CN101636314A - Fuselage of an aircraft or spacecraft and method of activelyinsulating such a fuselage - Google Patents
Fuselage of an aircraft or spacecraft and method of activelyinsulating such a fuselage Download PDFInfo
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- CN101636314A CN101636314A CN200880005827A CN200880005827A CN101636314A CN 101636314 A CN101636314 A CN 101636314A CN 200880005827 A CN200880005827 A CN 200880005827A CN 200880005827 A CN200880005827 A CN 200880005827A CN 101636314 A CN101636314 A CN 101636314A
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- air
- gap
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/066—Interior liners
- B64C1/067—Interior liners comprising means for preventing icing or condensation conditions
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The present invention relates to a fuselage (1) of an aircraft or spacecraft, with at least one shell element (2) and a structural element (7). An interspace (5; 9) to which air can be admitted by an air stream (10) is provided between the at least one shell element (2) and the structural element (7). The fuselage is distinguished by the fact that, to form the air-admitting air stream (10) as an outgoing/incoming air stream of a pressurized interior space (20) of the fuselage (1), the interspace (5; 9) is connected to a corresponding outgoing/ incoming air connection of the interior space (20). The invention also relates to a corresponding aircraft or spacecraft and to a method of actively insulating such a fuselage (1).
Description
Technical field
The present invention relates to cabin body and a kind of aircraft or spacecraft and a kind of initiatively isolated method of described cabin body that makes of a kind of aircraft or spacecraft with described cabin body.
Background technology
Such cabin body is made by a plurality of parts.Aircraft or spacecraft, for example aircraft not only subjects to huge load variations and stress in operational process, also subjects to sizable temperature contrast.For example, in specific cruising altitude, the external temperature of the external side in described cabin is approximately-55 ℃, and the numerical value that the internal temperature in the pressurised cabin zone remains on approximately+20 ℃.This relies on a/c system to be realized.Under the situation of conventional aircraft cabin body, body inboard, cabin is provided with thermal insulation layer, and described thermal insulation layer also forms sound isolating layer.
The cabin body can be individual layer shell or multilayered shell form, particularly double shells form.
Fig. 7 illustrates the part sectional view based on the individual layer shell cabin body 1 of applicant's known technology, and described cabin body has casing member 2, has additional strengthening 15 in described casing member inboard, for example is referred to as longeron.Traditional isolation structures 18 comprises the insulating barrier that is made of glass wool usually, and this insulating barrier is positioned at perithallium 17 and forms an integral body with perithallium 17, and this perithallium 17 for example is a plastic sheeting.This isolation structures 18 is between casing member 2 inboards and internal structural element 7, and this inner structure for example is the lining of cabin body.Described lining is for example made by the GRP material.It also can have side panel 16.This arrangement structure plays inner space 20 and hull 1 exterior extraneous 19 heat insulation and sound-deadened function.
Yet, the extra weight of isolation layer, the demand in space and the necessary installation requirements that cause thus are considered to disadvantageous here.In addition, owing to such structure that is provided with, the risk that the gathering of lime set can cause weight to increase and corrode, this accident needs cooresponding maintenance load.By 17 oven dry of described isolation layer 18 and described perithallium and transposing being eliminated steam gathers is necessary, and this is disadvantageous.
Therefore, the notion of double shells build section structure has been proposed, described in DE10154063.To this, Fig. 8 illustrates the part sectional view of the double shells cabin body 1 of prior art, and described double shells cabin body is made by for example fibre reinforced materials.
The casing member 2 of cabin body 1 has body skin element 3 and inner housing element 4, and both apart settings also form hollow gap 5.Described hollow gap 5 is provided with hollow gap member 6, described hollow gap member comprises for example the folded honeycomb structure structure or the similar structures of glass-felt plastic (GRP), carbon fibre reiforced plastic formation, is formed on theory of structure aspect actv. shearing resistance lamination (sandwich structure) and stablizes described section structure.Simultaneously, described hollow gap member has heat insulation and pugging, and owing to its compactedness, has increased the inner space of cabin body.Air-flow 10 forms of air shown in can arrow enter described hollow gap 5, and it is possible being referred to as the hydrofuge management for the condensing water vapors in the described hollow gap 5 thus.The inboard of described inner housing element 4 is towards described inner space 20, the lining setting thereon, decorative layer for example.
The said structure shortcoming is also to need other isolated work, otherwise just can not realize inner wall temperature for example is fixed on+20 ℃ target.
