Accession Number:

ADA164284

Title:

Stress Analysis of 27% Scale Model of AH-64 Main Rotor Hub.

Descriptive Note:

Technical memo.,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC

Personal Author(s):

Report Date:

1985-10-01

Pagination or Media Count:

49.0

Abstract:

The Aerostructures Directorate ASTD, NASA Langley Research Center, Hampton, VA as part of the continuing basic research in support of the Army helicopters, built a dynamically scaled model of the AH-64 helicopter rotor hub fig. 1. This model rotor system is designed for testing in NASA Langleys 4x7 m low-speed wind tunnel. The model will find continued use in future rotorcraft model testing. Hence, its structural integrity must be assured. This paper documents stress analysis for critical components of the rotor hub. The AH-64 hub is essentially articulated with some rotational stiffness about the leadlag hinge due to the elastomeric dampers and some centrifugally supported torsional stiffness in the strap pack. The critical components include the pitch case, the upper hub plate, the strap pack, and the leadlag hinge pin assembly. The analysis includes both static and fatigue considerations. Stress analysis of an AH-64 27 scale model rotor hub was performed. Component loads and stresses were calculated based upon blade root loads and motions. The static and fatigue analysis indicates positive margins of safety in all components checked. Using the format developed here, the hub can be stress checked for future applications. Keywords stress, model rotor hub.

Subject Categories:

  • Helicopters
  • Manufacturing and Industrial Engineering and Control of Production Systems
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE