Michael Piasecki

US Patent:

60657189, May 23, 2000

Filed:

Mar 23, 1998

Appl. No.:

9/045991

Inventors:

Michael W. Piasecki - Haverford PA

International Classification:

B64C 2704

US Classification:

244 1711

Abstract:

A universal power drive and lifting rotor system module adaptable for powering various types of single and multiple rotor VTOL aircraft comprising an elongated component support framework on the top of which a lifting rotor assembly and transmission are mounted onto the front end of which an engine is externally supported and the rear end of which is adapted for attachment and external support of a VTOL augmentation framework carrying a lifting rotor torque compensating unit. The rotor assembly and transmission receive power from a power train comprising a main drive shaft coupled to the engine and supported for rotation within the component support framework to extend longitudinally thereof and connected through a pulley and belt rotational power arrangement to the rotor transmission power input shaft extending from within the transmission to above the rear end of the component support framework. The outer free ends of the main power and transmission power input shafts have a coupling attachable to a rotatable shaft powering a rotor torque compensating unit carried on any one of a variety of VTOL augmentation auxiliary framework assemblies configured to be attachable to the rear end of the module component support framework. The attachable auxiliary framework assemblies include a framework on which is mounted a vertically rotating torque compensating tail rotor, a wing attached compound VTOL augmentation framework having a ducted propeller ahead of a slip stream deflecting tail assembly and a framework connecting a pair of back-to-back oriented modules comprising a dual rotor tandem VTOL.

US Patent:

20170297687, Oct 19, 2017

Filed:

Sep 28, 2016

Appl. No.:

15/278636

Inventors:

- Essington PA, US
Michael W. Piasecki - Haverford PA, US

International Classification:

B64C 27/08
B64C 1/06
B64C 1/00

Abstract:

A tandem rigid rotor system has a first rigid rotor system and a second rigid rotor system connected by a fuselage. The fuselage has at least one framing member connected between the first rigid rotor system and the second rigid rotor system, such that the framing member is torsionally flexible for controlling yaw of the tandem rigid rotor system. In certain embodiments, multiple framing members are connected between the first rigid rotor system and the second rigid rotor system in parallel. In certain embodiments, the torsional flexibility allows up to 20 degrees of movement away from the lateral axis. In certain embodiments, framing members are vertically and laterally rigid.