Aircraft with a transparent wall fixed to a structure via a shock protection system
An aircraft provided with a transparent wall interposed between an internal environment located in the aircraft and an external environment, the transparent wall being fixed to a supporting structure of the aircraft by a fixing system, the transparent wall having an internal face facing the internal environment and an external face facing the external environment. The fixing system comprises at least one martyr energy-absorbing pad, the energy-absorbing pad comprising at least one energy absorber connected to the transparent wall and to the supporting structure, the at least one energy absorber comprising an internal absorber attached against the internal face.
1 . An aircraft provided with a transparent wall interposed between an internal environment situated in the aircraft and an external environment, the transparent wall being fixed to a supporting structure of the aircraft by a fixing system, the transparent wall having an internal face facing the internal environment and an external face facing the external environment,
wherein the fixing system comprises at least one martyr energy-absorbing pad configured to deform according to an irreversible plastic deformation, the energy-absorbing pad comprising at least one energy absorber secured to the transparent wall and to the supporting structure, the at least one energy absorber comprising an internal absorber mechanically connected at least to the internal face;
wherein the at least one energy absorber comprises an external absorber mechanically connected to at least the external face and fixed to the supporting structure or to an external support fixed to the supporting structure.
2 . The aircraft according to claim 1 ,
wherein the internal absorber is fixed to the supporting structure or to an internal support fixed to the supporting structure.
3 . The aircraft according to claim 2 ,
wherein the internal absorber is fixed to the internal support fixed to the supporting structure, and the external absorber is fixed to the external support fixed to the supporting structure, and the aircraft comprises a frame comprising the external support and the internal support.
4 . The aircraft according to claim 1 ,
wherein the internal absorber is fixed to the transparent wall directly or via a bracket.
5 . The aircraft according to claim 1 ,
wherein the internal absorber and the external absorber of a same energy-absorbing pad are symmetrical with respect to the transparent wall.
6 . The aircraft according to claim 1 ,
wherein the at least one energy absorber comprises at least two energy absorbers, and the fixing system comprises the at least two energy absorbers having different stiffnesses along a same axis.
7 . The aircraft according to claim 1 ,
wherein the at least one energy absorber comprises a z-shaped structure provided with two end sections connected by an inner section, one of the end sections being secured to the transparent wall directly or via a bracket, and the other end section being secured to the supporting structure.
8 . The aircraft according to claim 1 ,
wherein the at least one energy absorber comprises a honeycomb structure.
9 . The aircraft according to claim 1 ,
wherein the at least one energy absorber has at least one deformable member in the form of a hollow truncated sphere, the deformable member extending from a circular-arc shaped base to an apex, the base being connected to the transparent wall.
10 . The aircraft according to claim 1 ,
wherein the at least one martyr energy-absorbing pad comprises a single energy-absorbing pad, and the single energy-absorbing pad extends continuously on an edge of the transparent wall.
11 . The aircraft according to claim 1 ,
wherein the at least one martyr energy-absorbing pad comprises a plurality of energy-absorbing pads spaced apart from each other along an edge of the transparent wall.
12 . An aircraft having a support structure and a transparent wall, the transparent wall disposed between an internal environment in the aircraft and an external environment, the transparent wall fixed to the support structure of the aircraft by a fixing system, the transparent wall having an internal face facing the internal environment and an external face facing the external environment,
wherein the fixing system comprises an energy-absorbing pad configured to deform according to an irreversible plastic deformation, the energy-absorbing pad comprising an energy absorber secured to the transparent wall and to the support structure, the energy absorber comprising an internal absorber mechanically connected to the internal face;
wherein the energy absorber comprises an external absorber mechanically connected to the external face and fixed to the support structure or to an external support fixed to the support structure.
13 . The aircraft according to claim 12 ,
wherein the internal absorber is fixed to the supporting structure or to an internal support fixed to the supporting structure.
14 . The aircraft according to claim 13 ,
wherein the external absorber is fixed to the external support fixed to the supporting structure, and the internal absorber is fixed to the internal support, and the aircraft comprises a frame comprising the external support and the internal support.
15 . The aircraft according to claim 12 ,
wherein the internal absorber is fixed to the transparent wall directly or via a bracket.
16 . The aircraft according to claim 12 ,
wherein the internal absorber and the external absorber of a same energy-absorbing pad are symmetrical with respect to the transparent wall.
17 . The aircraft according to claim 12 ,
wherein the energy absorber comprises two energy absorbers, and the fixing system comprises the two energy absorbers having different stiffnesses along a same axis.
18 . The aircraft according to claim 12 ,
wherein the energy absorber comprises a z-shaped structure provided with two end sections connected by an inner section, one of the end sections secured to the transparent wall directly or via a bracket, and the other end section secured to the supporting structure.
19 . The aircraft according to claim 12 ,
wherein the energy-absorbing pad comprises a plurality of energy-absorbing pads spaced apart from each other along an edge of the transparent wall.
20 . An aircraft having a support structure and a transparent wall, the transparent wall disposed between an internal environment in the aircraft and an external environment, the transparent wall fixed to the support structure of the aircraft, the transparent wall having an internal face facing the internal environment and an external face facing the external environment,
a single energy-absorbing pad secured to the transparent wall and to the support structure, the energy-absorbing pad configured to deform according to an irreversible plastic deformation, the energy-absorbing pad comprising an internal absorber mechanically connected to the internal face and an external absorber connected to the external face and fixed to the support structure, the internal absorber and the external absorber form respective portions of the single energy-absorbing pad.