Optimization of geostationary spacecraft design with two elements of large size-to-mass ratio
|1Alpatov, AP, 1Naumenko, RN |
1Institute of Technical Mechanics of the National Academy of Science of Ukraine and the State Space Agency of Ukraine, Dnipropetrovsk, Ukraine
|Kosm. nauka tehnol. 1997, 3 ;(3):043–046|
|Publication Language: Russian|
The problem on optimization of the design of a spacecraft of concrete configuration is considered. The purpose of the optimization is to minimize the influence of the solar pressure moment on the kinetic moment of the balance wheels of the spacecraft orientation system. The analytic relationships are obtained for calculating optimal geometric parameters of the spacecraft and optical characteristics of the surfaces entering into its design.
|Keywords: geostationary satellite, spacecraft and payloads|
Alpatov A. P., Naumenko R. N., Saltykov Yu. D. et al. Minimizing the time the solar pressure via the compensation reflector. Avtomatika-96: III Ukr. conf. on the automated management, Sevastopol, 9—14 sent., 1996, Vol. 3, 65— 66 (SevGTU, Sevastopol', 1996) [in Russian].
Alpatov A. P., Naumenko R. N., Shichanin V. N. Management Principles of the solar position pressure center and the ways of their technical realization. Avtomatika-95: II Ukr. conf. on the automated management, Lvov, 26—30 sent., 1995, Vol. 5, 3—4 (NVC ITIC, Lvov, 1995) [in Russian].
Bodner V. A. Aircraft Control Systems, 504 p. (Mashinostroenie, Moscow, 1973) [in Russian].
Raushenbakh B. V., Tokar E. N. Orientation control of spacecraft, 600 p. (Nauka, Moscow, 1974) [in Russian].