Heat input reduction in hypersonic flight by optimal trajectory control

Gottfried Sachs; Michael Dinkelmann

doi:10.2514/6.1996-3905

Heat input reduction in hypersonic flight by optimal trajectory control

Gottfried Sachs
, Michael Dinkelmann

TUM Emeriti of Excellence

Technical University of Munich

Research output: Contribution to conference › Paper › peer-review

3 Scopus citations

Abstract

Heat input reduction by optimal trajectory control is considered for the range cruise of a hypersonic carrier vehicle propelled by a turbo/ram jet combination. A mathematical model is developed for describing the unsteady heat transfer through a thermal protection wall system. This model is coupled to the equations of motion of the vehicle. An efficient optimization technique is applied for constructing a solution of the range cruise problem. The results show that a significant heat input reduction can be achieved while there is only a small increase in fuel consumption.

Original language	English
Pages	1-11
Number of pages	11
DOIs	https://doi.org/10.2514/6.1996-3905
State	Published - 1996
Event	Guidance, Navigation, and Control Conference and Exhibit, 1996 - San Diego, United States Duration: 29 Jul 1996 → 31 Jul 1996

Conference

Conference	Guidance, Navigation, and Control Conference and Exhibit, 1996
Country/Territory	United States
City	San Diego
Period	29/07/96 → 31/07/96

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10.2514/6.1996-3905

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title = "Heat input reduction in hypersonic flight by optimal trajectory control",

abstract = "Heat input reduction by optimal trajectory control is considered for the range cruise of a hypersonic carrier vehicle propelled by a turbo/ram jet combination. A mathematical model is developed for describing the unsteady heat transfer through a thermal protection wall system. This model is coupled to the equations of motion of the vehicle. An efficient optimization technique is applied for constructing a solution of the range cruise problem. The results show that a significant heat input reduction can be achieved while there is only a small increase in fuel consumption.",

author = "Gottfried Sachs and Michael Dinkelmann",

note = "Publisher Copyright: {\textcopyright} 1996 by G. Sachs and M. Dinkelmann. Published by the American Institute of Aeronautics and Astronautics, Inc.; Guidance, Navigation, and Control Conference and Exhibit, 1996 ; Conference date: 29-07-1996 Through 31-07-1996",

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AU - Dinkelmann, Michael

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N2 - Heat input reduction by optimal trajectory control is considered for the range cruise of a hypersonic carrier vehicle propelled by a turbo/ram jet combination. A mathematical model is developed for describing the unsteady heat transfer through a thermal protection wall system. This model is coupled to the equations of motion of the vehicle. An efficient optimization technique is applied for constructing a solution of the range cruise problem. The results show that a significant heat input reduction can be achieved while there is only a small increase in fuel consumption.

AB - Heat input reduction by optimal trajectory control is considered for the range cruise of a hypersonic carrier vehicle propelled by a turbo/ram jet combination. A mathematical model is developed for describing the unsteady heat transfer through a thermal protection wall system. This model is coupled to the equations of motion of the vehicle. An efficient optimization technique is applied for constructing a solution of the range cruise problem. The results show that a significant heat input reduction can be achieved while there is only a small increase in fuel consumption.

UR - https://www.scopus.com/pages/publications/84959093883

U2 - 10.2514/6.1996-3905

DO - 10.2514/6.1996-3905

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T2 - Guidance, Navigation, and Control Conference and Exhibit, 1996

Y2 - 29 July 1996 through 31 July 1996

ER -

Heat input reduction in hypersonic flight by optimal trajectory control

Abstract

Conference

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