CN100418849C

CN100418849C - Insulation package arrangement for insulating the interior of an aircraft fuselage

Info

Publication number: CN100418849C
Application number: CNB2005800019399A
Authority: CN
Inventors: 雷纳·穆勒; 彼得·图兰斯基; 维尔科·厄斯特赖希; 托尔斯滕·赖内尔特
Original assignee: Airbus Operations GmbH
Current assignee: Airbus Operations GmbH
Priority date: 2004-01-05
Filing date: 2005-01-05
Publication date: 2008-09-17
Anticipated expiration: 2025-01-05
Also published as: CN1906083A; DE102004001049A1; DE102004001049B4

Abstract

according to an exemplary embodiment, which may be installed near the fuselage structure, is believed protect the cabin region of an aircraft against fire whose flames act on the insulation package from outside the aircraft environment, thus clearly facilitating evacuation of the passangers from the vehicle. The insulation package arrangement may comprise several fuselage insulation packages (19-22) of an elongated form. These packages may adjoin the aircraft fuselage structure in the direction of the longitudinal axis (9) of the aircraft. They may longitudinally adjoin a support surface (31a) of the stringers (31) which are attached to the aircraft fuselage, or longitudinally adjoin an inner area (33a) of a panel of outer skin and are attached to both longitudinal sides of the ribs (32). Furthermore those insulation packages (19-22) may be completely enclosed by a burn-through-proof foil (11) which is arranged in a space enclosed by interior paneling and by the panels of the outer skin. The design of a fuselage insulation package may be implemented with burn-throughproof insulation of a larger cross section and/or a burn-through-proof barrier layer of a smaller cross section which are arranged within the fuselage insulation package either singly or in combination. In this arrangement, the insulation or the barrier layer extends near to or adjacent to an interior wall region of the foil wall. As an alternative only that insulation which on the longitudinal end of the fuselage insulation package continues outward with a flat insulation end section is atteched outside of and adjacent to the foil (11) circumference of the fuselage insulation package (19-22). Said end section of insulation is attached to a rib-attachment region which is arranged below the respective longitudinal sides of a rib (32) and near the stringer (31) by means of burn-through-proof attachment elements (4, 13).

Description

Be used for insulation package arrangement with the aircraft fuselage interior isolation

The cross reference of related application

The application requires the DE 10 2,004 001 049 that submits on January 5th, 2004 and the preceence of the US 60/600,106 that submits on August 9th, 2004, and two pieces of documents all are incorporated herein for your guidance.

Technical field

The present invention relates to a kind of free body that is used for aircraft, for example fire insulation or refractory protection.Particularly, the present invention relates to be used for insulation package arrangement that aircraft fuselage interior is isolated.

Background technology

Known traditional isolated system, as shown in Figure 1, this system comprises core material and the isolated material that is embedded in the insulation package haply, also comprises encapsulation piece.This core material and isolated material can comprise the product of fiber industry, specifically, for this product, widespread use glass fiber material (glass wool).This material reasonably well satisfies the heat insulation and sound-deadened demand of being considered.For unbodied relatively half-blank is installed (attaching) on Flight Vehicle Structure (or in its vicinity), (being made by these half-blanks) this insulation package is sealed by sealing thin slice.This end of sealing thin slice can be reinforced, make this insulation package can by the attaching part fully attaching in the body structure surface of aircraft.

In aircraft engineering, the attaching of insulation package occurs on the flank of airframe structure, and wherein employed attaching part is mostly by plastic material--and for example polyamide is made.

Fig. 2 shows the condition of a fire behind the alleged aircraft impact, and wherein Ran Shao kerosene may make the aluminium unit of aircaft configuration and the fuselage free body (internal separators) of aircraft burn.Fire may be burned in the main cabin suddenly by these holes.Therefore, expectation always provides a kind of fire insulation or refractory protection that better is used for airframe, and it can bear such condition of a fire in one long period.

In addition, traditional isolation attaching part is made by non-metallic material (plastics), and it may melt in fire.Thereby expectation always prolongs the anti-fire time of attaching part and free body is remained on its position and prevents that (burning) free body (insulation package) from dropping--such dropping will uncontrollable obstacle occur in aircraft inside.

In addition, WO 00/75012 A1 discloses a kind of airframe free body, and it is described as " refractory body ".This publication document discloses a kind of insulation package, and this insulation package is set to main free body and in the space between fuselage inner panel and exterior fuselage skin.In this device, the zone of this insulation package is by the protection of the film made by resistance fire material, wherein this film zone in the back-fire relief mode directly towards the exterior skin (mode with flameproof enclosure is prevented fires) of airframe.

Summary of the invention

According to an illustrative embodiment of the invention, a kind of insulation package and a kind of corresponding device thereof that is applicable in the space that is set in place between aircraft cabin inner panel and aircraft exterior skin is provided, comprises first insulation package of the first kind and second insulation package of second type.According to an aspect of the present invention, second insulation package of first insulation package of this first kind and second type is combined into the 3rd insulation package of the 3rd type.

Believe that because these subregion points or section line often are the thin spots of free body, this scheme can provide a kind of improved free body because the combination of first and second insulation package can reduce the many subregion points between first and second insulation package.

