Transcript of G2 Flywheel Module Design - NASA
E-15232 CoverNewTimothy P. Dever
G2 Flywheel Module Design
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at 301–621–0134
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7121 Standard Drive
Timothy P. Dever
G2 Flywheel Module Design
Prepared for the
sponsored by the American Institute of Aeronautics and
Astronautics
Providence, Rhode Island, August 16–19, 2004
Acknowledgments
7121 Standard Drive
Available electronically at http://gltrs.grc.nasa.gov
Level of Review: This material has been technically reviewed by
expert reviewer(s).
The G2 flywheel module was funded by NASA Glenn Research Center
under the Aerospace Flywheel Technology Program
which is part of the NASA Code R Space Base Energetics Program. The
work was performed by a team of NASA, university,
and contractor employees. The University of Toledo team included
Ralph Jansen, Kirsten Duffy, Peter Kascak, and Dan Clark.
Kirsten Duffy performed the rotordynamics analysis and Peter Kascak
worked on the motor specification. Dan Clark
performed the rotor windage loss calculations. Ronald Storozuk,
Analex Corporation, did the solid models and the detailed
drawings. The NASA team includes Kevin Konno, Jeffery Trudell,
Walter Santiago, Ramon Lebron, and Barbara Kenny.
Kevin Konno led the rotor design effort as well as the module
fabrication and assembly team. Jeff Trudell did thermal and
stress analysis. Walter Santiago and Ramon Lebron specified the
avionics, sensors, and connectors. Barbara Kenny also
worked on the motor specification. Aleksandr Nagorny working as a
GRC research associate estimated the motor losses. The
VCEL team lead by Alan Palazzolo at Texas A&M designed the
magnetic bearing. Andrew Kenny performed the magnetic
analysis. Jason Preuss did the solid modeling and detailed drawings
of the magnetic bearings.
NASA/CR—2006-213862 1
Timothy P. Dever QSS Group, Inc.
Cleveland, Ohio 44135
Design of a flywheel module, designated the G2 module, is
described. The G2 flywheel is a 60,000 rpm, 525 W-hr, 1 kW system
designed for a laboratory environment; it will be used for
component testing and system demonstrations, with the goal of
applying flywheels to aerospace energy storage and integrated power
and attitude control (IPACS) applications. G2 has a modular design,
which allows for new motors, magnetic bearings, touchdown bearings,
and rotors to be installed without a complete redesign of the
system. This design process involves several engineering
disciplines, and requirements are developed for the speed, energy
storage, power level, and operating environment. The G2 rotor
system consists of a multilayer carbon fiber rim with a titanium
hub on which the other components mount, and rotordynamics analysis
is conducted to ensure rigid and flexible rotor modes are
controllable or outside of the operating speed range. Magnetic
bearings are sized using 1-D magnetic circuit analysis and refined
using 3-D finite element analysis. The G2 magnetic bearing system
was designed by Texas A&M and has redundancy which allows
derated operation after the loss of some components, and an
existing liquid cooled two pole permanent magnet motor/generator is
used. The touchdown bearing system is designed with a squeeze film
damper system allowing spin down from full operating speed in case
of a magnetic bearing failure. The G2 flywheel will enable module
level demonstrations of component technology, and will be a key
building block in system level attitude control and IPACS
demonstrations.
Nomenclature
CMB Combination Magnetic Bearing RMB Radial Magnetic Bearing TD
Touchdown Bearing M/G Motor/Generator GRC Glenn Research Center ISS
International Space Station
I. Introduction NASA Glenn Research Center (GRC) has an ongoing
effort in flywheel technology development and
deployment for spacecraft applications (ref. 1). Flywheel systems
can be used to replace batteries for energy storage applications.
Flywheel modules can also be deployed in an array which provides
both energy storage and momentum control; this type of system is
called an Integrated Power and Attitude Control System (IPACS)
system. A flywheel system consists of a number of flywheel modules
and an electronics package which operates the flywheel
motor/generators, magnetic bearings, and telemetry. The benefits of
flywheel systems for energy storage applications are high energy
density, high power density, long life, deep depth of discharge,
and broad operating temperature ranges. In an IPACS configuration
an additional mass savings can be achieved through the combination
of the energy storage and the attitude control functions.
Flywheel modules for space use are designed to maximize energy
density and minimize losses. Typically the energy storage component
of the module is a rim composed of high strength carbon fiber.
Energy is transferred to and from the wheel using a
motor/generator. The flywheel module typically has some or all of
these ancillary components: magnetic bearings, touchdown bearings,
housing structure, sensors, connectors, and wiring harnesses. The
rotating components are placed along a hub with the rim in the
center of the hub. The motor, magnetic bearings, and touchdown
bearings populate each end of the hub, and the stationary parts of
these components are located within the housing.
NASA/CR—2006-213862 2
This paper describes the design and analysis of the G2 flywheel
module at GRC. A schematic of the G2 is shown in figure 1. The
module subsystems considered in this paper include the rotor,
magnetic bearings, motor/generator, touchdown bearings, and the
housing.
The rotor consists of three main parts: the rim, the motor rotor,
and the hub. The rim is the main energy storage component; it is
made of a multi-ring carbon fiber. The motor rotor is a two pole
permanent magnet synchronous motor, which was purchased from a
commercial vender. The rim and motor rotor are mounted on the hub,
which is made of titanium.
The magnetic bearings are used for low-loss suspension of the
rotor.
The motor/generator is used to store and retrieve energy from the
rotor.
Touchdown bearings are designed to capture the rotor in the event
of a magnetic bearing failure, and also to support the rotor when
the active magnetic bearings are turned off.
The module housing supports the static portions of the flywheel
system, such as the motor/generator and magnetic bearing stators,
the position sensors, the touchdown bearings etc. Additionally, the
housing is sealed, allowing vacuum testing of the module in the
laboratory.
II. G2 Requirements The G2 Flywheel Module requirements were
derived from the milestones of the NASA Aerospace Flywheel
Technology Program (AFTP). The G2 flywheel module will be one of
two modules used in a single axis integrated power and attitude
control (IPACS) demonstration at NASA Glenn Research Center. The
AFTP Program also develops component technologies that need to be
tested at the flywheel module level. G2 is modularly designed to
allow new components to be introduced without a complete redesign.
