DE2058440C3 - Device for covering a fuselage gap in aircraft - Google Patents

Description

The invention relates to a device for covering a fuselage gap in aircraft to accommodate a wing that can be pivoted into the fuselage, which one at the top and one at the bottom of the fuselage gap, made of flexible, has air-impermeable material existing, resiliently receding sealing body.

Such a device is known from DT-OS 531 357. With this facility they are respectively clamped at the edge of the fuselage gap, made of flexible, air-impermeable material and resiliently receding seal body by a number of wedge-shaped inflatable bladders formed inside the opening with their apices pointing into the interior of the fuselage and their parallel sides are mounted substantially vertically in order to fill the closure opening in the inflated state and to match with their outsides with the aircraft fuselage contours. The inside of the bellows is on lines connected via pressure reducing valves and a check valve to a pressure source and via a another check valve are in contact with the atmosphere. This well-known facility has the operational disadvantage that the inflatable bellows their Lose functionality if they are either caused by external influences, e.g. B. by bombardment damaged so that the blown air can escape, 5 or if the compressed air source is damaged, so that compressed air supply is no longer possible.

The invention is based on the object of providing a device for covering the fuselage gap in aircraft of the type mentioned to realize the un-

is dependent on the compressed air supply and which, moreover, has a simpler structure than the known device This problem is solved in that each Dichtungskörpeir consists of an apron with resilient inserts consists, which by means of tension straps fastened in the interior of the fuselage against pivoting out of the fuselage contour being held out. Such aprons are light, cheap and almost completely maintenance-free. The airtight Material is the actual seal, while the resilient inserts of the aprons are theirs Ve-lend shape and rigidity, so that in every pivot position of the wing they have a continuation of the fuselage contour Effect closure of the trunk gap.

According to a feature of the invention it is provided that the resilient inserts from individual, clamped from to the free edge extending, juxtaposed spring strips exist. Around For example, being able to determine the rigidity curve of the aprons over their area are different Forms of the spring strips provided. In one embodiment of the invention, the spring strips are when the aprons are folded, they are convexly arched. This form, which is already used, for example, for measuring tapes is known, gives the skirts great rigidity against outward bending while they are the inward curvature is hardly hindered.

According to the invention, simpler embodiments are characterized in that, for example, the width or the thickness of the spring bands decreases towards the free edge of the apron.

Another embodiment of the invention provides that the resilient inserts from per se known, consist of flattened spiral springs.

SiIi con rubber is preferably proposed as the material of the aprons, the resilient inserts being arranged between two layers of fabric within the aprons.

Several embodiments of the invention are shown in the drawing and described in more detail below. He is drawing

F i g. 1 section of an aircraft fuselage with a fixed inner wing and one around a Vertical axis pivoting outer wing,

F i g. FIG. 2 shows, in an enlarged illustration, a section through the fuselage in the region of the fuselage gap according to FIG the line H-II in Fi g. 1,

F i g. 3 shows a representation according to FIG. 2 with a wing partially pivoted into the fuselage gap,

F i g. 4 shows a representation according to FIG. 3 with the sash fully swiveled in,

F i g. 5 shows a plan view of an apron according to arrow V in FIG. 2,

F i g. 6 different spring inserts,
F i g. 7 a section through an apron.

F i g. 1 shows an aircraft fuselage 1 on which a fixed inner wing 2 is arranged. This inner wing contains the pivot bearing 3 for mounting the pivotable outer wing 4. When the outer wing

, from a pivoted position to a pivoted back position Position is moved, part of the wing penetrates the fuselage, where it is supported by a Body pocket 5 is added. This fuselage pocket forms a fuselage gap in the fuselage outer wall 6. which depending on the position of the outer wing is more or less filled by this. The remaining one The cross-section that is not filled in is indicated by the in the other !. Figures depicted aprons covered.

F i g. 2 shows a cross section through the fuselage 1 in the area of the fuselage gap 7, which opens the interior of the fuselage pocket 5 for the penetrating wing. Diesel hull pack is sacked by two aprons 8, 9 clamped at the upper and lower edge respectively. These aprons overlap with their free, seal off ends _s something to the fuselage gap. Se fuselage aprons are made of an elastic, impermeable material, for example silicone rubber. This materia! ensures that it slides well on the surface of the swiveled-in wing and that it is hardly carried along by the movement of the wing. Spring strips 10 are arranged in the interior of the aprons, which give the aprons shape and support. So that the aprons cannot fold ϊϊ of the fuselage contour outwards, 5 they are secured by fastening straps 11 guided into the interior of the fuselage pockets 5. Each of the aprons has one

Moi, B "wi" _k e! . .2 ".. (Min * si whose üb" Sch. "-.. Are bent dius, such as F i g 3 shows ^d In the final phase of Einschwenkvorganges' ^{e Scnu 'ze"'} "completely in the interior of the Humpies_ geic app (Fig. 4). Whereby the drawstrings 11 can fold. In ^ / [fJ '^ layers of drawstrings shown.ellL Es j

Depending on the requirements, more or fewer layers can be provided. ",. _R.

F i g. 5 shows a plan view of the apron in the direction of the arrow ν inr ig., It can be seen that each layer of tension springs J ^ reren, in the direction of the width of the_Sc «» rM other arranged ^^ J ^ S, for example with the ^mate . ⁿ . odor through volcano »« «. verbund «an exemplary embodiment for a« «. The insert consists of ral springs 12, which z. B. from which are already known and ⁵ « ^π ? _ς ^η ™ ^β

Other . ^Α . ^ ™ Γ ^ ^Β ^ ^Ρ _in before spring straps 13 before jelcnejn

Apron . ^tonv «f ^^ äerMndedn gg exercise w.rd reach ^ jJ Je Federban

opposite to the folding direction a ver, _e j _chze i-

Ben resistance, "tzer, and that""gtach tg bend in the desired direction on a radius.
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the bend

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losphere. By a certain, later to be »γ ic ■. ₆ .. ^. _ß .,

~~ ■ "■ ■ · - · - · -j-- <" -.:—ι -,., »„ „», Tp 7vuiRrhen two layers of tissue t'5 emge

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the wing with a relatively small bending angle 40 of the aprons 8 is stored.

In addition 5 sheets of drawings

Claims (7)

Patent claims: 1. Device for covering a ring fuselage gap in aircraft to accommodate one in the fuselage pivotable wing, each one at the top and one at the bottom of the fuselage gap clamped, made of flexible, air-impermeable material, resiliently receding Having sealing body, characterized in that each sealing body consists of an apron (8, 9) with resilient inserts, which is fastened by the inside of the fuselage Tension straps (11) is held against pivoting out of the fuselage contour. 2. Device according to claim 1, characterized in that the resilient inserts consist of individual, from the clamped to the free edge extending, juxtaposed spring strips (10,13,14,15) exist. 3. Device according to claims 1 and 2, characterized in that the spring strips (13, 14) in the folding direction of the aprons (8, 9) are convexly curved. 4. Device according to claims 1 and 2, characterized in that the width of the spring strips (14) to the free edge of the apron (8, 9) decreases. 5. Device according to claims 1 and 2, characterized in that the thickness of the spring strips (15) to the free edge of the apron (8, 9) decreases. 6. Device according to claim 1, characterized in that the resilient inserts from known per se, consist of flattened spiral springs (12). 7. Device according to dun claims 1 to 6, characterized in that the aprons (8, 9) from There are silicone rubber and that the resilient inserts (17) between two layers of fabric (16) are arranged within the aprons.