Several programs are investigating the benefits of advanced propellant and propulsion systems for future launch vehicles and upper stages. The two major research areas are the Metallized Propellants Program and the Advanced Concepts Program. Both of these programs have theoretical and experimental studies underway to determine the system-level performance effects of these propellants on future NASA vehicles

Palaszewski, Bryan A.

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NASA Technical Memorandum 103096
Advanced Launch Vehicle Propulsion at
the NASA Lewis Research Center
Bryan A. Palaszewski
Lewis Research Center
Cleveland, Ohio
Prepared for the
High Energy Density Materials Contractors' Conference
sponsored by the Air Force Office of Scientific Research
Long Beach, California, February 26-28, 1990
https://ntrs.nasa.gov/search.jsp?R=19900010794 2020-03-19T22:47:15+00:00Z

ADVANCED LAUNCH VEHICLE PROPULSION
AT THE
NASA LEWIS RESEARCH CENTER
Bryan Palaszewski
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, OH
ABSTRACT
At the NASA Lewis Research Center, several programs are
investigating the benefits of advanced propellant and propulsion
systems for future launch vehicles and upper stages. The two major
research areas are the Metallized Propellants Program and the
Advanced Concepts Program. Both of these programs have theoretical
and experimental studies underway to determine the system-level
performance effects of these propellants on future NASA vehicles.
METALLIZED PROPELLANTS
The Metallized Propellants Program is determining the performance
and the system benefits of propellant combinations such as
oxygen/kerosene/aluminum and oxygen/hydrogen/aluminum. In these
combinations, the aluminum is gelled with the kerosene or the
hydrogen. Adding the aluminum to the propellant increases its
overall density and/or the specific impulse. The density increases
reduce the volume of the vehicle, the tank mass and the total
launch mass. All of these factors also contribute to reducing the
drag of the launch vehicle during ascent. The specific impulse
increases further reduce the vehicle size and mass. These mass
reductions can significantly reduce the launch mass to orbit and
potentially reduce the overall cost of space transportation.
Vehicle and System Performance Studies
A set of systems studies to determine the benefits for metallized
propellant are underway. Using detailed upper stage and launch
vehicle mission analysis and design codes, the payload performance
for various propellant combinations can be determined. These
studies include earth orbital, planetary and lunar missions. The
initial mass in Low Earth Orbit (LEO) reductions over existing and
planned propulsion systems are estimated. These LEO mass savings
can also be translated into payload mass increases.
For launch vehicles, metallized propellants can provide increased
propellant density. A higher density propellant can reduce the size
of the launch vehicle stages and its dry mass. The reduced size
reduces the drag losses on the vehicle. Also, the higher density
propellant provides the ability to improve the Space Transportation
Systems (STS). Liquid Rocket Boosters with the same physical
dimensions as the current Solid Rocket Boosters have been studied
by NASA and its contractors. Used in the Liquid Rocket Boosters,
metallized propellants can deliver the same payload to LEO as the
current Solid Rocket Boosters within their volume constraints.
Other liquid propellant combinations cannot deliver the same
payload within these volume restrictions. Metallized propellants
can also be employed in improved versions of the current Atlas,
Delta and Titan systems.
Experimental Program
In the experimental program, both in-house and contracted experi-
mental work are continuing. Subscale test hardware using oxygen/
hydrocarbon/aluminum propellants has been fired at NASA-Lewis (Ref.
i). This test apparatus has produced preliminary data on the
aluminum combustion, specific impulse efficiency and the erosion
of the injector elements and the nozzle. Additional experiments are
being conducted using this and other subscale hardware. Higher
thrust levels will be tested in future contracted work. Propellant
rheology is also being studied both with computer models and test
facilities. Propellant batches are being formulated to determine
their flow properties and their long-term storage properties. Other
contracted research into novel propellants and gellants is also
funded under the NASA Research Announcement (NRA) Program.
University Research Program
Penn State University is conducting a series df experimental and
theoretical investigations of the formation of aluminum oxide and
its effect on metallized propellant performance. This work has led
to additional understanding of the mechanisms for agglomeration and
breakup of aluminum oxide particles in the rocket exhaust.
ADVANCED CONCEPTS FOR CHEMICAL PROPULSION
In the Advanced Concepts Program, very-high energy propellants,
such as atomic hydrogen and other High Energy Density Matter (HEDM)
propellant candidates, are being studied. This program has received
much valuable information from the research underway at the Air
Force Astronautics Laboratory and the Air Force Office of
Scientific Research.
