COMPONENT TESTING XV-9A HOT CYCLE RESEARCH AIRCRAFT

Abstract

The component tests included fatigue tests of the blade root-end and constant section areas, hub gimbal system, spar-to-segment and root-fitting-to- spar attachments, and material evaluation tests of the blade spars. Sealing tests were conducted on the joint between the Y-duct and tri-duct in the hub area, the joint area between the gas generator and diverter valve, and the fixed-duct joint on the rotor blade. Blade natural frequency tests were conducted to ensure that the natural frequencies of the rotor blade would not be in a critical frequency range. The instrumented flight blade was calibrated in a test fixture before the flight test program.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1965
Accession Number
AD0627361

Entities

People

  • G. D. Deveaux

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Fatigue Life
  • Fatigue Tests (Mechanics)
  • Governments
  • Heat Transfer
  • Materials
  • Measurement
  • Pressure Gages
  • Research Aircraft
  • Resonant Frequency
  • Static Tests
  • Strain Gages
  • Tensile Properties
  • Tensile Strength
  • Test And Evaluation
  • Test Fixtures

Readers

  • Aerospace Engineering