Evaluation of an Airborne Thrust Computing System. Volume I. System Performance Evaluation.

Abstract

An in-flight thrust measurement and display system (TMS) for an afterburning turbojet engine with a continuously variable exhaust nozzle has been developed by Computing Devices Company. A special-purpose digital computer calculates engine gross thrust using aerothermodynamic equations requiring ambient static pressure, and three engine tailpipe pressures as inputs. A reference gross thrust is also calculated for a nominal or average engine operating at military power under the prevailing ambient conditions. The display system provides updates of gross thrust and the percentage of the reference gross thrust at the rate of two per second. Flight-rated digital data recording equipment is interfaced with the system to provide a consistency check of the flight data. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1975
Accession Number
ADA040092

Entities

People

  • J. Allan Gravelle

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Human Systems
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Aircrafts
  • Airframes
  • Computing Devices
  • Data Acquisition
  • Data Processing
  • Exhaust Gases
  • Measurement
  • Performance Tests
  • Static Tests
  • Tape Recorders
  • Test And Evaluation
  • Test Equipment
  • Turbines
  • Turbofan Engines
  • Turbojet Engines

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Aerospace Test and Evaluation
  • Computational Modeling and Simulation