Performance requirements were set at the module level and
propagated to the component levels. The total parts cost per module
was minimized, and the design schedule was limited to 10 months.
Several power and energy requirements were imposed. The usable
stored energy shall be greater than 300 W-hr with a
charge-discharge rating greater than 1 kW, and the power bus
voltage was set at 120 V. The module shall be capable of simulating
Low Earth Orbit (LEO) cycles with a 90 minute nominal
charge/discharge time at 90 percent depth of discharge (DOD).
G2 size and environmental requirements were set for a laboratory
environment. Weight is not a significant factor but was limited to
250 pounds, and the size was limited to 20 inches in diameter by 36
inches long. A goal was set to minimize both of these quantities
within the budget constraints. The operating temperature will be
between 60 and 120 °F, and the G2 is required to operate in any
orientation so that it can be applied to future multi-axis IPACS
experiments.
A summary of the G2 requirements is included in table 1. The G2
design meets or exceeds all of the requirements.
TABLE 1.—G2 REQUIREMENTS SUMMARY Item Requirement Design Usable
energy >350 W-hr 525 W-hr Charge/discharge power rating >1 kW
1 kW Electrical power bus voltage <120V 120V Depth of discharge
90% 90% Weight <250 lbs 218 lbs. Volume 20 in. ∅ x 36 in. 12 in.
∅ x 30 in. Capable of operation in any orientation Yes Yes
Combo End Touchdown
NASA/CR—2006-213862 3
64 64 6
A) Bounce B) Tilt C) 1st Bending mode D) 2nd Bending mode
Figure 2.—Rotor modes.
III. G2 Rotor Design The function of the rotor is to store energy.
The G2 rotor consists of a carbon fiber rim for energy storage and
a
central titanium hub, on which the bearing and motor parts mount.
The carbon fiber rim is a multilayer press fit design, and it is
located at the axial center of the hub. The rotors of the magnetic
bearings located on each side of the rim, and the radial position
sensor arrays are located outboard of each magnetic bearing rotor.
The motor/generator is located further down the hub, outboard of
the radial magnetic bearing, and the touchdown bearings are located
at each end of the shaft. An axial position sensor and angle
resolver are located at the combination touchdown bearing end of
the rotor.
A. Rotordynamics Requirements Important rotor requirements include
the total and usable kinetic energy, the 1st bending mode
frequency, the
polar to transverse moment of inertia ratio (Ip/It), and the rotor
weight. The G2 rotor has been designed to store a total of 591 W-hr
of energy, with 525 W-hr usable energy; this
exceeds the requirement of 350 W-hr usable energy.
The bending mode frequency for this type of rotor should exceed the
maximum operating speed by 20 percent; the estimated bending
frequency is 71,900 rpm is equal to the requirement of 72,000 rpm
given the margin of error.
The Ip/It ratio must not be near unity; the G2 rotor Ip/It ratio is
0.5, providing greater margin than any of the previous GRC
flywheels, and the rotor weight will be 50 lbs which is under the
maximum requirement of 75 lbs.
A summary of the G2 rotor requirements is included in table 2. The
G2 rotor design meets all of the requirements.
B. Rotordynamics Analysis Rotordynamics analysis is central to the
flywheel module design process; the rotor is designed with control
in
mind. The modes of the rotor can be divided into two categories:
rigid body modes, and bending modes. Both sets of modes are
considered in the design process.
Rigid body modes describe rotordynamic behavior of the rotor
independent of rotor bending. The important radial rigid body modes
for the G2 design are the bounce and tilt modes, and the relevant
bending modes are the first and second rotor bending modes (fig.
2). The bounce mode describes translation of the center of mass of
the rotor (A), while rotation about the center of mass is called
the tilt mode (B). Although flexure of the rotor is decomposed into
many bending modes, typically only the 1st (C) and 2nd (D) bending
modes are low enough in frequency to be excited during flywheel
operation. The bending mode frequencies are a key driver for the
rotor design, because magnetic bearing control becomes
significantly more difficult if the bending mode frequencies fall
within the rotor operating speed.
In order to understand rotor bending modes, rotor design iterations
are conducted using free-free bending mode analysis. Critical
speeds are analyzed for operation on the magnetic bearings and the
mechanical touchdown bearings, and critical speed maps, plotting
mode frequencies versus bearing stiffnesses, are made for each
mode. Since the maximum operating speed for the G2 module is 60,000
rpm (1000 Hz), the bending modes are designed to be above 1000 Hz
throughout the operating range. Figure 3 shows the modes of the
final design, showing the 1st and
TABLE 2.—G2 ROTOR REQUIREMENTS Item Requirement Design Total
kinetic energy Usable kinetic energy
350 W-hr
591 W-hr 525 W-hr
1st Bending Mode >72,000 rpm 71,900 rpm Polar to transverse
moment of inertia (Ip/It) <0.8 or >1.2 0.5 Rotor weight
<75 lbs 50 lbs
NASA/CR—2006-213862 4
Rotor Speed (RPM)
1st Bending
2nd Bending
Figure 3.—Predicted G2 bending modes versus rotor speed.
Figure 4.—Radial MB rotor lamination PM
spin losses.
2nd bending modes, and the synchronous rotor speed (1E) and its
harmonics (2E and 3E). The 1st and 2nd bending mode frequencies are
at 1097 and 1961 Hz with the rotor at rest, and the bending modes
split with speed into forward and backward components. The 1st
bending mode forward and backward frequencies are 1180 and 1042 Hz
at 60,000 rpm, and the 2nd bending mode forward and backward
frequencies are 2057 and 1850 Hz at 60,000 rpm. Note that our goal
has been achieved; the bending modes are above 1000 Hz over the
entire operating range. Note that although the 1st backward bending
mode comes close to 1000 Hz at full speed, it should not pose a
problem - the forward components are of greater concern because
they can be excited by the rotor unbalance, while the backward
components are much more difficult to excite.
The rigid body mode frequencies are controlled by the rotor bearing
stiffnesses; since we operate on active magnetic bearings, the
bearing stiffnesses are set by the controller gains. Typically both
bounce and tilt modes are set below 100 Hz at rest. The bounce mode
frequency remains fixed throughout the speed range, while the tilt
mode splits into a forward whirl and backward whirl mode. The
backward whirl mode frequency decreases with speed, while the
forward whirl mode frequency ideally asymptotes to the ratio of the
polar and transverse moment of inertia of the rotor. Actual
placement of the rigid body modes is chosen by trading off several
design criteria, such as desired 1E/forward whirl crossover, bounce
mode stiffness, rigid body mode separation.
