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• Critical components of ITER can potentially be exposed to a 6kW

unabsorbed ECH microwave

• Takes >10 msec to deactivate microwave, so a fast shutter was explored

to act as a last resort safety fuse

• A 65 mm aperture shutter created by Uniblitz® can close in 52 msec

• To decrease close time, several possible solutions were proposed using

analytical models, prototype generation, and prototype tests

MOTIVATION

An iris shutter mechanism consists

of four fundamental parts: a base

plate, a rotating ring, shutter blades,

and an actuation input.

BACKGROUND

• Increase spring constant for the return mechanism to increase input E

• A new required spring constant value was calculated:

OBJECTIVES

1Department of Mechanical Engineering and Mechanics, Lehigh University, Bethlehem, PA; 2Princeton Plasma Physics Lab, Princeton, NJ

C. Bagley1, A. Zolfaghari2 , M. Gomez2

Analysis of Fast Shutter and Gaussian Telescope Mirror Moving Mechanisms for ITER

The Uniblitz® CS65 65 mm

Optical Shutter was considered

as a baseline 65 mm aperture

fast shutter (52 msec close time)

for application within ITER.

Figure 2: A standard iris mechanism displaying fundamental parts [1]

Base Plate

Rotating Ring

Shutter Blades

Actuation Input

• Discharge electromagnet which holds spring

• Spring returns to its natural length, closing the shutter

• Design modifications explored:

1) decrease blade mass

2) increase spring force

3) alter electromagnet properties

OBJECTIVES

• Explore current fast shutter mechanisms and capabilities

• Allow wave to pass through 65 mm aperture

• Close shutter in ~10 msec

• Use material that can withstand 6kW microwave

𝐸 =1

2𝑚𝑣2 → 𝐸 =

1

2𝑚

𝑑

𝑡

2

→ 𝑡 =𝑑 𝑚

2𝐸

Can decrease time to close t by: • Decreasing blade mass, m • Increasing input energy, E

ANALYSIS AND RESULTS • Current blades stainless steel or BeCu

• Less massive carbon-impregnated polyethylene terephthalate (PET),

“Carbon Feather” was proposed

• Comparable masses for 2in2 samples* of blade materials are shown

below, and the improved close time is predicted

BeCu Stainless Steel Carbon Feather

1.2 g 0.6 g 0.4 g

Upon prototyping and testing this new blade material, the close time was

found to be 28.8 msec, a 41% reduction, with slight losses due to frictional

factors.

Blades must block a 6 kW microwave. A prediction of the thermal failure

time of the blades was made based on thermal properties of PET [3],

assuming total absorption:

Specific heat 𝐶𝑝 1200 J/kg∙K

Melting point 𝑇𝑚 530 K

Latent heat of fusion ∆𝐻𝑓 1.35 x 105 J/kg

Blade mass 𝑚 0.5147 g

Room temp 𝑇𝑜 300 K

Microwave power 𝑃 6000 W

Power absorption % 𝛼 100%

𝒕𝒎 =𝑚 ∙ 𝐶𝑝 𝑇𝑚 − 𝑇𝑜 + ∆𝐻𝑓

𝛼 ∙ 𝑃

= 𝟑𝟓. 𝟑 𝒎𝒔𝒆𝒄

𝑘2

𝑘1=

𝑚2 𝑡22

𝑚1 𝑡21 =

0.00040.0072

0.00120.0492

= 16.33

𝒕 =𝒎

𝒌 𝒌 =

𝒎

𝒕2

• Electromagnetic force must equal spring force at its extended length to

hold shutter in stationary open position

𝐹𝑠𝑝𝑟𝑖𝑛𝑔 = −𝑘𝑥

𝐹𝐸𝑀 =𝐿𝐼2𝑙

2𝑑2

𝑓𝑜𝑟 𝑠𝑡𝑎𝑡𝑖𝑐 𝑠𝑡𝑎𝑡𝑒 (ℎ𝑒𝑙𝑑 𝑜𝑝𝑒𝑛): 𝐹𝑠𝑝𝑟𝑖𝑛𝑔 = 𝐹𝐸𝑀

−𝒌𝑥 =𝐿𝐼2𝑙

2𝑑2

• Increasing 𝒌 will require an increase in 𝐹𝐸𝑀

• Can increase 𝐹𝐸𝑀 by increasing the current I into the electromagnet

To identify factors to decrease close time, an energy analysis was performed:

