Nodal beam inertial flexure
AssigneeTextron Inc.
InventorDennis R. Halwes
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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.
Claims7
A structure for carrying a load from a super positioned vibratory support comprising:
- a. at least one nodalized beam supporting said load from nodal points on said beam and comprising two rigid arms extending toward one another from said nodal points with a multilayered flexible beam section interconnecting the confronting ends of said arms, and
- b. two members extending from said support, each of said members being connected, respectively, to one of said arms at a drive point, said drive points being located intermediate said nodal points on said beam.
Dependencies are inferred from the claim text.