Japanese Spaceplane and Hypersonic Technology Program overview - Progress of 1995-1996

Maita, Masataka; Kobayashi, Shígeo

doi:10.2514/6.1996-6005

“…Following the early paper studies, the development plans led to the HOPE-X, a full-scale demonstrator for the operational HOPE vehicle. "..Although the size and configuration of HOPE-X duplicate the operational HOPE, its gross weight will be about two-thirds of operational HOPE..." 151 Three experimental projects were defined initially during the early development plans that would lead to HOPE-X as each project would focus on specific disciplinary development. A fourth vehicle was added to the initial three experimental projects during the later program stage.…”

Section: Figure 24: Festip Concept Studies and Final Selectionmentioning

confidence: 99%

“…Approximately 20 flight tests were done to evaluate guidance performance, aerodynamic characteristics and performance." 151 Both, HYFLEX and ALFLEX are scored high on the aerothermodynamics and subsystems disciplines for their contribution in stability and control during the landing, while OREX is scored high on the thermal management and aerothermodynamics disciplines.…”

Section: B Lrv Efforts In Japanmentioning

confidence: 99%

Design Evolution and AHP-based Historiography of Lifting Reentry Vehicle Space Programs

Rana

¹

,

Chudoba

²

2016

Aiaa Space 2016

5

0

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The term "Historiography" is defined as the writing of history based on the critical examination of sources. In the context of space access systems, a considerable body of literature has been published addressing the history of lifting-reentry vehicle(LRV) research. Many technical papers and books have surveyed legacy research case studies, technology development projects and vehicle development programs to document the evolution of hypersonic vehicle design knowledge gained from the early 1950s onwards. However, these accounts tend to be subjective and qualitative in their discussion of the significance and level of progress made. Even though the information addressed in these surveys is considered crucial, it may lack qualitative or quantitative organization for consistently measuring the contribution of an individual program.The goal of this study is to provide an anatomy aimed at addressing and quantifying the contribution of legacy programs towards the evolution of the hypersonic knowledge base. This paper applies quantified analysis to legacy lifting-reentry vehicle programs, aimed at comprehensively capturing the evolution of LRV hypersonic knowledge base. Beginning with an overview of literature surveys focusing on hypersonic research programs, a comprehensive list of LRV programs, starting from the 1933 Silvervogel to the 2015 Dream Chaser, is assembled. These case-studies are assessed on the basis of contribution made towards major hypersonic disciplines. The Analytical Hierarchy Process (AHP) is used to develop an analytical model, to quantify and measure the strength and weakness of primary disciplines for every case-study. Sixty national and international case-studies are evaluated based on one system-level and five discipline-based criteria addressing aerothermodynamics, structure & materials, propulsion, thermal, and sub-system contributions. The AHP model allows a comparative assessment among the case-studies based on quantitative results, which identify a case-studys value and contribution for the growth of the primary disciplines, and the evolution of the overall hypersonic knowledge base. This analysis is further supported by an overview of the case-studies accessed, providing a brief description of LRV research history. An evolutionary pattern among the case-studies is recognized, demonstrating common aspects and influences of major programs throughout history.

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Computational Aerothermodynamic Design Issues for Hypersonic Vehicles

Gnoffo¹,

Weilmuenster²,

Hamilton³

et al. 1999

Journal of Spacecraft and Rockets

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A brief review of the evolutionary progress in computational aerothermodynamics is presented. The current status of computational aerothermodynamics is then discussed, with emphasis on its capabilities and limitations for contributions to the design process of hypersonic vehicles. Some topics to be highlighted include: घ1ङ aerodynamic coeaecient predictions with emphasis on high temperature gas eaeects; घ2ङ surface heating and temperature predictions for thermal protection system घTPSङ design in a high temperature, thermochemical nonequilibrium environment; घ3ङ methods for extracting and extending computational aeuid dynamic घCFDङ solutions for eaecient utilization by all members of a multidisciplinary design team; घ4ङ physical models; घ5ङ validation process and error estimation; and घ6ङ gridding and solution generation strategies. Recent experiences in the design of X-33 will be featured. Computational aerothermodynamic contributions to Mars Pathaender, METEOR, and Stardust घComet Sample returnङ will also provide context for this discussion. Some of the barriers that currently limit computational aerothermodynamics to a predominantly reactive mode in the design process will also be discussed, with the goal of providing focus for future research.

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Computational aerothermodynamic design issues for hypersonic vehicles

Olynick

¹

,

Venkatapathy

²

1997

32nd Thermophysics Conference

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A brief review of the evolutionary progress in computational aerothermodynamics is presented. The current status of computational aerothermodynamics is then discussed, with emphasis on its capabilities and limitations for contributions to the design process of hypersonic vehicles. Some topics to be highlighted include: घ1ङ aerodynamic coeaecient predictions with emphasis on high temperature gas eaeects; घ2ङ surface heating and temperature predictions for thermal protection system घTPSङ design in a high temperature, thermochemical nonequilibrium environment; घ3ङ methods for extracting and extending computational aeuid dynamic घCFDङ solutions for eaecient utilization by all members of a multidisciplinary design team; घ4ङ physical models; घ5ङ validation process and error estimation; and घ6ङ gridding and solution generation strategies. Recent experiences in the design of X-33 will be featured. Computational aerothermodynamic contributions to Mars Pathaender, METEOR, and Stardust घComet Sample returnङ will also provide context for this discussion. Some of the barriers that currently limit computational aerothermodynamics to a predominantly reactive mode in the design process will also be discussed, with the goal of providing focus for future research.

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Japanese Spaceplane and Hypersonic Technology Program overview - Progress of 1995-1996

Cited by 4 publications

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Design Evolution and AHP-based Historiography of Lifting Reentry Vehicle Space Programs

Design Evolution and AHP-based Historiography of Lifting Reentry Vehicle Space Programs

Computational Aerothermodynamic Design Issues for Hypersonic Vehicles

Computational aerothermodynamic design issues for hypersonic vehicles

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