CN112937833A - Airframe structure for aircraft, construction method thereof and aircraft - Google Patents
Airframe structure for aircraft, construction method thereof and aircraft Download PDFInfo
- Publication number
- CN112937833A CN112937833A CN202110244145.6A CN202110244145A CN112937833A CN 112937833 A CN112937833 A CN 112937833A CN 202110244145 A CN202110244145 A CN 202110244145A CN 112937833 A CN112937833 A CN 112937833A
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- Prior art keywords
- flame
- burn
- resistant
- airframe
- aircraft
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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
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
-
- 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
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
Abstract
The invention relates to an airframe structure for an aviation aircraft, wherein the airframe structure limits a containing space in the aviation aircraft, the outer side of the airframe structure is provided with a skin structure, the airframe structure comprises a flame burnthrough resistant layer structure and a plurality of airframe heat and sound insulation layer structures, the flame burnthrough resistant layer structure comprises a flame burnthrough resistant coating, the flame burnthrough resistant coating is arranged on the central part of the lower side of the airframe of the aviation aircraft, and the plurality of airframe heat and sound insulation layer structures are arranged on the other parts of the central part of the lower side of the airframe of the aviation aircraft except for the flame burnthrough resistant layer structure; the flame-burn-through resisting layer structure and the plurality of fuselage heat and sound insulation layer structures form an overlapping area at the edge of the central part of the lower side of the aircraft body. The invention also relates to an aircraft comprising such a body structure and to a construction method providing a flame burn-through resistant body structure.
Description
Technical Field
The present invention relates to an airframe structure for an aircraft, to an aircraft comprising such an airframe structure, and to a construction method providing a flame burn-through resistant airframe structure.
Background
Civil aircraft is from 2011, CCAR25 repaiies the card and updates to R4 version, the aircraft carries out CCAR25.856 b more than 20 seats comprehensively, wherein the angle that the airworthiness clause takes place from the small probability incident, the anti external flame of aircraft organism burns out the requirement has been proposed, nevertheless to the aircraft design, the whole fuselage of bearing the weight of the entity has been aggravated greatly, including the covering, floor and cargo compartment structure floor, the design degree of difficulty on the thermal-insulated sound insulating layer of fuselage the latter half, mainly for fuselage the latter half requirement forms the anti-flame layer, like thermal-insulated sound insulating layer and fuselage fixed mode, thermal-insulated sound insulating layer and passenger cabin or cargo compartment floor structure overlap area, passenger cabin or cargo compartment structure floor butt seam etc. satisfy anti-flame and burn out the performance.
Therefore, it is common practice in the art to make the thermal/acoustical insulation material (including the fixing means) of the lower half of the aircraft meet flame burn-through resistance at 1038 ± 55 degrees for 4 minutes, and the heat flux is less than 2.27w/cm ^2, thereby ensuring that the aircraft is on fire after an accidental crash, the whole body of the aircraft can resist external flame burn-through, and personnel in the cabin can have enough time to perform emergency evacuation.
Disclosure of Invention
In order to overcome the disadvantages, the invention takes the following measures: the utility model provides an anti flame burns out organism structure, according to anti flame burns out the requirement, utilizes to set up anti flame and burns out a layer structure at the organism structure inboard, sets up the heat-insulating sound-proof layer structure of organism and anti flame and burns out a layer structure and overlap (two-dimentional cross sectional dimension is greater than 6 inches) to structural discontinuity region (like structural joint and support etc.) adds scribbles hot wall sealant, realizes that the organism structure has the function of anti flame burns out the envelope.
To this end, according to one of its aspects, the invention provides a body structure for an aircraft, the body structure defining a housing space in the interior of the aircraft, the body structure being provided on its outside with a skin structure, wherein the body structure comprises:
a flame burnthrough resistant layer structure comprising a flame burnthrough resistant coating disposed only on a central portion of a lower side of an airframe of the aerospace vehicle,
in the region of the body below the cargo compartment floor, no flame-through-resistant layer is provided.
The fuselage heat and sound insulation layer structures are arranged on the other parts of the central part of the lower side of the aircraft body except the flame burn-through resistant layer structure;
wherein the flame burn-through resistant layer structure forms an overlapping area with the plurality of fuselage heat and sound insulation layer structures at the edge of the lower-side central portion of the aircraft body.
According to a preferred embodiment of the invention, the flame burn-through resistant coating is located on the inside or outside of the skin structure.
