An Accurate Guidance Algorithm for Implementation Onboard Satellite Launch Vehicles

نویسندگان
Mobed, Mohammad ID 1
Marrdonny, Mohamadd ID 2

1 Department of Electronical Engineering,Sharif University of Technology

2 Department of Electronical Engineering,Sharif University of Technology

doi
چکیده

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.

کلیدواژه‌ها
Disturbance rejection, Guidance systems, Satellites, Optimal trajectory, Launch vehicle