Development of a System for Improved Helicopter Blade Tracking - Phase 2.
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 30, 1995
- Accession Number
- ADA313337
Entities
People
- Kirk Frederickson
- Richard L. Bielawa
Organizations
- Rensselaer Polytechnic Institute