Predictive Terminal Guidance With Tuning of Prediction Horizon & Constrained Control .
AbstractContinvojs time-predictive control approach is employed to formulate an output tracking nonlinear, optimal, terminal guidance ,law for re-entry vehicles. The notable features of this formulation are that the system equations are not linearised and the evaluation of the guidance
equations does not need the information of vehicle parameters, such as drag and mass. The formulation allows to impose the physical constrains on the control inputs, i..e. on the demanded lateral acceleliations through a saturation mapping and the controls are obtained using a fixed point
iteration algorithm which converges typically in a few iterations. Further, a simple method of tuning the prediction horizon needed in the guidance equations is presented. Numerical simulations show that the guidance law achieves almost zero terminal errors in all states despite large errors in initial Conditions.
Wingrove, R.C. Survey .of atmosphere rentry guidance and control methods. AlAA Journal , 1963, 1(9), 2019-29. I
Kim, M. & Grider, K.V. Terminal guidance for impact attitude angle constrained flight trajectories. IEEE Trans. Aerosp.:Electron. Syst.,
, AES-9, 852-59.
York, R. &' Pastrick, H.L. Optimal terminal Guidance with constraints at final time. .J. Rockets Spacecraft, 1977, 14(6), 381-83.
De Virgilio, M.A.; :Wells, G.R. & Sdhiring, E.E. Optimal guidance for aetodynamically controlled re-entry vehicles. AlAA 'Journal, 1974,
Page, J.A. & Roger, R.O. Guidance and control of maneuvering re-entry vehicles. Proceedings of IEEE Conference on Decision and Control, 1977,659,.64.
Lu, P. Optimal predibive control of continuous nonlinear systems. InJ. J. Control, 1995,62(3),633-49.
Lu, P. Constrained trackiryg control of nonlinear systems. Syst. Control Lett., 1996, 27, 305-14.
Archer, S.M. & Sworder, D.D. Selection of the guidance variable for re-entry vehicle. J. Guid. Control Dyn., 1979,2(2), 130-38.
Vidyasagar, M. Nonlinear systems ranalysis. Prentice Hall, Englewood Cliffs, New Jersey 1993.
Romano, 1.1,&. Singh, S.N. I-O map inversion, zero dynamics and flight control. IEEE Trans. Aero. Electron. Syst., 1990 AES-26, 1022-29.
Regan, F .J. Re..entry' vehicle dynanlics. AIAA Education Seties, New York, 1984.
where otherwise noted, the Articles on this site are licensed under Creative Commons License: CC Attribution-Noncommercial-No Derivative Works 2.5 India