Application of Three Aeroservoelastic Stability Analysis Techniques
Abstract
This report describes two types of instabilities encountered by the YF-16 airplane that were caused by a coupling between the active control system and structural dynamics. Three mathematical models of the airplane were evaluated to determine the degree of correlation between analysis and flight tests. These mathematical models are described as: (1) Truncated Mode Analysis Using GVT Modes; (2) Truncated Mode Analysis Using Computed Modes; and (3) Residual Flexibility Method Using Computed Modes. Stability was determined in the frequency domain by employing the Nyquist criteria and the determinant plot. A method is presented for computing indicial functions from oscillatory generalized aerodynamic terms obtained from any linearlized aerodynamic theory. The equations for employing the indicial functions in a root locus stability analysis are presented. Stability was determined by the root locus method for the mathematical model described as the truncated mode analysis using computed modes. The degree of correlation between analysis and flight test is shown. Recommendations for analysis techniques, tests, and criteria are made.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1976
- Accession Number
- ADB015902
Entities
People
- A. M. Cunningham
- D. Watts
- E. E. Cwach
- R. L. Haller
- R. P. Peloubet Jr.
Organizations
- General Dynamics