Fig. 9 illustrates the conventional system of the pipeline system 12a of aircraft air-conditioning system (not shown).At this only as an example, show body 1a part, cabin among the figure briefly, wherein have the lateral duct part of pipeline system 12a.Frame of axis with direction indication is: vertical x of aircraft, horizontal y and vertical z.In the x direction, be extended with bottom X pipeline 13a and top X pipeline 14a, both are by upwardly extending Z pipeline 15a links to each other in z side substantially.Be two middle part pipeline 16a that extend in the x direction in addition shown in the middle part.Described a/c system (not shown) links to each other with this pipeline system 12a and the ventilation and the temperature of control cabinet body, keeps simultaneously pressing in the body of cabin.In addition, described a/c system also is used to make the outside, described cabin, for example zonal ventilation and cooling such as cargo hold, avionic device frame.Described a/c system flows into pipeline system 12a, and described pipeline system is designed to compressed air system and extends to whole aircraft.Warm air from described bottom X pipeline 13a through described Z pipeline 15a upwards, arrives described top X pipeline 14a and described middle part pipeline 16a and enters the cabin from the bottom.Described Z pipeline 15a is at cabin lining behind cabling.
Such air supply line has following shortcoming.Depend on cross-sectional plane, need relatively large installing space.Pipeline has constant weight, and this has increased the weight of aircraft.Such pipeline system needs the erection work of some.In addition, because described pipeline has very thin wall thickness, damage easily.
Summary of the invention
Be different from this background technology, the purpose of this invention is to provide a kind of no longer have cabin body, aircraft or the spacecraft of aforesaid drawbacks and initiatively isolated method.
According to the present invention, this purpose by having claim 1 or 12 features a kind of cabin body and/or have claim 10 or a kind of aircraft of 20 features or spacecraft and/or a kind of method with claim 11 feature realize.
Therefore, provide the cabin body of a kind of aircraft or spacecraft, described cabin body has an at least one casing member and a structural constituent, and between has the gap, and air can enter described gap by air-flow.Make pressurization inner space that the described air-flow in the described gap of air admission forms described cabin body for example the cabin outflow and flow into air-flow.Therefore, described gap is flowed out/is flowed into the air associated line accordingly with described inner space and links to each other.
Rely on air-flow flowing in described gap, isolated effect enhancing or that continue at least is provided from the pressurization inner space of described cabin body.This air-flow is discharged into usually in the atmosphere of aircraft.In operational process, for example, such air-flow flows into around the atmosphere of aircraft via being referred to as outflow control valve from described pressurised cabin consistently.Supply with the described air-flow of described inner space, for example, be heated to uniform temperature by the a/c system in aircraft.Though extra H Exch still can provide, and no longer needs.
Another advantage of the present invention is that described forced draft is produced by the equipment that constitutes described a/c system, therefore need not use extra energy in order to realize this active to completely cut off/ventilate.
Constitute initiatively isolation layer because described air-flow enters into the described gap of described cabin body, the conventional isolation layer thickness of installing is reduced, compared with prior art, reduced isolated needed space.In addition, compared with prior art, weight is alleviated equally.This also causes the increase in lighter weight and described engine room inside space.
Because the cancellation or the minimizing of isolation layer have also reduced installation workload.
In aerated area, the advantage that also has is: reduced condensation point or reduced at least because the water that condensation causes gathers.
The present invention also provides the cabin body of a kind of aircraft or spacecraft, and described cabin body has an at least one casing member and a structural constituent, and between has the space, and air can be by entering described gap.Described gap forms at least a portion of a/c system pipeline system.
Therefore, rely on heated air stream the flowing in described gap of described a/c system, obtained the advantage of isolated effect enhancing or that continue at least.Because this gap forms the part of described a/c system pipeline system or one minute, it has saved the needs to other Z pipeline 15a, because described gap extends in the z direction, shown in the above-mentioned explanation relevant with Fig. 8.Also can integrate described X pipeline 13A, 14A, so that obtain particularly advantageous weight saving by the quantity that reduces these parts.
Above-mentioned these design plans are possible for the situation of aforesaid individual layer shell cabin body, also are possible for the situation of the multilayer shell element with body skin element and inner housing element.Wherein, can be arranged between described inner housing element and the structural constituent by the described gap that air-flow is sent into air described.Yet described gap also can be arranged to and air can be sent between the described casing member, and described structure can comprise the sandwich type structure that for example has any core and panel material and can have also not have other isolation layer.Described casing member can be by metal, fiber composite materials or constituting by metal and fiber composite materials.
Improvement that the present invention is favourable and progress can be found in the dependent claims.
The described air-flow that is used to send into air or initiatively completely cuts off can pass through valve, and for example control cock is regulated and controlled.This valve can be arranged at the inlet that leads to described gap, portion or in its outlet within it.It also is possible that a plurality of valves appear in certain its.
Particularly advantageous in this respect is that the internal pressure that relies at least one valve to control described pressurization inner space at least in part is possible.
