Accession Number : ADA313337

Title :   Development of a System for Improved Helicopter Blade Tracking - Phase 2.

Descriptive Note : Final rept. Sep 92-Mar 95,

Corporate Author : RENSSELAER POLYTECHNIC INST TROY NY

Personal Author(s) : Bielawa, Richard L. ; Frederickson, Kirk

PDF Url : ADA313337

Report Date : 30 JUN 1995

Pagination or Media Count : 78

Abstract : This report presents the results of a demonstration of an experimental method of determining the flapping moment of inertia of a helicopter rotor blade. The purpose of the work was to validate an approach to measure a parameter which is thought to be a measure of manufacturing quality which relates directly to the blades ability to be flown with minimum vibration without extensive (and costly) adjustment. The accuracy of the method was demonstrated first for a simple prismatic bar. Measurements were then made on UH-60 Black Hawks' recently manufactured blades and a blade with a small mass added. The calculated and empirically estimated flapping moments of inertia for the prismatic bar were in excellent agreement. Calculated and experimentally determined flapping moments of inertia for the UH-6O Black Hawk blades were in satisfactory agreement. The experimental method was shown to be both precise and repeatable. The results presented in the report will serve as the basis for establishing a more production-oriented quality test procedure which could be used for new or repaired main rotor blades to reduce the number of tracking flights required to obtain satisfactory vibration characteristics.

Descriptors :   *HELICOPTER ROTORS, *ROTOR BLADES(ROTARY WINGS), *MOMENT OF INERTIA, ALGORITHMS, ATTACK HELICOPTERS, FLIGHT TESTING, VIBRATION, EQUATIONS OF MOTION, COMPUTER AIDED DESIGN, STATIC LOADS, AERODYNAMIC LOADING, QUALITY CONTROL, DATA ACQUISITION, FLAPS(CONTROL SURFACES), COMPUTER AIDED MANUFACTURING, DESIGN CRITERIA, HOVERING, PRISMATIC BODIES.

Subject Categories : Helicopters

Distribution Statement : APPROVED FOR PUBLIC RELEASE