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Hsu, S.

Publications and source records attributed to Hsu, S..

Semigroup approximation and robust stabilization of distributed parameter systems

Theoretical results that enable rigorous statements of convergence and exponential stability of Galerkin approximations of LQR controls for infinite dimensional, or distributed parameter, systems have proliferated over the past ten years. In addition, extensive progress has been made over the same time period in the derivation of robust control design strategies for finite dimensional systems. However, the study of the convergence of robust finite dimensional controllers to robust controllers for infinite dimensional systems remains an active area of research. We consider a class of soft-constrained differential games evolving in a Hilbert space. Under certain conditions, a saddle point control can be given in feedback form in terms of a solution to a Riccati equation. By considering a related LQR problem, we can show a convergence result for finite dimensional approximations of this differential game. This yields a computational algorithm for the feedback gain that can be derived from similar strategies employed in infinite dimensional LQR control design problems. The approach described in this paper also inherits the additional properties of stability robustness common to game theoretic methods in finite dimensional analysis. These theoretical convergence and stability results are verified in several numerical experiments.

Kurdila, A. J.

Large inclination change using lunar-swingby techniques

The use of lunar-swingby maneuvers to transfer a spacecraft from an equatorial orbit to a polar orbit has been investigated in order to verify the technical feasibility of the NASA/ESA equatorial science phase (ESP)/Cluster mission. The solar aspect angle constraints of the spacecraft spin-axis and the dependence of the total Delta-V cost of the transfer on the initial ESP orbital parameters (particularly perigee radius and inclination) have been studied. The results indicate that a satisfactory ESP-to-Cluster orbit transfer can be achieved using a double lunar-swingby sequence.

Lee, T.

Trajectories for the Sakigake extended-mission phase

The trajectory profile that will be used by Japan's Sakigake spacecraft to accomplish its extended-mission objectives is described. Currently, Sakigake is following a heliocentric trajectory that will return to the earth's vicinity in January 1992. Four earth gravity-assist maneuvers are planned to redirect Sakigake to an encounter with Comet Honda-Mrkos-Pajdusakova (HMP) in February 1996. While carrying out the earth-swingby maneuvers, the spacecraft will make several passes through previously unexplored regions of the distant geomagnetic tail.

Farquhar, R.