ETIF_Handbook_FINAL_.pdf

v table oF contentS Contents

1.0 Environmental Test Engineering Services And Facilities

1.1 Structural Dynamic Testing

1.1.1 Vibration Facility

1.1.2 Acoustic Test Facility

1.1.8 Mass Properties Measurement Facility (MPMF)

1.1.9 High Capacity Centrifuge Facility

1.1.10 Universal Static Test Facility

1.1.11 Small Static Test Facility

1.1.12 Universal Load Testing Machines

1.1.13 Modal Test Facility

1.2 Electromagnetic Testing

1.2.1 Electromagnetic Compatibility Testing

1.2.2 Magnetic Testing

1.3 Space Simulation Testing

1.3.1 Capabilities Summary

1.3.2 Temperature - Humidity

1.3.3 Thermal Vacuum

1.3.4 Solar Simulator (Facillity 211)

1.3.5 Thermal Vacuum Data Acquisition Facility

1.3.6 Thermal Conditioning Units

1.3.7 Electrical Heater Controller (Facility 242, Harrel)

1.3.8 Automated Electric Heater Controller (Facility 315)

1.3.9 Automated Electric Heater Controller (Facility 316)

1.3.10 Rapid Pumpdown System (Facility 208)

1.3.11 Contamination Monitoring

2.0 Integration Services And Facilities

2.1 Mechanical Integration

2.1.1 Handling of Spacecraft

2.1.2 Fabrication Support

2.1.3 Assembly

2.1.4 Functional Checks of Spacecraft Mechanisms

2.1.5 Field Support

2.1.6 Purge Systems

2.2 Thermal System Support Facility

2.3 Cable/Harness and Electrical System Support Facility

2.4 Cleanrooms

2.4.1 Spacecraft Checkout Area (SCA)

2.4.2 RFI Shielded Room

2.4.3 UD T4000 Vibration Test Cell

2.4.4 Space Environment Simulator (SES)

2.4.5 10/120 (Whitehouse) Cleanroom vi

2.4.6 29/160 Cleanroom

2.4.7 29/150 Cleanroom

2.4.8 Cleanroom Tents

2.4.9 Special Payloads Operations and Testing (SPOT) Clean Tents

2.4.10 Portable Down Flow Tents

2.4.11 Unidirectional Flow Clean Bench

2.4.12 Portable Particle Counters

2.4.13 Pressure, Temperature And Humidity Monitoring

2.4.14 Contamination Monitoring and Analysis Lab

2.4.15 Spacecraft Systems Development And Integration Facility (SSDIF), Bldg 29

3.0 Facility Support Services

3.1 Electrical Power

3.1.1 Normal House Power (Commercial)

3.1.2 Emergency Power Systems

3.2 High Pressure GN2 Generating & Storage Systems (Facilities 258 And 263)

3.3 Crane Capacities

3.4 Hydrasets

3.5 Lifting And Handling Devices

3.6 Doorway And Other Clearances

3.7 Air Bearing Supply Stations

3.8 Air Bearings

3.9 GN2 Purge Outlets

3.10 LN2 Fill Stations

3.11 LN2 Storage Vessels

3.11.1 Building 7, 106K Liter (28K Gal) Dewar (Facility 255)

3.11.2 Building 10, 242K Liter (64K Gal) Dewar (Facility 257)

3.12 Portable Air Conditioning (PAC) Units

Appendix – A: Abbreviations, Acronyms, And Symbols Appendix – B: Metric/English Conversion Factors Appendix – C: Decimal Prefixes

2 Environmental Test and Integration Facilities Handbook

1.1 STRUCTURAL DYNAMIC TESTING

1.1.1 Vibration Facility

General: The Vibration Laboratory provides all necessary services and equipment to perform shock and vibration testing of spacecraft and subsystems. Digital control systems provide sinusoidal, random, and transient waveform control to four separate electro-dynamic exciters. All exciters are rigidly mounted to very large reaction masses that are isolated from the building. Digital data acquisition systems condition and record accelerometer, force, and strain gage signals. A small machine shop with drill press, milling machine, and band saw is available for simple fixture fabrication.

Control System: Two control rooms equipped with a state of the art m+p Vibration Controllers provide excitation signals to the exciters. The controllers are capable of putting out sine, random and various transient waveforms (sine burst, classical shock and SRS shock). The controllers have VXI front ends that are configured with 32 channels each. The control rooms are also equipped with digital data recorders (to record time history data), vibration limiters (to provide secondary vibration limiting protection) and response instrumentation conditioning equipment.

Data Acquisition: For smaller channel counts data acquisition is provided by the m+p controllers. For larger channel counts data acquisition is done using a modular 192 channel DataMax system (hard drive digital recorder). Continuous data acquisition rates up to 50 ksamples/sec are achievable. An extensive quantity of accelerometers from Kistler and Endevco are available for your instrumentation needs. Tri-axial force transducers from Kistler are available for force-limited vibration testing. In the event strain data is needed a 32 channel strain gage conditioning system is available. Personnel trained by Vishay/Micro-Measurements are available for any strain gage installations.

