Accession Number:

AD0684315

Title:

HOT CYCLE ROTOR/WING COMPOSITE RESEARCH AIRCRAFT

Descriptive Note:

Final rept.

Corporate Author:

HUGHES TOOL CO CULVER CITY CA AIRCRAFT DIV

Personal Author(s):

Report Date:

1968-08-01

Pagination or Media Count:

346.0

Abstract:

A preliminary design study of a hot cycle rotorwing composite research aircraft is described. The hot cycle rotorwing uses a single lightweight lifting surface which functions as both a rotor for takeoff and a fixed wing for horizontal flight. The rotarywing is essentially an equilateral delta wing with short feathering blades at the three corners. The rotor is powered by a tip-jet hot cycle drive, and the turbojet exhaust is diverted from the rotor to provide forward propulsion. The hot cycle rotorwing provides the advantages of hovering efficiency, low downwash velocity, and helicopter-like flying qualities for vertical and low-speed flight, in addition to the high- speed capability and cruise efficiency of the jet airplane. Its simplicity and light weight are made possible through the combined use of the all-pneumatic hot cycle drive system and the dual-purpose rotorwing lift system. This eliminates the need for heavy and complex mechanical drive components and anti-torque tail rotor it permits flight as a helicopter and as an airplane without recourse to duplicate lifting systems or to folding, tilting, or retracting of lift systems to effect conversion.

Subject Categories:

  • Helicopters
  • Research and Experimental Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE