United Technologies Corporation

Robert Zincone

Evan A Fradenburgh

Carl M Ferrar

Charles V Galli

Optical fibers are used for monitoring the structural integrity of space based or aircraft structures where prompt notification of damage is required to effect rapid repair and thereby maintain safety and operational reliability. A plurality of optical fibers are disposed in an X-Y relationship, with the fibers optimally placed in a pattern comprised of multiple path reversals which provides extensive area coverage with a minimum of fibers thus defining multiple zones wherein damage within a zone is determined by interruption of the light through the damaged fibers.

High density fiber optic damage detection system

Air turbulence ahead of an aircraft is determined by scanning the beam of a variable focal distance laser airspeed unit close-in to the aircraft to determine aircraft airspeed and angle of attack, and scanning the beam at distances farther out from the aircraft and measuring airspeed. Discrepancies between the close-in measurement and the farther out measurement are quantifiably indicative of air turbulence.

Gust detection system

Orientation and/or position of a first body, such as the inboard end 42 of a helicopter blade 21, with respect to a second body, such as a rotor hub arm 36, is sensed by determining the position of the images 93, 95-97, of light from sources 80, 81 passed through slits 89, 90 on detector arrays 91, 92. Signal processing means (FIG. 5, FIG. 11) provide signals indicative of such image positions, which can be used to determine, from simple trigonometry, the orientation and/or position of the first body.

Optical position and orientation sensing systems

A helicopter rotor blade of composite material, characterized by the absence of a spanwise metal spar, has tip weight attachment means for supporting stacks of washer-like metal shim weights in the composite material of the blade adjacent its tip to obtain both dynamic chordwise and static spanwise balance of the blade. Three holes are bored in the composite material from the underside of the blade into which three tip weight assemblies are inserted and are adhesively or otherwise secured to the composite material. Each assembly includes a cylindrical liner, a central hollow stud and a nut which engages external threads on the stud for holding the weights in stacked configuration. A plate forming a closure for the hole completes the skin of the blade and a screw threaded into the end of the stud secures the plate in place.

Composite tip weight attachment

A helicopter rotor blade having at least one ramp tab of selected span and chord dimensions, weight and shaped to define an outer surface of selected angularity with respect to the blade chord and being selectively positioned along the blade trailing edge and bonded to its upper or lower surface so as to be totally within the blade chord profile and be effective to eliminate or reduce to within acceptable limits blade pitching moment dynamic unbalance.

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Norwalk, CT, United States of America

Robert Zincone