Structurally tunable cores are described that can be implemented, for example, in aircraft components. An example flex beam for coupling a rotor blade to a rotor hub includes a first composite laminate, a second composite laminate, a third composite laminate, first resilient core members and second resilient core members. The first composite laminate forms a first skin of the flex beam. The second composite laminate is located opposite the first composite laminate and forms a second skin of the flex beam. The third composite laminate is located between the first composite laminate and the second composite laminate. The first resilient core members extend between the first composite laminate and the third composite laminate. The second resilient core members extend between the second composite laminate and the third composite laminate.
FLEX BEAM COMPRISING STRUCTURALLY TUNABLE CORES
FLEXIBLER TRÄGER MIT STRUKTURELL ABSTIMMBAREN KERNEN
PLAQUE DE FLEXION COMPRENANT NOYAUX STRUCTURELLEMENT ACCORDABLES
2022-06-22
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |