Abstract: An energy absorbing structure for attenuating energy received from an energy source. The structure comprises a deformable structure formed by an ensemble of one or more first layers of a material having a positive Poisson's ratio, one or more second layers of a material having a negative Poisson's ratio and one or more third layers of an elastomeric material placed between a first layer and a second layer. The ensemble is arranged with the one or more third layers joined to the first and second layers for absorbing at least part of the energy through shear forces or a combination of traction and compression forces applied to the ensemble by the first and second layers as a consequence of their differential deformation after receiving the energy.

Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.

Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.

Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.

Abstract: An energy absorbing structure for attenuating energy received from an energy source. The structure comprises a deformable structure formed by an ensemble of one or more first layers of a material having a positive Poisson's ratio, one or more second layers of a material having a negative Poisson's ratio and one or more third layers of an elastomeric material placed between a first layer and a second layer. The ensemble is arranged with the one or more third layers joined to the first and second layers for absorbing at least part of the energy through shear forces or a combination of traction and compression forces applied to the ensemble by the first and second layers as a consequence of their differential deformation after receiving the energy.

Abstract: A deformable structure, such as a panel or a shock absorber, for absorbing energy from a mechanical and/or acoustic impact. The structure comprises an inner core and one or more external layers covering the inner core. The inner core comprises a set of first segments having a positive Poison's ratio and second segments having a negative Poisson's ratio. The first and second segments are arranged alternately and joined to one another so that the deformation received by one first segment is transmitted to an adjacent second segment and vice versa.

Abstract: A panel structure for an aircraft with at least one composite layer, and at least one net-shaped layer attached to the composite layer, wherein the net-shaped layer has a material suitable to improve the impact resistance of the panel structure. The net-shaped layer can be used to attach two composite layers. Alternatively, the net-shaped layer can be attached to a surface of one composite layer. In this last case, the net-shaped layer may be joined to a laminate sheet material and filled with a foam material. An impact reinforced panel structure is disclosed capable of withstanding any impact, such as a blade release, or a bird strike, without substantially modifying the manufacturing process.

Abstract: A deformable structure, such as a panel or a shock absorber, for absorbing energy from a mechanical and/or acoustic impact. The structure comprises an inner core and one or more external layers covering the inner core. The inner core comprises a set of first segments having a positive Poison's ratio and second segments having a negative Poisson's ratio. The first and second segments are arranged alternately and joined to one another so that the deformation received by one first segment is transmitted to an adjacent second segment and vice versa.

Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.

Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.

Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.