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. (e3355). Scientia Iranica, 17(2), e3355
MLA
Marrdonny,M , and Mobed,M . "An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles" .e3355 , Scientia Iranica, 17, 2, 2010, e3355.
HARVARD
Marrdonny M, Mobed M. (2010). 'An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles', Scientia Iranica, 17(2), e3355.
CHICAGO
M Marrdonny and M Mobed, "An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles," Scientia Iranica, 17 2 (2010): e3355,
VANCOUVER
Marrdonny M, Mobed M. An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles. Scientia Iranica. 2010;17(2):e3355.
