SATPC0042462 TAB 04 4 SOW.pdf

Icing Team: Facility Team:

E. Timko P. Rachow T. Bartkus P. Lizanich J. Casciano

Multi-Probe Traversing System for Icing Cloud Instrumentation Statement of Work and Supporting Information for Redesign

SCOPE

NASA Glenn Research Center has a requirement to calibrate the icing cloud generated in the Propulsion Systems Laboratory (PSL). The efforts to do this are increasingly more complicated than that of the Icing Research Tunnel (IRT) due mostly to the fact that access to the test section in the test cell is limited. Deicing of instrumentation cannot be done as it is in IRT, and other methods must be employed. These methods include but are not limited to added heaters, relocation out of the flow, and remote deicing measures. In the event that an instrument has built up ice, it takes time to clear the ice in order to take trusted measurements. When one instrument is deicing, another instrument can be in the flow collecting data and making the most of the test time allocated for a specific campaign. Successful demonstration of a multi-probe traversing system was completed in a Fundamental Icing Physics research project in 2018 (Ref 1) but with this, limitations to the traverse system design arose. A redesign of the Multi- Probe Traversing System (MPTS) will take place, and this document will provide further details for the cloud instrumentation.

The next design will still incorporate traversal, accomplished using Velmex bislides. Additionally, the next design will continue the use of heaters attached to leading edge of the airfoil struts holding the instrumentation in airstream.

BACKGROUND

Icing cloud capabilities have existed in PSL since 2011. Since 2013, several turbofan engine/rig and fundamental ice crystal icing tests have taken place but in 2018, non-icing campaigns held precedent leading to the removal and storage of the icing spray system from Test Cell 3. The NASA Glenn team has a requirement to reestablish the icing capabilities in Test Cell 3 and calibrate the icing cloud for ice crystal, mixed phase, and supercooled liquid icing. During calibration tests, the icing cloud characteristics of total water content (TWC), particle size distribution and overall cloud uniformity is determined.

Previously, this has been completed at the PSL instrumentation duct centerline for various cloud and tunnel flow control inputs. Through recent calibrations and fundamental ice crystal icing tests, it was apparent that a radial variation of properties of the icing cloud existed, but the amount of variation depended on the cloud and tunnel flow conditions. (Ref. 1 and Ref. 3) To establish a radial profile of the icing cloud at PSL, in-situ measurements with the selected calibration probes at various off-centerline positions is required.

In the interest of test time, a traversing system was developed to translate the icing probes radially to characterize the icing cloud. This traversing system saves test time, by not requiring the mid-cell manual adjustment [2 hours of testing time per adjustment] of icing instrumentation probes but instead allows for remote adjustment during operations.

OBJECTIVE

The Contractor shall design an improved and modified multi-probe traversing system to incorporate 6 smaller instruments [Multi-Wire (MW), Total Air Temperature (TAT) Probe, Rearward Facing Probe [RFP], Ice Detector (ID), Ice Crystal Detector (ICD) and an Aero-Thermal Probe (ATP)] and 2 flight instrumentation PI-IC (Particle Imager-Ice Crystal Probe) and OAP (Optical Array Probes

The MPTS-II design will have 4 vertical traversing struts for the smaller instruments and 1 horizontal traverse for the flight instrumentation probes. The small instruments that are installed will be used together for an entire test night without the need to change within a single test night. There are 2 extra small instrument probes and 1 other flight probes that would be intermittently changed/swapped during dayshift. These total the 6 small instruments and 2 flight instrumentation probes.

Current MPTS design utilizes all 6 small instruments next to one another and traverses using 4 x Velmex UniSlides. New design will plan to utilize Velmex BiSlides to accomplish traversal in all directions.

The Contractor shall also provide NASA and GE with drawings and structural analysis and participate in design meetings with the NASA and GE team.

Additional information on structural requirements and loading found section 3 of requirements.

We would like to have weekly progress update meetings on design as it moves through manufacturing and production and there is a possibility of having meetings with NASA and GE team as design nears completion and any small changes are ironed out.

REQUIREMENTS

This section will outline the engineering requirements of the MPTS II which will include details on the range of each instrument, repeatability precision, defined radial profile positioning, instrumentation compatibility and more.

1.) Smaller instrument traversing arm requirements:

a. The traversing arm size shall be optimized with respect to the aerodynamic profile and shall be fully retractable out of the flow.

