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Aerospace Systems Design Laboratory (ASDL)
Aerospace Systems Design Laboratory (ASDL)
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ItemA Unified Economic View of Space Solar Power (SSP)(Georgia Institute of Technology, 2000-10) Charania, Ashraf ; Olds, John R.Space Solar Power (SSP) is a concept to beam energy from space to terrestrial power grids that could be feasible in about twenty to forty years. Due to the current climate of limited government funding for such large-scale space projects, NASA would prefer more industry involvement (technically and more important financially) in SSP. This study seeks to offer a unified economic view of SSP by examining the breadth of the SSP business case, from the development of the infrastructure (the actual SSP satellites) to on-orbit delivery. The indigenously developed Space Solar Power Abbreviated Economics (SSPATE) model is used to establish financial relationships between: 1.) the prices distinct Earth-to-orbit (ETO) and in- space transportation companies charge to a hypothetical company building Solar Power Satellites (SPS); and 2.) the financial metrics (Net- Present-Value, Internal Rate of Return, etc.) that can merit a legitimate business case for all three ventures. Deterministic and probabilistic models reveal that inherent trade-offs exist in either making the transportation companies (an ETO Inc. and In-Space Inc.) or infrastructure company (SSP Inc.) viable. Major reductions in SSP launch mass (even at the same cost as larger systems) is seen as one of the main mechanisms to alleviate this imbalance.
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ItemIn-Space Deployment Options for Large Space Solar Power Satellites(Georgia Institute of Technology, 2000-10) Olds, John R. ; Way, David Wesley ; Charania, Ashraf ; Budianto, Irene Arianti ; Marcus, Leland R.This research was performed at the Space Systems Design Lab at the Georgia Institute of Technology, Atlanta, GA, with the charter of identifying economically attractive candidate space transfer vehicle systems for ferrying components of Space Solar Power (SSP) satellites from Low Earth Orbit (LEO) to Geostationary Earth Orbit (GEO). An aggressive price goal of only $400/kg of payload was established in order to control the cost of transportation for the SSP satellite developer. A multi-step decision process was employed to down-select from a large number of candidate systems to four. The final four concepts were Nuclear Thermal Rocket (NTR), Solar Thermal Rocket (STR), a rotating tether, and Solar Electric Propulsion (SEP). Additional concepts considered were Dual-Mode (Chemical/SEP) and All-Chemical. Results show that the most economical concept is one which is highly reusable, has a short turn-around time, a long vehicle life, and small propellant requirements. These characteristics result in a low fleet size and therefore lower debt requirements. These characteristics also lower the Initial Mass in Low Earth Orbit (IMLEO) and therefore lower deployment costs. The goal of $400/kg, or 2.5cents/kW-hr, for in-space transportation costs is very aggressive and difficult to achieve.
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ItemSpace Tourism: Making it Work for Fun and Profit(Georgia Institute of Technology, 2000-10) Olds, John R. ; McCormick, David Jeremy ; Charania, Ashraf ; Marcus, Leland R.This paper summarizes the findings of a recent study of space tourism markets and vehicles conducted by the Space Systems Design Laboratory at Georgia Tech under sponsorship of the NASA Langley Research Center. The purpose of the study was to investigate and quantitatively model the driving economic factors and launch vehicle characteristics that affect businesses entering the space tourism industry. If the growing public interest in space tourism can be combined with an economically sound business plan, the opportunity to create a new and profitable era for space flight is possible. This new era will be one in which human space flight is routine and affordable for many more people. The results of the current study will hopefully serve as a guide to commercial businesses wishing to enter this potentially profitable emerging market.
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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.