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  • 1
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    Utilizing air-turborocket and rocket propulsion for a single-stage-to-orbit vehicle (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 28; 560-566
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Utilizing air-turborocket and rocket propulsion for a single-stage-to-orbit vehicle (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: With appropriate technology advances, a horizontal-takeoff single-stage-to-orbit (SSTO) launch vehicle could be designed which utilizes a combination of air-turborocket (ATR) and rocket propulsion systems. Such a vehicle is currently under study at Langley, and this paper presents the results of that study. Estimated vehicle weight characteristics, engine characteristics, geometry, aerodynamics, performance, structures, and subsystems are summarized. Trade studies performed on the reference vehicle to optimize the initial thrust-to-weight ratio (T/W) and the T/W after transition to the rocket phase with respect to vehicle weights are also presented. Throughout the vehicle presentation, special attention is given to the design issues, sensitivities, and performance parameters involved.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-0295
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The personal aircraft: Status and issues (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Paper summarizes the status of personal air transportation with emphasis upon VTOL and converticar capability. The former obviates the need for airport operations for personal aircraft whereas the latter provides both ground and air capability in the same vehicle. Fully automatic operation, ATC and navigation is stressed along with consideration of acoustic, environmental and cost issues.
    Keywords: AERODYNAMICS
    Type: NASA-TM-109174 , NAS 1.15:109174
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Technology benefits and ground test facilities for high-speed civil transport development (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The advanced technology base necessary for successful twenty-first century High-Speed Civil Transport (HSCT) aircraft will require extensive ground testing in aerodynamics, propulsion, acoustics, structures, materials, and other disciplines. This paper analyzes the benefits of advanced technology application to HSCT concepts, addresses the adequacy of existing groundbased test facilities, and explores the need for new facilities required to support HSCT development. A substantial amount of HSCT-related ground testing can be accomplished in existing facilities. The HSCT development effort could also benefit significantly from some new facilities initially conceived for testing in other aeronautical research areas. A new structures testing facility is identified as critically needed to insure timely technology maturation.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-107670 , NAS 1.15:107670
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Some key considerations for high-speed civil transports (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Factors affecting the development of a new generation of high-speed (supersonic/hypersonic) transports are reviewed. Market projections of growth on long-range routes indicate a potential need for faster transport aircraft by the turn of the century. A review of NASA-sponsored studies shows how both market forces and technology combine to define mission performance and vehicle design constraints. The vehicle worth and price projected for a given vehicle are shown to relate to an assumed technology level. Preliminary results from an initial set of vehicle concepts lead to the conclusion that currently projected technology will need to be enhanced with increased research to meet the first market window around the year 2000.
    Keywords: AERONAUTICS (GENERAL)
    Type: AIAA PAPER 88-4466
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    The challenges and opportunities of supersonic transport propulsion technology (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The major challenges confronting the propulsion community for civil supersonic transport applications are identified: high propulsion system efficiency at both supersonic and subsonic cruise conditions, low-cost fuel with adequate thermal stability at high temperatures, low noise cycles and exhaust systems, low emission combustion systems, and low drag installations. Both past progress and future opportunities are discussed in relation to perceived technology shortfalls for an economically successful airplane that satisfies environmental constraints.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 88-2985
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Concept development of a Mach 3.0 high-speed civil transport (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A baseline concept for a Mach 3.0 high-speed civil transport concept was developed as part of a national program with the goal that concepts and technologies be developed which will enable an effective long-range high-speed civil transport system. The Mach 3.0 concept reported represents an aggressive application of advanced technology to achieve the design goals. The level of technology is generally considered to be that which could have a demonstrated availability date of 1995 to 2000. The results indicate that aircraft are technically feasible that could carry 250 passengers at Mach 3.0 cruise for a 6500 nautical mile range at a size, weight and performance level that allows it to fit into the existing world airport structure. The details of the configuration development, aerodynamic design, propulsion system design and integration, mass properties, mission performance, and sizing are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-4058 , L-16445 , NAS 1.15:4058
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Performance potential of an advanced technology Mach 3 turbojet engine installed on a conceptual high-speed civil transport (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The performance of an advanced technology conceptual turbojet optimized for a high-speed civil aircraft is presented. This information represents an estimate of performance of a Mach 3 Brayton (gas turbine) cycle engine optimized for minimum fuel burned at supersonic cruise. This conceptual engine had no noise or environmental constraints imposed upon it. The purpose of this data is to define an upper boundary on the propulsion performance for a conceptual commercial Mach 3 transport design. A comparison is presented demonstrating the impact of the technology proposed for this conceptual engine on the weight and other characteristics of a proposed high-speed civil transport. This comparison indicates that the advanced technology turbojet described could reduce the gross weight of a hypothetical Mach 3 high-speed civil transport design from about 714,000 pounds to about 545,000 pounds. The aircraft with the baseline engine and the aircraft with the advanced technology engine are described.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-4144 , L-16531 , NAS 1.15:4144
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    The challenges and opportunities of supersonic transport propulsion technology (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The major challenges confronting the propulsion community for civil supersonic transport applications are identified: high propulsion system efficiency at both supersonic and subsonic cruise conditions, low-cost fuel with adequate thermal stability at high temperatures, low noise cycles and exhaust systems, low emission combustion systems, and low drag installations. Both past progress and future opportunities are discussed in relation to perceived technology shortfalls for an economically successful airplane that satisfies environmental constraints.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-100921 , E-4178 , NAS 1.15:100921 , AIAA PAPER 88-2985
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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