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