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Hypersonic vehicle model and control law development using H(infinity) and micron synthesisThe control system design for a Single Stage To Orbit (SSTO) air breathing vehicle will be central to a successful mission because a precise ascent trajectory will preserve narrow payload margins. The air breathing propulsion system requires the vehicle to fly roughly halfway around the Earth through atmospheric turbulence. The turbulence, the high sensitivity of the propulsion system to inlet flow conditions, the relatively large uncertainty of the parameters characterizing the vehicle, and continuous acceleration make the problem especially challenging. Adequate stability margins must be provided without sacrificing payload mass since payload margins are critical. Therefore, a multivariable control theory capable of explicitly including both uncertainty and performance is needed. The H(infinity) controller in general provides good robustness but can result in conservative solutions for practical problems involving structured uncertainty. Structured singular value mu framework for analysis and synthesis is potentially much less conservative and hence more appropriate for problems with tight margins. An SSTO control system requires: highly accurate tracking of velocity and altitude commands while limiting angle-of-attack oscillations, minimized control power usage, and a stabilized vehicle when atmospheric turbulence and system uncertainty are present. The controller designs using H(infinity) and mu-synthesis procedures were compared. An integrated flight/propulsion dynamic mathematical model of a conical accelerator vehicle was linearized as the vehicle accelerated through Mach 8. Vehicle acceleration through the selected flight condition gives rise to parametric variation that was modeled as a structured uncertainty. The mu-analysis approach was used in the frequency domain to conduct controller analysis and was confirmed by time history plots. Results demonstrate the inherent advantages of the mu framework for this class of problems.
Document ID
19950006425
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Gregory, Irene M.
(NASA Langley Research Center Hampton, VA, United States)
Chowdhry, Rajiv S.
(NASA Langley Research Center Hampton, VA, United States)
Mcminn, John D.
(NASA Langley Research Center Hampton, VA, United States)
Shaughnessy, John D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1994
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NASA-TM-4562
L-17217
NAS 1.15:4562
Report Number: NASA-TM-4562
Report Number: L-17217
Report Number: NAS 1.15:4562
Accession Number
95N12838
Funding Number(s)
PROJECT: RTOP 505-70-64-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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