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  • 11
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    Optimum wing sizing of a single-stage-to-orbit vehicle (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An investigation has been conducted to determine preliminary wing designs for a single-stage-to-orbit (SSTO) vehicle. This vehicle has the following mission profile: vertical takeoff, boost-to-orbit, hypersonic reentry, and horizontal landing. For this vehicle, the wing is sized to meet Space Shuttle reentry aerodynamic requirements for hypersonic trim and horizontal landing, since reentry trajectories for the Shuttle and the SSTO vehicle are similar. A hypersonic and subsonic aerodynamic computer program was developed and combined with an existing optimization algorithm to automatically size and shape a wing which satisfies both reentry and landing requirements while also maintaining a minimum mass design. With this procedure, the influence of hypersonic and subsonic aerodynamic requirements, control surface size, and center-of-gravity positions on the initial wing design were investigated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 82-0174 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    Nozzle selection for optimized single-stage shuttles (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computerized preliminary design procedure has been used to determine rocket-engine bell-nozzle configurations which achieve either minimum gross mass or minimum dry mass on an advanced technology winged single-stage-to-orbit launch vehicle. This procedure evaluates the trade offs between the optimized ascent flight trajectory performance and the flight vehicle sizing driven by the engine mass and propellant requirements. Numerous mission, flight, and vehicle related requirements and constraints are satisfied in this process. Propulsion system configurations which incorporate dual-position nozzles are evaluated and compared to configurations using all fixed nozzles.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 76-162 , International Astronautical Congress; Oct 10, 1976 - Oct 16, 1976; Anaheim, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 13
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    Technology and methodology of separating two similar size aerospace vehicles within the atmosphere (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: During the past 10 years, the parallel separation, within the atmosphere, of two similar size aerospace vehicles has been investigated in technical areas such as static and dynamic stability, rocket exhaust plume interference, aerodynamic control, loads, and dynamic simulation. Advanced experimental and analysis techniques have been developed to analyze this problem. Results are presented which summarize some of this work. The effects of various parameters on the separation maneuver are illustrated using results from early and current space shuttle configurations. The technology and methodology that have been developed have helped verify the feasibility of separating similar size aerospace vehicles.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: AIAA PAPER 75-29 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Analysis of separation of the space shuttle orbiter from a large transport airplane (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of safely separating the space shuttle orbiter (140A/B) from the top of a large carrier vehicle (the C-5 airplane) at subsonic speeds was investigated. The longitudinal equations of motion for both vehicles were numerically integrated using a digital computer program which incorporates experimentally derived interference aerodynamic data to analyze the separation maneuver for various initial conditions. Separation of the space shuttle orbiter from a carrier vehicle was feasible for a range of dynamic-pressure and flight-path-angle conditions. By using an autopilot, the vehicle attitudes were held constant which ensured separation. Carrier-vehicle engine thrust, landing gear, and spoilers provide some flexibility in the separation maneuver.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-X-3492 , L-11074
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Integrating computer programs for engineering analysis and design (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The design of a third-generation system for integrating computer programs for engineering and design has been developed for the Aerospace Vehicle Interactive Design (AVID) system. This system consists of an engineering data management system, program interface software, a user interface, and a geometry system. A relational information system (ARIS) was developed specifically for the computer-aided engineering system. It is used for a repository of design data that are communicated between analysis programs, for a dictionary that describes these design data, for a directory that describes the analysis programs, and for other system functions. A method is described for interfacing independent analysis programs into a loosely-coupled design system. This method emphasizes an interactive extension of analysis techniques and manipulation of design data. Also, integrity mechanisms exist to maintain database correctness for multidisciplinary design tasks by an individual or a team of specialists. Finally, a prototype user interface program has been developed to aid in system utilization.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: AIAA PAPER 83-0597 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 16
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    The Aerospace Vehicle Interactive Design system (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Aerospace Vehicle Interactive Design (AVID) is a computer-aided design system that was developed for the conceptual and preliminary design of aerospace vehicles. The AVID system evolved from the application of several design approaches in an advanced concepts environment in which both mission requirements and vehicle configurations are continually changing. The basic AVID software facilitates the integration of independent analysis programs into a design system where the programs can be executed individually for analysis or executed in groups for design iterations and parametric studies. Programs that have been integrated into an AVID system for launch vehicle design include geometry, aerodynamics, propulsion, flight performance, mass properties, and economics.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-0233 , Aerospace Sciences Meeting; Jan 12, 1981 - Jan 15, 1981; St. Louis, MO
    Format: text
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    NASA TECHNICAL REPORTS
  • 17
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    Optimization and evaluation of main liquid rocket propulsion systems for advanced earth-to-orbit shuttles (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computerized preliminary design system is used to evaluate potential main liquid-rocket propulsion systems for advanced technology winged single-stage-to-orbit launch vehicles. Evaluated are trade-offs between ascent flight trajectory performance and flight vehicle sizing driven by engine mass and propellant requirements. Numerous mission, flight, and vehicle-related requirements and constraints are satisfied in the design process. With the design system, five dual-mode propulsion system concepts are compared to a baseline hydrogen and oxygen system in terms of the changes in vehicle dry mass and gross mass.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-972 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 18
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    Dual-fuel propulsion - Why it works, possible engines, and results of vehicle studies (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The reasons why dual-fuel propulsion works are discussed. Various engine options are discussed, and vehicle mass and cost results are presented for earth-to-orbit vehicles. The results indicate that dual-fuel propulsion is attractive, particularly with the dual-expander engine. A unique orbit-transfer vehicle is described which uses dual-fuel propulsion. One Space Shuttle flight and one flight of a heavy-lift Shuttle derivative are used for each orbit-transfer vehicle flight, and the payload capability is quite attractive.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-0878 , Conference on Advanced Technology for Future Space Systems; May 08, 1979 - May 10, 1979; Hampton, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 19
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    AVID - A design system for technology studies of advanced transportation concepts (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The basic AVID (Aerospace Vehicle Interactive Design) is a general system for conceptual and preliminary design currently being applied to a broad range of future space transportation and spacecraft vehicle concepts. AVID hardware includes a minicomputer allowing rapid designer interaction. AVID software includes (1) an executive program and communication data base which provide the automated capability to couple individual programs, either individually in an interactive mode or chained together in an automatic sequence mode; and (2) the individual technology and utility programs which provide analysis capability in areas such as graphics, aerodynamics, propulsion, flight performance, weights, sizing, and costs.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 79-0872 , Conference on Advanced Technology for Future Space Systems; May 08, 1979 - May 10, 1979; Hampton, VA
    Format: text
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    NASA TECHNICAL REPORTS
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