초록 ▼

Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symme

Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

대표청구항 ▼

1. An aircraft comprising a propulsion system formed by two engines mounted on each exterior side of a rear fuselage by pylons; the rear fuselage having a curved shape with at least a vertical symmetry plane and a central longitudinal axis, the rear fuselage being made of a composite material, the r

1. An aircraft comprising a propulsion system formed by two engines mounted on each exterior side of a rear fuselage by pylons; the rear fuselage having a curved shape with at least a vertical symmetry plane and a central longitudinal axis, the rear fuselage being made of a composite material, the rear fuselage comprising a skin and a plurality of frames arranged perpendicularly to the longitudinal axis, the rear fuselage being made of a composite material, wherein the rear fuselage comprises an internal shield the vertical symmetry plane in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of the engines in a failure event that would impact on critical elements of the opposite engine, the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments, and the internal shield is formed by a plurality of panels joined to a supporting structure attached to the rear fuselage. 2. The internal shield according to claim 1, wherein the internal shield made of a rigid material or of a deformable material or of a combination of several layers of rigid and/or deformable materials. 3. The internal shield according to claim 2, wherein the rigid material is one of the following: titanium, high performance steel, aluminum, carbon fiber reinforced material, glass fiber reinforced material, ceramic material. 4. The internal shield according to claim 2, wherein the deformable material is one of the following: an aramid dry fabric, a poly-paraphenylene-2 6-benzobisozazole (PBO) dry fabric, ultra-high molecular weight polyethylene fibers (UHMWPE). 5. The aircraft according to claim 1, wherein the two engines are turbofan, turboprop or propfan engines. 6. The aircraft according to claim 1, wherein the internal shield is formed by a unitary piece attached to the rear fuselage. 7. The aircraft according to claim 1, wherein each panel has a constant thickness. 8. The aircraft according to claim 1, wherein the energy absorption capability of the internal shield is comprised between 5-100 kJ. 9. The aircraft according to claim 8, wherein the energy absorption capability of the internal shield is comprised between 5-15 kJ.