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Paul Gloyer received his
B.S. in Aerospace Engineering (with Honors) from the University
of Kansas in May 1990. He then joined the
University of Tennessee Space Institute where he earned a Master
of Science degree in Aerospace Engineering in May 1993.
He also worked toward a Ph.D. in Aerospace Engineering until
1995. His graduate work focused on combustion instability
research. From 1995 to 2004, he served as Principal Engineer at
AeroAstro Inc, later becoming PacAstro (PA), before purchasing
the company which is now part of Gloyer-Taylor Laboratories,
LLC.*
In 2006, he relocated to the
University of Tennessee Space Institute for its strategic
location in the Tennessee Valley Corridor; he now manages his
firm while assisting the institute through his service as
Teaching Associate in the field of Aerospace Engineering; he
offers highly sought after short and semester-long
state-of-the-art courses on liquid and hybrid rocket engine
design; he also mentors graduate student teams and guides them
in developing and building functional rocket engines.
Paul Gloyer is an experienced
developer of advanced technologies and innovative propulsion
systems, and has been instrumental in the development of several
advanced aerospace systems, including the development of the
15,000 lbf thrust PA-E liquid oxygen cooled rocket engine, the
SPORT orbit transfer vehicle, and the Encounter solar sailcraft.
As President of Gloyer-Taylor Laboratories, LLC, he is actively
developing a variety of innovative propulsion technologies. His
experience includes:
–Program Manager for the
development of the PA-E Rocket Engine (AFRL Ph II SBIR)
–Principal Investigator for the development of a hypersonic
aerobraking system for an orbit transfer vehicle (AFRL Ph I
& II SBIR)
–Principal Investigator for the development of an
aerobraking system for deorbiting spacecraft at end-of-life
(DARPA Ph I SBIR)
–Principal Investigator for the development of the SHERPA
orbit transfer vehicle (MDA Ph I & II SBIR)
–Principal Investigator for the development of the N2O MiPS
micro propulsion system (NASA Ph I SBIR)
–Principal Investigator for the development of Metal Vaccro
bonding technology (NASA Ph I SBIR)
–Principal Investigator for the examination of nanosatellite
integration and test processes (NASA Ph I SBIR)
–Lead Engineer and mission architect for the Encounter solar
sailcraft (commercial program)
–Lead Engineer and mission architect for the SPORT orbit
transfer vehicle (commercial program)
–Lead Engineer for the development of the PA-X suborbital
rocket (AFRL Ph II SBIR)
–Consultant on the development of Orbital Technology’s
vortex rocket engine
–Consultant on the development of Rocketplane-XP propulsion
system for Rocketplane, Ltd.
Some of his patents and design
awards include:
(1.) U.S. Patent #6,550,720 “Aerobraking Orbit Transfer Vehicle”
(2.) U.S. Patent #6,561,461 “Orbit Transfer Vehicle with Support
Services”
(3.) 2nd place, 1989-1990 AIAA Undergraduate Team Airplane
Design
Competition
(4.) 1st place, 1992-1993 AIAA Graduate Team Space Design
Competition
(5.) 3rd place, 1993-1994 AIAA Graduate Team Rocket Engine
Design
Competition
(6.) 1st place, 1994-1995 AIAA Graduate Team Space Design
Competition.
Some of his publications include:
(1.) Gloyer, P., Pedlikin, J. and Repas, G., “PA-E15k Liquid
Oxygen Cooled Injector Design, Analysis and Test Results,” 52nd
JANNAF Propulsion Meeting, May 2004.
(2.) Gloyer, P., Pedlikin, J. and Repas, G., “The Identification
and Elimination of the PA-E15k Rocket Engine Instability
Mechanism,” 52nd JANNAF Propulsion Meeting, May 2004.
(3.) Gloyer, P., “A Preliminary Study of Oxygen Rich Combustion
Gas Generator Technology for LOX Tank Pressurization,” M.S.
Thesis, University of Tennessee, Knoxville, TN, May 1993.
(4.) Gloyer, P., “Small Payload ORbit Transfer (SPORT™) system:
An Innovative Approach to Lowering Mission Costs Without
Increased Risk,” 14th Annual USU Conference on Small Satellites,
SSC00-IV-6, Logan, Utah, August 2000.
(5.) Gloyer, P., Robinson, T., et al., “Aerobraking to Lower
Apogee in Earth Orbit with the Small Payload Orbit Transfer
(SPORT™) Microsatellite Vehicle,” 15th Annual USU Conference on
Small Satellites, SSC01-XI-8, Logan, Utah, August 2001.