• Carbon feather blades decrease total close time 𝒕 by 41%

• Need spring constant 𝒌 to be ~16.33× greater for a ~10 msec close time

• Increasing 𝒌 requires a larger 𝐹𝐸𝑀

• Can increase I to increase 𝐹𝐸𝑀

CONCLUSIONS

• Mechanism maintains the parallelism, angle bisection, and angle

congruency of the Gaussian mirror setup under all simulated load

cases

• Mechanism has appropriate degrees of freedom to allow the thermal

deformation

• The addition of a spring between the mirror base plates limits the

total displacement and returns mechanism to nominal position

• ITER vacuum vessel expands and contracts thermally, making it

impossible to maintain a direct alignment of reflectometry microwaves

• Mechanism designed for Equatorial Port 11 to maintain the alignment of

reflectometry waves into a small interspace waveguide

MOTIVATION

CONCLUSIONS

REFERENCES [1] Abhijeet. "Iris Mechanism and Animation." GrabCad. N.p., n.d. Web. 24

July 2015.

[2] Shutter Damping Assembly. Viglione, D. and Yan, H.H. and Jones, J.T.,

assignee. Patent US 8317417 B2. 27 Nov. 2012. Print.

[3] SI Chemical Data Book (4th ed.), Gordon Aylward and Tristan Findlay,

Jacaranda Wiley

[4] Pelcovits, Robert A.; Josh Farkas (2007). Barron's AP Physics C.

Barron's Educatonal Series. p. 646. ISBN 0764137107.

Figure 3: Uniblitz® CS65 65mm Optical Shutter activation mechanism [2]

*Samples courtesy of Vincent Associates®

ACKNOWLEDGEMENTS This work was made possible by funding from the Department of Energy

for the Summer Undergraduate Laboratory Internship (SULI) program and

is supported by the US DOE Contract No.DE-AC02-09CH11466

3 msec, 6%

49 msec, 94%

Total Close Time Breakdown

ElectromagnetSpring

• Shutter to be used as fuse: block the wave until it can be deactivated, which

takes ~100 msec

• Lower-bound estimate of failure time

• Tubes of coolant can surround shutter to prevent failure and extend lifetime

Figure 7: Spring added between baseplates

• A majority (94%) of the total close time is governed by the spring-

linkage actuation

• Forces applied to the front

waveguide holder (right,

brown) to simulate thermal

expansion

• Mechanisms mounted in

both horizontal and vertical

directions

Baseplates maintain parallel alignment

Mirror arm maintains bisection

Angles maintain congruency

Figure 1: Equatorial Port 11, proposed shutter location

Figure 4: Breakdown of electromagnet and spring role in close time

Figure 5: ITER vacuum vessel: Equatorial Port 11, location of 7 Gaussian Mirror

Moving Mechanisms

Figure 6: Required geometric specifications for mechanism

ANALYSIS • Mechanism tested under spring-reinforced and non spring-reinforced

cases (see GIF)

• 10 N preloaded 5000 N/m spring added to limit displacement and

return mechanism to nominal position

RESULTS

Front waveguide

holder

Horizontal Mounts

Vertical Mount

PORT PLUG

X displacement Y displacement Z displacement Total

Figure 8: Vertical mount, forces applied in +Y & +Z to simulate vacuum vessel expansion

X displacement Y displacement Z displacement Total

Figure 9: Horizontal mount, forces applied in +Y & +Z to simulate vacuum vessel expansion

FUTURE WORK

• Assemble ½ size 3D printed prototype of mechanism

• Test prototype under simulated displacement cases shown above

• Submit invention disclosure and work towards patenting

FORCE

X displacement Y displacement Z displacement Total

Figure 10: Vertical mount, force applied in –X to simulate vacuum vessel expansion

X displacement Y displacement Z displacement Total

FORCE

Figure 11: Horizontal mount, force applied in –X to simulate vacuum vessel expansion

• Forces applied in +Y, +Z and then –X to simulate thermal expansion of

ITER vacuum vessel

• Spring was added to limit displacement and return mechanism to its

nominal position (see GIFs)

• Resulting displacements for X, Y, and Z shown below for both horizontal

and vertical mounts

• Parallel alignment and angles were studied for all load cases