Can on the body of described cabin, assemble extra isolation layer, the lining that for example has isolated characteristic.Thereby obtained the improvement effect of described active isolation layer.In this respect, another advantage is improved sound insulation.
It also is possible on the described casing member that isolated parts in the described gap are assemblied in.Yet because the cause of described active isolation layer, needed insulation thicknesses is little more a lot of than prior art.Therefore, obtained the improved effect of whole isolated parts.Here, another advantage is improved sound insulation.
The present invention also provides a kind of aircraft or spacecraft, and it is formed with above-mentioned cabin body.
The feature that the initiatively isolated correlation method of a kind of above-mentioned cabin body that makes aircraft or spacecraft has is: described active is isolated to be realized by air-flow, and described air-flow is the outflow/inflow air-flow of body pressurization inner space, described cabin.
Based on the shown preferred embodiment of schematic figures, hereinafter the present invention will be described in more detail.
Description of drawings
Fig. 1 illustrates the part sectional view according to an embodiment of cabin of the present invention body.
Fig. 2 illustrates the part sectional view according to another embodiment of cabin of the present invention body.
Fig. 3 illustrates the part sectional view according to the another embodiment of cabin of the present invention body.
Fig. 4 illustrates the part sectional view according to the another embodiment of cabin of the present invention body.
Fig. 5 illustrates the part sectional view according to the another embodiment of cabin of the present invention body.
Fig. 6 illustrates the part sectional view according to the another embodiment of cabin of the present invention body.
Fig. 7 illustrates the part sectional view according to the individual layer shell cabin body of prior art.
Fig. 8 illustrates the part sectional view according to the double shells cabin body of prior art.
Fig. 9 illustrates the part explanatory view according to the cabin body of the pipeline system with a/c system of prior art.
1: cabin body 2: casing member
3: housing department 4: inner casing portion
5: hollow gap 6: the hollow gap member
7: structural constituent 8: isolated parts
9: gap 10: air-flow
11: inlet 12: outlet
13: access valve 14: outlet valve
15: support 16: side panel
17: perithallium 18: isolated
19: the outside 20: inner space
1a: cabin body 2a: casing member
3a: housing department 4a: inner casing portion
5a: structural constituent 6a: hollow gap
7a: hollow gap member 8a: isolated parts
9a: gap 10a: air-flow
11a: the second air-flow 12a: pipeline system
13a: bottom X pipeline 14a: top X pipeline
15a:Z pipeline 16a: middle part pipeline
17a: isolated 18a: perithallium
19a: additional strengthening 20a: side panel
21a: outside 22a: inner space
X, y, z: coordinate
The specific embodiment
Hereinafter, unless otherwise noted, in institute's drawings attached, parts identical or that function is identical all have identical Reference numeral.
Prior art shown in Fig. 7 to 9 was described in front.
Fig. 1 illustrates the part sectional view according to first embodiment of the cabin body 1 of single hull structure of the present invention.In this example, described cabin body 1 is for example cabin body (not shown) of aircraft of aircraft or spacecraft.
According to an embodiment, the casing member 2 in left side is with extraneous 19 in the drawings, and for example atmosphere is connected.For the inboard of described casing member 2, to strengthen and be provided with completely cutting off parts 8 by for example additional strengthening on vertical (perpendicular to page) 15, described isolated parts have certain thickness and for example are adhered to the inboard of described casing member 2.
In addition, have structural constituent 7 on the direction of the inner space 20 of described cabin body 1, described structural constituent for example is the lining in cabin, itself and 8 settings spaced apart of described isolated parts, thus form gap 9.
Air can be admitted to this gap 9 by the air-flow of representing with arrow 10.Its also can be opposite direction flow.In this example, by being flowed out by so-called outflow control valve, 11 pressurised cabin from described aircraft or spacecraft do not flow out described air-flow 10 but conduct outflow air passes through to enter the mouth, and process air inlet valve 13 also flows into described gap 9, only illustrates with way of example here.Described air inlet valve 13 can be for example outflow control valve or such improvement valve.A plurality of such gaps can appear in the described aircraft.Described air-flow 10 also can similar shape becomes the air-flow that enters to described cabin body 1 pressurization inner space.
Described air-flow 10 for example is dispersed into the surface in described gap 9 by the a/c system in described cabin heating and with its waste heat, has formed initiatively isolated thus.Therefore, increased described cabin body 1 from described inner space 20 to described extraneous 19 heat transmission resistance.Thereby, the energy that is incorporated into described air-flow 10 not by release be dispersed into described extraneous 19, but be advantageously used for initiatively isolated, thereby also reduced the energy requirement of described a/c system.
Only be useful on initiatively isolated energy and distribute, described air-flow 10 just can continue to flow through exporting 12, is used for further using or handling.One access valve 13 or outlet valve 14 are set.Also possible is that it is arranged in the described gap 9.The combination of two valves 13,14 is shown in this embodiment.Much less, a plurality of valve 13 parallel connections also are possible.
Described interior cabin pressure can be regulated or control by described valve 13,14.For this reason, described valve 13,14 forms for example control cock of the pipeline system of a/c system.Relevant control structure is not shown, but also can be used for regulating and controlling described air-flow 10.Described air-flow 10 can also be as the part of the whole effluent stream in described cabin.Also possible is that the described air-flow that flow into described cabin is used for this purpose wholly or in part.Above-mentioned combination also is possible: effluent stream is accepted in a plurality of gaps 9 and a plurality of gap 9 acceptance inflow air-flows are possible.
In Fig. 2, with many housings, especially the bivalve body structure illustrates second embodiment according to cabin of the present invention body 1.
Described many casing structures of described cabin body 1 are configured to bivalve casing member 2 in this embodiment.Housing department 3 is set to the external world 19 of a side towards unshowned described aircraft.One routine setting spaced apart of its opposite side and inner casing portion 4 forms hollow gap 5, is provided with hollow gap member 6 in described hollow gap.Described hollow gap member 6 is connected to described inner casing portion 4 with described housing department 3 in the non-mode that is just cooperating and has isolated and sound insulation value with respect to described inner space 20.Described hollow gap member 6 can be saturating, that is to say that air can enter into described hollow gap 5.
The inboard of described casing member 2 is towards described inner space 20, is the inboard of described inner casing portion 4 in this example.On the direction of described inner space 20, described structural constituent 7 and described inner casing portion 4 keep at a certain distance away and are provided with and form the enterable described gap 9 of air with described inner casing portion 4.
In this example, described air-flow 10 or its part air flow stream are crossed described hollow gap 5 and described gap 9 (second, than the cooresponding dotted line of small arrow).Described air-flow is heated with aforementioned manner and emission energy arrives described hollow gap 5 and described gap 9, and it is isolated to form actv..
In addition, the described gap 9 of also flowing through of the described air-flow here.In the case, it is possible that described structural constituent 7 also has insulating effect, thereby relies on described air-flow 10 and the passive isolated of described structural constituent 7 can obtain initiatively isolated particularly advantageous combination.
The function of described valve 13,14 just as described in Figure 1.In this example shown in Figure 2, valve 13,14 can be respectively applied for gap 5,9.
It also is possible that only described hollow gap 5 is accepted described air-flow 10.
Fig. 3 illustrates the embodiment according to described cabin of the present invention body 1, and the difference of itself and embodiment shown in Figure 2 only is, isolated parts 8 are arranged at the inboard of the described inner casing portion 4 in the described gap 9.In this structure, for instance, described isolated parts have formed and isolated combine passive isolated of the active that forms by described air-flow 10.Here, the function of described valve 13,14 also as previously mentioned.
The known field engineering of the pipeline system by a/c system, described inlet 11 is connected to the outflow/inflow air connection pipe of the ventilation inner space 20 that has existed.Utilize the method for attachment of heating ventilation and air-conditioning system in the known aircraft to set up being connected separately between described valve 13,14 and gap 5 and 9 respectively.For instance, for example the common pipeline of rectangle or round section can be connected to each space or space group with the menifold branch form from valve 13 beginnings.These connections for example can be designed to make it to be carried out the transition to the cross-sectional plane of the inlet in each gap by the cross-sectional plane of described air inlet pipe with certain suitable manner.Connection to described outlet 12 is finished in a similar fashion.
Be arranged among the in-to-in embodiment in described gap 5,9 in described control cock, described control cock can be equally correspondingly be provided with according to the heating ventilation and air-conditioning pipeline of aircraft.Here, for example the bonded assembly appropriate section air that is set to be used to import between described gap 5,9 parts separately is possible.The sidepiece that defines the described casing member in described gap separately also can be designed to for example have corresponding conduit, so that they form air lead and described clearance portion being connected to control cock.Such conduit also can increase and is used for isolated described air-flow of described active and the interchange of heat between the described gap.
Fig. 4 illustrates the part sectional view according to another embodiment of the cabin body 1a of individual layer shell structure of the present invention.Described cabin body 1a is unshowned aircraft in this example, for example the cabin body of aircraft.
In the left side of this figure, casing member 2a links to each other with the extraneous 21a of aircraft.It is being reinforced structure 19a reinforcement and is being provided with isolated parts 8a on described casing member 2a inboard vertically (perpendicular to the direction of drawing), and described isolated parts have certain thickness and are fixed on the inboard of described casing member 2a.
In addition, structural constituent 5a, for example lining in cabin and the described isolated parts 8a setting that is spaced a distance forms gap 9a thus.A plurality of such gaps can appear in the described aircraft.