For example, first insulation package of the first kind can be the insulation package that is used for fuselage flank or frame area, and second insulation package of second type can be the insulation package in the territory, place of fuselage.The difference of this two classes insulation package can be: the size of thickness, size etc. for example; The material of insulation package; Or the material of thin slice and/or thin slice or layering, wherein this thin slice can be encapsulated in this insulation package the part at least.

In addition, the anti-attaching part that burns can be used for the 3rd insulation package setting and/or is attached on the structure of aircraft, for example on the framework of fuselage, flank or the stringer.The anti-attaching part that burns like this can be made of metal, but also can be made by the refractory material that for example has dystectic plastics etc.And this insulation package can be arranged so that packaging part self also protects the attaching part to avoid it to be exposed in the fire.This can for example be embodied as and insulation package is set and makes it form around the liner of this attaching part or form a kind of flameproof enclosure.

Believing to provide a kind of improved insulation package arrangement that is used for aircraft, this device can be used to the internal insulation part, go up the cabin space that stops the flame of coming from aircraft environment outside burning things which may cause a fire disaster burning to enter (just having implemented to land in an emergency) aircraft thereby can advance this, perhaps can prolong the time of keeping out fire by this device.Believe the design of this insulation package and near the fire savety of the separated interior regions the attaching of airframe structure is suitable for realizing improving the exterior skin that is arranged on structure thereof.

Can prevent to burn the cabin space that the propagation of flame of coming enters aircraft from the outside burning things which may cause a fire disaster of aircraft environment according to the insulation package of exemplary embodiment of the invention, wherein the design of insulation package and the attaching on airframe structure thereof are embodied as and make the area of aircraft cabins of aircraft be protected and prevent spreading of the exterior fire of aircraft environment.In addition, for example the needed time is prolonged because fastener lost efficacy, and believes that the passenger is more convenient significantly from withdrawing of aircraft.

Description of drawings

Introduce illustrative embodiments of the present invention in more detail with reference to following each figure.

Fig. 1 shows traditional fuselage free body of commercial aircraft;

Fig. 2 shows the condition of a fire behind the bump relevant with (alleged) of the aircraft that is about to stop;

Fig. 3 shows the insulation package arrangement that aircraft fuselage interior is isolated of being used for according to exemplary embodiment of the invention, and it has the anti-thin slice encapsulation piece that burns of insulation package;

Fig. 4 shows the details " X " among Fig. 3, shows the attaching according to the isolation end of two fuselage insulation package on the flank of exemplary embodiment of the invention;

Fig. 5 shows the first attaching part according to the spacer pin form of exemplary embodiment of the invention;

Fig. 5 a shows the longitudinal sectional drawing of the spacer pin shown in Fig. 5;

Fig. 6 shows the second attaching part according to the shading ring form of the truncated cone form of exemplary embodiment of the invention;

Fig. 6 a shows the birds-eye view according to the shading ring of the truncated cone form shown in Fig. 6 of exemplary embodiment of the invention;

Fig. 7 shows the structure fixer of attaching in stringer, and it comprises the riveted joint attaching according to the isolated part of the fuselage insulation package of exemplary embodiment of the invention;

Fig. 7 a shows the attaching of isolated part that has the flank of extension according to exemplary embodiment of the invention on the head of flank.

The specific embodiment

In order more easily to understand Fig. 1--a free body has been shown among this Fig. 1, need be as what foreword proposed, the structural unit of airframe not only comprises stringer 31, also comprise a plurality of flanks 32, wherein all plates of the exterior skin 33 of aircraft fuselage structure are strengthened by stringer, and described flank be arranged to (approximately) with spacing c perpendicular to the longitudinal axis 9 of aircraft and attaching in stringer 31.(alleged) flank supporting member 40 is combined on these flanks 32 at attaching end not, the longitudinal axis 9 that this flank supporting member 40 is parallel to aircraft extends, and wherein (according to present embodiment) flank supporting member 40 (the not freedom of attaching) end is perpendicular to 9 one-tenth angles of the longitudinal axis of aircraft.

Fig. 1 shows (the fuselage free body) insulation package 3 (having general reference characteristic) of the position on (close) aircraft exterior skin 33.Under the various situations, this insulation package 3 includes alleged field insulation package 17 and alleged flank insulation package 16, and these two all installs and be attached near the exterior skin 33 in a conventional manner respectively or attaching becomes to put the stringer bearing surface 31a that leans against stringer 31 last (promptly in the structural region of the aircraft fuselage structure that limits).Thus, Fig. 1 shows an insulation package 17 and has been arranged between (two) flank 32 that separates with distance c, and the inner face of the exterior skin plate of close (resting) exterior skin 33.In addition, flank insulation package 16 has been placed on the flank supporting member, and wherein this flank insulation package 16 is guided and puts on the vertical side 41 that leans against flank in both sides.When as shown in Figure 3 side is observed, flank insulation package 16 not only before alleged flank vertically side 41 (right-hand side) be directed, but also behind alleged flank vertically side 41 (left-hand side) be directed.

These two insulation package are sealed by flammable plastic tab fully.They are arranged in the space that plate limited (Fig. 1 does not show) by the inside coating of aircraft and exterior skin 33.