Small instrumentations are mounted to a custom-made sensor vertical support strut assembly [Dwg No. 141004MRA526]. A new longer set of 4 of these will need to be created to attach our small instrumentation to the BiSlide’s to traverse in and out of the flow. The new design will still need a hollowed feedthrough and an aerodynamic profile for components exposed to the flow to reduce drag and loading applied to hardware.

b. There shall be a deicing capability for any part of the traversing arm that is exposed to the icing cloud. This shall include multizone anti-icing capabilities with respect to position of the probe as to not overheat any part not exposed to the flow.

This was previously accomplished through use of 3 x Omega Engineering Kapton Insulated Flexible Heaters per small instrumentation strut mount. Due to the new struts needing a longer area for traversal, larger Omega Engineering Kapton Insulated Flexible Heaters can be used to adequately cover the surface for anti-icing capabilities.

c. Traversing speed, from stowed position to measurement position shall not exceed 30 seconds.

Lead screw pitch and motor determines this, although our application and other loading requirements may make this request less likely. We desire to be as close as possible to this time for traversing an 80” Velmex BiSlide full stroke.

d. A design factor for ice accretion shall be made for vibrational resonant frequency issues while in the flow when there is ice accretion on the arm.

e. The interface shall enable the power and data cables for each instrument be connected and have a clear pass through the traverse arm.

Previous design required mounting of the small instrumentation power supplies onto the vertical slides support plate assembly [Dwg No. 141004MRA505]. Likely this still be required for new design to ensure cables are routed properly and have enough room.

f. Each traversing arm shall be remotely controlled from a PLC system. The distance between the system and the PLC system shall be 75feet. The PLC system shall be controlled via MMI which shall be extended from the fiber optic premise system from both the control room and the test cell area. Terminal style language that the Velmex VXC stepper motor controllers use for control can be implemented into PSL and for development of a Labview/MMI screen.

g. The position of each instrument shall be measured and reported though a ModBus feed to PSL’s data acquisition system, COBRA. The position shall also be reported through a serial data feed to appropriate instrument’s data acquisition system (SEA M300 or Artium AIMS). The reference position in cartesian coordinates (0,0) will be set to the calibration duct centerline. See Appendix G for example of previous control panel page.

The serial interface found on the Velmex VXC stepper motor controllers will likely be our means of communicating to the SEA M300/Atrium AIMS but the first requirement of the instrument’s positions being communicated to the PSL DAQ Cobra can be accomplished likely via your Encoders.

h. Position repeatability precision to +/- ¼”

i. Traverse to cover entire defined duct size of 54” diameter

Traverse range will be covered under 60”/80” Velmex BiSlides.

j. The sampling location shall maintain an axial distance aft of the exit plane of 6”

This should be factored into the design as the mounting plates and orientation of hardware will determine how close to the duct we can get to achieve the 6” distance.

Small Instrumentation Design:

X Axis Traversal: Framing and linear stages will need to be rigid against forces applied by facility cooling air/flowing icing air. Linear stage setup:

1. 4 x 80” Motorized BiSlide Linear Stage [Nema 34 Motor]

Z Axis Traversal: Mounting hardware for linear stages and instrumentation shall be rigid enough to withstand forces applied by facility cooling air/flowing icing air. Linear stage setup:

1. 4 x 70” Motorized BiSlide Linear Stage [Nema 34 Motor] Each stage will have a custom traversing arm that possesses proper feedthroughs, mounting holes for the stage and instrumentation, as well as an aerodynamic profile to reduce drag forces imposed on arm as icing air flows across it.

2.) Flight probe traversing strut requirements

a. Same requirements from 1a-1i

b. Careful execution of movement as to not collide with separate IKP traversing system

c. The sampling location shall maintain an axial location aft of the exit plane no further than 12” This distance will be accomplished through a combination of design and mounting bracket placement. We will want to try and keep center of gravity of flight instrumentation close to slide to not induce to much of a moment but will want the sampling location to still sit no further than 12” away from the exit plane.

d. The flight probes must have the arms oriented so that the lenses are vertical, ie., to prevent any pooling on a flat lens.

This shouldn’t be an issue as we will mount the flight instrumentation vertically as shown in the reference images.