Air can enter this gap 9a by the air-flow 10a shown in the arrow.Described gap 9a links to each other with top X pipeline 14a with the bottom X pipeline 13a of the pipeline system 12a of aircraft air-conditioning system shown in Figure 6.Because described gap 9a forms described Z pipeline 15a (see figure 9) wholly or in part, so it forms the part of described pipeline system 12a system.
For example, described air-flow 10a takes hot air described bottom X pipeline 13a out of and its waste heat is applied to the surface of described gap 9a, forms initiatively isolated thus.So increased the resistance of heat transfer of described cabin body 1a from described inner space 22a to described extraneous 21a.The energy of introducing described air-flow 10a is advantageously used for initiatively and completely cuts off, and also can reduce the energy requirement of described a/c system thus.
Only distribute when it is used for initiatively isolated energy, described air-flow 10a flows into described top X pipeline 14a or described middle part pipeline 16a (see figure 9).
For example, described X pipeline 13a and/or described X pipeline 14a can be integrated into the part of described gap 9a, have reduced number of components and the weight of pipeline system 12a thus.
Zonal structure of the present invention shown in Fig. 5, particularly another embodiment of double hull configuration cabin body 1a.
Many casing structures of described cabin body 1 are presented as bivalve casing member 2a in this example.Outer hull spare 3a is set to the extraneous 21a of a side towards unshowned described aircraft.The setting that is spaced a distance of the side of its opposition side and inner shell element 4a forms hollow gap 6a, is provided with hollow gap member 7a in described hollow gap.Described hollow gap member 7a is connected described outer hull element 3a with the non-mode that is just cooperating and has heat insulation for described inner space 22a and isolation performance sound insulation with described inner shell element 4a.Described hollow gap member 7a can be saturating, that is to say that air can enter into described hollow gap 6a.
The inboard of described casing member 2a is the inboard of the described inner casing 4a of portion in this example towards described inner space 22a.On the direction of described inner space 22a, described structural constituent 5a and the described inner casing 4a of portion are provided with at interval and form the enterable described gap 9a of air with the described inner casing 4a of portion.
In this example, described air-flow 10a or its part air-flow (than small arrow) flow through described hollow gap 5a and described gap 9a ().Described air-flow 10a is heated with aforementioned manner and emission energy arrives described hollow gap 6a and described gap 9a, and it is isolated to form actv..
In addition, the air-flow 10a described here described gap 9a that also flows through.In the case, it is possible that described structural constituent 5a also has insulating effect, thereby relies on the passive isolated of described air-flow 10a and described structural constituent 5a can obtain initiatively isolated particularly advantageous combination.
As according to as described in Fig. 4, described gap 9a and described hollow gap 6a are connected to the described pipeline system 12a of described a/c system, and form same section with it.In this example shown in Figure 5, for will be with it same section integrated, only described gap 9a or described hollow gap 6a self being connected to described pipeline system 12a also is possible certainly.
Fig. 6 illustrates another embodiment according to cabin body 1a of the present invention, and its second embodiment part that is different from according to Fig. 5 is: at first be that only hollow gap 6a forms the Z pipeline 15a of pipeline system 12a.Yet described gap 9a accepts the second air-flow 11a, and described second air-flow is used for air is sent into the zone of described structural constituent 5a back, promptly described gap 9a.This second air-flow 11a also can be as initiatively isolated.This says it is to realize easily to a certain extent, because the mounting structure of this second air-flow 11a often exists.By for example increasing the total throughout of this second air-flow 11a, the active that brings thus in this example is isolated to have obtained enhancing.
In order further to improve isolated property, will completely cut off the inboard that parts 8 are applied to the described inner casing 4a of portion in the described gap 9a in this embodiment.In this was provided with, for instance, described isolated parts 8a relied on the described second air-flow 11a just to form and isolated combine passive isolated of described active through described hollow gap 6a through described gap and described air-flow 10a.Yet, to the pipeline system 12a part of a/c system integrated, only may in hollow gap 6a, realize to the integrated of Z pipeline 15a and with aforesaid connection side.
Divide other field engineering that is connected the pipeline system of known aircraft of employing or spacecraft a/c system to finish between the pipeline system 12a of existing a/c system and described gap 6a, the 9a.For instance, the common bottom X pipeline 13a with rectangle or round section pipeline is connected to each gap or dwell set as menifold with the form of arm.These connect and for example can be designed so that it carries out the transition to the shape of cross section that enters each clearance opening with suitable manner from the shape of cross section of described air inlet pipe.Described gap 6a, 9a with form described top X pipeline 14a and being connected in a similar fashion of middle part X pipeline 16a.
The present invention is not limited to the above embodiments.
