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Application of an advanced trajectory optimization method to ramjet propelled missilesThe mission performance characteristics of ramjet-propelled missiles are highly dependent upon the trajectory flown. Integration of the trajectory profile with the ramjet propulsion system performance characteristics to achieve optimal missile performance is very complex. Past trajectory optimization methods have been extremely problem dependent and require a high degree of familiarity to achieve success. A general computer code (CTOP) has been applied to ramjet-powered missiles to compute open-loop optimal trajectories. CTOP employs Chebyshev polynomial representations of the states and controls. This allows a transformation of the continuous optimal control problem to one of parameter optimization. With this method, the trajectory boundary conditions are always satisfied. State dynamics and path constraints are enforced via penalty functions. The presented results include solutions to minimum fuel-to-climb, minimum time-to-climb, and minimum time-to-target intercept problems.
Document ID
19810030613
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Paris, S. W.
(Boeing Aerospace Co. Seattle, WA, United States)
Fink, L. E.
(Boeing Aerospace Co. Seattle, Wash., United States)
Joosten, B. K.
(NASA Johnson Space Center Houston, Tex., United States)
Date Acquired
August 11, 2013
Publication Date
December 1, 1980
Publication Information
Publication: Optimal Control Applications and Methods
Volume: 1
Subject Category
Aircraft Design, Testing And Performance
Accession Number
81A15017
Distribution Limits
Public
Copyright
Other

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