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. and Mobed, M. (2010). An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles. Scientia Iranica, 17(2), -.
MLA
Marrdonny, M. , and Mobed, M. . "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. -.
CHICAGO
M. Marrdonny and M. Mobed, "An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles," Scientia Iranica, 17 2 (2010): -,
VANCOUVER
Marrdonny, M., Mobed, M. An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles. Scientia Iranica, 2010; 17(2): -.
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