According to a preferred embodiment of the invention, the flame-burn-through resistant coating comprises a fire-resistant paint or a fire-retardant coating, which does not burn through under conditions of flame burning of at least 1200 degrees for up to 4 minutes.
According to a preferred embodiment of the present invention, the flame-resistant coating or the fire retardant coating may be an inorganic high-temperature binder of silicate or phosphate type.
According to a preferred embodiment of the invention, the two-dimensional cross-sectional length of the overlapping area is greater than 6 inches.
According to a preferred embodiment of the invention, the flame-through-resistant layer structure is connected to the plurality of fuselage insulation layer structures in the overlap region by means of flame-resistant velcro, foam or foaming agent.
According to a preferred embodiment of the invention, the flame-burn-through resistant layer structure is provided with discontinuous areas.
According to a preferred embodiment of the invention, the discrete areas of the flame-burn-through resistant layer structure are covered by a firewall sealant.
According to another aspect of the invention, the invention provides an aircraft for aviation comprising an airframe structure as defined above.
According to a further aspect of the invention, the invention provides a construction method for providing a flame-burn-through resistant airframe structure for an aircraft, the airframe structure defining a containment space inside the aircraft, a skin structure being provided outside the airframe structure, wherein the construction method comprises:
arranging a flame burnthrough resistant layer structure, so that the flame burnthrough resistant layer structure comprises a flame burnthrough resistant coating which is only arranged on the middle part of the lower side of the aircraft body,
in the region of the body below the cargo compartment floor, no flame-through-resistant layer is provided.
Arranging a plurality of fuselage heat and sound insulation layer structures, so that the fuselage heat and sound insulation layer structures are arranged on the other parts of the lower side central part of the aircraft body except the flame burn-through resistant layer structure;
wherein the flame burn-through resistant layer structure forms an overlapping area with the plurality of fuselage heat and sound insulation layer structures at the edge of the lower-side central portion of the aircraft body.
According to a preferred embodiment of the invention, the flame burn-through resistant coating is located on the inside or outside of the skin structure.
According to a preferred embodiment of the invention, the flame-burn-through resistant coating comprises a fire-resistant paint or a fire-retardant coating, which does not burn through under conditions of flame burning of at least 1200 degrees for up to 4 minutes.
According to a preferred embodiment of the present invention, the flame-resistant coating or the fire retardant coating may be an inorganic high-temperature binder of silicate or phosphate type.
According to a preferred embodiment of the invention, the overlap region is configured such that its two-dimensional cross-sectional length is greater than 6 inches.
According to a preferred embodiment of the invention, the flame-through-resistant layer structure is connected to the plurality of fuselage insulation layer structures in the overlap region by means of flame-resistant velcro, foam or foaming agent.
According to a preferred embodiment of the invention, the flame-burn-through resistant layer structure is provided with discontinuous areas.
According to a preferred embodiment of the invention, the discrete areas of the flame-burn-through resistant layer structure are covered by a firewall sealant.
Drawings
For a better understanding of the above and other objects, features, advantages and functions of the present invention, reference should be made to the preferred embodiments illustrated in the accompanying drawings. Like reference numerals in the drawings refer to like parts. It will be appreciated by persons skilled in the art that the drawings are intended to illustrate preferred embodiments of the invention without any limiting effect on the scope of the invention, and that the various components in the drawings are not drawn to scale.
Fig. 1 is a sectional view of an airframe structure for an aircraft according to the present invention.
Fig. 2 is a detail view of the airframe structure for an aerospace vehicle according to the invention at an overlap region.
List of reference numerals
1. Machine body structure
2. Cabin floor
3. Cargo compartment floor
4. Heat insulation layer structure of machine body
5. Flame-burning-resistant layer structure
6. Overlapping area
7. Flame-retardant velcro, foam or foaming agent
8. Discontinuous region
9. Body region below cargo compartment floor
Detailed Description
Reference will now be made in detail to the embodiments of the present invention, examples of which are illustrated in the accompanying drawings. What has been described herein is merely a preferred embodiment in accordance with the present invention and other ways of practicing the invention will occur to those skilled in the art and are within the scope of the invention. In the following detailed description, directional terms, such as "left", "right", "upper", "lower", "inner", "outer", and the like, are used with reference to the orientation as illustrated in the drawings, wherein "longitudinal" refers to the length direction of an aerospace vehicle. Components of embodiments of the present invention can be positioned in a number of different orientations and the directional terminology is used for purposes of illustration and is in no way limiting. In particular, the term "inboard" as used herein refers to a side that is located within the airframe structure of an aircraft. The term "outboard" as used herein refers to a side that is located outside the airframe structure of an aircraft.
