Publication Date:
2006-03-02
Description:
A preliminary investigation into the use of modern control theory for the design of controls for a supersonic inlet is described. In particular, the task of controlling a mixed-compression supersonic inlet is formulated as a linear optimal stochastic control and estimation problem. An inlet can exhibit an undesirable instability due to excessive inlet normal shock motion. For the optimal control formulation of the inlet problem, a non quadratic performance index, which is equal to the expected frequency of inlet unstarts, is used. This physically meaningful performance index is minimized for a range of inlet disturbance and measurement noise covariances.
Keywords:
AIRCRAFT PROPULSION AND POWER
Type:
NASA, Washington Fourth Inter-Center Control Systems Conf.; p 323-335
Format:
text
Permalink