ABSTRACT
VLADIMIRM. MATROSOV1, MIKHAIL F. RESHETNEV2, VALENTINA. RAYEVSKY2 and YEVGENY I. SOMOV3
1 Stability and Nonlinear Dynamics Research Center o f Mechanical Engineering Research Institute o f Russian Academy o f Sciences, Room. 312, Bid. 5, Dm.Ulianov Str., Moscow; 117333, Russia Fax: 007 095 752 7867; E-mail: vladimir@matrosov.mccme.ru 2Research and Production Association “Applied Mechanics ” (NPO PM), 52 Lenin Street, Krasnoyarsk, 660026, Russia Fax: 007 391 97 21183; E-mail: root@npopm.krasnoyarsk.su 3 Irkutsk Computing Center, Siberian Branch, Russian Academy o f Sciences, P.O. Box 1233, Irkutsk, 644033, Russia Fax : 007 3952 462654; E-mail: somov@icc.ccsoan.irkutsk.su
During the recent 30 years it has accumulated a substantial experience in designing SC’s attitude control systems (ACSs), characterized by high survivability and autonomy at the expense of usage of functional excessibility (spacecrafts Molniya, Raduga, Gorizont, Ekran, Lutch, Gals, Express, etc.). The principal dynamic requirements to ACS of modem SCs of
this class are: (і) continuous precision З-axis orientation of the SC’s body, which requires only some minimum number of measurements under the conditions of possible onboard ACS equipment failures, disturbances on optical devices from the Sun, Moon, etc., and also in executing SC’s orbit correction; (ii) possibility of SC’s body re-orientation for its orbit correction, as well as autonomous orientation of the solar array panels (SAPs) and each receiving-transmitting antenna (RTA) with respect to the SC’s body; (iii) robustness to variations of SC’s inertial and rigidity characteristics under minimum mass, size and energetic expenditures.
