A hypersonic cruiser concept for the 21st century

Orton, G. F.; Scuderi, Lee

doi:10.2514/6.1998-5525

Cited by 6 publications

(3 citation statements)

References 6 publications

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“…Because various Ti-based alloys and composites are among the top candidate advanced materials used for reentry environments [24][25], it is imperative that combustibility and ignition of aerospace metals be appreciated.…”

Section: Resultsmentioning

confidence: 99%

Crystallographic oxide phase identification of char deposits obtained from space shuttle Columbia window debris

et al. 2010

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Abstract:Analyzing the remains of Space Shuttle Columbia has proven technically beneficial years after the vehicle breakup. This investigation focused on charred deposits on fragments of Columbia overhead windowpanes . Results were unexpected relative to the engineering understanding of material performance in a reentry environment. The TEM analysis demonstrated that the oxides of aluminum and titanium mixed with silicon oxides to preserve a history of thermal conditions to which portions of the vehicle were exposed. The presence of Ti during the beginning of the deposition process, along with the thermodynamic phase precipitation upon cool down, indicate that temperatures well above the Ti melt point were experienced. The stratified observations implied that additional exothermic reaction, expectedly metal combustion of a Ti structure, had to be present for oxide formation. Results are significant for aerospace vehicles where thermal protection system (TPS) breaches cause substructures to be in direct path with the reentry plasma.

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Section: Resultsmentioning

confidence: 99%

Crystallographic oxide phase identification of char deposits obtained from space shuttle Columbia window debris

et al. 2010

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“…A survey of the literature revealed a wide range of design strategies for mitigating the high temperatures experienced in hypersonic flight. [53][54][55][56][57][58][59][60] This study considers a thermal protection system consisting of an outer heat shield and middle insulation layer on top of the structure as shown in Fig. 7.…”

Section: Control Surface Modelmentioning

confidence: 99%

Proper Orthogonal Decomposition for Reduced-Order Thermal Solution in Hypersonic Aerothermoelastic Simulations

Falkiewicz

Cesnik

2011

AIAA Journal

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The ability to perform full-order aerothermoelastic simulations of hypersonic vehicles is hindered by the strong coupling exhibited between the aerodynamics, heat transfer, and structural dynamic response in the hypersonic flight regime. As a result of these interactions, alternative techniques are necessary to obtain computationally tractable systems of governing equations and their solutions. This work addresses the use of proper orthogonal decomposition for reduced-order solution of the heat transfer problem within a hypersonic modeling framework. The specific challenge of handling time-dependent boundary conditions due to transient aerodynamic heating is discussed. An overview of the proper orthogonal decomposition is given and two methods for solution of the reduced system of ordinary differential equations are outlined. The methodology is applied to a representative hypersonic vehicle control surface model for two cases in which the time-history of the thermal load vector is known a priori : one in which the boundary conditions are time-independent and another in which they are time-varying. Results demonstrate the ability of the reduced-order solution to approximate the full-order solution with reasonable accuracy. Finally, a time-marching hypersonic aerothermoelastic framework is described in which proper orthogonal decomposition is used for the transient thermal solution.

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“…This philosophy carries over into the design strategies for hypersonic cruisers powered by air-breathing pro pulsion systems. As recommended by Orton and Scuderi [67]: ''The Mach 10 dual-role vehicle's airframe is a cold, integral structure design in which the cryogenic hydrogen fuel tanks also carry the vehicle's structural loads. Hot structure is used for the horizontal wings and vertical tails.…”

Section: Load-carrying Structuresmentioning

confidence: 99%

Fifty years of hypersonics: where we've been, where we're going

Bertin¹,

Cummings²

2003

Progress in Aerospace Sciences

342

128

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Hypersonic flight has been with us since 22 September 1963, when Robert M. White flew the North American X-15 at 4520 mph at an altitude of 354; 200 ft-a Mach number of 6.7! This remarkable achievement was accomplished over six decades due to intensive research and development by a large number of scientists and engineers. In spite of that momentous achievement, designers have found the hypersonic environment to be harsh and non-forgiving. New programs since the 1960s have often uncovered the unknown unknowns, usually the hard way-early flights of new systems have often revealed problems of which the designers were unaware. Such problems include: the ineffectiveness of the body flap for the Space Shuttle Orbiter, the viscous/inviscid interactions produced by the umbilical fairings that damaged the conical section tile protection system of the Gemini Capsule, and the shock/shock interaction that damaged the X-15A-2 when it carried the hypersonic ramjet experiment. In order to continue to make advances in hypersonic flight a sustained and visionary effort is essential to generate required knowledge and technology. In order to better prepare for future developments in hypersonic flight, this article reviews the advances made within the past 50 years and then looks into the future, not just for new technological developments, but for new ways of thinking about the unknown challenges that lie ahead.

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A hypersonic cruiser concept for the 21st century

Cited by 6 publications

References 6 publications

Crystallographic oxide phase identification of char deposits obtained from space shuttle Columbia window debris

Crystallographic oxide phase identification of char deposits obtained from space shuttle Columbia window debris

Proper Orthogonal Decomposition for Reduced-Order Thermal Solution in Hypersonic Aerothermoelastic Simulations

Fifty years of hypersonics: where we've been, where we're going

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