Stability Characteristics of a Combat Aircraft with Control Surface Failure
Abstract
In this thesis, an investigation of the stability characteristics of an aircraft which has sustained damage to a primary control surface was performed. The analysis was performed using wind tunnel data taken on an F-16 model in a test. The coupled, non-linear, aircraft equilibrium equations for constant altitude, rectilinear flight were derived. The aircraft stability and control derivatives were developed and analyzed to identify aerodynamic coupling with implications for an aircraft with failed control surface(s). Three control schemes which allow for progressively greater independence among the control surfaces were formulated for use in the evaluation of an aircraft with an actuator failure of the rudder. The investigations were conducted at two flight conditions representative of the aircraft at cruise and landing approach velocities. Regions in alpha/beta space where equilibrium is obtainable were investigated to identify remaining control authority, drag characteristics, and aircraft orientation. The matrix decomposition techniques of Singular Value Decomposition and the Row Reduced Echelon Form of the augmented matrix were used to provide additional insight into the interrelationship of the control surfaces at different points within the defined trim region. (aw)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1989
- Accession Number
- ADA216196
Entities
People
- Stephen M. Zaiser
Organizations
- Air Force Institute of Technology