JUH-1H Pneumatic Boot Deicing System Flight Test Evaluation

Abstract

The concept of operation of the Pneumatic Boot Deicing System as a deice system is feasible under the conditions tested when installed on the test UH-1H helicopter. A cooperative effort between NASA and the B.F. Goodrich Company led to the development of a prototype pneumatic boot deicing system designed for use on a helicopter main rotor system. Flight tests were conducted to establish an operational envelope and evaluate the feasibility of the pneumatic deicing concept. Phase I consisted of a ground and inflight structural loads survey which established an operational envelope. Phase II was a limited aircraft performance and handling qualities evaluation, and Phase III involved artificial icing tests. Thirteen problem areas were identified with the prototype Pneumatic Boot Deicing System installation, two of which were corrected during the evaluation. Major problem areas included excessive increases in power required for flight and deicer material erosion and breakdown.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1983
Accession Number
ADA140986

Entities

People

  • Loran A. Haworth
  • Ralph Woratschek
  • Randall G. Oliver

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Air Pressure
  • Aircrafts
  • Army Aviation
  • Control Systems
  • Engineering
  • Failure Mode And Effect Analysis
  • Fixed Wing Aircraft
  • Flight Testing
  • Gages
  • Measurement
  • Performance Tests
  • Plastic Explosives
  • Regulators
  • Strain Gages
  • Test And Evaluation
  • Test Methods
  • Time Intervals

Readers

  • Aerospace Engineering