STUDIES RELATIVE TO THE DEVELOPMENT OF A ONE-MAN HELICOPTER. PART 1

Abstract

Feasibility studies were made of a portable, one-man helicopter. The requirements were (1) a maximum 100-1b stripped empty weight, (2) a maximum of 10 1/9 nautical miles without reserves, and (3) a cruising speed of 45 knots. The stripped empty weight included allowances for stabilization and for a ground support strut but did not include fuel tanks. The total weight of the pilot and equipment was assumed to be 225 lb. Only machines powered by either tip-mounted rockets or a ramjet appeared to meet the requirements. A study based on possible extreme reductions in air-frame weight indicated weights of the order of 60 lbs. With portability requirements eliminated, the choice of configuration appeared to depend on the operational flexibility geared drives against the relative mechanical simplicity of tip drives. The results of the investigation are presented in the form of charts of maximum range is vs empty weight and design gross weight.

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Document Details

Document Type
Technical Report
Publication Date
Sep 30, 1953
Accession Number
AD0021342

Entities

People

  • Kenneth Mann

Organizations

  • Hughes Aircraft Company

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Communication Equipment
  • Contracts
  • Fuel Consumption
  • Fuel Tanks
  • Gas Turbines
  • Ground Support
  • Helicopters
  • Landing Gear
  • Mach Number
  • Propulsion Systems
  • Rotary Wing Aircraft
  • Security
  • Tail Rotors

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Systems Analysis and Design