C. Thermal Analysis Thermal analysis must be performed on the rotor
system to verify that the flywheel module will be capable of
continuous operation, without overheating. Because the rotor is
levitated and operated under vacuum, radiation is the exclusive
heat transfer path for the rotor.
In order to complete this thermal analysis, rotor losses are
predicted for the magnetic bearings, the motor/generator, and the
effects of windage.
1. Magnetic Bearing Spin Losses
Losses due to the magnetic bearing operation are called magnetic
bearing spin losses. These losses include control flux, permanent
magnet (PM) bias flux, and amplifier switching frequency
losses.
Although the magnetic bearings are capable of providing significant
forces to levitate the rotor, under typical operating conditions
they are operated near a zero force level. Because of this, bearing
control flux is neglected in the loss analysis.
Pulse width modulated (PWM) amplifiers are used to generate the
currents for the magnetic bearings. The currents generated at the
switch frequencies (typically 20 to 30 kHz) constitute another
possible loss source. However, this current component is greatly
reduced via power filters before reaching the magnetic bearing
actuators, so the switching related power losses in the bearings
can also be neglected.
Since the control flux and switching frequency losses can be
neglected, magnetic bearing spin loss estimate is calculated with
only the PM bias field
NASA/CR—2006-213862 5
0
1
2
3
4
5
6
7
8
9
10
Speed (RPM)
Lo ss
RHJ 5/7/04 Figure 5.—G2 windage loss estimate.
applied. Magnetic bearing eddy current and hysteresis loss
estimates for the rotor components due to the PMs are made using 3D
FEA (see fig. 4); the estimated bias losses are less than 1W at
full speed.
2. Motor/Generator Spin Losses
The motor/generator was purchased from an outside vendor. The
proprietary nature of the design made it difficult to predict the
losses. The full power efficiency was predicted at 94 to 95
percent. The rotor losses were not predicted.
3. Windage Loss Analysis
Windage loss estimates were made using the method presented by Liu
(ref. 2). The free-molecule wall shear stress equation with slip
velocity correction is the basis for the calculations; for our
analysis, it is converted into a windage power equation for a
cylindrical surface (eq. 1). This equation estimates the windage
power loss on the outer surface of the carbon fiber rim section;
losses on the faces of the rim and the hub surfaces were neglected
in this analysis.
( ) ( ) ( )( )LLaLRTPCwP /21//232/2, λλωπ += (1)
Power loss for decade isobars between 1e-5 and 10 mTorr are shown
in figure 5. A turbo molecular vacuum pump will be attached to the
flywheel module on the central housing section which surrounds the
rim, and the vacuum level is anticipated to be better than 10-3
mTorr. Based on the calculations in figure 5, the windage power
loss at this vacuum level is expected to be less than 1 W at full
operating speed.
4. 1-D Thermal Model
In order to understand the maximum allowable heat load due to
losses, a one dimensional (1-D) thermal model was made to estimate
the temperature rise as a function of total losses on the rotor.
This model allows input of a total power loss value and an
effective emissivity of the system; in the model, the total losses
are distributed between the loss mechanisms described above. The
model was run for multiple total loss values, and over multiple
effective emissivities, and the results are presented in figure
6.
The epoxy resin used in the G2 rim has a glass transition
temperature of 180 °F; this is the thermally limiting component in
the flywheel, and this upper limit is marked in red. Since the
estimated effective emissivity of the G2 is estimated to be about
0.7, the maximum allowable power losses to limit rotor rim
temperature to 180 °F are estimated to be about 45 W.
Steady Rim 1D Temperature vs Heat Load
100 120 140 160 180 200 220 240 260 280 300
0.5 0.6 0.7 0.8 0.9 1
Emissivity, Effective
Te m
pe ra
tu re
(F )
Q=100W Q=80W Q=60W Q=40W Q=20W Limit180F
Figure 6.—G2 1-D thermal model.
NASA/CR—2006-213862 6
Figure 7.—G2 MB controller schematic.
IV. Magnetic Bearing System The G2 flywheel utilizes an active
magnetic
bearing (MB) system, consisting of two magnetic bearings which
provide five-axis levitation. A radial magnetic bearing (RMB) at
the motor end of the shaft controls two radial degrees of freedom
(X1 and Y1), while the combination magnetic bearing (CMB, located
at the end opposite the motor) controls two radial degrees of
freedom as well as the axial degree of freedom (X2, Y2, and Z). A
simplified diagram of the feedback control system is shown in. The
MB controller issues current commands to a pulse width modulated
(PWM) amplifier; the PWM drives current into the magnetic bearing
actuator, which in turn produces forces which levitate the rotor.
The rotor position is sensed using non-contact eddy current
sensors; this sensor signal is conditioned and fed back into the
controller.
A. Magnetic Bearing Requirements Requirements were developed for
the load, stiffness, electrical and dimensional attributes of the
MB actuators. The load specifications require that both MBs to be
able to support 30 lbs radially at 1500 Hz. Both MBs beat
this specification, with 40 lbs. (RMB) and 44 lbs. (CMB) capacity.
Additionally, the bearings are required to support three times the
rotor weight at 0 rpm; since the rotor weighs 50 lbs, this means
that at 0 rpm, both the RMB and the CMB must provide 75 lbs. of
force, each, radially, and the CMB must also provide 150 lbs. of
force axially. The CMB bearing meets the DC load requirements, but
the RMB DC load capacity is slightly below the specification (70
vs. 75 lbs), although this is not expected to be a problem. Current
and position stiffness are actuator parameters that have a
significant impact on the magnetic bearing control. The minimum
current stiffnesses are 7.5 lbs/A radially and 15 lbs/A axially,
and the designed current stiffnesses exceed these requirements,
with 8.8 lbs/A and 9.3 lbs/A radially for the two MBs, and 18.8
lbs/A axially. The design objective was to minimize position
stiffness; the resultant position stiffnesses are 6160 lbs/in and
6890 lbs/in radially for the RMB and CMB, and 7910 lbs/in axially.
