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

Young, David Anthony; Kokan, Timothy Salim; Clark, Ian G.; Tanner, Christopher; Wilhite, Alan W.

Title:

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
relation.isOrgUnitOfPublication	dc68da3d-4cfe-4508-a4b0-35ba8de923fb
relation.isOrgUnitOfPublication	a348b767-ea7e-4789-af1f-1f1d5925fb65
relation.isOrgUnitOfPublication	a348b767-ea7e-4789-af1f-1f1d5925fb65