Publikationsdatum:
2019-07-13
Beschreibung:
The U.S. Navy and NASA are currently involved in the design and development of an unsymmetric-skew-wing aircraft capable of 65 deg wing sweep and flight at Mach 1.6. A generic skew-wing aircraft model was developed for 45 deg wing skew at a flight condition of Mach 0.70 and 3048 m altitude. At this flight condition the aircraft has a wing flutter mode. An active implementable control law was developed using the linear quadratic Gaussian design technique. A method of modal residualization was used to reduce the order of the controller used for flutter suppression.
Schlagwort(e):
AIRCRAFT STABILITY AND CONTROL
Materialart:
NASA-TM-86808
,
H-1346
,
NAS 1.15:86808
,
American Control Conference; Jun 18, 1986 - Jun 20, 1986; Seattle, WA; United States
Format:
application/pdf
