NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Press Enter or click the Search button to begin your search.

Back to Results
On the formulation of a minimal uncertainty model for robust control with structured uncertaintyIn the design and analysis of robust control systems for uncertain plants, representing the system transfer matrix in the form of what has come to be termed an M-delta model has become widely accepted and applied in the robust control literature. The M represents a transfer function matrix M(s) of the nominal closed loop system, and the delta represents an uncertainty matrix acting on M(s). The nominal closed loop system M(s) results from closing the feedback control system, K(s), around a nominal plant interconnection structure P(s). The uncertainty can arise from various sources, such as structured uncertainty from parameter variations or multiple unsaturated uncertainties from unmodeled dynamics and other neglected phenomena. In general, delta is a block diagonal matrix, but for real parameter variations delta is a diagonal matrix of real elements. Conceptually, the M-delta structure can always be formed for any linear interconnection of inputs, outputs, transfer functions, parameter variations, and perturbations. However, very little of the currently available literature addresses computational methods for obtaining this structure, and none of this literature addresses a general methodology for obtaining a minimal M-delta model for a wide class of uncertainty, where the term minimal refers to the dimension of the delta matrix. Since having a minimally dimensioned delta matrix would improve the efficiency of structured singular value (or multivariable stability margin) computations, a method of obtaining a minimal M-delta would be useful. Hence, a method of obtaining the interconnection system P(s) is required. A generalized procedure for obtaining a minimal P-delta structure for systems with real parameter variations is presented. Using this model, the minimal M-delta model can then be easily obtained by closing the feedback loop. The procedure involves representing the system in a cascade-form state-space realization, determining the minimal uncertainty matrix, delta, and constructing the state-space representation of P(s). Three examples are presented to illustrate the procedure.
Document ID
19920000809
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Belcastro, Christine M.
(NASA Langley Research Center Hampton, VA, United States)
Chang, B.-C.
(Drexel Univ. Philadelphia, PA., United States)
Fischl, Robert
(Drexel Univ. Philadelphia, PA., United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1991
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TP-3094
L-16893
NAS 1.60:3094
Report Number: NASA-TP-3094
Report Number: L-16893
Report Number: NAS 1.60:3094
Accession Number
92N10027
Funding Number(s)
PROJECT: RTOP 505-66-01-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available