Helicopter blade assembly adapted

a technology for helicopter blades and blades, applied in the direction of rotors, marine propulsion, vessel construction, etc., can solve the problem of imposing a maximum forward speed limit on helicopter blades, and achieve the effect of controlling the lift characteristics of swept disks

Inactive Publication Date: 2002-01-24
MORRIS DAVID CURT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

0008] The shape and, therefore, the lift characteristics of the "swept" disk are controlled by governing the camber of the blades as t

Problems solved by technology

Unfortunately, the aerodynamics of rotating blades impose a limit on helicopter maximum forward speed (apart from drag, motive power and other considerations).
Even with the addition of independent propulsion from either a propeller or jet engine, the individual blade flight characteristics present the following problem at high speeds.

Method used

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  • Helicopter blade assembly adapted
  • Helicopter blade assembly adapted
  • Helicopter blade assembly adapted

Examples

Experimental program
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Embodiment Construction

[0035] A preferred embodiment of a rotatable blade assembly 10, according to the present invention is shown in FIGS. 1a-4b. Each of blades 12 has a hinge 14 between a distal end 16 and a proximal end 18. Each proximal end 18 is fixedly mounted to a mast 20. A connector 22 connects each distal end 16 to a collar 24, which is rotatably mounted about a vertically adjustable circular track element 26, which itself is vertically adjustably mounted about horizontally adjustable hollow post structure 28. In greater detail, connector 22 connects radially projecting eyelet 30 of collar 24 with downwardly projecting eyelet 32 of blade 12, so that as blades 12 rotate, collar 24 is pulled about a circular track 34 of track element 26. A pair of rollers 36 help to guide each connector 22. Hollow post structure 28 is horizontally adjustably mounted to a circular plate 38 which forms a portion of the frame of a helicopter.

[0036] A vertically oriented actuator 44, typically hydraulic or electrical,...

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PUM

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Abstract

A helicopter blade assembly for permitting rapid forward flight in a helicopter having separate means for providing a forward impetus is disclosed. The assembly has a set of rotatable blades attached to a substantially vertical mast. These blades slope downward near to their distal ends, thereby creating an inverted disk virtual air foil when the blades are rapidly rotated by the mast. In a preferred embodiment the camber of the blades and, therefore, the shape of the virtual air foil is controllable.

Description

[0001] This application is a continuation of U.S. Patent Application 08 / 730,871 filed Oct. 18, 1996.[0002] The present invention relates to helicopters. More specifically the present invention relates to a helicopter blade assembly.[0003] 1. Background of The Invention[0004] The helicopter, when introduced, was a revolutionary aircraft. With its ability to take off and land vertically, the helicopter was able to accomplish maneuvers that no fixed wing craft could perform. Unfortunately, the aerodynamics of rotating blades impose a limit on helicopter maximum forward speed (apart from drag, motive power and other considerations).[0005] The standard single, tandem or lateral-twin rotor helicopter blades provide lift as well as forward impetus. Even with the addition of independent propulsion from either a propeller or jet engine, the individual blade flight characteristics present the following problem at high speeds. In forward flight, a blade advances into the airstream and then ret...

Claims

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Application Information

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IPC IPC(8): B64C27/46B64C27/72
CPCB64C27/46B64C27/72Y02T50/34Y02T50/30
InventorMORRIS, DAVID CURT
OwnerMORRIS DAVID CURT