The electrical specifications are a result of trades between power
electronics and magnetic bearing actuator issues. The bus voltage
was limited to 110V and the current to 10 A, and the designed
hardware operates within these limits. A minimum bandwidth
requirement of 1500 Hz was established to minimize phase lag in the
control system, and the RMB bandwidth is 2200 Hz and the CMB
bandwidth is 2000 Hz. The dimensional requirements reflect
rotordynamics issues and the need to fit with the other components
of the flywheel. The lamination ID is maximized and the overall
bearing length is minimized to increase the rotor bending mode
frequencies, while the lamination OD is limited by the strength of
the magnetic materials.
TABLE 3.—MAGNETIC BEARING REQUIREMENTS Item Requirement Design Load
RMB – DC Radial Load Capacity 75 lbs 70 lbs RMB – 1500 Hz Load
Capacity 30 lbs 40 lbs CMB – DC Radial Load Capacity DC Axial Load
Capacity
75 lbs 150 lbs
74 lbs 150 lbs
CMB – 1500 Hz Radial Load Capacity 30 lbs 44 lbs Stiffness Current
Stiffness – RMB – Radial CMB – Radial CMB – Axial
7.5 lbs/A 7.5 lbs/A 15 lbs/A
8.8 lbs/A 9.3 lbs/A
18.8 lbs/A Position Stiffness – RMB – Radial CMB – Radial CMB –
Axial
minimize minimize minimize
6160 lbs/in 6890 lbs/in 7910 lbs/in
Electrical Voltage 110V max 102V Current 10A max 10/8 A Bandwidth –
RMB – Radial CMB – Radial
1500 Hz 1500 Hz
2200 Hz 2000 Hz
2 in. 2 in.
2.0 in. 2.0 in.
3 in. 3 in.
2.9 in. 2.9 in.
Bearing Length RMB CMB
2.5 in. 2.5 in.
2.07 in 2.28 in
Figure 8.—G2 MB design.
The G2 MB requirements are summarized in table 3. Both magnetic
bearing actuators exceed the specifications in almost all aspects;
the small load capacity exception in the RMB is not expected to
have any performance impact. B. Magnetic Bearing Actuator
Both the combination and the radial magnetic bearings were designed
for the G2 module; a drawing of the combo MB is presented in figure
8. Two key requirements for the MB design were low power
consumption and load capacity.
In order to minimize losses, a PM bias, homopolar design was
selected for the radial and combo. PM bias was selected because
this approach eliminates the need for bias current in the MB,
preventing the associated I^2 R losses. The homopolar bearing
design was selected because, in this design configuration, the
magnetic field variation in the rotor laminations due to the bias
flux is minimized; this is desirable, as these field variations
cause hysteresis and eddy current losses. Finite element methods
were used to optimize the stator poles to further reduce the flux
variation.
The design target for the MB static load capacity was three times
the rotor weight of 50 lbs, or 150 lbs total. The radial portion of
both final design bearings each have a capacity of 75 lbs, meeting
the total 150 lb requirement, while the axial portion of the combo
bearing also provides 150 lbs capacity.
C. Magnetic Bearing Power and Control System A detailed schematic
of the magnetic bearing power and control system is shown in figure
9. The major
components of the MB control system include the position sensors,
sensor signal conditioning, MB controller, and PWM/power
filters.
Non-contact eddy current sensors are used to locate the rotor in
the G2 unit. Ten sensors are used in all: two sets of four radial
sensors are located above and below the rim, near the magnetic
bearings, and two additional sensors, which measure axial position
and angular reference, are located at the top of the unit. Each set
of radial sensors is run off of common oscillators, to avoid beat
frequency crosstalk noise which can arise due to differences in
sensor oscillator drive frequencies (ref. 3).
One key portion of the sensor signal conditioning in the anti-alias
filters, which are first order 8 kHz low pass filters. These
filters prevent aliasing in the digital controller. The filter
corners were selected to efficiently eliminate potential noise
while minimizing phase lag.
NASA/CR—2006-213862 8
Touchdwn Brg 1
I-A2
I-B2
I-C2
I-A1
I-B1
I-C1
I-Z
A1, B1, C1 CMD
A2, B2, C2 CMD
FDBK
I-A2
I-B2
I-C2
I-A1
I-B1
I-C1
I-Z
I-A2
I-B2
I-C2
I-A2
I-B2
I-C2
I-A1
I-B1
I-C1
I-A1
I-B1
I-C1
I-ZI-Z
A1, B1, C1 CMD
A2, B2, C2 CMD
A1, B1, C1 CMD
A2, B2, C2 CMD
FDBK
Figure 9.—G2 MB power and control system.
The MB controller is written in a rapid development software
environment, then compiled and run on a digital
controller which includes A/D and digital inputs, a CPU, and D/A
outputs. The user interface for the controller is implemented on a
PC (ref. 4). The MB control algorithm issues seven current commands
based on the position inputs. Each magnetic bearing actuator has
three radial control axes (A,B,C) instead of the traditional two
axes (X,Y) for redundancy, and the combination magnetic bearing has
an axial (Z) control axis. First order 40 kHz low pass filters are
used for reconstruction of the D/A signal; this corner frequency
was also selected to reduce noise while eliminating phase
lag.
Seven PWM amplifiers produce current proportional to the commands.
The seven amplifiers have synchronous switching frequencies to
reduce amplifier to amplifier beating noise picked up by the
sensors5, and they operate on a 120 V Bus. The current output from
the PWMs is filtered using a 50 kHz low pass filter and a trap
filter at the PWM switching frequency (ref. 6). At the actuator the
currents produce magnetic fields resulting in forces on the
levitated rotor.
V. Motor/Generator System A permanent magnet motor/generator (M/G)
system is used to transfer energy to and from the flywheel
rotor.
Flywheels designed at NASA Glenn Research Center are intended for
use in Low Earth Orbit (LEO), thus, they will typically be either
charging or discharging, and will have only short periods where
there will be no power transfer. For this type of load profile,
permanent magnet motors provide the highest efficiency and the
highest power density. Other types of motors would be more
appropriate for applications which required short high-power
transfer periods and long hold periods.
NASA/CR—2006-213862 9
A. Motor/Generator Requirements The M/G requirements stem from the
need
to charge and discharge the flywheel over a 90 minute LEO orbit.