Insulation package arrangement according to exemplary embodiment of the invention can be arranged in some spaces, for example be arranged in the space to be separated, these spaces comprise the space that the inside coating by exterior skin 33 and aircraft cabin has been sealed, and this space is provided with abreast with the distance (transverse to the longitudinal axis 9 directions of fuselage) that limits.

With reference to Fig. 2, will " condition of a fire " of aircraft after landing in an emergency be described.In such (supposition) condition of a fire--be called in " the bump back condition of a fire " 7, if consider: (damaging) after the mechanical action externally (having the exterior skin 33 of defective) aircaft configuration 8 from the outside and thus shown in aircraft zone overflowing and burning and cause under the situation of fire owing to kerosene, in the fuselage--promptly at engine room inside, emergency situations will occur to the passenger and crew, be appreciated that structure so: the structure fire resistance time periods such as fuselage and panel should prolong and prolong as far as possible to allow for example collaborative withdrawing.

Below, the corresponding improvement and illustrative embodiments proposed, it can provide improved protection.Wherein, with reference to referring to Fig. 3 and follow-up Fig. 4,4a, 5,5a and 6.

In order to realize in this respect--wherein planning provides better fire savety and this zone, inner space to be arranged near the exterior skin 33 of aircraft for for example zone, inner space (area of aircraft cabins) that separates of passenger plane, what need proposition is, according to the embodiment shown in Fig. 3, be recommended in the anti-thin slice of making by the fire prevention sheeting at this place 11 that burns and seal fully and be used for the fuselage insulation package 19 that the inside with airframe isolates.Under various situations, sheeting only fire-resistant or the delay fire may not be enough.By only providing complete lamellae seals from one's body in fuselage insulation package 19, this (unpredictable and can not expect) of the fire relevant (no matter any reason) with aircraft always unfeasible when the imminent disaster of antagonism is coerced with the disaster danger of antagonism fire under the situation.

Fig. 3 shows advanced fuselage isolated system.Show the fuselage insulation on the aircraft fuselage structure, this device comprises a plurality of

fuselage insulation package

19,20,21,22 that are provided with along aircraft longitudinal axis 9 directions, and wherein said packaging part is an elongated shape.

Each fuselage insulation package 19～22 comprises field insulation package and the flank insulation package 17,18 (with reference to Fig. 1) that combines, under various situations, for fuselage insulation package 19～22, its being arranged on aircraft fuselage structure meets each and

flank insulation package

17,18 as shown in Figure 1 to the full extent.Because this combination, the frequency that in the fuselage free body, engages (interruption) (shown in Fig. 1) minimized or reduce (comparing) with the conventional mounting of such insulation package 3 at least half, viewpoint from fire savety, in the zone of fuselage free body attachment point, it has the less weak link with respect to fire.

With field and

flank insulation package

17,18 only use meet the heat insulation and sound insulation unformed half-blank (for example glass fiber material) of demand and this free body by flammable plastic tab sealing different be, anti-anti-barrier layere or these two kinds anti-spacer assemblys that burn of burning that burn free body or small cross sections of larger cross-section have been adopted in the design of each fuselage insulation package 19～22 that is proposed, therefore, these prevent burning spacer assembly or (separately) setting individually, perhaps in being attached to corresponding fuselage insulation package 19～22.

In this device, one or two prevents that burning spacer assembly is arranged to or is close to or put the inner wall area that is against (thin slice 11) thin slice wall.

Alternatively, can expect that anti-free body or the barrier layere of burning is directed into outside and peripheral adjacent with this thin slice of the thin slice 11 of each fuselage insulation package 19～22, the periphery that this free body or barrier layere are attached to the bearing surface of stringer 31 and are attached to thin slice 11 by bonding connection.

To key drawing 4 in more detail below, wherein show the details shown in Fig. 3 " X ".Clearly show that the anti-free body that burns, its cross-sectional plane is greater than the cross-sectional plane of barrier layere, and wherein said free body is arranged in the corresponding fuselage insulation package 19～22 and withdraws from described fuselage insulation package and become smooth isolation end sections 12 (having the anti-thickness that burns thin slice) on the end of thin slice 11.The technology that relates at the exit point sealing sheet of isolated part 12 does not go through at this.

This smooth isolation end sections 12 is from fuselage insulation package 19～22 outwards continuity along its length of each elongated shape, this isolation end sections 12 will be used for the end side attaching of fuselage insulation package 19～22 on

corresponding stringer

32a, 32b, 32c, and wherein said attaching makes an explanation with reference to Fig. 4.

Fig. 3 for example also shows, and the first fuselage insulation package 20 is arranged in puts on the bearing surface 31a that is against (corresponding) stringer 31 between (numbering like this) the 3rd flank 32c and the first flank 32a, and described flank separates with distance to a declared goal c.

The front and rear that Fig. 3 also shows this first fuselage insulation package 20 is with respect to (two) of the flank of the first alleged flank 32a

vertical side

41a, 41b situation of attaching laterally, and wherein the isolated part 12 that withdraws from of this first fuselage insulation package 20 is attached to the first flank 32a (as shown in Figure 4) with the isolated part that withdraws from of (mentioning below) second fuselage insulation package 21.

