By Jay Miller
Publication through Miller, Jay
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Aerodynamic Characteristics and Control Effectiveness of the HL-20 Lifting Body Configuration at Mach 10 in Air. NASA Technical Memorandum 209357 (September 1999) 6. : HL20 aeroblockset MATLAB. The Mathworks 7. : Six-Degree-of-Freedom Guidance and Control-Entry Analysis of the HL-20. Journal of Spacecraft and Rockets 30(5) (1993) 8. : Design examples using mu-synthesis: Space shuttle lateral axis FCS during re-entry. In: IEEE Control Decision Conference, vol. 25, pp. 2218–2223 (1986) 9. : Application of LPV modeling, design and analysis methods to a re-entry vehicle.
In: AIAA GNC 2009 (2009) 13. : Nonlinear WorstCase Analysis of an LPV Controller for Approach-Phase of a Re-entry Vehicle. In: AIAA GNC 2009 (2009) 14. : Analysis of the Controlled NASA HL20 Atmospheric Re-entry Vehicle based on Dynamic IQCs. In: AIAA GNC 2009 (2009) 15. : IQC-Based IQC LPV Controller Synthesis for the NASA HL20 Atmospheric Re-entry Vehicle. In: AIAA GNC 2009 (2009) A Linear Parameter Varying Controller for a Re-entry Vehicle Benchmark 27 16. : Research on Gain Scheduling. Automatica 36, 1401–1425 (2000) 17.
The key concept of the two step method, is that the identification procedure has been split into two consecutive steps, as substantiated in ref. . More precisely, the global non-linear one step identification method is decomposed in two separate steps, where the nonlinear part is isolated in the aircraft state estimation step. Consequently, the aerodynamic model parameter identification procedure in the second step can be simplified to a procedure which is linear in the parameters, but involves nonlinear regressors.