Flight Instrumentation Design:

X Axis Traversal: Framing and linear stages will need to be rigid against forces applied by facility cooling air/flowing icing air. An aerodynamic profile icing guard will need to be applied to icing air flow side of the linear stage. Mounting hardware for flight instrumentation will need to place each probe at correct depth location with respect to outlet of duct. Linear stage setup:

1. 1 x 80” Motorized BiSlide Linear Stage [Nema 34 Motor]

Z Axis Traversal: Mounting hardware for linear stages and instrumentation shall be rigid enough to withstand forces applied by facility cooling air/flowing icing air. Linear stage setup:

1. 2 x 80” Motorized BiSlide Parallel Coupled Linear Stage [Nema 34 Motor]

3.) The traverse system shall have sufficient structural strength to manage the loads imposed on it during PSL operating conditions.

a. Structural design factors shall be:

i. A factor of 1.5 for yield strength

ii. A factor of 2.5 for ultimate strength

Design shall incorporate design factors highlighted above and be capable of withstanding expected loading of hardware based on weight of components, complimentary mounting hardware, and loading imposed on structure from facility conditions highlighted below.

b. The atmospheric and flow conditions in PSL Test Cell 3 are as follows:

i. Static Pressure (Ps): 12.2 to 1.7 psia [Altitude: 5,000-50,000 ft]

ii. Total Air Temperature (Tt): [-40° to +50° F]

iii. Mass Flow: [0 – 330 lbm/s]

iv. Airspeed Range: [0 – 185 m/s]

The design should be capable of withstanding pressure, temperature, and load conditions applied during testing operations. Secondary 40 psig cooling air supply is utilized for keeping additional instrumentation to 60℉ ± 10℉, although the motors should withstand altitude pressure conditions and not overheat. This point is referenced again in our appendix A.

Important to note humidity created can propagate to a variety of areas in testing area but that coldest temperature conditions and ice formation to likely only occur inside of area where hardware is exposed to flow stream [Instrumentation, small instrumentation weldment support strut, flight instrumentation bislide].

4.) The support structure/frame of the traverse system shall be a floor-mounted design with adaptability to different calibration duct sizes. The frame must not be supported by ducting as this could change for each test entry.

a. Previous design relied on ducting to support framing.

New design shall not use ducting to support and must be independently supported from floor will be tied into facility using mounting plates with variable location placement.

5.) The traversing subsystems shall not pass the same space as the other systems. See Appendix A for lessons learned on collision risks.

6.) The interface shall enable the instruments’ power and data cables be connected and have clear pass through the traverse arm.

7.) The traverse actuation system shall control the strut heaters operating on 115 VAC 60 cycle power.

8.) The traverse system shall consist of a frame and actuation system that can be assembled and disassembled at PSL. The actuation system shall incorporate hoist rings to raise actuation system onto the frame in PSL test cell 3. Entire design should be easily assembled and disassembled using properly rated fasteners and incorporate hoist/lifting points for movement into place using an overhead crane [5 Ton crane available]. Ideally the upper sub-assembly will be the small instrumentation, and lower subassembly will be the flight instrumentation that can be stacked and bolted together.

Final Design:

Framing design shall incorporate multiple tie-down or connection points on base of frame to integrate custom facility mounting brackets to nearest available tie-down location.

Framing shall incorporate multiple positions for vertically mounted small instrumentation linear stage system to adjust for changing reference height if a riser is added underneath system. Frame shall be made in a way that is easily assembled, disassembled, transported and stored. Framing, linear stages, and accompanying hardware shall be rated to within stand loads applied by facility as well as conditions hardware will be exposed to such as potential water, pressure and temperature variations [Limit switches rated for water exposure, lubrication rated for pressure and potential light water exposure, hardware rated for adequate cooling]. Controls for linear stages shall be re-incorporated into system with already compatible interface hardware and ready for use. Velmex Inc. hardware assembly and bislides are proven, trusted, and were previously integrated into PSL already for icing cloud characterization research. First party warranty for craftsmanship and operational integrity required for procured hardware.

The requirements for each instrument are listed below. Schematics and line drawings for the instruments can be found in Appendix B though G.

Instrumentation:

1.) Ice Detector (ID) [Small Instrument]

a. Manufacturer: Goodrich/Rosemount Aerospace/UTC Aerospace/Collins

Aerospace (Model Series 0871LM5)

b. Operation: Vibrating pin reduces in vibration frequency when ice accretes.

