Accession Number : ADA320319

Title :   Lateral-Directional, Full Envelope Control Law Design for F-16 with Thrust Vectoring,

Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH

Personal Author(s) : Reigelsperger, William C. ; Hammett, Kelly D. ; Banda, Siva S.

PDF Url : ADA320319

Report Date : 1994

Pagination or Media Count : 12

Abstract : A manual flight control system for the lateral directional dynamics of a modern fighter aircraft incorporating thrust vectoring is presented. Design goals are posed in terms of maintaining acceptable flying qualities during high alpha maneuvering while also achieving robustness to model parameter variations and unmodeled dynamics over the entire flight envelope. The need for gain scheduling is eliminated by using an inner loop dynamic inversion/outer loop structured singular value (u) - synthesis control structure which separately addresses operating envelope variations and robustness concerns, respectively. Performance objectives are based on commanding sideslip angle and stability axis roll rate. Realistic representations of both structured (real parametric) and unstructured uncertainty are included in the design/analysis process. A flight condition dependent control selector maps generalized controls to physical control deflections, considering actuator redundancy, effectiveness, and saturation issues. An angle of attack dependent command prefilter shapes commands to produce desired responses. Structured singular value analysis, low-order equivalent system (LOES) fits, and linear step responses demonstrate satisfaction of design goals. Simulation shows excellent control at both low and high angles of attack without gain scheduling.

Descriptors :   *JET FIGHTERS, *THRUST VECTOR CONTROL SYSTEMS, MANEUVERABILITY, AERODYNAMIC STABILITY, DYNAMIC RESPONSE, ANGLE OF ATTACK, SIDESLIP, SYSTEMS ANALYSIS, FLIGHT ENVELOPE, CONTROL THEORY, FLIGHT MANEUVERS, FLIGHT SIMULATION, AIRCRAFT DESIGN.

Subject Categories : Attack and Fighter Aircraft
      Flight Control and Instrumentation
      Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE