Engineer Control
Resume:
GEORGE P. DAVAILUS
******.********@***.***
**** ******** ***** **, **********, AL 35801
RESEARCH AND DEVELOPMENT SCIENTIST/ENGINEER
Guidance, Navigation, and Control Algorithms ~ Software Development ~ UNIX
~ Windows ~ System Analysis and Simulation ~ Proposal Development ~ C/C++ ~
FORTRAN ~ Matlab
. Secret Security Clearance (Inactive)
INVENTED ALGORITHMS/EQUATIONS
Linear Time Invariant (LTI) Six Degree of Freedom Differential Equations
. Possesses the unique and exclusive capability to devise GNC algorithms
for difficult aerospace maneuvering scenarios without using gain
scheduling or other types of nonlinear control.
. Developed a 3D dynamic geometric/graphical flight dynamics solution
for guidance and autopilot commands.
. Currently developing a full fidelity six degree of freedom (6-DOF)
state feedback control loop with constant gains using quaternion
mathematics to separate inertial and body rotational dynamics.
PROFESSIONAL SUMMARY
Guidance, Navigation, and Control (GNC) Engineer; Technical Lead for SLS
Mass Properties 2012 to present
Aerodyne Industries (Jacobs Engineering Subcontractor), Huntsville, AL
. Technical lead for validating component and integrated vehicle mass
properties values for the Space Launch System.
. Included more detailed atmospheric models in a 6-DOF simulation and
validated them with Monte-Carlo methods.
. Analyzed dynamics of asynchronous solid rocket booster (SRB) separation
from the core with Monte-Carlo methods.
Lead Guidance, Navigation, and Control (GNC) Engineer
2010 to 2011
Masten Space Systems, Mojave, CA
. Matlab 6-DOF suborbital vertical takeoff vertical landing (VTVL) rocket
flight simulation (Autocoded to C)
o Created flight profiles up to 30 km in altitude in preparation for
NASA CRuSR launches.
o Modified vehicle properties (mass properties, engine
characteristics, rcs, etc.) and analyzed simulation results for new
suborbital VTVL rocket to ensure attitude control system stability
and nominal mission conditions.
. Hardware in the Loop (HWIL) simulation (written in C)
o Validated flight profiles up to 5 km in altitude for NASA CRuSR
launches including abort condition limits.
o Analyzed HWIL simulation results for planned vehicle flight tests
to ensure parameters were properly set.
. Hands on operational/field engine/vehicle testing
o Issued commands remotely to onboard flight management system
(activating/deactivating valves, testing various engine components,
initiating engine ignition) during field testing.
o Created a detailed checklist for flight preparations and
suggestions for dealing with off nominal conditions.
o Set up equipment during engine/flight test preparations including
wireless and GPS antennas.
. Lead Investigator for NASA SBIR Proposal Submission (Navigation and
Flight Dynamics Software Topic)
o Proposed using a quaternion exponential Kalman (QEK) filter to map
the nonlinear state equations to an equivalent linear space to meet
NASA's objective of improving the navigation filter for GNC
systems.
Guidance, Navigation, and Control (GNC) Engineer
2008 to 2009
Miltec Missiles and Space, Huntsville, AL
. Upper atmospheric hypersonic glider 6-DOF simulation (written in FORTRAN)
o Conducted linear stability analysis on glider endo- and exo-
atmospheric maneuvers.
o Conducted research into and began development of a dynamic
inversion autopilot.
o Began applying quaternion exponentials to autopilot design to
improve control system robustness
. Lead Investigator for AFRL Broad Agency Announcement (BAA) Proposal
Submission (Responsive Space Attitude)
o Searched through BAAs for suitable topics, discovered a Responsive
Space Attitude Determination and Control solicitation, and
confirmed compatibility of topic with research interests with AFRL
point of contact.
o Proposed using quaternion mathematics to develop a flight control
solution for GNC design time reduction.
GEORGE P. DAVAILUS
Page 2
. Integration of C++ foreign anti-tank 6-DOF missile distributed simulation
with scene generator
o Tested simulation autopilot with step commands, zero acceleration
and step acceleration commands.
o Modified and debugged line of sight (LOS) proportional derivative
guidance subroutine using azimuth and elevation angles to the
missile and target, including guidance gain tuning for trajectory
optimization.
o Integrated missile simulation into a distributed simulation
containing a scene generator and a missile/target tracker,
including synchronizing the different applications and retuning the
guidance gains.
o Developed a roll autopilot to keep the missile at a zero roll
angle.
Doctoral Student Research Assistantship, Old Dominion University, Norfolk,
VA 2003 to 2008
. Invented a new type of eigenvalue for quaternion mathematics to
facilitate development of a linear time invariant (LTI) set of 6-DOF
equations. Currently formulating a quaternion frequency domain method of
solution.
. Dissertation research in inertial guidance, navigation and attitude
control.
. Presented conference papers at professional AIAA conferences/exhibits.
Research Scientist and Engineer (GS-12 Series 1520 Mathematician)
1990 to 2003
Naval Surface Warfare Center, Dahlgren Division, Dahlgren, VA
. SLBM Research and Analysis Division
o Developed a simulation for an experimental flapped re-entry body
and analyzed the resulting trajectory.
o Reduced 6-DOF reentry simulation execution time by two-thirds by
fitting a time varying sine wave to the quaternion components and
switching the state vector from angular velocity to quaternion
first derivative.
o Investigated further hypersonic 6-DOF modifications using
quaternion mathematics.
o Researched application of genetic algorithms, simulated annealing,
and other combinatorial algorithms to sequencing and grouping of
missile attacks.
o Analyzed terrain effects on the fuzing system, and conducted other
fuze studies.
o Developed a graphical program for analyzing plume impingement on re-
entry bodies.
o Replaced the Runge-Kutta method with a predictor-corrector method
in a 6-DOF re-entry simulation in the upper part of the atmosphere
and combined with other modifications to reduce the execution time
by 85%.
o Developed an object-oriented 6-DOF hypersonic re-entry simulation
in C++.
Career Note: Additional Position as Systems Engineer (Contractual) for
Aerodyne Industries, LLC
. Antares six degree of freedom launch vehicle simulation using Trick
simulation environment (written in FORTRAN)
o Added Monte Carlo capabilities for mass properties dispersions of
launch vehicle elements within Trick.
Education
Ph.D. in Aerospace Engineering, Old Dominion University, Norfolk, VA
expected graduation Fall 2013
M.S. in Computer Science, Virginia Polytechnic Institute and State
University, Blacksburg, VA December 1994
Bachelor of Science in Mathematics (computational track), Pennsylvania
State University, State College, PA May 1990
Publications
Davailus, G.P.; "Linear Time Invariant Formulation of the Gyroscopic
Problem using Quaternion Mathematics". AIAA-2011-1224, 49th AIAA Aerospace
Sciences Meeting; Orlando, FL., January 2011
Davailus, G.P.; Newman, B.A.; "The Application of Quaternion Algebra to
Gyroscopic Motion, Navigation, and Guidance", AIAA-2005-5945, AIAA
Guidance, Navigation, and Control Conference and Exhibit; San Francisco,
CA., August 2005
Davailus, G.P.; "The Transformation of Oscillatory Equations in Six Degree
of Freedom Trajectory Simulations Involving Coordinate Transformations",
M.S. Thesis, Department of Computer Science, Virginia Polytechnic Institute
and State University, Blacksburg, Virginia, 1994.
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