"This thesis presents a flight control law for the ascent phase of flight of the next generation of reusable launch vehicles (RLVs). The control law developed and presented here is a new suboptimal nonlinear control technique. This new technique, called the θ-D method, is synthesized by adding perturbations to a typical optimal control formulation with a quadratic cost function. The controller expressions are obtained by getting an approximate closed-form solution to the Hamilton-Jacobi-Bellman equation. The θ-D method is able to avoid iterative online solutions due to the fact that the solution is closed form. A controller using this method has been designed for the ascent phase of a reusable launch vehicle and implemented in a six degrees-of-freedom high fidelity simulator being run at the NASA Marshall Space Flight Center. Simulation results show that the θ-D controller achieves accurate tracking for the ascent phase of the reusable launch vehicle while being robust to external disturbances and plant uncertainties"--Abstract, page iii.
Balakrishnan, S. N.
Sarangapani, Jagannathan, 1965-
Mechanical and Aerospace Engineering
M.S. in Aerospace Engineering
University of Missouri--Rolla
ix, 42 pages
© 2004 David Thomas Drake, All rights reserved.
Thesis - Restricted Access
Space vehicles -- Control systems
Nonlinear control theory
Reusable space vehicles
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Electronic access to the full-text of this document is restricted to Missouri S&T users. Otherwise, request this publication directly from Missouri S&T Library or contact your local library.http://merlin.lib.umsystem.edu/record=b5411369~S5
Drake, David, "Nonlinear suboptimal control for reusable launch vehicles" (2004). Masters Theses. 3699.
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