(6.) Rogan, J., Gloyer, P., et al., “Encounter 2001: Sailing to
the Stars,” 15th Annual USU Conference on Small Satellites,
SSC01-II-2, Logan, Utah, August 2001.
(7.) Cohen, D., Gloyer, P., and Rogan, “Preliminary Design of a
High Performance Solar Sailing Mission,” 16th Annual USU
Conference on Small Satellites, SSC02-II-5, Logan, Utah, August
2002.
(8.) Rogers, A., Gloyer, P., Carlson, R., and Buckley, S.,
“SHERPA: A Flexible, Modular Spacecraft for Orbit Transfer and
On-Orbit Operations,” 17th Annual USU Conference on Small
Satellites, SSC03-II-2, Logan, Utah, August 2003.
*Gloyer-Taylor Laboratories LLC
was formed in early 2004 from a merger of PacAstro and Aspect
Engineering. PacAstro was originally founded in the late
eighties and was focused on developing the PA-2 Small Launch
Vehicle and supporting rocket technologies. PacAstro
achievements include the development of the PA-X Suborbital
technology demonstration rocket, the 15,000 lbf vacuum thrust
PA-E15k rocket engine, and the 30,000 lbf vacuum thrust PA-E30k
rocket engine. PacAstro was spun off from its parent company,
AeroAstro Inc., in 2003 in preparation for the merger with
Aspect Engineering.
In late 2005, the PacAstro division of Gloyer-Taylor
Laboratories LLC relocated to Tullahoma, Tennessee after the
Waveland, Mississippi office was destroyed by hurricane Katrina.
The new PacAstro office is located on the campus of the
University of Tennessee Space Institute (UTSI), next to the Air
Force Arnold Engineering and Development Center (AEDC). The
PacAstro office is equipped with several computer workstations
with rocket design tools, including design and analysis
worksheets, SolidWorks 3D solid modeling and CEQUEL combustion
chemistry code. As part of this relocation, Gloyer-Taylor
Laboratories LLC has set up a joint propulsion research facility
with UTSI.**
The Aspect Engineering division of Gloyer-Taylor Laboratories
LLC is located in Murrieta, California. The California office
has computer workstations with both 2-D CAD and 3-D parametric
solid modeling software. This office also uses spreadsheets and
proprietary software in the design and evaluation of composite
pressure vessels and tankage. NASA-generated software LEW-10352
is used in the generation of dome contours for filament wound
pressure vessels. The California office has in-house filament
winding capability with a CMC model ULD computer-controlled
filament winding machine capable of producing parts up to 24
inches in diameter, Fibergraphix software for pattern
generation, a programmable oven for laminate curing, and 0ºF
freezer for storage of prepreg materials and pre-mixed
adhesives.
Lastly, the facilities and practices used during this effort
meet the environmental laws and regulations of federal, state
(California and Tennessee), and local Governments for, but not
limited to, the following groupings: airborne emissions,
waterborne effluents, external radiation levels, outdoor noise,
solid and bulk waste disposal practices, and handling and
storage of toxic and hazardous materials.
**Gloyer-Taylor Laboratories LLC has established a
propulsion research facility at the University of Tennessee
Space Institute. This facility leverages the infrastructure and
data acquisition systems offered by the UTSI Research
Facilities. The Gloyer-Taylor Laboratories LLC facility includes
several propulsion test systems; in what follows, these systems
are described.
Hybrid Rocket Test System. This system allows testing of
conventional hybrid rocket fuel grains. It permits the use of
transparent fuel grains, such as acrylic, to enable optical
examination of the combustion flow field and fuel regression.
The system also allows testing of different fuels up to 2 inches
in grain diameter, and the use of flat sidewalls to minimize
optical distortion during flow visualization.
Vortex Hybrid Rocket Test System. This system allows
testing of vortex flow fields in a combustion chamber; it was
instrumental in the original vortex hybrid rocket research,
which Paul Gloyer used to initiate the vortex technology under
development by Orbital Technologies Corporation (ORBITEC). This
system comprises transparent sidewalls to permit optical
examination of the combustion flow fields and fuel regression.
The system allows testing of fuel grains up to 4 inches in
diameter and a wide variety of vortex flow fields, including
unidirectional, bidirectional, monopole, and multipole vortices.
Propellant Chemistry Test System. This system allows
chemicals to be mixed remotely to explore alternative propellant
chemistries. After mixing, the system permits the new propellant
grain to be immediately tested in rocket combustion chambers to
evaluate propellant performance.
Rocket Propulsion System Test System. Currently under
development with internal funding, this system can allow testing
of rockets with thrust levels up to 5,000 lbf. This unit is
equipped to test monopropellant, hybrid and bipropellant rocket
engines, and their associated pressurization and propellant feed
systems. |