Indicates presence of supercooled liquid (SCL). Can infer fully glaciated ice crystal cloud if frequency does not change. Clears accrete ice off strut and pin by cycling through de-ice heating.

c. Range of motion: probe entire area of 54” diameter duct

d. No combinations of motions expected with this probe

e. Data required: probe position as coordinates

f. Data outputs from probe: vibration frequency, probe operational status (clean, iced, deicing), deice cycle count

g. M300 data system interface outputted to KVM system

h. Connector: D38999 / 24WD97PN (mates with D38999 / 26WD97SN) - 40ft length

i. Power consumption

i. Sensing mode: Less than 10 Watts at 28 VDC

ii. De-icing mode: 330 Watts max at 28 VDC

j. Weight: 0.85 lbs

k. Line Drawings / Mounting Interface: See Appendix B

Figure 1: Ice Detector

2.) Total Air Temperature Probe (TAT) [Small Instrument]

a. Manufacturer: Rosemount Aerospace, Inc., (Model 102LJ2AG with Ejector)

b. Operation: Provides temperature measurement under atmospheric icing conditions: ice crystals, mixed phase, and supercooled liquid.

c. Range of motion: probe entire area of 54” diameter duct

d. No combinations of motions expected with this probe

e. Data required: probe position as coordinates

f. Data outputs from probe: total air temperature, deice heat on/off

g. M300 data system interface outputted to KVM system

h. Connector

i. Electrical: D38999 / 24FD97PN (Must verify), Must determine cable length

ii. “Air Pressured Ejector”: compressed air at 7 to 40 psig pressure, must determine air tube length

i. Power consumption

i. Sensing mode: 5 Watts max at 28 VDC

ii. Rated Heater Voltage: 115V RMS or 115 VDC, self-limiting

iii. 325 Watts in-flight power consumption

j. Discrete outputs: customer selectable output configuration

k. Weight: 0.95 lb

l. Line Drawings / Mounting Interface: See Appendix C

Figure 2: TAT probe with electrical interface capped in yellow, and air pressured ejector interface capped in red.

3.) Multi-Element Sensor (MW) [Small Instrument]

a. Manufacturer: SEA Inc.

b. Operation: Hot-wire elements maintained at constant temperature to measure total liquid water content

c. Range of motion: probe entire area of 54” diameter duct

d. No combinations of motions expected with this probe

e. Data required: probe position as coordinates

f. Data outputs from probe: total water content (power and temperature of all wires and cowling)

g. M300 data system interface outputted to KVM system

h. Connector: see schematics and image below (same as ICD). Must find PSL’s cable, length currently unknown.

i. Power consumption

i. 3.5 – 54 A range, 11 amps typical

ii. Power supply = 28 VDC nominal, 18-32 VDC

j. Discrete outputs: customer selectable output configuration

k. Weight: Sensor head: 1.5 lb; Power Control Box: 12.0 lb

l. Serial ports: 2 RS-422

m. Line Drawings / Mounting Interface: See Appendix D

n. Special Notes: The MW probe head is interchangeable with the ICD probe head.

The design can eliminate one of the traverse arms as either the MW or ICD will be used.

M300

Figure 3: MW system components. The multi-element control system is embedded in the M300. Bottom image shows how the MW has the same mechanical and electrical cable interfacing as the ICD.

4.) Rearward Facing Probe (RFP)

a. Categorized as a “small” instrument

b. Manufacturer: NASA inhouse.

i. RTD located near probe inlet measures air temperature.

ii. Humidity measured by sampling air collected from probe inlet utilizing pump to draw air to downstream Licor and/or SpectraSensor

c. Operation:

i. Measures air temperature at test section during cloud off and cloud on (ice crystal clouds only).

ii. Measures background humidity at test section during cloud off and cloud on (ideally ice crystal clouds, possibly SCL clouds)

d. Range of motion: probe entire area of 54” diameter duct

e. No combinations of motions expected with this probe

f. Data required: probe position as coordinates

g. Data outputs from probe: Temperature and humidity (ppm water vapor)

h. RTD instrumentation and Licor/Spectrasensor instruments connected to M300 data acquisition system, outputted to KVM system.

i. Connector:

i. Temp: Omega RTD-3-F3105-360-T wire coupled with Accutech AI-1500 transmitter, connected to Analogue-to-Digital Converter

ii. Humidity: Teflon tubing within probe connects to suction pump and

Licor/SpectraSensor humidity panel

j. Power consumption: Various instruments located outside of tunnel

k. Weight: 1.2 lbs for entire tube length

l. Line Drawings / Mounting Interface: The aluminum tube is 48” in length and 7” in width (bent section) with 0.75” outer diameter. A simple mounting collar with set screws is used to hold the RFP in place (see image of mounting collar). Can provide more details of mounting collar if needed.

m. Special notes:

i. RFP design faces backward with inlet tip about 7” aft of vertical portion of tube

ii. Probe hanging down orientation required

Figure 2: Images of 2 RFP and its mounting collar used at IRT.

