• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:

    公开号:AT510153A4
    申请号:T0173810
    申请日:2010-10-19
    公开日:2012-02-15
    发明作者:
    申请人:Facc Ag；
    IPC主号:
    专利说明:

    1
    The invention relates to a decompression unit for use in a decompression opening of a wall element of an aircraft, with a fastenable via a frame in or above the decompression panel, which panel is movable at a predetermined differential pressure to release the decompression opening from the frame. During the flight of an aircraft, the pressure in the cabin is increased, in order to create normal environmental conditions for the passengers and the flight personnel also in the usual flight altitudes. Accordingly, the internal pressure of an aircraft relative to the environment is increased, which is why the cabin is designed in the form of a pressurized cabin. To regulate the pressure in the cabin of an aircraft corresponding exhaust valves are provided.
    Most aircraft have multiple sections, which are divided by corresponding wall elements. For example, the passenger compartment of a passenger aircraft is correspondingly separated from the cargo compartment. Under the term wall element are understood to mean both substantially vertically arranged elements, but also substantially horizontally arranged floor elements and ceiling elements. In the intermediate walls between such cabins so-called decompression units must be arranged, which open when exceeding a predetermined differential pressure between the rooms on both sides of the wall element and allow pressure equalization. For example, a hole in the outer skin of the aircraft can lead to a corresponding negative pressure in the cargo compartment, through which the differential pressure between the passenger compartment and the cargo compartment could rise to an inadmissibly high value and lead to the destruction of the wall elements. In such a case, the decompression panels release and release corresponding decompression openings in the wall elements, via which a pressure equalization between the spaces can be made quickly. Such decompression (blow-out) panels must trigger when exceeding a predetermined differential pressure within the shortest possible time. Decompression panels for aircraft are known in various embodiments.
    For example, US 5 871 178 A describes a decompression panel in which the decompression openings are covered by resiliently mounted panels. When a certain differential pressure is exceeded, the spring force of the fasteners is overcome and the panel is moved out of the opening. The disadvantage here is that the spring force, which is overcome, is not clearly defined.
    EP 291 661 B1 describes a similar decompression panel for intermediate walls and / or intermediate floors of aircraft, which is held in the decompression opening by means of uniformly distributed holding and clamping devices. The retaining springs are equipped with predetermined breaking points, which break when exceeding a predetermined differential pressure. Also, this construction is relatively complex and does not guarantee a fast trip time.
    The object of the present invention is to provide an above-mentioned decompression unit, which is as simple and inexpensive as possible, and which triggers when exceeding a predetermined differential pressure as quickly and reliably. Disadvantages of known systems should be prevented or at least reduced.
    The object of the invention is achieved in that the panel is formed by at least one cured prepreg with at least one filled by a cured resin parting line as a predetermined breaking point, which parting line breaks when exceeding the predetermined differential pressure. The decompression unit according to the invention is characterized by a particularly simple and inexpensive to produce construction and guarantees a release in a very short time. In the preparation, one or more prepreg layers in the uncured state are severed on a freely definable contour and then cured in the usual manner in an autoclave. The produced parting line is automatically filled by the resin contained in the prepreg. The cured resin in the parting line thus forms the predetermined breaking point, which breaks when the differential pressure is exceeded. By appropriate choice of the width of the parting line and the height of the parting line or the number of prepreg layers, the differential pressure at which the predetermined breaking 3-point breaks, can be set relatively accurately and reliably. The width of the parting line with respect to the tripping method is not particularly relevant here; It is only important that in the production of the parting line, the fibers of the prepreg layer, in particular the glass fibers of a glass fiber prepreg, are severed. The course of the parting line can be adapted to the respective geometric conditions. The decompression unit according to the invention is also characterized by a very low mass of the panel, which ensures a very fast tripping time. In addition, the decompression unit on the visible side can be easily adapted to the usual interior of an aircraft cabin.
    According to a feature of the invention, the parting line in the panel may be self-contained. This ensures safe release of the decompression opening in the event of a differential pressure being exceeded. Alternatively, the parting line can of course not be self-contained, whereby the panel is not completely torn off the decompression opening in the case of release, but is unfolded accordingly. By appropriate choice of the size of the decompression opening ensures that the time required for pressure equalization air can get in the shortest possible time from one side of the wall element to the other side of the wall element.
    If a plastic film is arranged on at least one side of the at least one prepreg layer, the production of the panel can be facilitated because the plastic film serves as a carrier material and thus the transport of the panel into the autoclave for curing is simplified. In addition, the plastic film gives the panel an optimal visual appearance. In particular, a polyvinyl fluoride film, which is available, for example, under the trade name Tedlar® from DuPont, has proven particularly useful. This polymer film is already used for coating panels in aircraft and is characterized by a particularly small thickness and high resistance.
