X-22A TRI-SERVICE V/STOL RESEARCH AIRCRAFT

Abstract

The Propulsion System Test Stand operated 6.3 hours. Installations of the reworked shafts, couplings, viscous mounts, and Beta control were completed. The stand was also stiffened to eliminate stand vibration at high engine speeds. Phase II variable pitch operation was initiated. Using the Master Control and Beta System, the propeller speed control was checked satisfactorily. The Flight Control-Hydraulic System Test Stand was completed and checked, less the duct rotation system installation. The Feel System overdrive and Elevon instability were investigated. The Test Stand was used, excluding these trouble areas, to perform development testing. In the shop, aircraft No. 1 progressed with Wing and Fin permanent installations. Systems fabrication and installation moved satisfactorily. Fuselage No. 2 was removed from the basic fixture into aircraft No. 2 final assembly. After cleanup, systems installations were started. Fuselage No. 3 for static test was begun. Major components for aircraft No. 1 are essentially completed. Components for No. 2 are in final phases and No. 3 for static test are progressing.

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Document Details

Document Type
Technical Report
Publication Date
Jan 15, 1965
Accession Number
AD0463577

Entities

Organizations

  • Bell Aircraft Corporation

Tags

Communities of Interest

  • Air Platforms
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Assembly
  • Circuit Boards
  • Control Systems
  • Ejection Seats
  • Engineering
  • Fabrication
  • Free Flight
  • Fuselages
  • Landing Gear
  • Manufacturing
  • Propulsion Systems
  • Static Tests
  • Test And Evaluation
  • Test Stands
  • Wind Tunnels

Readers

  • Aerospace Engineering
  • Software Engineering