The flywheel is intended to operate between 20,000 and 60,000 rpm;
the motor power requirement is 1 kW at 20,000 rpm and 3 kW at
60,000 rpm. The number of motor poles is minimized to reduce the
frequency requirements of the power electronics and controls; the
selected motor has two poles, which is the minimum possible number.
The motor voltage is selected to work with the ISS bus and future
satellites, and the design value of 78 V meets the requirement of
72 V±10 percent. A total harmonic distortion (THD) <5 percent is
required to minimize torque ripple, and the selected motor's THD is
less than 3 percent. The physical dimensions of the motor are
limited by the other parts of the system; the motor has a rotor
outer diameter (OD) or 1.5 in., and the stator OD is 3.0 in. and it
is 3.1 in. long. The G2 motor requirements are summarized in table
4. The motor meets all of the specifications.
B. Motor/Generator Design The M/G was designed by a subcontractor;
it is a two pole permanent magnet motor rated at 3 kW at
60,000 rpm, and it can produce 1 kW at 20,000 rpm. The line to line
back EMF voltage was measured on a sister unit at 78 V with less
than 3 percent THD. The physical dimensions of the motor are
appropriate for this application, and the motor full power
efficiency was estimated at 94 to 95 percent.
C. Motor/Generator Power and Control System Figure 10 is a
schematic of the power and control system for the
motor/generator.
TABLE 4.—G2 MOTOR/GENERATOR REQUIREMENTS Item Requirement Design
Power @ 20,000 rpm 1 kW 1 kW Number of poles <=4 2 Back EMF
Voltage 72 V ±10% 78 Sinusoidal Back EMF, THD < 5% ≈ 3%
Dimensions Rotor OD Stator OD Stator Length
< 2.9 in. < 8 in. <4 in.
1.5 in. 3.0 in. 3.1 in.
NASA/CR—2006-213862 10
The major components of this system include the DC bus, antialias
filters, the motor/generator controller, the PWM circuit and
inverter, the power filter and the emergency load.
The DC bus includes a DC power supply, the DC load, and the DC
filter; the bus voltage and current signals are fed back to the
motor-generator controller through first order low pass anti-alias
filters.
As with the MB controller, the motor-generator controller is
written in a rapid development software environment, then compiled
and run on a digital controller which includes A/D and digital
inputs, a CPU, and D/A outputs, and the user interface for the
controller is implemented on a PC. Advanced motor/generator control
features include position sensorless control, and bus regulation.
The position sensorless motor controller algorithm uses the phase A
and B currents as inputs (ref. 7), eliminating the need for an
angular position sensor. The bus regulation algorithm uses the DC
Bus current and voltage as feedback (ref. 8).
The M/G control algorithm outputs duty cycle information for three
phases to the PWM board, which performs a comparison to a triangle
wave reference to produce switch states. A driver chip is used to
run the gates on the six switch inverter.
Power filters are used to minimize high frequency noise in the
system (ref. 9), and the emergency load is used at the end of a
test run, to dump the stored rotor power.
VI. Touchdown Bearing System The touchdown bearing system on the G2
module has two functions: to support the flywheel rotor when
the
magnetic bearings are turned off, and to control the rotor position
in the event that the magnetic bearing system has suffers a failure
during operation.
When the bearings are turned off, the touchdown bearing supports
the weight of the rotor, with assistance from the permanent magnets
in the motor and magnetic bearings.
The touchdown bearing system is also designed for the worst case
magnetic bearing failure, which requires spin down from full
operating speed on the touchdown bearings. This case could be
caused by loss of power to the magnetic bearings, a major
malfunction in the controller hardware, or a combination of several
failures in the magnetic bearing actuator.
A. Touchdown Bearing Requirements Touchdown bearing requirements
can be grouped into five categories: bending mode critical speeds,
radial
displacement limits, radial force limits, temperature limits, and
radial gap. As is the case with the magnetic bearings, the T/D
bearings are designed so that their bending mode critical
frequencies are kept out of the operating speed range. The G2
bending critical on the touchdown bearings is expected to be 84,300
rpm, which provides a 40 percent margin above top operating speed
of 60 krpm.
The displacements must be limited by the T/D bearing during the
touchdown event and subsequent spin down; displacements need to be
kept below 20 mils to ensure that the rotor does not contact the
stationary parts of the flywheel (the magnetic bearing and motor
stators have gaps of 20 and 30 mils, respectively). Per the design,
the G2 touchdown displacements will be held to below 20 mils in the
event of a worst case (full speed) touchdown, and will decrease to
less than 2 mils during the spin down.
The maximum radial force specification is 1500 lbs; by selection of
the T/D mechanical bearing, the G2 bearings loads are designed to
be below 500 lbs. during rotor touchdown and spin down.
High temperature materials (>200 °F) are necessary because the
rotor energy during a touchdown is dissipated through friction in
the T/D bearing system. All of the materials used in the G2
touchdown bearing are rated to operate beyond 300 °F.
The required T/D bearing radial gap is >5 mils, and the gap was
designed for 7 mils. The G2 T/D bearing requirements are summarized
in table 5. The T/D bearings meet all of the specifications.
TABLE 5.—TOUCHDOWN BEARING REQUIREMENTS Item Requirement Design
Bending Critical Speed on TD's >72000 rpm 84300 Radial
Displacement during spin down on TD's
< 20 mils < 2 mils
Radial force on TD's during spin down < 1500 lbs. <500 lbs
Radial displacement on TD's during touchdown at 60 krpm
<20 mils <20 mils
<1500 lbs. <500 lbs
Touchdown bearing radial gap >5 mils 7 mils
NASA/CR—2006-213862 11
-15
-10
-5
0
5
10
15
D(4)x, mils
D (4
)y , m
D(4)x, mils
D (4
)y , m
D(4)x, mils
D (4
)y , m
Figure 13.—G2 T/D bearing transient analysis.
B. Touchdown Bearing Design The design of the touchdown bearing is
centered about a rotordynamics analysis of the touchdown event. One
key requirement is that, in the event of a touchdown, the transient
behavior cannot cause the rotor to enter a
whirl mode instability; this type of instability can cause damage
to the module. Additionally, displacement amplitudes and forces are
estimated throughout the operating range to ensure that
they are within the limits through all the critical frequencies.