    In order to ensure the tightness of the decompression unit in the untripped state, it is advantageous if, at the, 4
    Wall element facing side of the panel, a strip of elastic material, in particular foam, is arranged. This foam strip seals the decompression opening accordingly.
    In order to additionally ensure the fire protection regulations and also the required smoke-tightness, a fire protection strip made of flame-retardant material can also be arranged on the side of the panel facing the wall element. Such a fire-resistant strip made of flame-retardant material can be used in addition to or instead of the above-mentioned foam strip. In this case, a so-called intumescent fire protection laminate based on graphite, as it is already used in fire doors, particularly suitable. For example, such a fire-resistant laminate is available under the brand name Intumex® L.
    For connecting the frame of the decompression unit with the wall element of the aircraft, corresponding connecting elements can be provided.
    When the fasteners are formed by screws, bolts or the like, replacement of the decompression unit is relatively easy.
    If, in addition to or instead of screws or bolts, the frame of the decompression unit is glued, an exchange of the decompression unit can not be done or not so easy.
    In order to prevent the panel or parts of the panel from being moved uncontrollably out of the decompression opening in the event of a pressure difference being exceeded, at least one element may be provided to secure the panel. Such a securing element is particularly relevant in a self-contained parting line, so that the panel is held in the event of triggering the decompression unit to the wall element.
    In the simplest case, such securing elements may be formed by cables which are arranged between the frame of the decompression unit or the wall element and the panel. 5
    For example, one end of the rope can be connected to the connecting elements on the frame, whereas the other free end of the rope can be glued to the panel.
    In order to prevent accidental breaking of the parting line of the panel by mechanical action from one side of the decompression unit, a protective grid connectable to the frame can be arranged on this side of the panel. This protective grid prevents the panel from being pressed out of the decompression opening, for example by hand or with one foot, and thus also when the differential pressure falls below a release of the decompression opening takes place. The protective grid is advantageously also produced by a grid formed from at least one prepreg.
    If the parting line has a width of 0.1 to 0.8 mm, the secure separation of the fibers of the prepreg layer is ensured and a simple production of the parting line by conventional methods possible.
    The invention will be explained in more detail with reference to the accompanying figures.
    Show:
    1 shows the view of a wall element of an aircraft with a decompression opening and a decompression unit arranged therein according to the present invention;
    Figure 2 is a view of the wall element 3 according to Figure 1 from the other side;
    Figure 3 is a sectional view through the wall element 3 according to Figure 2 along the section line III-III;
    FIGS. 4a and 4b are sectional views of two different embodiments of a panel of a decompression unit according to the invention;
    FIGS. 5a to 5c show various arrangements of a parting line in the plane of the decompression unit; and
    FIG. 6 shows a further embodiment of a decompression unit with a protective grid arranged thereon.
    FIG. 1 shows a view of a decompression unit 1 in a decompression opening 2 of a wall element 3 in an aircraft. Accordingly, the decompression opening 2 is covered in the wall element 3 by a panel 5, which panel 5 is formed by at least one cured prepreg 6 with at least one filled by hardened resin parting line 7 as a predetermined breaking point (see Figure 4a and 4b). By the parting line 7 in the panel 5 ensures that the fibers of the prepreg, in particular the glass fibers, are severed and thus a predetermined breaking point is formed, which is filled only by hardened resin. In the case of exceeding the predetermined differential pressure Δρ the brittle resin is broken in the parting line 7 and the panel 5 is moved out of the decompression opening 2, whereby a pressure equalization between the two sides of the wall element 3 can take place.
    FIG. 2 shows a rear view of the decompression unit 1 according to FIG. 1. In this case, the panel 5 is connected to the wall element 3 via a frame 4. For connection, for example, corresponding connecting elements 10, which can be formed by screws, bolts or the like. In a continuous, self-contained parting line 7, the panel 5 would be moved completely out of the decompression opening 2 in the decompression case. In order to secure the panel 5 in the event of triggering, fuse elements 11 may be provided. These securing elements 11 may be formed, for example, by cables which are fastened between the connecting elements 10 on the frame 4 and the panel 5.
    The sectional view according to Figure 3 shows the wall element 3 and the panel 5, which is arranged in the illustrated example via a strip 8 of elastic material, in particular foam, in the wall element 3. In addition, a fire protection strip 9 made of flame-retardant material can be arranged in order to achieve the required fire protection regulations and smoke-tightness - 7 ·· ··· «• φ · ·> ···· * «to be able to guarantee.
