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Daniel Guggenheim School of Aerospace Engineering
Daniel Guggenheim School of Aerospace Engineering
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ItemExploration of the Design Space for the ABLV-GT SSTO Reusable Launch Vehicle(Georgia Institute of Technology, 2000-09) Bradford, John Edward ; Olds, John R. ; Bechtel, Ryan S. ; Cormier, Timothy A. ; Messitt, Donald G.The ABLV-GT is a conceptual design for an advanced reusable launch vehicle based on the current NASA Langley ABLV concept. It is a Vision Vehicle class, horizontal takeoff, horizontal landing singlestage-to-orbit vehicle. Main propulsion is provided by Aerojet's 'Strutjet' LOX/LH2 rocket-based combined cycle engine design. The ABLV-GT is designed to deliver 25,000 Ibs. to the orbit of the International Space Station from Kennedy Space Center. This paper will report the findings of a conceptual design study on the ABLV-GT performed over the last year by members of the Space Systems Design Lab at Georgia Tech. This work has been sponsored by the Advanced Reusable Transportation Technologies program office at NASA Marshall Space Flight Center. Details of the concept design including external and internal configuration, mass properties, trajectory analysis, aerodynamics, and aeroheating are given. This vehicle study resulted in the closure of 18 different vehicle designs. The trade variables included air-breathing transition Mach number, mechanical versus thermal choke engine, and payload weight. Initial results for a vehicle with a turbine-powered lowspeed propulsion system were generated and will be presented. Finally, a low earth orbit concept with a reduced payload weight will be shown.
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ItemHyperion: An SSTO Vision Vehicle Concept Utilizing Rocket-Based Combined Cycle Propulsion(Georgia Institute of Technology, 1999-11) Olds, John R. ; Bradford, John Edward ; Charania, Ashraf ; Ledsinger, Laura Anne ; McCormick, David Jeremy ; Sorensen, KirkThis paper reports the findings of a conceptual launch vehicle design study performed by members of the Space Systems Design Laboratory at Georgia Tech. Hyperion is a conceptual design for an advanced reusable launch vehicle in the Vision Vehicle class. It is a horizontal takeoff, horizontal landing SSTO vehicle utilizing LOX/LH2 ejector scramjet rocket-based combined cycle (RBCC) propulsion. Hyperion is designed to deliver 20,000 lb. to LEO from the Kennedy Space Center. Gross weight is estimated to be 800,700 lb. and dry weight is estimated to be 123,250 lb. for this mission. Preliminary analysis suggests that, with sufficient launch traffic, Hyperion recurring launch costs will be under 200 dollars per lb. of payload delivered to LEO. However, nonrecurring costs, including development cost and acquisition of three airframes, is expected to be nearly 10.7B dollars. The internal rate of return is only expected to be 8.24 percent. Details of the concept design including external and internal configuration, mass properties, engine performance, trajectory analysis, aeroheating results, and concept cost assessment are given. Highlights of the distributed, collaborative design approach and a summary of trade study results are also provided.
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ItemStargazer: A TSTO Bantam-X Vehicle Concept Utilizing Rocket-Based Combined Cycle Propulsion(Georgia Institute of Technology, 1999-11) Olds, John R. ; Ledsinger, Laura Anne ; Bradford, John Edward ; Charania, Ashraf ; McCormick, David Jeremy ; Komar, D. R.This paper presents a new conceptual launch vehicle design in the Bantam-X payload class. The new design is called Stargazer. Stargazer is a two-stage-to-orbit (TSTO) vehicle with a reusable flyback booster and an expendable LOX/RP upper stage. Its payload is 300 lbs. to low earth orbit. The Hankey wedge- shaped booster is powered by four LOX/LH2 ejector scramjet rocket-based combined-cycle engines. Advanced technologies are also used in the booster structures, thermal protection system, and other subsystems. Details of the concept design are given including external and internal configuration, mass properties, engine performance, trajectory analysis, aeroheating results, and a concept cost assessment. The final design was determined to have a gross mass of 115,450 lb. with a booster length of 99 ft. Recurring price per flight was estimated to be $3.49M. The overall conceptual design process and the individual tools and processes used for each discipline are outlined. A summary of trade study results is also given.
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ItemSCCREAM v.5: A Web-Based Airbreathing Propulsion Analysis Tool(Georgia Institute of Technology, 1999-06) Bradford, John Edward ; Olds, John R.To properly assess the advantages and disadvantages of various RBCC design options at the conceptual vehicle level, an engine performance analysis tool is required. This tool must be capable of modeling engine performance effects that will subsequently be propagated throughout the conceptual design process via trajectory analysis, weight assessment, fuel balance calculations, thermal environment, life cycle cost, etc. For a given engine configuration, the tool will need to generate engine thrust and Isp as a function of altitude and Mach number for each operating mode of an RBCC engine. A project to create a new computer program for the analysis of RBCC engines has already been initiated. Called SCCREAM, for Simulated Combined-Cycle Rocket Engine Analysis Module, it is intended for use in the conceptual phase of airbreathing launch vehicle design. This paper will detail the capabilities of the latest version of SCCREAM and present the results of validation efforts. Combustor thermodynamic properties and overall engine performance for a sample engine will be compared with industry standard codes. Results from the new scram-rocket mode will be discussed. Ejector mode performance plots generated over the web will also be presented.
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ItemImprovements and Enhancements to SCCREAM, A Conceptual RBCC Engine Analysis Tool(Georgia Institute of Technology, 1998-07) Bradford, John Edward ; Olds, John R.A rocket based combined-cycle engine analysis tool suitable for use in the conceptual design environment has recently been established. While this tool was being used in the design environment, new analysis capabilities were desired and areas for improvement were noted. This paper will detail the recent improvements made to the conceptual design tool, SCCREAM, and present the results generated by the added capabilities. The improvements range from an additional engine analysis mode, alternate propellant combinations, and a new user-interface which enables remote execution. The improvements and added capabilities to SCCREAM will be discussed and the program methodology will be examined in detail when appropriate. Results generated by SCCREAM’s new scramjet analysis mode are then shown to compare very well with an industry standard code, RJPA. Engine performance generated by SCCREAM for a single stage to orbit launch vehicle are then compared with historical airbreathing engine performance data, and other industry common analysis codes.
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ItemSCCREAM (Simulated Combined-Cycle Rocket Engine Analysis Module): A Conceptual RBCC Engine Design Tool(Georgia Institute of Technology, 1997-07) Olds, John R. ; Bradford, John EdwardRocket-based combined-cycle engines are currently under consideration for use on future, reusable launch vehicles. By combining traditional rocket and airbreathing operating modes into a single engine, multi-mode RBCC engines offer a number of advantages for launch vehicle designers including higher trajectory averaged Isp than pure rockets and higher installed thrust-to-weight ratios than pure airbreathers. This paper presents a new computer tool capable of predicting RBCC engine performance (thrust and Isp) over a wide range of flight conditions and engine operating modes. The tool is called SCCREAM - Simulated Combined-Cycle Rocket Engine Analysis Module. SCCREAM is an object-oriented workstation-level code written in C++. It uses quasi-1D flow analysis, component and combustion efficiencies, and an inlet pressure recovery schedule as simplifying assumptions. SCCREAM was created for the conceptual launch vehicle design environment and is capable of quickly generating large tables of engine performance data for use in trajectory optimization. An overview of SCCREAM and the program logic is presented. Results from SCCREAM are favorably compared to historical RBCC engine performance data and to data generated by other engine design tools.