The key touchdown bearing properties, stiffness, damping, and
friction are modified to minimize loads and displacements of the
rotor.
The G2 combination and radial touchdown bearing designs are shown
in figure 11 and figure 12. Radial stiffness and damping are
controlled by O-rings and a squeeze film damper, and axial
stiffness of the combination touchdown bearing is controlled by
wave springs. Friction is determined by the ball bearing and the
touchdown surface between the bearing and the rotor, and anti-
rotation pins stop the bearing housing from turning with respect to
the housing. Adjustments of the outer touchdown bearing housings
with respect to the adjoining parts of the flywheel housing are
used to align the touchdown bearing, magnetic bearing and motor
centerlines.
C. Touchdown Bearing Rotordynamics Transient analysis is used to
determine wether the rotor enters an unstable whirl phenomenon when
it itially
touches down. Typical transient analyis results are shown in figure
13 corresponding to: A) stable touchdown with gravity, B) stable
touchdown without gravity and C) unstable touchdown which will
induce whirl.
Stable touchdown with gravity (Case A) must be achieved; this
covers the flywheel operation on earth in horizontal orientation.
Additionally, stable touchdown without gravity (Case B) must also
be achieved with touchdown; this case covers operation in space,
and also operation of the flywheel in a vertical orientation.
A touchdown like the one modeled in Case C must be avoided, as an
unstable touchdown which will induce whirl can result in major
damage to the flywheel module.
NASA/CR—2006-213862 12
O-Ring/Squeeze-Film Damper Support, 0.2 mils Unbalance
0.00
0.25
0.50
0.75
1.00
1.25
1.50
1.75
2.00
Rotor Speed (RPM)
Bounce Mode
Conical Mode
O-Ring/Squeeze-Film Damper Support, 0.2 mils Unbalance
0
100
200
300
400
500
600
Rotor Speed (RPM)
CBB - 75F RBB - 75F CBB - 150F RBB - 150F
Figure 14.—G2 T/D bearing steady state analysis.
The combination of touchdown bearing stiffness and damping, along
with the friction coefficient of the touchdown surfaces and the
bearing drag, determine operation during touchdown. In order to
ensure that the unstable whirl mode is avoided, a map of the
touchdown stability region as a function of damping and stiffness
is made, and the touchdown bearing is designed to operate within
this region, while simultaneously meeting the response and force
requirements (table 5).
Steady state rotordynamics analyis is used to predict the shaft
response and forces at the touchdown bearings (fig. 14). A combined
0.2 mil mass excentricity unbalance force is added at the faces of
the rim to simulate the worst case unbalance, and the bounce mode
is stimulated with parallel unbalance vectors at each end and the
conical mode is stimulated with orthogal unbalance vectors. Note
that the analyses demonstrate that the force and displacement
specifications are met (<2 mils, <1500 lbs), per table
5.
VII. Housing The housing is layered to allow reconfiguration of the
module with less hardware modifications. There are six
layers: combination touchdown bearing, combination magnetic
bearing, rotor, radial magnetic bearing, motor/generator and radial
touchdown bearing. Each layer has all the external power, signal,
thermocouple, and cooling interfaces needed to operate the
component. The housing was not weight optimized. The wall thickness
is relatively high to ensure that no significant structural modes
exist in the operating speed range.
VIII. Conclusions NASA Glenn Research Center has completed the
design of the G2 flywheel module. G2 is a modular low cost
flywheel which can be used for component and system level flywheel
hardware research and systems demonstrations. The G2 flywheel will
deliver 525 W-hr usable energy operating at 90 percent depth of
discharge between 60,000 and 20,000 rpm. It will provide 1 kW of
power at 20,000 rpm and 3 kW of power at 60,000 rpm on a 120V
electrical bus. The module weights 218 lbs. It is approximately 12
inches in diameter and 30 inches long. G2 is intended to be
operated in a laboratory environment and can be mounted in any
orientation. Completion of the G2 flywheel will enable component
flywheel technology development, and in combination with D1 will
allow full speed, power and torque testing to demonstrate single
axis IPACS at NASA Glenn Research Center.
References
1. McLallin, K., Jansen, R., Fausz, J., Bauer, R., “Aerospace
Flywheel Technology Development for IPACS Applications,”
NASA/TM—2001-211093, October 2001.
2. Liu, H.P., Werst, M., Hahne, J., “Prediction of Windage Losses
of an Enclosed High Speed Composite Rotor in Low Air Pressure
Environments,” 2003 ASME Summer Heat Transfer Conference,
Proceedings of HT 2003, ASME, Las Vegas, NV.
NASA/CR—2006-213862 13
3. Dever, T.P., Palazzolo, A.B., Thomas, E.M., and Jansen, R.H.,
“Evaluation and Improvement of Eddy Current Position Sensors in
Magnetically Suspended Flywheel Systems,” July 2001 IECEC
Conference Proceedings, Savannah, Georgia, 2001.
4. Dever, T., et. al., Magnetic Bearing Controller Improvements For
High Speed Flywheel System,” August 2003 IECEC Conference
Proceedings, Portsmouth, VA, 2003.
5. Jansen, R., Lebron, R., Dever, T., Birchenough, A., “PWM
Switching Frequency Effects on Eddy Current Sensors for
Magnetically Suspended Flywheel Systems,” August 2003 IECEC
Conference Proceedings, Portsmouth, VA, 2003.
6. Lebron, R., et. al., “Magnetic Bearing Amplifier Output Power
Filters For Flywheel Systems,” August 2003 IECEC Conference
Proceedings, Portsmouth, VA, 2003.
7. Kenny, B.H., Kascak, P.E. “Sensorless Control of Permanent
Magnet Machine for NASA Flywheel Technology Development,” 37th
Annual IECEC, Washington DC, July 28—August 2, 2002.
NASA/TM—2002-211726.
8. Kenny, B.H., Kascak, P.E., “DC Bus Regulation with a Flywheel
Energy Storage System,” Proceedings of the Society of Automotive
Engineers Power Systems Conference, October 29–31, 2002, Coral
Springs, Fl., CD-ROM. NASA/TM—2002- 211897.
9. Santiago, W., “Inverter Output Filter Effects on PWM Motor
Drives of a Flywheel Energy Storage System,” August 2004 IECEC
Conference Proceedings, Providence, RI, 2004.
