Lazarus: A SSTO Hypersonic Vehicle Concept Utilizing RBCC and HEDM Propulsion Technologies

dc.contributor.author Young, David Anthony
dc.contributor.author Kokan, Timothy Salim
dc.contributor.author Clark, Ian G.
dc.contributor.author Tanner, Christopher
dc.contributor.author Wilhite, Alan W.
dc.contributor.corporatename American Institute of Aeronautics and Astronautics
dc.date.accessioned 2007-05-30T21:19:19Z
dc.date.available 2007-05-30T21:19:19Z
dc.date.issued 2006-11
dc.description 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference November 2006, Canberra, Australia en_US
dc.description.abstract Lazarus is an unmanned single stage reusable launch vehicle concept utilizing advanced propulsion concepts such as rocket based combined cycle engine (RBCC) and high energy density material (HEDM) propellants. These advanced propulsion elements make the Lazarus launch vehicle both feasible and viable in today's highly competitive market. The Lazarus concept is powered by six rocket based combined cycle engines. These engines are designed to operate with HEDM fuel and liquid oxygen (LOX). During atmospheric flight the LOX is augmented by air traveling through the engines and the resulting propellant mass fractions make single stage to orbit (SSTO) possible. A typical hindrance to SSTO vehicles are the large wings and landing gear necessary for takeoff of a fully fueled vehicle. The Lazarus concept addresses this problem by using a sled to take off horizontally. This sled accelerates the vehicle to over 500 mph using the launch vehicle engines and a propellant cross feed system. This propellant feed system allows the vehicle to accelerate using its own propulsion system without carrying the necessary fuel required while it is attached to the sled. Lazarus is designed to deliver 5,000 lbs of payload to a 100 nmi x 100 nmi x 28.5° orbit due East out of Kennedy Space Center (KSC). This mission design allows for rapid redeployment of small orbital assets with little launch preparation. Lazarus is also designed for a secondary strike mission. The high speed and long range inherent in a SSTO launch vehicle make it an ideal global strike platform. Details of the conceptual design process used for Lazarus are included in this paper. The disciplines used in the design include aerodynamics, configuration, propulsion design, trajectory, mass properties, cost, operations, reliability and safety. Each of these disciplines was computed using a conceptual design tool similar to that used in industry. These disciplines were then combined into an integrated design process and used to minimize the gross weight of the Lazarus design.
dc.identifier.uri http://hdl.handle.net/1853/14679
dc.language.iso en_US en_US
dc.publisher Georgia Institute of Technology en_US
dc.publisher.original American Institute of Aeronautics and Astronautics (AIAA)
dc.relation.ispartofseries SSDL ; AIAA-2006-8099 en_US
dc.subject High-energy-density material en_US
dc.subject Launch vehicles en_US
dc.subject Lazarus en_US
dc.subject Liquid oxygen en_US
dc.subject Rocket-based combined-cycle (RBCC) en_US
dc.subject Single-stage to orbit (SSTO) en_US
dc.title Lazarus: A SSTO Hypersonic Vehicle Concept Utilizing RBCC and HEDM Propulsion Technologies en_US
dc.type Text
dc.type.genre Paper
dspace.entity.type Publication
local.contributor.corporatename Space Systems Design Laboratory (SSDL)
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
local.contributor.corporatename Daniel Guggenheim School of Aerospace Engineering
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relation.isOrgUnitOfPublication a348b767-ea7e-4789-af1f-1f1d5925fb65
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