Accession Number:

ADA339188

Title:

Piloted Simulation of an F-16 Flight Control System Designed Using Quantitative Feedback Theory

Descriptive Note:

Final rept. Feb 96-Sep 97

Corporate Author:

VEDA INC DAYTON OH

Personal Author(s):

Report Date:

1997-09-01

Pagination or Media Count:

99.0

Abstract:

The purpose of this report is to determine the applicability of the Quantitative Feedback Theory QFT approach to designing the control laws for a modern military flight control system. This report documents a portion of the QFT research program, specifically, the implementation of a QFT design on a manned simulation of the NF-16D Variable Stability Inflight Simulator Test Aircraft VISTA F-16. The control law design addresses the subsonic flight envelope of the VISTA F-16 including changes in aircraft configuration. The design was accomplished as a SISO longitudinal loop and a MIMO lateral loop, and incorporates pilot handling qualities within the specifications. Imbedding handling qualities in the system through prudent choice of control variable ensured that the performance specifications were met. Flexibility in the prefilter design allowed the closed loop response to be shaped for proper feel. The handling qualities were evaluated in a high fidelity, manned simulation of the system. The QFT design provided level 1 handling qualities per the specifications in the pitch channel. It did not provide level 1 handling qualities in the lateral channel, but the design requires minor modification to meet level 1.

Subject Categories:

  • Attack and Fighter Aircraft
  • Flight Control and Instrumentation

Distribution Statement:

APPROVED FOR PUBLIC RELEASE