Many of the high energy propellants provide large increases in
specific impulse. But along with the great potential of high-energy
propellants are the attendant problems of free-radicals: produc-
tion, storage and transportation. All of these factors are being
investigated to determine the critical research directions for
applying this material to propulsion. Only if these technical
barriers are overcome will we gain the benefits of these
propellants and propulsion systems.
Vehicle and System Performance Studies
Currently, atomic hydrogen is being analyzed for launch vehicles
and upper stages. Using atomic hydrogen, the launch mass of future
launch vehicles can be reduced by a factor of 3 to i0 over
currently planned Space Transportation System-Cargo (STS-C) and
2
Advanced Launch System (ALS) vehicles (Ref. 2). The specific
impulse range to deliver this reduced mass is 750 to 1500 ibf-
s/ib m. Advanced upper stages using this propellant can also provide
a benefit to the planetary program. Placing a spacecraft on a very
high energy trajectory is possible if the specific impulse of
atomic hydrogen can exceed 750 ib_-s/ib m.
In addition to the vehicle studies, the facilities for producing,
transporting and storing atomic hydrogen are being analyzed. Large
cryogenic storage facilities and magnetic field coils or generators
are required for atomic hydrogen propellants. These facilities are
being studied to determine the what size facility is best suited
to each launch vehicle configuration.
University Research Program
A set of experimental and theoretical studies are underway at the
University of Hawaii at Manoa and the University of Iowa (Iowa
City). Atomic hydrogen research is being conducted at the
University of Hawaii. The storage density and the methods which
may enable increases in that density are under investigation.
Experiments are being conducted to understand the energy release
phenomena during recombination. The atomic hydrogen is stored in
solid cryogenic hydrogen. Tritium decay is used to form the atomic
hydrogen in the solid hydrogen.
At the University of Iowa, a survey of advanced propellants is
being conducted. From this survey, the potential specific impulse
of the very advanced propellants will be estimated. This study will
allow a preliminary screening of the high energy density
propellants and identify which propellant may be applicable to
future NASA missions.
CONCLUSIONS
Advanced propulsion technology can provide several benefits to
high-energy space missions. Some of these benefits are signifi-
cantly reduced launch mass, increased payload delivery and
potentially lower transportation system costs. Several current
research programs in both metallized propellants and advanced
concepts are identifying the research directions to gain
significant benefits for future NASA missions. With a combination
of in-house studies and experiments, contracted research and
university grants, a wide range of propulsion system technologies
with potentially significant benefits are under investigation.
REFERENCES
Galecki, D., "Ignition and Combustion of Metallized Propellants,"
NASA Lewis Research Center, AIAA Paper 89-2883, presented at the
25th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Monterey, CA
July 10-12, 1989.
Palaszewski, B., "Atomic Hydrogen As A Launch Vehicle Propellant,
NASA Lewis Research Center, NASA Technical Memorandum 102459, AIAA
Paper 90-0715, presented at the 28th AIAA Aerospace Science
Meeting, Reno, NV, January 8-11, 1990.
Report Documentation Page
Nalional Aeronaulics and
Space Administration
t. Report No. 2. Government Accession No. 3. Recipient's Catalog No.
NASA TM- 103096
5. Report Date4. Title and Subtitle
Advanced Launch Vehicle Propulsion at the NASA Lewis Research Center
7. Author(s)
Bryan A. Palaszewski
9. Performing Organization Name and Address
National Aeronautics and Space Administration
Lewis Research Center
Cleveland Ohio 44135-3191
12. Sponsoring Agency Name and Address
National Aeronautics and Space Administration
Washington, D.C. 20546-0001
6. Performing Organization Code
8. Performing Organization Report No.
E-5417
10. Work Unit No.
506-42
11. Contract or Grant No.
13. Type of Report and Period Covered
Technical Memorandum
14. Sponsoring Agency Code
15. Supplementary Notes
Prepared for the High Energy Density Materials Contractors' Conference sponsored by the Air Force Office of
Scientific Research, Long Beach, California, February 26-28, 1990.
16. Abstract
At the NASA Lewis Research Center, several programs are investigating the benefits of advanced propellant and
propulsion systems for future launch vehicles and upper stages. The two major research areas are the Metallized
Propellants Program and the Advanced Concepts Program. Both of these programs have theoretical and
experimental studies underway to determine the system-level performance effects of these propellants on future
NASA vehicles.
18. Distribution Statement
Unclassified- Unlimited
Subject Category 15
17. Key Words (Suggested by Author(s))
Metallized propellants
Launch vehicles
Atomic Hydrogen
High energy density matter
19. Security Classif. (of this report) 20. Security Classif. (of this page) 21. No. of pages
Unclassified Unclassified 6
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