CONTROL LAW FOR AN AIRCRAFT SUPERSONIC AIR INLET WITH INTERNAL COMPRESSION.

This paper deals with a supersonic air inlet Laval-type. Based on thermo- and gasdynamic phenomena, the authors have determined the possibilities of Laval-type intake starting process; the starting envelope of the intake was also defined and graphically depicted. Some operating regimes of the intake, correlated to engine's operation were studied and intake's adjusting possibilities were described, as intake's work-lines; these lines were depicted on intake's operational envelope and some control law(s) were determined with respect to the worklines. Possible control architecture may be emphasized. [ABSTRACT FROM AUTHOR]