Fig. 1 shows an embodiment of an airframe structure for an aircraft according to the invention, the airframe structure 1 defining an accommodation space in the interior of the aircraft, in which accommodation space a cabin floor 2 and a cargo compartment floor 3 are arranged parallel to each other. The airframe structure 1 is provided with a skin structure (not shown) on the outside of the airframe structure 1.
As shown in fig. 1, the airframe structure 1 includes a plurality of fuselage insulation 4 and flame-burn-through resistant 5 layers. The flame-through resistant layer structure 5 comprises a flame-through resistant coating which is provided only on the lower central part of the aircraft body of the aircraft, wherein the flame-through resistant layer is no longer provided in the region 9 of the aircraft body below the cargo compartment floor.
A plurality of fuselage insulation 4 (two are shown in fig. 1) are arranged on the other part of the central part of the underside of the aircraft body than the flame-burn-through-resistant layer. Because the flame-resistant combustion coating is only arranged on the middle part of the lower side of the aircraft body of the aircraft, the flame-resistant combustion coating is not arranged in the aircraft body area 9 below the cargo compartment floor, the weight of the aircraft body can be reduced while the flame-resistant combustion condition is met, and the cost is reduced. The plurality of fuselage heat and sound insulation layer structures 4 comprise heat and sound insulation materials, and the flame burnthrough resistant layer structure 5 comprises flame-resistant paint and fireproof coating, such as inorganic high-temperature adhesive of silicate and phosphate, and is not burnthrough under the condition of flame combustion at least 1200 ℃ for 4 minutes, so that the fuselage heat and sound insulation layer structures 4 are replaced to play the function of flame burnthrough resistance. The flame resistant combustion coating may be disposed on the interior side or the exterior side of the skin structure.
As shown in fig. 1, the flame-burn-through resistant layer structure 5 forms an overlap region 6 with the plurality of fuselage heat and sound insulating layer structures 4 at the edge of the lower, central part of the aircraft body. In the overlap region 6, the flame-through resistant layer structure 5 is located on the inside of the skin structure, while the plurality of fuselage insulation 4 structures are located on the inside of the flame-through resistant layer structure 5. According to a preferred embodiment, not shown, the flame-penetration resistant layer structure 5 may be located on the outside of the skin structure, while a plurality of fuselage insulation 4 structures are likewise located on the inside of the flame-penetration resistant layer structure 5. However, it is conceivable for a person skilled in the art that the flame-resistant layer structure 5 and the plurality of fuselage insulation 4 may be arranged differently depending on the actual situation, for example, further components or layers may be arranged between the flame-resistant layer structure 5 and the plurality of fuselage insulation 4, or the plurality of fuselage insulation 4 may be arranged on the outside of the flame-resistant layer structure 5.
As shown in the detail view of the airframe structure for an aerospace vehicle according to the invention at the overlap area of fig. 2, the two-dimensional cross-sectional length of the overlap area 6 is greater than 6 inches per AC25.856-2A, ensuring that the two different flame-burn-through resistant media have sufficient overlap in the butt-joint region to avoid flame burn-through in this area. Further, the flame-burn-through resistant layer structure 5 is connected to the plurality of fuselage insulation 4 layers in the overlap region 6 by flame-retardant velcro, foam or foaming agent 7, such as polyurethane, respectively.
Referring to fig. 1, the flame-resistant layer structure 4 is provided with discrete areas 8, such as structural joints and brackets. The discontinuous areas 8 of the flame-burn-through resistant layer structure 5 are covered by a fire-wall sealant or a flame-retardant foaming agent, thereby realizing that the aircraft belly structure has the function of flame-burn-through resistance.
According to a further aspect thereof, the invention also relates to an aircraft for aviation comprising an airframe structure 1.
A method of construction according to yet another aspect of the present invention to provide flame burn through resistant airframe structures will now be described. Firstly, a body structure 1 for an aircraft is provided, the body structure 1 defining an accommodation space in the interior of the aircraft, in which accommodation space a cabin floor 2 and a cargo compartment floor 3 are arranged parallel to one another. The airframe structure 1 is provided with a skin structure (not shown) on the outside of the airframe structure 1.