5.) Ice Crystal Detector

a. Categorized as a “small” instrument

b. Manufacturer: SEA Inc.

c. Operation: constant-temperature hot-wire, simultaneous measurement of liquid and ice water content

d. Range of motion: probe entire area of 54” diameter duct

e. No combinations of motions expected with this probe

f. Data required: probe position as coordinates

g. Data outputs from probe: total water content (power and temperatures from instrument components)

h. M300 data system interface outputted to KVM system

i. Connector: See image below (same as MW). Must find PSL’s cable, length currently unknown.

j. Power consumption: need power consumption

k. Discrete outputs: customer selectable output configuration

l. Weight: ~2 lbs

m. Line Drawings / Mounting Interface: See Appendix F (Need line drawings)

n. Special Notes: The ICD probe head is interchangeable with the MW probe head.

The design can eliminate one of the traverse arms as either the MW or ICD will be used.

Figure 5: ICD sharing the same mechanical and electrical cable interfacing as the MW.

6. Particle Imager – Ice Crystal (PI-IC) probe [Flight Instrument]

a. Manufacturer: Artium Technologies

b. Operation: Measures ice crystal cloud (only) particle size distribution by visually imaging particles that pass-through sample area between camera and LED light source. It can measure ice crystal particle between 3.7 and 1500 microns in diameter.

c. Range of motion: probe entire area of 54” diameter duct

d. No combinations of motions expected with this probe

e. Data required: probe position as coordinates

f. Data outputs from probe: Images of particles captured – sent to PI-IC computer

g. Interfaces with dedicated PI-IC computer using AIMS software

h. Connector: Multiple. See Figure below for cable interfaces.

i. In and out feed for air purge (to prevent condensation inside internal cavity).

ii. 12 pin cable that powers heater and electronics (75 ft length). See Appendix E for power connector details.

iii. Fiber optic cable for video data (75 ft length)

i. Power consumption:

i. Internal heaters (240 V, ~1600W),

ii. Internal electronics (28VDC, unknown power consumption, but likely negligible)

j. Weight: 12.2 lbs

k. Line Drawings / Mounting Interface: See Appendix E

Figure 4: Images of the PI-IC and sample output of particles captured by probe. Cable and mounting interface on the right

7.) Canister Flight Probe [Flight Instrument]

a. Optical Array Probe

b. Manufacturer: Legacy OAP230s and CIP were manufactured by Particle

Measuring Systems but Science Engineering Associates has since developed OAP- 1D2D probes.

c. Operation:

i. OAP-230: Measures particle size using diode shadowing method with an array of photodiodes.

ii. OAP-1D2D: Uses optical fibers and avalanche photodiodes. Records monochromatic 2D images as well as recording the number of individual counts for 1D data stream (Ref 5)

d. Range of motion: probe entire area of 54” diameter duct

e. No combinations of motions expected with this probe

f. Data required: probe position as coordinates

g. Data outputs from probe: Particle size, number density, LWC

h. M300 data system interface outputted to KVM system

i. Connector: see Figure 9

j. Power consumption

i. Probe Power:

a. OAP-230s are 120 VAC

b. OAP-1D2DY is 120 VAC

ii. Deice:

a. OAP-230s are 28 VDC

b. OAP-1D2D is 120 VAC

k. Discrete outputs: customer selectable output configuration

l. Weight: 40 lbs

m. Serial ports: RS-422

n. Line Drawings / Mounting Interface: See Figure 8 and Appendix F

o. Special note: ensure proper dimension for routing of multi-connector cabling

(Figure 7).

Figure 5: OAP installed in Icing Research Tunnel and teardrop mounting interface.

Figure 6: Multi-connector cable for OAP-1D2DY

REFERENCES

[1] Van Zante, J.F., et al. “Update on the NASA Glenn Propulsion Systems Lab Icing and Ice Crystal Cloud Characterization (2017),” AIAA Aviation 2018 Forum. DOI: 10.2514/6.2018-3969

[2] Struk, P., et al. “Ice-Crystal Icing Accretion Studies at the NASA Propulsion Systems Laboratory,” International Conference on Icing of Aircraft, Engines, and Structures, SAE Technical Paper. 2019. DOI: 10.4271/2019-01-1921

[3] Bartkus, T. P. and Struk, P. M. “Comparisons of CFD Simulations of Icing Wind Tunnel Clouds with Experiments Conducted at the NASA Propulsion Systems Laboratory,” AIAA Aviation 2020 Forum. DOI: 10.2514/6.2020-2832

[4] Droplet Measurement Technologies: Cloud Droplet Probe (CDP) Manual. DOC-0029, Rev O.

