Article contents
Aircraft dynamics optimisation via linear matrix inequalities
Published online by Cambridge University Press: 04 July 2016
Abstract
This paper deals with the problem of determining an optimal controller which minimises the norm of a given aircraft while guaranteeing that an upper limit of its norm is not exceeded. The problem is tackled by means of a linear matrix inequality formulation, which allows one to constrain the eigenvalues of the model to within a fixed region of the complex plane. Key features of the method are the possibility of simultaneously
-
1. keeping the maximum value of the input demand under control
-
2. taking flying quality requirements into account
-
3. assuring a minimum level of system robustness against uncertainties of the model.
The approach is simple to handle and is well suited to the design of aircraft stability augmentation systems. A discussion of two case studies demonstrates the effectiveness of the procedure.
- Type
- Research Article
- Information
- Copyright
- Copyright © Royal Aeronautical Society 1996
References
- 2
- Cited by