Title:
Lazarus: A SSTO Hypersonic Vehicle Concept Utilizing RBCC and HEDM Propulsion Technologies
Lazarus: A SSTO Hypersonic Vehicle Concept Utilizing RBCC and HEDM Propulsion Technologies
Author(s)
Young, David Anthony
Kokan, Timothy Salim
Clark, Ian G.
Tanner, Christopher
Wilhite, Alan W.
Kokan, Timothy Salim
Clark, Ian G.
Tanner, Christopher
Wilhite, Alan W.
Advisor(s)
Editor(s)
Collections
Supplementary to
Permanent Link
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.
Sponsor
Date Issued
2006-11
Extent
Resource Type
Text
Resource Subtype
Paper