2012.

[5] Lilie, L. et al. “A New 1D2D Optical Array Particle Imaging Probe for Airborne and Ground Simulation Cloud Measurements,” SAE Technical Paper. 2023. DOI: 10.4271/2023-01-1415

[6] King, M.C., et al. “Particle Size Calibration Testing in the NASA Propulsion System Laboratory,” AIAA Aviation 2018 Forum. DOI: 10.2514/6.2018-3971.

[7] King, M.C., et al. “Particle Size Measurements from the First Fundamentals of Ice Crystal Icing Physics Test in the NASA Propulsion Systems Laboratory,” AIAA Aviation 2017 Forum. DOI:

10.2514/6.2017-4244

APPENDICES

Appendix A (MPTS I Lessons Learned)

The first multi-probe traversing system that was developed had performance and operation issues. This section outlines the issues with the electrical components and the traversing strut interface.

The motors were undersized:

• When testing at ambient temperature, the motors got close to their operational temperature limit.

• A few times during testing this caused the probe to stop moving because the controls had an overtemp limit built in. This resulted in time lost while waiting a few minutes for it to cool down.

• There were a few flow conditions where the motor wasn’t strong enough to push the probe all the way into the flow. There was a possibility that the next sized motor (at least from that brand) had a larger footprint and would require a re-design of the probe traverse.

The larger nema 34 stepper motors (Velmex) could ensure a more robust traversal system from a loading standpoint, while ensuring they stay as cool as possible. Secondary 40 psig cooling air supply is utilized for keeping additional instrumentation to 60℉± 10℉, although the motors should still withstand altitude pressure conditions and not overheat.

The cables trays were also undersized. There was a concern that all the cabling would not fit in the trays that were on the system. Everything was able to fit but a redesign would benefit from larger cable trays.

The previous traversing system used IGUS e-tracks, therefore cable routing will need to be considered into the design offered. If using something different than something IGUS offers, PSL would like to ensure its sized up and routed properly to prevent any damage to cables/instrumentation.

Any cable routing will require the design to incorporate mounting holes attach the cable management system to the assembly. If using larger IGUS e-tracks we can procure if mounting holes are factored in for install.

Limit switches on the non-intrusive and/or airfoil were not correctly rated for any water exposure and some of the limit switches on the MPTS probes were not the correct type. Please ensure limit switches are rated for water/humidity exposure.

The airfoil was too heavy and when the motor would stop, the airfoil would slide down and a brake was installed. However, at some conditions or with enough ice accretion, the brake would fail, and the airfoil would slip again.

The previous traversing system did not use Velmex hardware but intended design will use 2 x 80” Velmex bislides in parallel to lift 1 x 80” Velmex bislide that will traverse our flight instrumentation [Flight Cannister Probe/Particle Imager]. Our heaviest flight instrumentation hardware will weigh 40 lbs.

not including any mounting bracket hardware.

Appendix B (Ice Detector (ID))

Appendix B Figure 1: Line drawing of Ice Detector (ID) with mounting interface

Appendix B Figure 2: Interfacing instrumentation for Ice Detector

Appendix C (Total Air Temperature Probe (TAT))

Appendix C Figure 1: Line drawing for TAT

Appendix D (Multiwire Probe (MW))

Appendix D Figure 1: Multi-element sensor configuration and installation overview

Appendix D Figure 2. Probe interface box and breaker box that sends 28VDC from power supply to sensor.

Appendix D Figure 3: Dimensions of MW probe head

Appendix D Figure 4: Dimensions of cabling

Appendix D Figure 5: Dimensions of cabling

Appendix D Figure 6: MW power box dimensions

Appendix E (Particle Imager – Ice Crystals (PI-IC))

Appendix E Figure 1: Line drawings of PI-IC with overall dimensions

Appendix E Figure 2: Details of the mounting interface

Appendix E Figure 3: Power cable connector for PI-IC

Appendix F (Optical Array Probe (OAP) and Cloud Imaging Probe (CIP))

Appendix F Figure 1: Line Drawing of OAP-230X but also compatible with OAP-230Y and OAP-1D2DY and

CIP

Appendix G (Sample Control Panel (PLC) Page used from MPTS-1 at PSL)

Appendix G Figure 1. Sample Control Panel Page for MPTS-1