A structure (2) for an aircraft (1) comprises transverse walls (3-8) connected to longitudinal walls (9-12); each wall (3-12, 18, 18B) comprises two jackets (19) of composite material disposed on either side of an intermediate arrangement (20); a wall includes a corrugated core (70) presenting corrugations extending along an axis (Z) substantially parallel to the jacket, such that the capacity of the wall to absorb energy in the event of an impact along said axis is increased; a wall includes a zone of weakness (45) encouraging controlled degradation of the wall in the event of such a shock.
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