This publication is available from the NASA Center for AeroSpace
Information, 301–621–0390.
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Available electronically at http://gltrs.grc.nasa.gov
E–15232
19
Flywheel; Design; Motor; Generator; Magnetic bearing
University of Toledo 2801 W. Bancroft St. Toledo, Ohio
43606–3390
Prepared for the Second International Energy Conversion Engineering
Conference sponsored by the American Institute of Aeronautics and
Astronautics, Providence, Rhode Island, August 16–19, 2004. Ralph
H. Jansen, University of Toledo, 2801 W. Bancroft St., Toledo, Ohio
43606; and Timothy P. Dever, QSS Group, Inc., 21000 Brookpark Road,
Cleveland, Ohio 44135. Project Manager, Kerry L. McLallin, retired.
Responsible person, Raymond F. Beach, Power and Electrical
Propulsion Division, NASA Glenn Research Center, organization code
RPE, 216–433–5320.
Design of a flywheel module, designated the G2 module, is
described. The G2 flywheel is a 60,000 RPM, 525 W-hr, 1 kW system
designed for a laboratory environment; it will be used for
component testing and system demonstrations, with the goal of
applying flywheels to aerospace energy storage and integrated power
and attitude control (IPACS) applications. G2 has a modular design,
which allows for new motors, magnetic bearings, touchdown bearings,
and rotors to be installed without a complete redesign of the
system. This design process involves several engineering
disciplines, and requirements are developed for the speed, energy
storage, power level, and operating environment. The G2 rotor
system consists of a multilayer carbon fiber rim with a titanium
hub on which the other components mount, and rotordynamics analysis
is conducted to ensure rigid and flexible rotor modes are
controllable or outside of the operating speed range. Magnetic
bearings are sized using 1-D magnetic circuit analysis and refined
using 3-D finite element analysis. The G2 magnetic bearing system
was designed by Texas A&M and has redundancy which allows
derated operation after the loss of some components, and an
existing liquid cooled two pole permanent magnet motor/generator is
used. The touchdown bearing system is designed with a squeeze film
damper system allowing spin down from full operating speed in case
of a magnetic bearing failure. The G2 flywheel will enable module
level demonstrations of component technology, and will be a key
building block in system level attitude control and IPACS
demonstrations.
Unclassified -Unlimited Subject Categories: 18, 20, 31, 33, and
37
E-15232 CoverNew.pdf
E-15232 layout.pdf
E-15232 RDPnew.pdf
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<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>
/SUO
<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>
/SVE
<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>
/ENU (Use these settings to create Adobe PDF documents for quality
printing on desktop printers and proofers. Created PDF documents
can be opened with Acrobat and Adobe Reader 5.0 and later.)
>> /Namespace [ (Adobe) (Common) (1.0) ] /OtherNamespaces [
<< /AsReaderSpreads false /CropImagesToFrames true
/ErrorControl /WarnAndContinue /FlattenerIgnoreSpreadOverrides
false /IncludeGuidesGrids false /IncludeNonPrinting false
/IncludeSlug false /Namespace [ (Adobe) (InDesign) (4.0) ]
/OmitPlacedBitmaps false /OmitPlacedEPS false /OmitPlacedPDF false
/SimulateOverprint /Legacy >> << /AddBleedMarks false
/AddColorBars false /AddCropMarks false /AddPageInfo false
/AddRegMarks false /ConvertColors /NoConversion
/DestinationProfileName () /DestinationProfileSelector /NA
/Downsample16BitImages true /FlattenerPreset <<
/PresetSelector /MediumResolution >> /FormElements false
/GenerateStructure true /IncludeBookmarks false /IncludeHyperlinks
false /IncludeInteractive false /IncludeLayers false
/IncludeProfiles true /MultimediaHandling /UseObjectSettings
/Namespace [ (Adobe) (CreativeSuite) (2.0) ]
/PDFXOutputIntentProfileSelector /NA /PreserveEditing true
/UntaggedCMYKHandling /LeaveUntagged /UntaggedRGBHandling
/LeaveUntagged /UseDocumentBleed false >> ] >>
setdistillerparams << /HWResolution [600 600] /PageSize
[612.000 792.000] >> setpagedevice
<< /ASCII85EncodePages false /AllowTransparency false
/AutoPositionEPSFiles true /AutoRotatePages /None /Binding /Left
/CalGrayProfile (Dot Gain 20%) /CalRGBProfile (sRGB IEC61966-2.1)
/CalCMYKProfile (U.S. Web Coated \050SWOP\051 v2) /sRGBProfile
(sRGB IEC61966-2.1) /CannotEmbedFontPolicy /Warning
/CompatibilityLevel 1.4 /CompressObjects /Off /CompressPages true
/ConvertImagesToIndexed true /PassThroughJPEGImages true
/CreateJDFFile false /CreateJobTicket false /DefaultRenderingIntent
/Default /DetectBlends true /DetectCurves 0.0000
/ColorConversionStrategy /sRGB /DoThumbnails true /EmbedAllFonts
true /EmbedOpenType false /ParseICCProfilesInComments true
/EmbedJobOptions true /DSCReportingLevel 0 /EmitDSCWarnings false
/EndPage -1 /ImageMemory 1048576 /LockDistillerParams false
/MaxSubsetPct 100 /Optimize true /OPM 1 /ParseDSCComments true
/ParseDSCCommentsForDocInfo true /PreserveCopyPage true
/PreserveDICMYKValues true /PreserveEPSInfo true /PreserveFlatness
true /PreserveHalftoneInfo false /PreserveOPIComments false
/PreserveOverprintSettings true /StartPage 1 /SubsetFonts true
/TransferFunctionInfo /Preserve /UCRandBGInfo /Preserve
/UsePrologue false /ColorSettingsFile (None) /AlwaysEmbed [ true
