Department of Electronical Engineering,Sharif University of Technology
Abstract
An algorithm for guiding a launch vehicle carrying a small satellite to a sun synchronous
LEO is presented. Before the launch, a nominal path and the corresponding nominal control law for
the entire journey are computed. For each sampling instant during the guided
ight, a linear equation
approximately relating the di erences between the actual and nominal values is considered, and a Least-
Squares formula using data from on-line state measurements is applied to compute the actual control.
The coecient matrices of the Least-Squares formula can be determined by o -line computations. The
method enjoys simplicity of implementation by onboard computers, as well as robust accuracy against
strong winds and uncertainties in thrust magnitude.
Marrdonny, M., & Mobed, M. (2010). An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles. Scientia Iranica, 17(2), -.
MLA
Mohamadd Marrdonny; Mohammad Mobed. "An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles". Scientia Iranica, 17, 2, 2010, -.
HARVARD
Marrdonny, M., Mobed, M. (2010). 'An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles', Scientia Iranica, 17(2), pp. -.
VANCOUVER
Marrdonny, M., Mobed, M. An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles. Scientia Iranica, 2010; 17(2): -.
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