Similarly, use constructed, the second fuselage insulation package 21 is arranged between the first flank 32a and the second flank 32b and puts on the bearing surface 31a that is against stringer 31, described flank separates with distance to a declared goal c, and the isolated part 12 that withdraws from of this second fuselage insulation package is attached to the second flank 32b (as shown in Figure 4) with the isolated part that withdraws from of (below mention and corresponding numbering) the 4th fuselage insulation package 22.

Again, use described technology, the 3rd fuselage insulation package 19 be arranged in the 3rd mentioned flank 32c and and the 3rd flank separate and be arranged on distance c between the flank in its place ahead and put on the bearing surface 31a that is against (accordingly) stringer 31, the isolated part 12 that withdraws from of the 3rd fuselage insulation package is attached to the 3rd flank 32c (as shown in Figure 4) with the isolated part that withdraws from of the first fuselage insulation package 20.In addition, show the arrangement of the 4th fuselage insulation package 22, the isolated part 12 that withdraws from of the 4th fuselage insulation package is attached to the second flank 32b (as shown in Figure 4) with the isolated part that withdraws from of the second fuselage insulation package 21.

For attaching, to use and anti-ly to burn attaching

part

4,13, its shape and design are shown among Fig. 5,5a, 6, the 6a, and its layout shown in Fig. 4 (with reference to accompanying drawing, withdraws from isolated part 12 attachings in flank 32a～32c).

Except above-mentioned explanation, it should be noted that, the embodiment relevant with one of them placement (it can put the interior zone of the plate that is against exterior skin) of fuselage insulation package 19～22 explained in more detail, yet such placement can be expected in theory.For this reason, only it should be noted that each fuselage insulation package below predetermined stringer bearing surface 31a and the placement that is arranged on the exterior skin 33 will carry out in the mode of the placement of the installation explained above being similar to.If need, this attaching can be carried out on the vertical side 41a of the appointment of single flank, 41b.

Fig. 4 shows the first and second

fuselage insulation package

20,21 in the attaching of the first flank 32a, wherein with advised the same, the embodiment of this attaching is technical to be applied in all flank 32a, 32b of being provided with along the direction of aircraft longitudinal axis 9, the same range as on the 32c (up to n flank), and two

fuselage insulation package

20,21 are put continuously and leaned against stringer bearing surface 31a and go up, put and lean against on the definite stringer bearing surface 31a of flank.Its condition precedent is that (in working in front) is drilled with through hole 24 in flank attaching zone 15.

In addition, in the packaging part zone that is limited of each fuselage insulation package 19～22, be formed with an alleged poroid lead-through, wherein this packaging part zone is gone up and is provided with for the first vertical side 41a that flank is put the position, rear portion (side direction right side) that leans against (in this case) the first flank 32a.

The packaging part zone that is arranged on corresponding fuselage insulation package 19～22 downstreams is put and is leaned against on the flank supporting member 40 and side direction is put on the end, drift angle that leans against flank supporting member 40, this packaging part zone extends to the first smooth free body end sections 12a of (for example first) fuselage insulation package 20 in the thin slice end, this free body end sections 12a puts on the second vertical side 41b that leans against the first flank 32a at opposite side (side direction left side), and this second vertical side 41b is positioned at the place ahead.First flat end of described free body 12a partly comprises alleged poroid depressed part.Owing to the end that its place, end in adjacent (being provided with continuously) second fuselage insulation package 21 of the second smooth isolation end sections 12b--is continued in thin slice--, it will be arranged on the bearing surface of the first free body part 12a or its below, this free body end sections 12b also comprises alleged poroid depressed part.If it is superimposed each other that poroid lead-through, through hole and this two poroid depressed parts are arranged to, the anti-spacer pin that burns of the first attaching part can pass the packaging part zone of the first fuselage insulation package 20 that is limited the hole, pass the through hole in flank attaching zone 15 and pass the attaching zone of two smooth free body part 12a, 121b and feeding.

According to Fig. 5,5a, the design of spacer pin is embodied as cylindrical chipware 25 and cylindric plastic wrapper 28, and wherein, under various situations, near the end of pin 27, chipware 25 includes flange shape protuberance 26.The shape of chipware 25 is as shown in its longitudinal sectional view among Fig. 5, and it is embedded in the plastic-like overcoat 28.About middle part at overcoat 28, draw (ring type) flange 29, at a distance of in this flange 29, start from the cylindrical peripheral of overcoat 28 and be parallel to the bearing pin 43 of (spacer pin) the first attaching part 4 that distributes along its length direction, be provided with a plurality of pine tree shape protuberances 30, these pine tree shape protuberances 30 are arranged to each other apart from being a.This pine tree shape protuberance 30 is equivalent to cylindrical-conical stepped level portion 44, and wherein, level portion 44 starts from the periphery of overcoat 28,, its tapered conical realizes by the taper convergent of the periphery of overcoat.The end regions of overcoat 28 is the form of depressions of domeshape.The profile of described end regions is similar to paraboloidal profile, is equivalent to the shape of the parabolic swivel realized by parabolic shape the vertical section, the stepped level portion 44 that wherein parabolical branch end green phase is vertically inwardly drawn for bearing pin 43 and continuing.This chipware 25 is made of metal, and promptly steel is preferably corrosion-resistant steel.Different therewith, overcoat is made by the plastics of poor thermal conductivity.

