Odonata Research LLC possesses the expertise to support obtaining a Type Certificate(TC) for a new aircraft, an Amended Type Certificate(ATC) for modifications to an existing aircraft, and a Supplemental Type Certificate(STC) to enhance an aircraft. We have demonstrated the necessary technical competence and knowledge of the pertinent regulations and certification procedures to make certain findings for the FAA as a DER in the following areas. The current CLOA can be reviewed on the Designee Management System
Odonata Research LLC is proficient at performing aeroelastic and loads analysis of aircraft using MSC Nastran, Zona ZAERO, and customer proprietary software. We also have experience performing linear and nonlinear finite element analyses (FEA) in ANSYS.
Odonata Research LLC is actively engaged in engineering software development to create computational tools that enable engineers to utilize the full potential of computing resources. Expertise is primarily in developing novel engineering analyses and in automating pre and post-processing of engineering data. The software is primarily offered as custom processing and analysis tools per client request.
Odonata Research LLC has conducted research to develop and demonstrate innovative analyses. While the research is often proprietary, public examples are listed below.
This report documents the evaluation of the
aeroelastic analysis capability of the Unsteady Transonic
Small-Disturbance code (USTSD) applied to a business jet
configuration. In USTSD, the solution to the transonic
small-disturbance equation is calculated in the frequency
domain. Pressure distributions, lift, drag, and pitching
moment coefficients are calculated and compared with
available data. With a 2D boundary layer analysis
included, the finite-difference solution of the
non-conservative TSD equation tends to provide better
correlation with data as compared with the conservative
formulation in steady flow. In flutter analysis, the
non-conservative formulation generated a higher flutter
speed than the conservative formulation.
The development of a dynamic
aircraft seat analysis is presented in this paper. This
analytical model is a nonlinear finite element model
composed of a seat frame and cushion, restraint system,
glare shield and a rigid body model of a 50th percentile
Hybrid-II anthropomorphic test dummy (ATD)
occupant. Results from this analytical model are
correlated with empirical results obtained during a
full-scale dynamic test. The analysis is representative of
the dynamic test.
The purpose of this paper is
to demonstrate
the effect of coupling at the laminate level on coupling
at the structural level. Four extension-shear coupled
laminates are examined. The laminates are then used in
structures with circular, square and airfoil
cross-sections. The properties of those cross-sections
are used to describe a general elastic beam using a method
from Kosmatka. The coupling properties of the beam are
compared with those of the laminate using a normalized
coupling coefficient, stiffness coupling ratio and
compliance coupling ratio. The normalized compliance ratio
compared well between the laminate and the cross-sections
for all cases.
Postbuckling analysis of
composite laminates representative of wind turbine blade
substructures, utilizing the commercial finite element
software ANSYS, is presented in this paper. The
procedure was validated against an existing postbuckling
analysis. Three shell element formulations, SHELL91,
SHELL99 and SHELL181, were examined. It was found that
the SHELL181 element with reduced integration should be
used to avoid shear locking. The validated procedure was
used to examine the variation of the buckling behavior,
including postbuckling, with lamination schedule of a
laminate representative of a wind turbine blade shear
web. This analysis was correlated with data from a
static test. A 100% postbuckling reserve in a composite
structure representative of a shear web was quantified
through test and analysis. The buckling behavior of the
shear web was improved by modifying the lamination
schedule to increase the web bending
stifness. Modifications that improved the buckling load
of the structure did not always equate to improvements
in the postbuckling reserve.
Thomas M. Hermann has a strong background in
aeroelastic analysis of aerospace structures with
proficiency in multiple commercial packages. He has
performed structural dynamic, aeroelastic, and dynamic loads
analysis of aircraft ranging from twin turboprop, carrier
based, AEW aircraft to a twin turbofan transport and
business jets utilizing both customer proprietary and
Nastran aeroelastic models. In addition, he performed
composite laminate design, testing and analysis with
application directed at wind turbine blades. In the course
of all of these tasks, he acquired software development
skills in several languages including Python, Fortran,
Matlab, and Common Lisp.
His career objective is to improve engineering productivity through proper application of state-of-the-art methodology, analyses, and software.
Odonata Research LLC