A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35° C. to 1,650° C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

The invention concerns an insulating part comprising a sealed casing defining an inner enclosure (7), the part having thermal conductivity of less than 100 mW/m.K, the sealed casing (3) comprising at least one thin metal sheet (30, 31) having a thickness of less than 1 mm and welded peripherally to keep the enclosure under low pressure and/or controlled atmosphere, the weld, which is produced in a chamber under low pressure and/or controlled atmosphere, having a leakage rate of less than 10.sup.−6 Pa.Math.m.sup.3/s, after a first thermal treatment according to the standard RTCA-DO 160-G, section 5, Cat A (from −55° C. to 400° C.) and a second thermal treatment at −196° C. for 1 hour.

The invention concerns an insulating part comprising a sealed casing defining an inner enclosure (7), the part having thermal conductivity of less than 100 mW/m.K, the sealed casing (3) comprising at least one thin metal sheet (30, 31) having a thickness of less than 1 mm and welded peripherally to keep the enclosure under low pressure and/or controlled atmosphere, the weld, which is produced in a chamber under low pressure and/or controlled atmosphere, having a leakage rate of less than 10.sup.−6 Pa.Math.m.sup.3/s, after a first thermal treatment according to the standard RTCA-DO 160-G, section 5, Cat A (from −55° C. to 400° C.) and a second thermal treatment at −196° C. for 1 hour.

A low heat release veneer product for aircraft interior components may include at least one substrate layer, at least one thermally-conductive layer disposed on the at least one substrate layer, at least one veneer layer disposed on the at least one thermally-conductive layer, and at least one coating disposed on the at least one veneer layer. One or more of the at least one substrate layer, the at least one thermally-conductive layer, the at least one veneer layer, or the at least one coating may be compliant with an OSU 65/65 rate of heat release test.

A low heat release veneer product for aircraft interior components may include at least one substrate layer, at least one thermally-conductive layer disposed on the at least one substrate layer, at least one veneer layer disposed on the at least one thermally-conductive layer, and at least one coating disposed on the at least one veneer layer. One or more of the at least one substrate layer, the at least one thermally-conductive layer, the at least one veneer layer, or the at least one coating may be compliant with an OSU 65/65 rate of heat release test.