Design consideration Fig. 6 of the second attaching

part

13,6a are embodied as the alleged truncated cone with the bevelled shading ring form of tack.Bottom surface and end face 46 and 47 realize with separator or loop member, and it is designed to be anti-burning.Be provided with in the periphery of these separators or loop member that to be designed to be the insulated jacket 50 of anti-burning property, this insulated jacket 50 mechanically is connected on the element of the element of bottom surface and end face at edge side.

Truncated cone can be designed so that end face 46 comprises first separator, and one of them hole is arranged on the central authorities of this dish.The diameter in this hole should be less than the overall diameter of the end regions 42 of the parabolic shape of domeshape overcoat 28, makes the hole wall of the separator made by plastic material can be guided the parabolical branch end of the parabolical end regions 42 that closely is coupled to overcoat 28.Need not further explain in advance, because the flexibility of being allowed of plastic material makes that first separator made by plastic material can be mobile on the domeshape overcoat 28 of the first attaching part 4 of (adopting close-fitting) spacer pin, and, only can on domeshape overcoat 28, guide this separator quite arduously along this reversing sense that moves.Because this embodiment will also be considered second separator that is made of plastics, this dish forms the bottom surface 46 of truncated cone, wherein, there is a hole in central authorities at this dish, the diameter in this hole equals or is slightly larger than the overall diameter of domeshape overcoat 28 of the first attaching part 4 of spacer pin, makes described second separator can be coupled on the domeshape overcoat 28 of spacer pin.Turn back to the explanation in Fig. 3 and 4, therefore, be clear that more, in last analysis, it may be suitable that the second attaching part 13 for the treatment of fixedly to be attached to smooth isolation end sections 12,12a, the 12b of

vertical side

41,41a, the 41b of

flank

32,32a, 32b, 32c designs in such a way.

Alternatively, realize being designed to the second attaching part 18 that truncated cone and it comprise second plastic hoop 49 of the first plastic barrier ring 48 of big circumference and less circumference.In this design, the periphery of first shading ring 48 is inlayed in the end face 47 of truncated cone of the into described second attaching part 13, and the periphery of second shading ring 49 is inlayed in the bottom surface 46 of truncated cone of the into described second attaching part 13.Can expect that on the interior ring diameter of first and

second shading rings

48,49, a plurality of isolation mounts 51 along circumferentially spaced are along the vertical position attaching.Yet, if these isolation mounts are only in the periphery setting of the periphery and the dish type chipware 52 of second shading ring 49, wherein the overall diameter of chipware 52 can (slightly) less than the interior ring diameter of second shading ring 49, just can be enough.The chipware 52 and second shading ring 49 are flat in the same plane, and wherein this chipware 52 comprises that at the center of dish a hole and this chipware 52 are embedded in the plastic wrapper.

The aperture that it is pointed out that second shading ring 49 can be less than the overall diameter of the end regions that is embodied as parabolic shape 42 of domeshape overcoat 48, promptly for the above-mentioned reason of mentioning about the above-mentioned embodiment in the hole of first separator.Dish type cone part is made of metal.It comprises steel, is preferably corrosion-resistant steel.

The above-mentioned overcoat of mentioning of chipware 2 uses the plastic material of poor thermal conductivity to realize.

For integraty, it should be noted that, the separator and the shading ring that are configured to the second attaching part 13 are arranged to parallel to each other, the element that wherein forms bottom surface 46 (promptly, second shading ring 49) element (that is first shading ring 48) the spacer ring spacing b (height distance of ring) that is arranged to and forms end face 47 is provided with.The periphery of these elements is sealed by the insulated jacket 50 that is attached to the ring periphery.

What need to replenish is, can be attached on the edge of bottom surface 46,47 of the described second attaching part 13 because be designed to the anti-a plurality of isolation mounts 51 that burn, and the second attaching part 13 also can be suitable with the shape of the shading ring of alleged truncated cone form.In this device, circumferential isolation mount is attached to first shading ring 48 and has on the periphery than second shading ring 49 of big circumference, and this support 51 supports this two rings with cage shape form.Alternatively, can expect these isolation mounts 51 by (forming bottom surface 46) second separator and (forming end face 47) first separator support, the end of isolation mount 51 is attached on the separator by the edge.

It should be noted that also a plurality of fuselage insulation package 19～22 are arranged on the inner structure of fuselage, wherein this fuselage insulation package 19～22 is arranged in the airframe structure zone that is limited by

flank

32,32a, 32b, 32c.In this device, design on the vertical side 41 of

flank

32,32a, 32b, 32c, 41a, 41b in isolated part the smooth isolation end sections 12 of continuous (at least two) fuselage insulation package 19～22, the poroid depressed part of 12a, 12b be sent to the first attaching part 4, this attaching part 4 is one and is designed to the anti-spacer pin that burns.Thereby, on corresponding vertical side 41 of corresponding flank, 41a, 41b, 41c, form the overlapping of alleged free body end sections 12,12a, 12b.Described free body end sections 12,12a, the 12b attaching on vertical side 41 of flank, 41a, 41b, 41c, on the first attaching part (4) is fixing by the second attaching part 13, and this second attaching part 13 is separator or loop member.

