Volume 6, 2013Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics
|Page(s)||569 - 582|
|Section||Launchers trajectory optimization|
|Published online||02 December 2013|
The through optimization of fail-safe branched injection trajectories of launch vehicles in view of aerodynamic load constraints on the basis of the maximum principle
Central Aerohydrodynamic Institute (TsAGI) Zhukovsky 140180, Moscow Region, Russia
A problem of through optimization of fail-safe branched trajectories of launchers in view of aerodynamic load constraints and restrictions on ground impact areas of separated parts (SP) is considered. The failsafety is regarded to the possibility of a recoverable vehicle (RV) to return from any point of the ascent trajectory to landing points without excess of allowable g-loads. So, the purpose is determination of the launcher optimal control in view of constraints on all trajectory branches: the main, corresponding to an active injection leg, and side branches, corresponding to SP fall trajectories and imaginary RV emergency trajectories, which form a continuum. The problem solution is based on the Pontryagin maximum principle (PMP).
© Owned by the authors, published by EDP Sciences, 2013
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 2.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.