For example, the present invention can be used for the situation of single two or many casing structures, and described casing member is formed by the composite of metal, fiber composite materials or metal and fiber composite materials.
Also possible is that described air-flow 10 not only can be heated, and also can be cooled.This possible situation is, if for example a side of cabin body 1 is exposed to high-heating radiation, as the situation of spacecraft example.The opposite side of described cabin body need be heated by air-flow, and is needed cooling by a thermal-radiating side.For example rely on described valve 13,14 corresponding setting to adopt different Hs Exch with switching and described a/c system, this is possible.
Single-piece partly is divided into described gap 9a and 6a also is possible.In the case, can be these separated portions relies on suitable control cock and makes them heat independently of one another, cool off, provide or cut off air and supply with.
In addition, it is a plurality of to it may be noted that " one " does not get rid of.In addition, be to be noted that feature or the step described with reference to embodiment also can be used for and described other embodiment or improved other features or step combination.
Claims (according to the modification of the 19th of treaty)
1, (1,1a), described cabin body has at least one casing member (2 to the cabin body of a kind of aircraft or spacecraft, 2a) and structural constituent (5a, 7), gap (5,6a, 9,9a) be arranged on described casing member (2,2a) and described structural constituent (5a, 7) between, can be by air-flow (10,10a) to described gap (5,6a, 9, send into air 9a), it is characterized in that: for form described cabin body (1,1a) pressurization inner space (20, the air-flow of supplying gas of conduct outflow/inflow air-flow 22a) (10,10a), described gap (5,6a, 9,9a) with described inner space (20,22a) corresponding outflow/inflow air-flow links to each other, and described space (5,6a, 9,9a) hollow gap (5,6a, 9,9a) at least a portion of pipeline (12a) the system pipeline system (12a) of formation a/c system.
2, cabin as claimed in claim 1 body (1,1a), it is characterized in that: described casing member (2,2a) for the form of a plurality of parts and have housing department (3,3a) and inner casing portion (4,4a), can by described air-flow (10,10a) send into air and form described a/c system described pipeline (12a) system pipeline system (12a) at least a portion described gap (9,9a) be arranged on described inner casing portion (4,4a) and described structural constituent (5a, 7) between.
3, cabin as claimed in claim 1 or 2 body (1,1a), it is characterized in that: described casing member (2,2a) for the form of a plurality of parts and have housing department (3,3a) and inner casing portion (4,4a), (3,3a) (4,4a) limiting one can be by described air-flow (10 with inner casing portion for described housing department, 10a) send into air hollow gap (5,6a) and form at least a portion of pipeline (12a) the system pipeline system (12a) of a/c system.
4, as claim 2 or 3 described cabin bodies (1,1a), it is characterized in that: air can be by described air-flow (10,10a) enter described gap (9 simultaneously, 9a) and described hollow gap (5,6a), described space (9,9a) gap (9,9a) form a plurality of parts of separating of described pipeline (12a) the system pipeline system (12a) of described a/c system with described central space (6a).
5, (1,1a), it is characterized in that: described hollow gap (6a) forms the part of the pipeline system (12a) of described a/c system, and air can be admitted to described gap (9a) by second air-flow (11a) as claim 2 or 3 described cabin bodies.
6, the described cabin of at least one as described above claim body (1,1a), it is characterized in that: described casing member (2,2a) be provided with isolated parts (8,8a).
7, (1,1a), it is characterized in that: described structural portion structural constituent (5a, 7) has isolation performance to the described cabin of at least one as described above claim body.
8, the described cabin of at least one as described above claim body (1,1a), it is characterized in that: can regulate described air-flow (10) by described valve (13,14).
9, (1,1a), it is characterized in that: described valve (13,14) is a control cock to cabin as claimed in claim 8 body.
10, as claimed in claim 8 or 9 the cabin body (1,1a), it is characterized in that: described valve (13,14) be used for controlling at least in part described pressurization inner space (20, internal pressure 22a).
11, the described cabin of at least one as described above claim body (1,1a), it is characterized in that: described casing member (2,2a) being combined to form by metal, fiber composite materials or metal and fiber composite materials.
12, have the described cabin of aforementioned at least one claim body (1, aircraft 1a) or spacecraft.
13, the cabin body (1 that initiatively completely cuts off aircraft or spacecraft, method 1a), described cabin body (1,1a) according at least one formation in the aforementioned claim 1 to 11, it is characterized in that: described active is isolated to be realized with air-flow (10), described air-flow be described cabin body (1, pressurization inner space 1a) (20, inflow/effluent stream 22a).
Claims (20)
1, the cabin body (1) of a kind of aircraft or spacecraft, described cabin body has at least one casing member (2) and structural constituent (7), gap (5,9) be arranged between described casing member (2) and the described structural constituent (7), can be by air-flow (10) to described gap (5,9) send into air in, it is characterized in that: for the air-flow of supplying gas (10) of the conduct outflow/inflow air-flow that forms described cabin body (1) pressurization inner space (20), described gap (5,9) is connected with described inner space (20) corresponding outflow/inflow air-flow connection structure.
2, cabin body as claimed in claim 1 (1), it is characterized in that: described casing member (2) is for the form of a plurality of parts and have housing department (3) and inner casing portion (4), can be arranged between described inner casing portion (4) and the described structural constituent (7) by the described gap (9) that described air-flow (10) send into air.
3, cabin body as claimed in claim 1 or 2 (1), it is characterized in that: described casing member (2) is for the form of a plurality of parts and have housing department (3) and inner casing portion (4), and described housing department (3) and inner casing portion (4) limit the hollow gap (5) that can send into air by described air-flow (10).
4, as claim 2 or 3 described cabin bodies (1), it is characterized in that: air can be sent into described gap (9) and described hollow gap (5) simultaneously by described air-flow (10).
5, at least one as described above claim described cabin body (1) is characterized in that: described casing member (2) is provided with isolated parts (8).
6, at least one as described above claim described cabin body (1) is characterized in that: can regulate described air-flow (10) by at least one valve (13,14).
7, cabin body as claimed in claim 6 (1) is characterized in that: described valve (13,14) is a control cock.
8, as claim 6 or 7 described cabin bodies (1), it is characterized in that: described valve (13,14) is used for controlling at least in part the internal pressure of described pressurization inner space (20).
9, at least one as described above claim described cabin body (1) is characterized in that: described casing member (2) being combined to form by metal, fiber composite materials or metal and fiber composite materials.
10, the aircraft or the spacecraft that have aforementioned at least one claim described cabin body (1).
11, the method that initiatively completely cuts off the cabin body (1) of aircraft or spacecraft, described cabin body (1) is according at least one formation in the aforementioned claim 1 to 9, it is characterized in that: described active is isolated to realize that with air-flow (10) described air-flow is the inflow/effluent stream of the pressurization inner space (20) of described cabin body (1).
12, the cabin body (19) of a kind of aircraft or spacecraft, described cabin body has at least one casing member (2a) and structural constituent (5a), gap (6a, 9a) be arranged between described casing member (2a) and the described structural constituent (5a), can be by air-flow (10a) to described gap (6a, send into air 9a), it is characterized in that: described gap (9a) forms at least a portion of the pipeline system (12a) of an a/c system.
13, cabin body as claimed in claim 12 (19), it is characterized in that: at least one casing member (2a) is for the form of a plurality of housings and have housing department (3a) and inner casing portion (4a), and the described gap (9a) of a part that forms pipeline (12a) system of described a/c system is arranged between described inner casing portion (4a) and the described structural constituent (5a).
14, as claim 12 or 13 described cabin bodies (1), it is characterized in that: described casing member (2a) is for the form of a plurality of housings and have housing department (3a) and inner casing portion (4a), and described housing department (3a) and inner casing portion (4a) limit the described hollow gap (6a) of at least a portion of the pipeline system (12a) that forms described a/c system.
15, as claim 13 or 14 described cabin bodies (1), it is characterized in that: described gap (9a) and described hollow gap (6a) form a plurality of parts of separating of the pipeline system (12a) of a/c system.
16, as claim 13 or 14 described cabin bodies (1), it is characterized in that: described hollow gap (6a) forms the part of the pipeline system (12a) of described a/c system, and air can be admitted to described gap (9a) by second air-flow (11a).
17, as at least one described cabin body (1) in the claim 12 to 16, it is characterized in that: described casing member (2a) is provided with isolated parts (8a).
18, as at least one described cabin body (1) in the claim 12 to 17, it is characterized in that: described structural constituent (5a) has isolation performance.
19, as at least one described cabin body (1) in the claim 12 to 18, it is characterized in that: described casing member (2a) being combined to form by metal, fiber composite materials or metal and fiber composite materials.
20, the aircraft or the spacecraft that have at least one described cabin body of claim 12 to 19 (1).