At last, Fig. 7 shows the structure fixer 53 that is attached to stringer 31, and this stringer is attached to the contact surface of exterior skin 33, (and if needing) corresponding stringer attaching of adjacency.Yet this structure fixer 53 also can be attached to

flank

32,32a, 32b, 32c or be attached to the not attaching end of

flank

32,32a, 32b, 32c at (extension) flank head place.This diagrammatic sketch illustrates very may be in order to the scheme of these smooth free body end sections 12 of attaching, 12a, 12b, its by the riveted joint of this component arrangement or screw lock are had another anti-attaching part that burns make fuselage insulation package 19～22 the bearing surface of structure fixer 53 and (shown in illustrate medium dip) extend between the strut member.The screw and nut that this another attaching part is set to the rivet made by steel or titanium or is made by steel or titanium or plastics.This spiral connecting piece can comprise polyamide material or CFK material.

Attaching or rivet that Fig. 7 is illustrated in free body end sections 12 on the flank extended

structure fixer

53,12a, 12b connect, this flank extended structure fixer 53 with described anti-burn attaching parts the flank of

corresponding flank

32,32a, 32b, 32c extend on the free end connect by spiral and attaching in the flank head of

flank

32,32a, 32b, 32c (this flank head is not having to make under the situation of flank supporting member 40).

As the measure of Fig. 7 and 7a guaranteed in this device with riveted joint or screw lock as described in the relevant system shortsightedness zone of structural structure fixer 53, prevent that (entering from the aircraft external environment condition) flame from burning suddenly.In this device, screw lock or rivet this alleged " fiery barrier layere " between this prevention zone and aircaft configuration.

At last, it should be noted that the fuselage insulation package relevant with Fig. 1 remains traditional insulation package made from glass fibre (glass wool) 3.In this device, the core of described insulation package only satisfies heat insulation and the sound-deadened demand.

(at this also) mainly is the product of optical fiber industry, wherein uses the glass fiber material that has superiority most.Because the disaster hidden-trouble that passenger and crew's (significantly) is existed, thereby will need insulation package 3 is further improved in future to the design of the employed insulation package 3 of tradition.This will become clearer with reference to the example shown in Fig. 2.

Fire savety for the entire arrangement that satisfies involved aircraft fuselage interior free body at least in part, the fuselage insulation package of mentioning among Fig. 3 19～22 (up to the n packaging part), core (glass fibre) will be sealed by the above-mentioned anti-thin slice of mentioning 11 that burns that is designed to fully.The thin slice 11 that is provided for sealing corresponding fuselage insulation package 19～22 uses the anti-material that burns to realize, in other words, use following sheeting to realize, promptly be superior to owing to the fire that acts on thin slice 11 outside faces or the expansion effect of the flame (shown in Fig. 2) of the fire 7 on the sheeting transmits.This sheeting will be a complete barrier layere for burning fire, and the surf zone of thin slice 11 is exposed to this burning fire when example is as shown in Figure 2 in the fire.

Because term " anti-burning " is very relevant with " fire prevention ", wherein " fire prevention " is the synonym of " fire-resistant ", thereby thin slice 11 will comprise the material with long-time fire retardancy, and described material has suitable fire-resistance property.The type of the degree of tolerance fire 7 and institute use sheeting and the thickness of thin slice wall are relevant, wherein the flameproof time length is relevant with the time span that uses thin slice 11, think that it has very long time span, begin lasting (limited) a period of time from the use of thin slice 11, for example up to sheeting because the aging moment that will lose the performance of its tolerance fire 7 of thin slice, perhaps up to the performance of expected such tolerance fire 7 with situation about reducing.

The state of the influence (in this case) " be not sensivity " of flame on sheeting that is exposed to fire 7 described in term " insensitivity ".Owing to can expect other sensivity of sheeting, for example to the sensivity of the environmental conditions on from insulation package 3 external actions to sheeting in the position of using thin slice 11, describe " anti-burning " and will mainly comprise " sensivity " to fire 7, in fact use therein sheeting also is (and should also be) sensivity in aircraft engineering to other influence, for example for pollute in the air and other chemical affect, for electricity harm, for the influence of ambient pressure etc.

Correspondingly, thin slice 11 should be realized with the material with goodish and long lasting fire retardancy thus, this material has tolerance and/or insensitive for the fire 7 that may run into, for this reason, the thin slice wall will can not burn because of the influence of burning fire 7, even on sheet surface when expansion influence also be so, and can avoid fire 7 spreading on sheet surface.

Reference numeral

1 isolated material 2 is sealed thin slice

3 insulation package, 4 first attachment elements; Spacer pin

The condition of a fire behind 7 bumps; Fire 8 aircaft configurations

9 aircraft longitudinal axis, the 11 anti-thin slices that burn

12 smooth slider end sections 12a the first slider end sections

12b the second slider end sections 13 second attachment elements; Truncated cone

15 rib section 17 insulation package in attaching zone

18 rib section insulation package 19 the 3rd rib section insulation package

20 first rib section insulation package, 21 second rib section insulation package

22 the 4th rib section insulation package 24 through holes; Boring

25 (the first attachment element 4) cylindrical core part

The flange shape protuberances 27 of 26 (chipwares 25) (chipware 25) pin end

28 overcoats, 29 flanges

30 pine tree shapes swell 31 stringers

31a stringer bearing surface 32 flanks

The 32a first flank 32b second flank

32c the 3rd flank 33 exterior skins

33a (plate of exterior skin 33) inner face 40 flank supporting members

Vertical side of 40a (flank supporting member 40) end 41 flanks

First vertical side of 41a flank; Back (left side), second vertical side of side 41b flank; Preceding (right side), side