/TimesNewRomanPS-BoldItalicMT /TimesNewRomanPS-BoldMT
/TimesNewRomanPS-ItalicMT /TimesNewRomanPSMT ] /NeverEmbed [ true ]
/AntiAliasColorImages false /CropColorImages true
/ColorImageMinResolution 300 /ColorImageMinResolutionPolicy /OK
/DownsampleColorImages true /ColorImageDownsampleType /Bicubic
/ColorImageResolution 300 /ColorImageDepth -1
/ColorImageMinDownsampleDepth 1 /ColorImageDownsampleThreshold
1.00000 /EncodeColorImages true /ColorImageFilter /DCTEncode
/AutoFilterColorImages true /ColorImageAutoFilterStrategy /JPEG
/ColorACSImageDict << /QFactor 0.15 /HSamples [1 1 1 1]
/VSamples [1 1 1 1] >> /ColorImageDict << /QFactor 0.15
/HSamples [1 1 1 1] /VSamples [1 1 1 1] >>
/JPEG2000ColorACSImageDict << /TileWidth 256 /TileHeight 256
/Quality 30 >> /JPEG2000ColorImageDict << /TileWidth
256 /TileHeight 256 /Quality 30 >> /AntiAliasGrayImages false
/CropGrayImages true /GrayImageMinResolution 300
/GrayImageMinResolutionPolicy /OK /DownsampleGrayImages true
/GrayImageDownsampleType /Average /GrayImageResolution 300
/GrayImageDepth -1 /GrayImageMinDownsampleDepth 2
/GrayImageDownsampleThreshold 1.00000 /EncodeGrayImages true
/GrayImageFilter /DCTEncode /AutoFilterGrayImages true
/GrayImageAutoFilterStrategy /JPEG /GrayACSImageDict <<
/QFactor 0.76 /HSamples [2 1 1 2] /VSamples [2 1 1 2] >>
/GrayImageDict << /QFactor 0.15 /HSamples [1 1 1 1] /VSamples
[1 1 1 1] >> /JPEG2000GrayACSImageDict << /TileWidth
256 /TileHeight 256 /Quality 30 >> /JPEG2000GrayImageDict
<< /TileWidth 256 /TileHeight 256 /Quality 30 >>
/AntiAliasMonoImages false /CropMonoImages true
/MonoImageMinResolution 1200 /MonoImageMinResolutionPolicy /OK
/DownsampleMonoImages true /MonoImageDownsampleType /Average
/MonoImageResolution 300 /MonoImageDepth -1
/MonoImageDownsampleThreshold 1.00000 /EncodeMonoImages true
/MonoImageFilter /CCITTFaxEncode /MonoImageDict << /K -1
>> /AllowPSXObjects false /CheckCompliance [ /None ]
/PDFX1aCheck false /PDFX3Check false /PDFXCompliantPDFOnly false
/PDFXNoTrimBoxError true /PDFXTrimBoxToMediaBoxOffset [ 0.00000
0.00000 0.00000 0.00000 ] /PDFXSetBleedBoxToMediaBox true
/PDFXBleedBoxToTrimBoxOffset [ 0.00000 0.00000 0.00000 0.00000 ]
/PDFXOutputIntentProfile (None) /PDFXOutputConditionIdentifier ()
/PDFXOutputCondition () /PDFXRegistryName () /PDFXTrapped /False
/Description << /CHS
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/CHT
<FEFF4f7f752890194e9b8a2d7f6e5efa7acb7684002000410064006f006200650020005000440046002065874ef653ef5728684c9762537088686a5f548c002000700072006f006f00660065007200204e0a73725f979ad854c18cea7684521753706548679c300260a853ef4ee54f7f75280020004100630072006f0062006100740020548c002000410064006f00620065002000520065006100640065007200200035002e003000204ee553ca66f49ad87248672c4f86958b555f5df25efa7acb76840020005000440046002065874ef63002>
/DAN
<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>
/DEU
<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>
/ESP
<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>
/FRA
<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>
/ITA
<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>
/JPN
<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>
/KOR
<FEFFc7740020c124c815c7440020c0acc6a9d558c5ec0020b370c2a4d06cd0d10020d504b9b0d1300020bc0f0020ad50c815ae30c5d0c11c0020ace0d488c9c8b85c0020c778c1c4d560002000410064006f0062006500200050004400460020bb38c11cb97c0020c791c131d569b2c8b2e4002e0020c774b807ac8c0020c791c131b41c00200050004400460020bb38c11cb2940020004100630072006f0062006100740020bc0f002000410064006f00620065002000520065006100640065007200200035002e00300020c774c0c1c5d0c11c0020c5f40020c2180020c788c2b5b2c8b2e4002e>
/NLD (Gebruik deze instellingen om Adobe PDF-documenten te maken
voor kwaliteitsafdrukken op desktopprinters en proofers. De
gemaakte PDF-documenten kunnen worden geopend met Acrobat en Adobe
Reader 5.0 en hoger.) /NOR
<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>
/PTB
<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>
/SUO
<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>
/SVE
<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>
/ENU (Use these settings to create Adobe PDF documents for quality
printing on desktop printers and proofers. Created PDF documents
can be opened with Acrobat and Adobe Reader 5.0 and later.)
>> /Namespace [ (Adobe) (Common) (1.0) ] /OtherNamespaces [
<< /AsReaderSpreads false /CropImagesToFrames true
/ErrorControl /WarnAndContinue /FlattenerIgnoreSpreadOverrides
false /IncludeGuidesGrids false /IncludeNonPrinting false
/IncludeSlug false /Namespace [ (Adobe) (InDesign) (4.0) ]
/OmitPlacedBitmaps false /OmitPlacedEPS false /OmitPlacedPDF false
/SimulateOverprint /Legacy >> << /AddBleedMarks false
/AddColorBars false /AddCropMarks false /AddPageInfo false
/AddRegMarks false /ConvertColors /NoConversion
/DestinationProfileName () /DestinationProfileSelector /NA
/Downsample16BitImages true /FlattenerPreset <<
/PresetSelector /MediumResolution >> /FormElements false
/GenerateStructure true /IncludeBookmarks false /IncludeHyperlinks
false /IncludeInteractive false /IncludeLayers false
/IncludeProfiles true /MultimediaHandling /UseObjectSettings
/Namespace [ (Adobe) (CreativeSuite) (2.0) ]
/PDFXOutputIntentProfileSelector /NA /PreserveEditing true
/UntaggedCMYKHandling /LeaveUntagged /UntaggedRGBHandling
/LeaveUntagged /UseDocumentBleed false >> ] >>
setdistillerparams << /HWResolution [600 600] /PageSize
[612.000 792.000] >> setpagedevice