270 Volt DC Variable Speed Generator and Control Unit, Aircraft Electrical Power System.

Abstract

This task included the setup, instrumentation, testing and data compilation for a single generator 270 volt DC (direct current) aircraft electric power system. The generator system was interconnected, instrumentation was completed, and operational tests were conducted. Several deficiencies were observed: (a) The generator coolant reservoir was too small to contain the coolant expansion at operating temperatures. This caused coolant loss through the reservoir relief valve. An external expansion tank was added to correct this problem. (b) A water cooled heat exchanger did not provide controllable generator coolant temperature. An air cooled exchanger was substituted in the test setup with improved results. (c) The generator drive stand speed was limited to 10,500 RPM (revolutions per minute). Repair and adjustment of drive electronics was required to obtain speeds over the range 9,000 to 18,000 RPM.

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Document Details

Document Type
Technical Report
Publication Date
Sep 18, 1980
Accession Number
ADA358709

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Air Cooled
  • Aircrafts
  • Carbon Dioxide
  • Classification
  • Control Panels
  • Electric Power
  • Flash Point
  • Generators
  • Heat Exchangers
  • Instrumentation
  • Military Aircraft
  • Security
  • Test And Evaluation
  • Voltage Regulation
  • Water Flow
  • Wiring Diagrams

Readers

  • Aerospace Test and Evaluation
  • Combustion and Flow Dynamics.
  • Electrical Engineering

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems