Page 40 - ASME AM3D/IDETC/CIE 2015 Program
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IDETC/CIE KEYNOTE & PLENARY LECTURES
Wednesday, August 5 PTG KEYNOTE
SESSION: MSNDC-VIB-18-2
9:30AM – 11:10AM
Location: Room 302, Level 3 Tuesday, August 4
SESSION: PTG-10-1
2:00PM – 3:00PM
Matt Snyder Location: Room 108, Level 1
European Office of Aerospace Research and
Development (EOARD). Air Force Office of
Scientific Research Philippe Velex
LaMCoS, INSA
OPTIMIZATION OF MULTI-STATE RECONFIGURABLE
AEROSTRUCTURES: VIBRATION CHALLENGES IN
AEROSPACE VEHICLE DESIGN
ON SOME CONCEPTS AND ISSUES IN GEAR DYNAMIC
Abstract: A reconfigurable aircraft is capable of in-flight shape SIMULATIONS
change to increase mission performance or provide multi-mission
capability. While configurability at some scale has always been a Abstract: In this presentation a number of classic concepts widely
consideration in aircraft design (the Wright flyer used wing warping used in the simulations of gear dynamics are examined and some of
for roll-control), increasingly complex reconfiguration has been their limitations are highlighted. Particular emphasis is placed on the
sought, such as that demonstrated by the Lockheed-Martin folding concepts of mesh stiffness, mesh excitations and mesh damping.
wing (DARPA Morphing Aircraft Structures program). However, the Depending on gear geometry and operating conditions, conventional
benefits achieved from reconfiguration can be offset by the weight approaches can prove inadequate and more complex models may be
penalty incurred from the actuation system and required supporting required. The notion of transmission error is critically assessed and
structure. As such, a design tool is required that efficiently produces the possibility of extending it to multi-mesh geared systems is
a light weight reconfigurable structure and provides fundamental discussed. Finally, the various sources of mesh damping are
information to assist the structural engineer. Here a method for the considered and it is shown that different damping mechanisms may
constrained simultaneous optimization of a multi-state aircraft is a prevail depending on the instant contact conditions between the
proposed where the flutter of the air vehicle is considered. The talk tooth flanks.
will conclude with a number of research challenges for future work to
enhance the viability of reconfigurable vehicles and to take advantage
of recent advancements in materials, manufacturing and structures Biography: Professor Velex received a MEng. in Mechanical
related research. Engineering from INSA Lyon (France) in 1984, PhD from the same
establishment in 1988 and was appointed Full Professor of Mechani-
cal Engineering in 1998. He currently serves as the Head of the
Biography: Major Matt Snyder, United States Air Force, received his ‘Mechanical Systems and Contact’ research group of LaMCoS
undergraduate degree in Mechanical Engineering from Cedarville (INSA Lyon) and is the Holder of the SAFRAN-INSA Chair on
University, Ohio and his PhD in Aircraft Structures from the Aeronau- Innovative Mechanical Transmissions for Aeronautics.
tics Department of Purdue University. He taught as an Assistant
Professor at the United States Air Force Academy in the Department
of Engineering Mechanics where he was named the Engineering
Mechanics Outstanding Academy Educator in 2007. He is currently
an International Program Officer for the European Office of Aero-
space Research and Development, London, UK, one of the overseas
offices of the Air Force Office of Scientific Research. He manages
an international research portfolio in the area of advanced aerospace
materials and structures.
40
Wednesday, August 5 PTG KEYNOTE
SESSION: MSNDC-VIB-18-2
9:30AM – 11:10AM
Location: Room 302, Level 3 Tuesday, August 4
SESSION: PTG-10-1
2:00PM – 3:00PM
Matt Snyder Location: Room 108, Level 1
European Office of Aerospace Research and
Development (EOARD). Air Force Office of
Scientific Research Philippe Velex
LaMCoS, INSA
OPTIMIZATION OF MULTI-STATE RECONFIGURABLE
AEROSTRUCTURES: VIBRATION CHALLENGES IN
AEROSPACE VEHICLE DESIGN
ON SOME CONCEPTS AND ISSUES IN GEAR DYNAMIC
Abstract: A reconfigurable aircraft is capable of in-flight shape SIMULATIONS
change to increase mission performance or provide multi-mission
capability. While configurability at some scale has always been a Abstract: In this presentation a number of classic concepts widely
consideration in aircraft design (the Wright flyer used wing warping used in the simulations of gear dynamics are examined and some of
for roll-control), increasingly complex reconfiguration has been their limitations are highlighted. Particular emphasis is placed on the
sought, such as that demonstrated by the Lockheed-Martin folding concepts of mesh stiffness, mesh excitations and mesh damping.
wing (DARPA Morphing Aircraft Structures program). However, the Depending on gear geometry and operating conditions, conventional
benefits achieved from reconfiguration can be offset by the weight approaches can prove inadequate and more complex models may be
penalty incurred from the actuation system and required supporting required. The notion of transmission error is critically assessed and
structure. As such, a design tool is required that efficiently produces the possibility of extending it to multi-mesh geared systems is
a light weight reconfigurable structure and provides fundamental discussed. Finally, the various sources of mesh damping are
information to assist the structural engineer. Here a method for the considered and it is shown that different damping mechanisms may
constrained simultaneous optimization of a multi-state aircraft is a prevail depending on the instant contact conditions between the
proposed where the flutter of the air vehicle is considered. The talk tooth flanks.
will conclude with a number of research challenges for future work to
enhance the viability of reconfigurable vehicles and to take advantage
of recent advancements in materials, manufacturing and structures Biography: Professor Velex received a MEng. in Mechanical
related research. Engineering from INSA Lyon (France) in 1984, PhD from the same
establishment in 1988 and was appointed Full Professor of Mechani-
cal Engineering in 1998. He currently serves as the Head of the
Biography: Major Matt Snyder, United States Air Force, received his ‘Mechanical Systems and Contact’ research group of LaMCoS
undergraduate degree in Mechanical Engineering from Cedarville (INSA Lyon) and is the Holder of the SAFRAN-INSA Chair on
University, Ohio and his PhD in Aircraft Structures from the Aeronau- Innovative Mechanical Transmissions for Aeronautics.
tics Department of Purdue University. He taught as an Assistant
Professor at the United States Air Force Academy in the Department
of Engineering Mechanics where he was named the Engineering
Mechanics Outstanding Academy Educator in 2007. He is currently
an International Program Officer for the European Office of Aero-
space Research and Development, London, UK, one of the overseas
offices of the Air Force Office of Scientific Research. He manages
an international research portfolio in the area of advanced aerospace
materials and structures.
40
