Stress Analysis of 27% Scale Model of AH-64 Main Rotor Hub.
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 Langley's 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 lead/lag 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 lead/lag 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1985
- Accession Number
- ADA164284
Entities
People
- Robert V. Hodges
Organizations
- National Aeronautics and Space Administration