Abstract
The steady-state response of a controlled system is of particular importance in non-zero set point regulation, and nowhere is this of more concern than in the piloting of aircraft. Possible equilibrium states are, to a large extent, independent of the aircraft's stability and transient behavior; hence, stability and command objectives can be specified separately. Singular as well as nonsingular steady-state response may be desirable from the pilot's viewpoint, i.e. a constant command vector can imply varying state and control vectors. The flight control structure can be designed to account for this characteristic, while allowing full state or state-estimate feedback if desired. Dissimilar command vectors lead to markedly different responses in systems whose eigenvalues and eigenvectors are identical. A methodology for designing to achieve proper command response is presented, and numerical and graphical illustrations are provided for a generic lightweight fighter aircraft example.
Original language | English (US) |
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Pages (from-to) | 343-348 |
Number of pages | 6 |
Journal | Automatica |
Volume | 18 |
Issue number | 3 |
DOIs | |
State | Published - May 1982 |
All Science Journal Classification (ASJC) codes
- Control and Systems Engineering
- Electrical and Electronic Engineering
Keywords
- Aerospace control
- closed-loop systems
- control system synthesis
- control theory
- dynamic response
- multivariable control systems
- state-space methods