42 end regions 43 (the first attaching part 4) bearing pin

44 level portions 46 (the second attaching part 13) bottom surface

47 (the second attaching part 13) end face, 48 first shading rings

49 second shading rings, 50 insulated jackets

51 isolation mounts, 52 dish type chipwares

53 structure fixers

A (between the pine tree shape protuberance 30) spacing

B (between the shading ring 48 and 49) spacing

C (between

flank

32,32a, 32b, the 32c) spacing

Claims

1. one kind is used for insulation package arrangement that aircraft fuselage interior is isolated, its structural unit not only comprises stringer (31), also comprise a plurality of flanks (32), all plates by the exterior skin (33) of this stringer (31) aircraft fuselage structure are strengthened, and described flank is provided with perpendicular to the longitudinal axis (9) of aircraft with distance to a declared goal (c) and attaching in described stringer (31), and a flank supporting member (40) is combined in the described flank (32) at attaching end not, the longitudinal axis (9) that this flank supporting member (40) is parallel to aircraft extends, in this device, the a plurality of fuselage insulation package (19～22) that include elongated packaging part shape at the airframe structure place of aircraft along the direction setting of the longitudinal axis (9) of aircraft, wherein, described fuselage insulation package (19～22) end wise is put on the bearing surface (31a) that leans against stringer (31), this stringer attaching is in airframe or be arranged to end wise and put the inner face (33a) that is against the exterior skin plate, and, described fuselage insulation package (19～22) is attached to flank (32,32a, 32b, vertical side (41 32c), 41a, 41b), described fuselage insulation package (19～22) also is arranged to be sealed fully and be positioned at the space of being sealed by inner panel and exterior skin plate by thin slice (11); The design of this insulation package arrangement realizes with the anti-anti-barrier layere that burns that burns free body and/or small bore of big cross-sectional plane, describedly anti-burn free body and anti-ly burn that barrier layere is provided with separately or in conjunction with being arranged in the fuselage insulation package (19～22), wherein guide free body or barrier layere and make it be arranged to be close to or put the inner wall area that is against the thin slice wall, perhaps only the free body attaching in the outside and put on the periphery of the thin slice (11) that is against fuselage insulation package (19～22), long end in fuselage insulation package (19～22), described free body extends outwardly and has smooth free body end sections (12,12a, 12b), this free body end sections utilizes the anti-attaching part (4 that burns in flank attaching zone (15), 13) attaching is in flank (32,32a, 32b, 32c), wherein said flank attaching zone (15) is arranged on flank (32,32a, 32b, vertical side (41 32c), 41a, below 41b) and in abutting connection with stringer (31).

2. insulation package arrangement as claimed in claim 1, wherein, in described flank attaching zone (15), be drilled with a through hole (24), and in the packaging area of fuselage insulation package (19～22), in a side in abutting connection with the front portion or the vertical side of flank (41a, 41b) that is provided with of rear portion, be provided with the isolation end sections (12,12a, 12b) of poroid lead-through and formation, and, comprise poroid depressed part in the vertical side of flank (41a, 41b) that opposite side is set in abutting connection with the front portion or the rear portion is provided with.

3. insulation package arrangement as claimed in claim 2, wherein, the first attaching part (4) is in case the spacer pin that burns realizes that under the situation that each element is arranged to be superimposed, this first attaching part passes described poroid lead-through, passes described through hole and passes described poroid depressed part and feeding.

4. insulation package arrangement as claimed in claim 3, wherein, the design of described spacer pin realizes that with cylindrical chipware (25) and cylindric plastic wrapper (28) wherein, near the end of pin (27), described chipware (25) comprises flange shape protuberance (26).

5. insulation package arrangement as claimed in claim 4, wherein, described chipware (25) is embedded in the plastic-like overcoat (28).

6. insulation package arrangement as claimed in claim 4, wherein, greatly about described overcoat (28) middle part, draw a flange (29), at a distance of in this flange (29), originate in the cylindric periphery of overcoat (28) and be parallel on the length range of this chipware (25) in its extension, be provided with a plurality of pine tree shape protuberances (30), these pine tree shape protuberances are arranged to separate each other.

7. insulation package arrangement as claimed in claim 6, wherein, described pine tree shape protuberance (30) forms cylindrical-conical stepped level portion (44), and wherein this level portion (44) starts from the periphery of overcoat (28) and the tapered conical of this level portion (44) realizes by the taper convergent of the periphery of overcoat (28).

8. insulation package arrangement as claimed in claim 4, wherein, the end regions (42) of described overcoat (28) is the form of depressions of domeshape, the profile of described end regions (42) is a parabolic shape, the stair-stepping level portion (44) that the shape that is equivalent to the parabolic swivel realized with parabolic shape the vertical section, wherein parabolical branch end green phase are vertically inwardly drawn for bearing pin (43) and continuous.

9. insulation package arrangement as claimed in claim 4, wherein, described chipware (25) is made of metal, and promptly be formed from steel, and described overcoat (28) is made of plastics.

