COMPONENT TESTING XV-9A HOT CYCLE RESEARCH AIRCRAFT
Summary rept. 29 Sep 1962-15 Mar 1965
HUGHES TOOL CO CULVER CITY CA AIRCRAFT DIV
Pagination or Media Count:
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.
- Research and Experimental Aircraft