    Figures 4a and 4b show two embodiments of a panel 5 for forming the decompression unit according to the invention 1. In the embodiment of Figure 4a, the panel 5 consists of a prepreg layer 6 with the parting line 7, which is filled by Har2. On one side of the prepreg layer 6 of the panel 5, a plastic film 13, in particular a polyvinyl fluoride film, is arranged. This plastic film 13 can be used as Trägermaterιοί and gives the panel 5 a corresponding optics. The width b of the parting line 7 is selected according to the manufacturing method of the parting line 7 and is preferably between 0.1 and 0.8 mm.
    If, instead of a prepreg layer, two or more prepreg layers 6 according to FIG. 4 b are used to construct the panel 5, the parting line 7 becomes correspondingly higher, which has an effect on the response of the decompression unit 1. Thus, by arranging several prepreg layers 6 one above the other, the pressure difference Δρ for triggering the decompression panel can be adjusted accordingly. By arranging a plurality of prepreg plies 6 it is thus ensured that the
    Decompression unit 1 does not trigger at too low pressure differences Δρ.
    FIGS. 5a to 5c show different possible arrangements of a self-contained parting line 7. In the embodiment according to FIG. 5a, the parting line is arranged over three sides of a rectangle, whereby the panel 5 is unfolded in the case of decompression. In the embodiment according to FIG. 5b, three parting lines 7 are arranged in a star shape, whereas in FIG. 5c the parting line 7 is arranged in the form of a circular or elliptical sector. The respective shape of the parting line 7 can be easily adapted to the respective spatial conditions.
    Finally, FIG. 6 shows a view of a decompression unit 1, wherein a protective grid 12 is arranged above the decompression opening 2, which prevents an unintentional separation of the parting line 7 of the panel 5 due to mechanical action. [• • * · · · · mechanische mechanische mechanische mechanische mechanische. • • • • • * * «« • • • • • • • • * • »• * • - 8 The protective grid 12 is preferably also formed by at least one prepreg layer. Alternatively, naturally also embodiments of metal rods or plastic rods are conceivable.
    权利要求:
    Claims (12)
    [1]
    9. Claims 1. A decompression unit (1) for use in a decompression opening (2) of a wall element (3) of an aircraft, comprising a panel (5) which can be fastened in or over the decompression opening (2) via a frame (1) Panel (5) at a predetermined differential pressure (Δρ) for releasing the decompression opening (2) from the frame (4) is movable, characterized in that the panel (5) by at least one cured prepreg layer (6) with at least one cured resin filled parting line (7) is formed as a predetermined breaking point, which parting line (7) breaks when exceeding the predetermined differential pressure (Δρ).
    [2]
    2. decompression unit (1) according to claim 1, characterized in that the parting line ¢ 7) is closed in itself.
    [3]
    3. decompression unit (1) according to claim 1 or 2, characterized in that on at least one side of the at least one prepreg layer (6) a plastic film (13), in particular a Po-lyvinylfluoridfo, lie, is arranged.
    [4]
    4. decompression unit (1) according to one of claims 1 to 3, characterized in that on the, the wall element (3) facing side of the panel (5) a strip (8) made of elastic material, in particular foam, is arranged.
    [5]
    5. decompression unit (1) according to one of claims 1 to 4, characterized in that on the, the wall element (3) facing side of the panel (5) a fire protection strip (9) is arranged from flame-retardant material.
    [6]
    6. decompression unit (1) according to one of claims 1 to 5, characterized in that on the frame (4) elements (10) for connection to the wall element (3) are provided.
    [7]
    7. decompression unit (1) according to claim 6, characterized in that the connecting elements (10) by screws, bolts or the like. Are formed. 10
    [8]
    8. decompression unit (1) according to one of claims 1 to 7, characterized in that the frame (4) is glued to the wall element (3).
    [9]
    9. decompression unit (1) according to one of claims 1 to 8, characterized in that at least one element (1.1) for securing the pressed in case of exceeding the predetermined pressure difference (Δρ) from the decompression opening (2) part of the panel (5) is provided within the parting line (7).
    [10]
    10. decompression unit (1) according to claim 9, characterized in that the securing element (11) is formed by a rope.
    [11]
    11. decompression unit (1) according to one of claims 1 to 10, characterized in that on at least one side of the panel (5) with the frame (4) connectable protective grid (12) is arranged.
    [12]
    12. decompression unit (1) according to one of claims 1 to 11, characterized in that the parting line (7) has a width (b) of 0.1 to 0.8 mm. GH / stl:
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    引用文献:
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