ENGINEERING FLIGHT TEST OF THE CH-47 (CHINOOK) HELICOPTER INTEGRAL WEIGHT AND BALANCE SYSTEMS (ENSURE)

Abstract

An engineering research evaluation of two proposed integral weight and balance systems for the CH-47 Chinook Helicopter was conducted to determine the feasibility of such systems. The primary function of the systems is to accurately predict the aircraft gross weight and center of gravity location along with cargo hook load. The evaluation of these systems was conducted at Edwards Air Force Base, California, by the US Army Aviation Test Activity. The systems were tested throughout the entire envelope of allowable gross weight and center of gravity for the CH-47A aircraft. The testing consisted of determining the effects of rotor rpm, terrain, wind and control position, for various loading configurations, upon the indicated values of gross weight and center of gravity for the STAN and STOW weight and balance systems. Also, evaluated were the problems of installation and calibration of the systems, repeatability, reliability, and compatibility with other systems. Both systems performed reasonably well with the helicopter in a static mode (rotors not turning).

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1968
Accession Number
AD0832821

Entities

People

  • Allyn E. Higgins
  • Harold C. Catey
  • Robert F. Forsyth
  • Samuel R. Schwartz

Organizations

  • Edwards Air Force Base

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Air Force Facilities
  • Aircrafts
  • Army Aviation
  • Calibration
  • California
  • Center Of Gravity
  • Deficiencies
  • Department Of Defense
  • Engineering
  • Environment
  • Governments
  • Gravity
  • Measurement
  • Reliability
  • Test And Evaluation

Readers

  • Aerospace Test and Evaluation
  • Logistics and Supply Chain Management.