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University of California, Irvine

Aerospace Plane Guidance

Sponsored by NASA Langley Research Center (1988-1993)
Research Carried out at Princeton University (1988-1993)
and at UCI (1993-1995)


Future generation aerospace planes, using a combination of airbreathing and rocket propulsion to accelerate to orbital energy, pose significant challenges in guidance and control due to (i) the high degree of coupling between flight control, structural control, engine control and thermal control, (ii) the large flight envelope and (iii) the high performance demands. Theory and techniques from geometric nonlinear dynamics and control were used to develop effective guidance logic for aerospace plane ascent. Robust, near minimum-fuel guidance logic was developed using a blend of singular perturbations, feedback linearization, and variable structure control.

References:

Jean-Paul Kremer, Studies in Flight Guidance Using Nonlinear Techniques, Ph.D. Dissertation, Princeton University, Dec. 1995.

J.-P. Kremer and K.D. Mease, "Aerospace Plane Ascent Guidance Considering Aeropropulsive Effects," Paper 95-3329, AIAA Guidance, Navigation and Control Conf., Baltimore, Aug. 1995.

K.D. Mease and M.A. Van Buren, "Geometric synthesis of Aerospace Plane Ascent Guidance," Automatica, Dec. 1994.

Markus A. Van Buren, Robust Nonlinear Feedback Guidance for an Aerospace Plane, Ph.D. Dissertation, Princeton University, June 1992.

M.A. Van Buren and K.D. Mease, "Aerospace Plane Guidance Using Time-Scale Decomposition and Feedback Linearization," J. Guidance, Control, and Dynamics, Vol. 15, No. 5, pp. 1166-1174, 1992.

 

 


Flight Dynamics and Control Lab Flight Dynamics and Control Lab

 University Of California, Irvine

To contact Professor Mease: kmease@uci.edu


(Last Revised 7 July 1997)