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Optimal trajectories for an aerospace plane. Part 2: Data, tables, and graphsData, tables, and graphs relative to the optimal trajectories for an aerospace plane are presented. A single-stage-to-orbit (SSTO) configuration is considered, and the transition from low supersonic speeds to orbital speeds is studied for a single aerodynamic model (GHAME) and three engine models. Four optimization problems are solved using the sequential gradient-restoration algorithm for optimal control problems: (1) minimization of the weight of fuel consumed; (2) minimization of the peak dynamic pressure; (3) minimization of the peak heating rate; and (4) minimization of the peak tangential acceleration. The above optimization studies are carried out for different combinations of constraints, specifically: initial path inclination that is either free or given; dynamic pressure that is either free or bounded; and tangential acceleration that is either free or bounded.
Document ID
19910006698
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Miele, Angelo (Rice Univ. Houston, TX, United States)
Lee, W. Y. (Rice Univ. Houston, TX, United States)
Wu, G. D. (Rice Univ. Houston, TX, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-187848
AAR-248-PT-2
NAS 1.26:187848
Meeting Information
Meeting: 1990 American Control Conference
Location: San Diego, CA
Country: United States
Start Date: May 23, 1990
End Date: May 25, 1990
Accession Number
91N16011
Funding Number(s)
CONTRACT_GRANT: NAG1-1029
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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