公开(公告)号：US3858831A

公开(公告)日：1975-01-07

申请号：US42823573

申请日：1973-12-26

Applicant: TEXTRON INC

Inventor： HALWES DENNIS R

IPC: B64C27/00 ,  B64C27/04

CPC classification number: B64C27/001 ,  B64C2027/002 ,  B64C2027/005

Abstract: A helicopter having a lift unit including a multiblade helicopter main rotor system and a nodalized module including a beam driven in response to blade developed vertical forces has a fuselage unit connected to the beam only at vibration nodal points along the beam. The coupling between the lift unit and the fuselage comprises two rigid arms which form the beam and which extend toward one another from the nodal points. A multilayered flexible beam section interconnects the arms to accommodate beam bending in the flexible section. A rigid member is attached to each of the arms at drive points intermediate the nodal points in supporting relation from the lift unit.

Abstract translation: 具有升降机单元的直升机包括多叶直升机主转子系统和包括响应于叶片展开的垂直力驱动的梁的节点模块，具有仅沿着梁的振动节点连接到梁的机身单元。 提升单元和机身之间的联接包括形成梁的两个刚性臂，并且从节点相对延伸。 多层柔性梁部分互连臂以适应柔性部分中的梁弯曲。 刚性构件在与升降单元的支撑关系中的节点之间的驱动点附接到每个臂。