Further, in the construction method of the present invention, a plurality of fuselage heat and sound insulating layer structures 4 and flame burn-through resistant layer structures 5 are provided for the airframe structure 1 such that the flame burn-through resistant layer structures 5 are provided only on the lower central portion of the airframe of the aircraft, and such that a plurality of fuselage heat and sound insulating layer structures 4 (two are shown in fig. 1) are provided on the portions of the lower central portion of the airframe of the aircraft other than the flame burn-through resistant layer structures. The flame burn through resistant coating structure is located either inboard or outboard of the skin structure.
Further, in the construction method of the invention, the flame burn-through resistant layer structure 5 is made to form an overlap region 6 with the plurality of fuselage heat and sound insulation layer structures 4 at the edge of the lower, central part of the fuselage of the aircraft. In the embodiment shown in fig. 1, in the overlap region 6, the flame-penetration resistant layer structure 5 is located on the inside of the skin structure, while the plurality of fuselage insulation 4 layers are located on the inside of the flame-penetration resistant layer structure 5.
Further, in the construction method of the present invention, the two-dimensional cross-sectional length of the overlap region 6 is made greater than 6 inches, ensuring that the two different flame burnthrough resistant media have sufficient overlap in the butt-joint region to avoid flames in this region. Further, the flame-burn-through resistant layer structure 5 is connected to the plurality of fuselage insulation 4 layers in the overlap region 6 by flame-retardant velcro, foam or foaming agent 7, such as polyurethane, respectively.
Finally, in the construction method of the invention, in the case where the flame-penetration resistant layer structure 4 is provided with discontinuous areas 8 (for example, structural joints and brackets, etc.), the discontinuous areas 8 of the flame-penetration resistant layer structure 5 are covered by a firewall sealant or flame-retardant foaming agent, thereby achieving the flame-penetration resistant function of the aircraft belly structure.
The invention has the advantages that:
1) the anti-fire penetration layer structure is used for resisting fire penetration, the main fire-proof requirement of the cargo compartment floor structure is lowered, the weight is reduced, and the cost is saved.
2) The using amount of the heat and sound insulation layer at the bottom of the airplane is reduced, so that the weight of the whole airplane is reduced, for example, the weight of a 150-seat airplane is saved by 15-18 kg, and the weight of a branch airplane is saved by 10-12 kg;
3) the accumulation of water vapor, dust, oil stain and the like on the belly in the service process of the airplane is avoided, and the service life of the heat and sound insulation layer of the airplane is prolonged.
The foregoing description of various embodiments of the invention is provided for the purpose of illustration to one of ordinary skill in the relevant art. It is not intended that the invention be limited to a single disclosed embodiment. As mentioned above, many alternatives and modifications of the present invention will be apparent to those skilled in the art of the above teachings. Thus, while some alternative embodiments are specifically described, other embodiments will be apparent to, or relatively easily developed by, those of ordinary skill in the art. The present invention is intended to embrace all such alternatives, modifications and variances of the present invention described herein, as well as other embodiments that fall within the spirit and scope of the present invention as described above.
Claims (17)
1. An airframe structure for an aircraft, the airframe structure defining a receiving space within the aircraft, an exterior side of the airframe structure being provided with a skin structure, wherein the airframe structure includes:
a flame burnthrough resistant layer structure comprising a flame burnthrough resistant coating disposed only on a central portion of a lower side of an airframe of the aerospace vehicle,
the fuselage heat and sound insulation layer structures are arranged on the other parts of the central part of the lower side of the aircraft body except the flame burn-through resistant layer structure;
wherein the flame burn-through resistant layer structure forms an overlapping area with the plurality of fuselage heat and sound insulation layer structures at the edge of the lower-side central portion of the aircraft body.
2. Airframe structure as defined in claim 1, wherein the flame burn-through resistant coating is located inboard or outboard of the skin structure.
3. Airframe structure as defined in claim 1, wherein said flame burn-through resistant coating comprises a fire resistant paint or fire retardant coating, which does not burn through under conditions of flame burning of at least 1200 degrees for up to 4 minutes.
4. Airframe structure as defined in claim 3, wherein the flame-resistant coating or fire-retardant coating is an inorganic high-temperature binder of silicate or phosphate type.
5. Airframe structure as recited in claim 1, wherein said overlapping area has a two-dimensional cross-sectional length greater than 6 inches.
6. Airframe structure as defined in claim 1, wherein the flame-burn-through resistant layer structure is connected to each other with the plurality of fuselage insulation layer structures in the overlapping area by flame-retardant velcro, foam or foaming agent.
7. Airframe structure as defined in claim 1, wherein said flame-burn-through resistant layer structure is provided with discontinuous areas.
8. Airframe structure as defined in claim 7, wherein the discrete areas of the flame-burn-through resistant layer structure are covered by a firewall sealant.
9. An aircraft for aviation comprising an airframe structure as defined in any one of claims 1 to 8.
10. A construction method for providing a flame-burn-through resistant airframe structure for an aircraft, the airframe structure defining a receiving space within the aircraft, an exterior side of the airframe structure being provided with a skin structure, wherein the construction method comprises:
arranging a flame burnthrough resistant layer structure, so that the flame burnthrough resistant layer structure comprises a flame burnthrough resistant coating which is only arranged on the middle part of the lower side of the aircraft body,
arranging a plurality of fuselage heat and sound insulation layer structures, so that the fuselage heat and sound insulation layer structures are arranged on the other parts of the lower side central part of the aircraft body except the flame burn-through resistant layer structure;
wherein the flame burn-through resistant layer structure forms an overlapping area with the plurality of fuselage heat and sound insulation layer structures at the edge of the lower-side central portion of the aircraft body.
11. The method of claim 10, wherein the flame burn-through resistant coating is located inboard or outboard of the skin structure.
12. The method of claim 10, wherein the flame burn through resistant coating comprises a fire resistant paint or coating that does not burn through at least 1200 degrees of flame burn for up to 4 minutes.
13. The method of claim 12, wherein the flame-resistant coating or fire-retardant coating is an inorganic high-temperature binder of silicate or phosphate type.
14. The method of claim 10, wherein the overlap region is configured such that its two-dimensional cross-sectional length is greater than 6 inches.
15. The method of construction of claim 10 wherein the flame-resistant burn-through layer structure and the plurality of fuselage insulation layer structures are connected to each other within the overlap region by flame-retardant velcro, foam, or a foaming agent.
16. The method of constructing as claimed in claim 10, wherein the flame-burn-through resistant layer structure is provided with discontinuous regions.
17. The method of claim 16, wherein the discrete areas of the flame-burn-through resistant layer structure are covered by a firewall sealant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110244145.6A CN112937833A (en) | 2021-03-05 | 2021-03-05 | Airframe structure for aircraft, construction method thereof and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110244145.6A CN112937833A (en) | 2021-03-05 | 2021-03-05 | Airframe structure for aircraft, construction method thereof and aircraft |
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| CN112937833A true CN112937833A (en) | 2021-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110244145.6A Pending CN112937833A (en) | 2021-03-05 | 2021-03-05 | Airframe structure for aircraft, construction method thereof and aircraft |
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| US20100276539A1 (en) * | 2006-12-13 | 2010-11-04 | Falk Brinkmann | Fire protection device for an aircraft or spacecraft |
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| JP2016132391A (en) * | 2015-01-21 | 2016-07-25 | 三菱航空機株式会社 | Aircraft and body cooling structure |
| CN105923144A (en) * | 2016-05-30 | 2016-09-07 | 中国商用飞机有限责任公司 | Flame-burning-through-resistant machine and flame-burning-through-resistant floor used for flame-burning-through-resistant machine |
| CN209142375U (en) * | 2018-09-14 | 2019-07-23 | 中国商用飞机有限责任公司 | Aircraft heat-and sound-insulating layer fixation kit |
| CN111849229A (en) * | 2020-07-30 | 2020-10-30 | 湖南理工学院 | Fire escape passage fireproof powder coating and preparation process thereof |
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2021
- 2021-03-05 CN CN202110244145.6A patent/CN112937833A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4235398A (en) * | 1978-12-18 | 1980-11-25 | The Boeing Company | Thermal insulation for aircraft fuselage |
| CN101432045A (en) * | 2006-05-02 | 2009-05-13 | 空中客车德国有限公司 | Fire barrier for an aircraft fuselage |
| US20100276539A1 (en) * | 2006-12-13 | 2010-11-04 | Falk Brinkmann | Fire protection device for an aircraft or spacecraft |
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| CN111849229A (en) * | 2020-07-30 | 2020-10-30 | 湖南理工学院 | Fire escape passage fireproof powder coating and preparation process thereof |
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