Accession Number:

AD0775337

Title:

Development of Optimal Control Modes for Advanced Technology Propulsion Systems

Descriptive Note:

Annual technical rept. 1 Feb 1973-31 Jan 1974

Corporate Author:

UNITED AIRCRAFT RESEARCH LABS EAST HARTFORD CT

Report Date:

1974-03-01

Pagination or Media Count:

63.0

Abstract:

A nonlinear multivariable feedback controller was defined for the idle to military operating regime 9 to 100 percent thrust of the Pratt and Whitney Aircraft F401 variable cycle turbofan engine. The analytical design involved linearizing the F401 engine dynamics about five steady-state operating points between idle and military thrust, applying linear optimal control synthesis methods at each point, and combining the five optimal linear controllers into a single nonlinear controller which has feedback gains that are scheduled with high compressor speed. Variable fan, compressor and exhaust geometries as well as main burner fuel flow are coordinated by the controller to achieve rapid engine dynamic response.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE