Engineering Flight Test, AH-1G (HueyCobra) Helicopter Autorotational Entry Characteristics

Abstract

Engineering flight tests were conducted to quantitatively evaluate the response of the AH-1G HueyCobra helicopter to simulated sudden engine failures at high airspeed and high engine power combinations in two configurations. Additionally, simulated engine failures were investigated at 100 knots calibrated airspeed (KCAS) with the stability and control augmentation system (SCAS) ON and OFF to determine the differences in aircraft response with an inoperative SCAS. Aircraft response to simulated sudden engine failure was characterized by rapid roll attitude changes and rapid main rotor rpm decay rates, both of which were unacceptable at the maximum engine torque settings. The severity of the aircraft response is primarily a function of engine torque at the time of failure. The AH-1G helicopter fails to comply with both the present and proposed military specifications for flying qualities of helicopters with regard to autorotational entry at high-airspeed/high-torque conditions.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1971
Accession Number
AD0887550

Entities

People

  • Brock M. Nicholson
  • Marvin W. Buss

Organizations

  • Edwards Air Force Base

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Actuators
  • Aircraft Equipment
  • Aircrafts
  • Airfoils
  • Airframes
  • Army Aviation
  • Control Systems
  • Control Systems Engineering
  • Engineering
  • Fire Control Systems
  • Instrumentation
  • Night Sights
  • Reaction Time
  • Specifications
  • Standards
  • Tail Rotors
  • Test And Evaluation

Readers

  • Aerospace Engineering