| 摘要 |
A gas turbine engine mount (50) for an aircraft wing including a link body (200) having a first joint (210; 510), a second joint (220; 520) and a linking structure (230; 530) connecting the first joint (210; 510) to the second joint (220; 520). The linking structure (230; 530) includes at least a flexing portion (234; 534) and an elastic portion. The flexing portion (234; 534) is configured to flex during a load outside of an expected load window. |
