HEAVY-LIFT TURBOJET ROTOR SYSTEM. VOLUME 12. FUEL PUMP AND CONTROL SYSTEM DESIGN

Abstract

The report discusses the proposal of a combination hydromechanical- electronic fuel control and fuel pump for control of a helicopter rotor tip mounted engine (CAE Model 357-1) which during normal operation is subjected to 235g of centrifugal force. The proposed preliminary design is submitted to meet the specification requirement of the engine in the tip turbojet hover mode of operation. Analytical design studies and preliminary test results show feasibility of this design for operation in a 235g field.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0624822

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Sensors

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Airframes
  • Brushless Dc Motors
  • Centrifugal Force
  • Closed Loop Systems
  • Control Systems
  • Fuel Pumps
  • Fuel Systems
  • Gas Turbines
  • Generators
  • Heat Transfer
  • Jet Engines
  • Measurement
  • Transducers
  • Turbines
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems