fire (7) that the film surface zone of this film (11) is stood during firing accident; And

Wherein said insulation package (3) is sealed by film (11) basically,

Wherein the hose-like end of film (11) is formed on the edge of the outside of the end of described film and thin film encapsulation thereof and insulation package (3), suppose that the contact position of film (11) wall that hose-like is shaped is shaped as the attachment portion (50) of the film (11) with planar design, wherein said wall is radially relative with half of flexible pipe perimembranous

Wherein the attached end (50) of film (11) is according to Z-shaped folding, and one of the film fold domain (B11, C11, D11) of attachment portion (50) that will be by folding the film (11) that obtains is stacked on one.

2, isolation structure according to claim 1,

Wherein said film (11) use has the material of height, lasting refractory ability and implements, described film (11) is implemented as the fire (7) that is enough to resist generation and/or insensitive to it, even therefore be subjected to the dauer effect of fire (7) in the film surface zone, membrane wall also can be owing to being subjected to burning fire (7) influence and not burnt, and hinder or prevented burning fire (7) spreading in the film surface zone.

3, isolation structure according to claim 1,

Wherein on the peripheral part of film (11), have film and strengthen zone (A).

4, isolation structure according to claim 3,

Wherein said film strengthens the zone to be implemented by laying a plurality of anti-films (11,11a, 11b) that burn layer by layer.

5, according to each described isolation structure in claim 1 and 4,

Wherein consider to use the anti-film (11,11a, 11b) that burns as fire-proof curtain or jointly as fire-proof curtain.

6, isolation structure according to claim 1,

Wherein film (11) utilizes carrier thin film to implement, and the fiber applications of fire-proof curtain is on described carrier thin film.

7, isolation structure according to claim 6,

Wherein the fiber of fire-proof curtain uses ceramic-fibre to implement.

8, according to claim 3 and 4 or 7 described isolation structures,

Wherein film or film reinforcement are formed by ceramic-fibre.

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