A fuselage impact load distribution structure includes: a front unit configured to be located at a front end with respect to a wing attached to a fuselage; a rear unit configured to be located at a rear end with respect to a wing attached to the fuselage; a support unit configured to be located between the front unit and the rear unit; and a wing unit. The support unit is configured to transmit a load applied to the fuselage when the fuselage falls. The wing unit is configured to be located in and connected to the support unit so as to transmit a load when the fuselage falls. Loads in the length direction of the fuselage pass through the front unit and are distributed to the wing units through the supporting units.
一种机身碰撞载荷分布结构包括:前部单元,被构造成相对于附接到机身的机翼位于前端;后部单元,被构造成相对于附接到机身的机翼位于后端;支撑单元,被构造成位于前部单元和后部单元之间;以及机翼单元。支撑单元被构造成在机身坠落时传递施加到机身的载荷。机翼单元被构造成位于支撑单元中,并连接到支撑单元,以便在机身坠落时传递载荷。机身长度方向上的载荷经过前部单元,并通过支撑单元分布到机翼单元。
Fuselage collision load distribution structure
机身碰撞载荷分布结构
2024-08-02
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |