Atomic Hydrogen as a Launch Vehicle Propellant - NASA Technical ...
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Z
-_
:NASATechnical
Memorandum
162459
_
.....
AIAA-90-0715
Atomic Hydrogen Vehicle Propellant
Bryan Lewis
as a Launch
A. Palaszewski Research Center
Cleveland,
Ohio
Prepared for the 28th Aerospace Sciences Meeting sponsored by the American Institute Reno, Nevada, January 8-11, 1990 LAUNCH VEHICLE
"ROPrLLA.T
of Aeronautics
(NASA)
]Z p CqCL
BiI A
and Astronautics
21! G__/ZO
Uncl as 0754_I0
ATOMIC
HYDROGEN
AS
A LAUNCH
Bryan National
A.
Aeronautics Lewis
An analysis launch vehicles of the would
of was
facilities be needed
presented. for two
several atomic conducted. A
and the for these
The Gross systems
hydrogen discussion
technologies vehicles
is
Liftoff Weights were estimated;
that also
(GLOW) their
specific impulses (Isp) were 750 and 1500 ib_-s/ib m . The atomic hydrogen launch vehicles were also compared to the currently planned Advanced Launch System design concepts. Very significant GLOW reductions of 52 to 85 percent are possible over the Advanced Launch System designs. Applying atomic was than mass
hydrogen
propellants
also considered. 750 Ibt-s/Ibm) savings over
to
upper
Space Administration Center
Ohio
Abstract
44135
MECO
Main
Mt
Final
Mo
Initial
NASA
National Aeronautics Administration
O2/H 2
Oxygen/Hydrogen
02/RP-I
Oxygen/Kerosene
STS
Space
Greek
stages
Very high Isp (greater is needed to enable advanced oxygen/hydrogen
a
PROPELLANT
Palaszewski*
and Research
Cleveland,
VEHICLE
Engine
Cut
Mass
Off
(kg)
Mass
(kg) and
Transportation
Space
System
Symbols
AV
Velocity
Change
(km/s)
propulsion. Introduction Associated
with
high-Isp challenging fields are hydrogen magnetic to be storage
UD
the
potential
benefits
atomic hydrogen are several problems. Very high magnetic required to maintain the atomic
in a solid hydrogen matrix. The field strength has been estimated 30 kilogauss (3 Tesla). Also the temperature of the propellant is 4
K. This very low temperature will large refrigeration facility for vehicle. The design considerations very high recombination propellant are also discussed. tion rate of 210 cm/s is atomic hydrogen. This high rate the
of
can produce very launch vehicle.
segmentation may be needed rate.
to to
high Unique
"inhibit" reduce
require a the launch for a
rate
for the A recombinapredicted for recombination
acceleration insulation
the propellant its recombination
Nomenclature AFAL
Air
ALS
Advanced
BECO
Booster
GLOW
Gross
HEDM
High-Energy
IUS
Inertial
Upper
Isp
Specific
Impulse
JPL
Jet
Propulsion
LEO
Low
Earth
Force
Astronautics Launch
for or
Laboratory
System
In the vehicle
development designs,
of the
NASA need
advanced launch for increased
payload delivery to orbit, increased reliability and reduced launch cost are crucial considerations. New technologies are being studied for the new vehicles such as the Advanced Launch System and the ShuttleC (Refs. includes avionics, production
i, 2, 3 and 4). These technologies lightweight tankage and structures, aerothermodynamics, automated facilities, operations and rocket
engines. Additional possible propellant
performance
increases
with the combinations.
use
of Both
will
be
high-energy increases
the propellant I,p and increases propellant density are methods of the launch vehicle's performance.
in
in the improving Many
possible propellant combinations that can produce high I,v are being studied both experimentally and theoretically. These studies are underway as part of the United States Air Force High Energy Density Materials (HEDM) Program (Ref. 5) and the NASA-Lewis Research Center Advanced Concepts Program.
I,p is atomic hydrogen. In this potential benefits and the advancements that are required successful propellant
use are
of atomic discussed.
increased paper, the technology for the
hydrogen Using
as atomic
hydrogen will require new propellant production and storage facilities. These new facility and production requirements must be contrasted with the significant performance propellant.
capability
of
the
new
a
4O
metric tons The ALS and deliver 96 are used performance