10. insulation package arrangement as claimed in claim 1, wherein, the described second attaching part (13) is realized with alleged truncated cone (shading ring of truncated cone shape dress), its bottom surface and end face (46,47) are realized to be designed to anti-separator that burns or loop member, and an anti-insulated jacket (50) that burns is bound up on plate edge or the ring edge side by dish or the ring with big periphery.

11. as claim 8 or 10 described insulation package arrangements, wherein, the end face of described truncated cone comprises first separator, one of them hole is arranged on the central authorities of this first separator, the diameter in this hole is less than or equal to the overall diameter of end regions (42) of the parabolic shape of domeshape overcoat (28), makes the hole wall of (because flexibility of plastic material) separator to be guided and closely is coupled to the parabola branch end of the parabola shaped end regions (42) of overcoat (28).

12. insulation package arrangement as claimed in claim 10, wherein, the end face of described truncated cone (47) comprises first plastic barrier ring (51) with long circumference and the second plastic barrier ring (49) with little circumference, wherein, on the overall diameter of the interior diameter of first shading ring (48) and second shading ring (49) with the vertical position attaching a plurality of isolation mounts (51) along circumferentially spaced.

13. as claim 4,8,10 or 12 described insulation package arrangements, wherein, the design of described second shading ring (49) comprises dish type chipware (52), wherein this chipware (52) comprises a hole in disk center, the diameter in this hole is less than or equal to the overall diameter of the end regions (42) of the domeshape overcoat of realizing with parabolic shape (48), and the design of this second shading ring (49) also comprises plastic wrapper.

14. insulation package arrangement as claimed in claim 13, wherein, described dish type chipware (42) is embedded in the described plastic wrapper.

15. insulation package arrangement as claimed in claim 13, wherein, described dish type chipware (42) is made of metal, and promptly be formed from steel, and the overcoat of this chipware (42) comprises plastics.

16. insulation package arrangement as claimed in claim 10, wherein, the described second attaching part (13) is embodied as the shading ring of truncated cone form, its bottom surface and end face (46,47) are connecting on the plate edge side or are connecting on the ring edge side by having large diameter dish by the dish with big circumference, wherein be provided with a plurality of anti-isolation mounts (51) that burn that are designed to be, second separator that described isolation mount will have described bottom surface (46) supports to arrive in first separator with end face (47) or first shading ring (48).

17. as each described insulation package arrangement in claim 1～3 and 10, wherein, be arranged on by flank (32,32a, 32b, 32c) a plurality of fuselage insulation package (19～22) in the zone of the airframe structure of Xian Dinging are arranged on the inner structure of fuselage, and at flank (32,32a, 32b, a vertical side (41 32c), 41a, 41b), the smooth isolation end sections (12 of continuous described (at least two) fuselage insulation package (19～22) in an isolated part, 12a, poroid depressed part 12b) is sent to the first attaching part (4), this first attaching part is to be designed to the anti-spacer pin that burns, thereby, corresponding vertical side (41 at corresponding flank, 41a, 41b, 41c) go up formation free body end sections (12,12a, 12b) overlapping, and vertical side (41 at flank, 41a, 41b, 41c), described free body end sections (12,12a, 12b) guarantee by the second attaching part (13) that in the attaching of the first attaching part (4) this second attaching part (13) is separator or loop member.

18. insulation package arrangement as claimed in claim 1, wherein, the design of each fuselage insulation package (19～22) is consistent with the field insulation package that position and tradition are used, the direction of its longitudinal axis along aircraft (9) is arranged on the aircraft fuselage structure or near the aircraft fuselage structure, and to limit the stringer bearing surface (31a) that distance (c) vertically is adjacent to stringer (31), and the flank insulation package of using with tradition is consistent, the flank supporting member (40) of vertical side of its abutment ribs (41,41a, 41b) and each flank (32,32a, 32b, 32c); Under various situations, it comprises the combination of single insulation package and flank insulation package, it is sealed and/or is comprised anti-free body and/or the anti-barrier layere that burns of burning by the anti-thin slice (11) that burns fully, wherein, corresponding insulation package and flank insulation package anti-burnt element does not have interruptedly and extends from the fuselage insulation package (19～22) of combination.

19. insulation package arrangement as claimed in claim 1, wherein, the smooth isolation end sections that extends from fuselage insulation package (19～22) (12,12a, 12b) screw lock or be riveted on the anti-attaching part that burns, structure fixer (53) stringer outstanding from stringer (31) is attached to exterior skin (33), or be attached to the head of each flank of extending from the not attaching end of flank (32,32a, 32b, 32c) (32,32a, 32b, 32c), or be attached to flank supporting member (40).

20. insulation package arrangement as claimed in claim 19, wherein, putting in the relevant system shortsightedness zone of the independent strut member that leans on, the free body (1) of fiery barrier layere and isolated part (12a, 12b) screw lock and the riveted joint of thin slice (11) and/or fuselage insulation package (19～22) will have been constituted with structure fixer (53) or this fixer.

21. insulation package arrangement as claimed in claim 1, wherein, described another attaching part is the rivet of being made by steel or titanium, or the spiral connecting piece of being made by steel or titanium or plastics.

22. insulation package arrangement as claimed in claim 21, wherein, the screw and nut of described spiral connecting piece for making by polyamide or CFK material.