This 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 single-stageto-orbit (SSTO) vehicle utilizing LOX/LH2 ejector scramjet rocket-based combined cycle (RBCC) propulsion. Hyperion is designed to deliver 20,000 lb. to low earth orbit from 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 per lb. of payload delivered to low earth orbit. However, non-recurring costs including development cost and acquisition of three airframes, is expected to be nearly $10.7B. The internal rate of return is only expected to be 8.24%. 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. NOMENCLATURE C t thrust coefficient I sp specific impulse (sec.) I* equivalent trajectory averaged I sp (sec.) MR mass ratio (gross weight/burnout weight) q dynamic pressure (psf) T/W e
The Rocket Engine Design Tool for Optimal Performance-2 (REDTOP-2) is a newly created engineering design tool for use in the conceptual and preliminary design of space transportation systems utilizing liquid propulsion rocket engines. REDTOP-2, one of many unique engineering tools commercially available from SpaceWorks Engineering, Inc. (SEI), represents a novel entry into the current suite of propulsion modeling tools. REDTOP-2 is capable of analyzing the flowpath characteristics of numerous engine configurations to perform a power balance of the turbomachinery hardware (pumps and turbines) to achieve a user specified main chamber combustion pressure. The engine performance, in terms of thrust and specific impulse (Isp), is then determined based on the results of this power balance and the flow conditions (pressure, temperature, flowrate, etc.) in the chamber(s) and nozzle(s). Engine weight is assessed at the main component level using a combination of empirical and physics based analysis methods to provide vacuum, ambient, and sea-level thrust-to-weight (T/W) values. A cost model capable of predicting engine development, first unit, and production costs has been incorporated. Additionally, REDTOP-2 features a topdown modeling approach for computing engine safety and reliability metrics. REDTOP-2 is written in the modern, object-oriented C++ programming language and will execute on PC, Mac, and SGI platforms. Execution times are on the order of 30 seconds to 5 minutes, depending on the computing platform, engine configuration and design option selected by the user. User interface options currently include a command-line execution with ASCII file manipulation, filewrappers for use in Phoenix Integration's ModelCenter© environment, and a PC-based graphical user interface (GUI). This paper will describe the REDTOP-2 tool and its capabilities. Sample results obtained from exercising the tool for a number of different existing engine designs will be presented. Results from a multi-variable sensitivity study on a LOX/LH2 fuel-rich, single preburner staged-combustion engine will be highlighted. Two sample applications involving vehicle designs will be discussed. The first involves probabilistic/uncertainty analysis for an all-rocket vehicle design and the second the rocket main propulsion system analysis of an airbreathing, two-stage RLV concept with first stage tail-rockets and all-rocket second stage propulsion. Finally, future directions in the development of REDTOP-2 will be discussed.
An independent assessment of the Advanced Reusable Transportation System (ARTS) has been conducted. The ARTS concept is an all-rocket, fully reusable launch vehicle utilizing electromagnetic launch assist. ARTS is fitted with a dual-fuel main propulsion system utilizing flight proven Space Shuttle Main Engines and RD-180s. Nominally, the vehicle is intended to operate without a crew using autonomous guidance and control. Conceptual analysis shows that the vehicle could boost a payload of 48,140 lbs to a 110 nmi circular orbit in its baseline configuration. The DDT&E cost of such a system is estimated to be $8.8B (FY2003) using existing liquid rocket engines, while the total cost to the first vehicle is $11B. An alternative design configuration incorporating an additional SSME in the propulsion system is also explored. With this increased thrust, the payload potential is shown to increase to 60,770 lbs, while the cost to first vehicle rises to $12.1B. A summary of the disciplinary design tools used in this analysis, including mass properties, trajectory simulation, aerodynamics, and non-recurring cost is provided. The implementation of these tools in a collaborative design process is also discussed. NOMENCLATURE CAD
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-toorbit (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. NOMENCLATURE C t thrust coefficient I sp specific impulse (sec.) q dynamic pressure (psf) T/W e engine thrust-to-weight ratio This paper summarizes part of an 18 month Bantam-X concept study conducted by the Space Systems Design Laboratory at Georgia Tech with the support and collaboration of NASA Marshall Space Flight Center. The study goal was to investigate a promising concept based on rocket-based combinedcycle (RBCC) propulsion for longer range Bantam-class missions. NASA MSFC currently has an ongoing development program in RBCC engines.
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