Applications Claiming Priority (9)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US90303307P | 2007-02-23 | 2007-02-23 | |
| US90303407P | 2007-02-23 | 2007-02-23 | |
| US60/903,033 | 2007-02-23 | ||
| US60/903,034 | 2007-02-23 | ||
| DE102007008987.4 | 2007-02-23 | ||
| DE102007008986.6 | 2007-02-23 | ||
| DE102007008987A DE102007008987B4 (en) | 2007-02-23 | 2007-02-23 | A fuselage of an aircraft or spacecraft and a method of actively isolating such a fuselage |
| DE200710008986 DE102007008986A1 (en) | 2007-02-23 | 2007-02-23 | Trunk for air or spacecraft, has shell element and structural component and gap is provided between shell element and structural component and is vented by air flow |
| PCT/EP2008/052120 WO2008101986A1 (en) | 2007-02-23 | 2008-02-21 | Fuselage of an aircraft or spacecraft and method of actively insulating such a fuselage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101636314A true CN101636314A (en) | 2010-01-27 |
| CN101636314B CN101636314B (en) | 2013-04-17 |
Family
ID=39645897
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008800058274A Expired - Fee Related CN101636314B (en) | 2007-02-23 | 2008-02-21 | Fuselage of an aircraft or spacecraft and method of actively insulating such a fuselage |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN101636314B (en) |
| DE (1) | DE102007008987B4 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530252A (en) * | 2010-12-15 | 2012-07-04 | 波音公司 | Method and apparatus for air flow control in an aircraft sidewall volume |
| CN103204242A (en) * | 2013-03-25 | 2013-07-17 | 大连理工大学 | Double air channel wall for airplane |
| CN105000166A (en) * | 2015-04-29 | 2015-10-28 | 中国航空工业集团公司北京航空材料研究院 | Heat insulation structure used for high-mach-number air vehicle |
| CN106428520A (en) * | 2015-08-04 | 2017-02-22 | 空中客车作业有限公司 | Aircraft insulation system and aircraft air conditioning and insulation arrangement |
| CN111452985A (en) * | 2019-01-22 | 2020-07-28 | 波音公司 | System and method for passively removing moisture from air within a vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2969978T3 (en) | 2015-01-22 | 2024-05-23 | Safran Aerotechnics | Uses of heat from aircraft fuel cells |
| FR3038582B1 (en) * | 2015-07-07 | 2018-11-09 | Airbus | COVER PANEL OF AN AIRCRAFT FUSELAGE INTEGRATING THERMAL AND ACOUSTIC INSULATION |
| IT201700103537A1 (en) * | 2017-09-15 | 2019-03-15 | Mecaer Aviation Group S P A | AIRCRAFT PROVIDED WITH A PERFECT FUSELAGE |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE465772B (en) * | 1990-03-06 | 1991-10-28 | Ctt Systems Hb | PROCEDURE AND DEVICE TO PREVENT THE CONDUCT OF SCALE CONSTRUCTIONS |
| US5788184A (en) * | 1997-01-04 | 1998-08-04 | Eddy; Robert G. | Aircraft passenger safety enhanced fuselage insulation blanket |
| US5897079A (en) * | 1997-08-18 | 1999-04-27 | Mcdonnell Douglas Corporation | Air curtain insulating system for aircraft cabin |
| CA2256887C (en) * | 1998-12-21 | 2008-07-08 | Indoor Air Technologies Inc. | Environment control system for aircraft having interior condensation problem reduction, cabin air quality improvement, fire suppression and fire venting functions |
| DE10154063B4 (en) * | 2001-11-02 | 2013-11-28 | Airbus Operations Gmbh | Double-walled core composite, preferably fiber composite |
-
2007
- 2007-02-23 DE DE102007008987A patent/DE102007008987B4/en not_active Expired - Fee Related
-
2008
- 2008-02-21 CN CN2008800058274A patent/CN101636314B/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530252A (en) * | 2010-12-15 | 2012-07-04 | 波音公司 | Method and apparatus for air flow control in an aircraft sidewall volume |
| US9102392B2 (en) | 2010-12-15 | 2015-08-11 | The Boeing Company | Method and apparatus for air flow control in an aircraft sidewall volume |
| CN102530252B (en) * | 2010-12-15 | 2016-05-11 | 波音公司 | In aircraft sidewall spaces for the method and apparatus of air stream control |
| CN103204242A (en) * | 2013-03-25 | 2013-07-17 | 大连理工大学 | Double air channel wall for airplane |
| CN103204242B (en) * | 2013-03-25 | 2015-07-22 | 大连理工大学 | Double air channel wall for airplane |
| CN105000166A (en) * | 2015-04-29 | 2015-10-28 | 中国航空工业集团公司北京航空材料研究院 | Heat insulation structure used for high-mach-number air vehicle |
| CN106428520A (en) * | 2015-08-04 | 2017-02-22 | 空中客车作业有限公司 | Aircraft insulation system and aircraft air conditioning and insulation arrangement |
| CN111452985A (en) * | 2019-01-22 | 2020-07-28 | 波音公司 | System and method for passively removing moisture from air within a vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102007008987A1 (en) | 2008-08-28 |
| CN101636314B (en) | 2013-04-17 |
| DE102007008987B4 (en) | 2012-11-29 |
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