Environmental Test and Integration Facilities Handbook 3

Vibration Exciters:

Facility 409 – Unholtz-Dickie T4000-2 Shaker

Usable Frequency Range 5 – 2500 Hz Amplifier Model 2XSAI180 (360 kVA) Maximum Force (Sine) 40,000 lbf (178 kN) pk Maximum Force (Random) 40,000 lbf (178 kN) rms Maximum Displacement (Continuous duty) 1.7” pk-pk Maximum Displacement (Intermittent duty) 2.0” pk-pk Maximum Velocity (Sine) 85 in/s (2.1 m/s) Maximum Velocity (Shock) 165 in/s (4.2 m/s) Shaker Internal Load Support 4,000 lb (1,818 kg)

Slip Table Team T-Film Dimensions 50” x 50” Pitch Moment Capacity 3.7 x 106 in-lb (418 kN-m) Roll Moment Capacity 3.7 x 106 in-lb (418 kN-m) Yaw Moment Capacity 1.62 x 105 in-lb (18 kN-m)

4 Environmental Test and Integration Facilities Handbook

Facility 410 – Unholtz-Dickie T4000-3 Shaker

Usable Frequency Range 2 – 2500 Hz Amplifier Model 2XSAI180 (360 kVA) Maximum Force (Sine) 40,000 lbf (178 kN) pk Maximum Force (Random) 40,000 lbf (178 kN) rms Maximum Displacement (Continuous duty) 2.7” pk-pk Maximum Displacement (Intermittent duty) 3.0” pk-pk Maximum Velocity (Sine) 85 in/s (2.1 m/s) Maximum Velocity (Shock) 165 in/s (4.2 m/s) Shaker Internal Load Support 4,000 lbs (1,818 kg)

Slip Table Team T-Film Dimensions 74” x 74” Pitch Moment Capacity >7.0 x 106 in-lb (790 kN-m) Roll Moment Capacity >7.0 x 106 in-lb (790 kN-m) Yaw Moment Capacity >2.16 x 105 in-lb (75 kN-m)

Environmental Test and Integration Facilities Handbook 5

Facility 411 – Unholtz-Dickie T2000-3 Shaker (Coming Summer 2013)

Usable Frequency Range 5 – 3000 Hz Amplifier Model 2XSAI180 – T2000 (360 kVA) Maximum Force (Sine) 25,000 lbf (111 kN) pk Maximum Force (Random) 23,000 lbf (102 kN) rms Maximum Displacement (Continuous duty) 2.7” pk-pk Maximum Displacement (Intermittent duty) 3.0” pk-pk Maximum Velocity (Sine) 80 in/s (2.0 m/s) Maximum Velocity (Shock) 165 in/s (6.0 m/s) Shaker Internal Load Support 1,500 lbs (680 kg)

Slip Table None (Vertical testing only)

6 Environmental Test and Integration Facilities Handbook

Facility 412 – Unholtz-Dickie T2000-3/CSTA Shaker

Usable Frequency Range 5 – 2500 Hz Amplifier Model 2XSAI180 (360 kVA) Maximum Force (Sine) 25,000 lbf (171 kN) pk Maximum Force (Random) 23,000 lbf (102 kN) rms Maximum Displacement (Continuous duty) 2.7” pk-pk Maximum Displacement (Intermittent duty) 3.0” pk-pk Maximum Velocity (Sine) 80 in/s (2.0 m/s) Maximum Velocity (Shock) 235 in/s (6.0 m/s) Shaker Internal Load Support 1,500 lbs (680 kg)

Slip Table CSTA/T2000-24-24 Dimensions 24” x 24” Pitch Moment Capacity 5.0 x 104 in-lb (790 kN-m)

8 Environmental Test and Integration Facilities Handbook

Technical Specifications

Max SPL (Empty Chamber) 150 dB

Horns/Generator 25 Hz Exponential /Wyle WAS 3000 50 Hz Hypex/Wyle WAS 3000

(future upgrade)

Frequency range 25Hz – 10 KHz

Acoustic Media Gaseous Nitrogen

Microphones (4 - 8) 0-175 dB

Physical Characteristics

Interior 33’ L x 27’ W x 42’ H

Payload Access 14’ 11” W x 30’ H

Personnel Door 3’ W x 6’ 6” H

Crane Capacity 7.5 ton

Test Viewing CCTV

Instrumentation Booms (2) 78 channels each

12 Environmental Test and Integration Facilities Handbook

1.1.11 Small Static Test Facility

The Portable Static Test Facility is a structural test bed designed for the application of multiple, individual static loads to payload components, sub-assemblies and associated hardware.

Various mounting arrangements of hydraulic actuators allow simultaneous manually-controlled loading at multiple locations.

Instrumentation including load cells, strain gages and displacement transducers can be installed, connected to and monitored by a 600-channel Vishay System 5000 Data Acquisition System.

Parameter Specification Vertical Load up to 20,000 lbs.(9,072 kg) Lateral Load up to 80,000 lbs. (36,288 kg) Physical Characteristics Specification Internal Test Envelope 9’ L x 9’ W x 10’ H (2.74 m x 2.74 m x 3.10 m) Facility Weight 32,000 lbs. (14,515 kg) Overhead Crane Capacity 15,000 lbs. (6,804 kg)

Environmental Test and Integration Facilities Handbook 15

1.2 ELECTROMAGNETIC TESTING

1.2.1 Electromagnetic Compatibility Testing

Introduction: Two anechoic shielded testing facilities are available for performing Electromagnetic Compatibility (EMC) tests. These facilities meet electromagnetic performance requirements specified by MIL-STD-462, and support the performance of EMC tests specified by Mil-Std-461-C/E/F and the GSFC “General Environmental Verification Specification” (GEVS). Both facilities provide very low level ambient electromagnetic environments and the ability to contain internally-generated, radiated electromagnetic waves.

All electrical power, communications, and other facility wiring are filtered; the facility structures are locally bonded to earth ground; and ventilation ducts and other apertures are designed as waveguide-below-cutoffs.

Contamination-sensitive items are tested in the Large EMC Facility (Class 10k cleanroom), or they are bagged in non-reflective materials (Melonex) if tested in the Small EMC Facility.

Integral Instrumentation: Generated interference measurements are typically made using a Rohde and Schwarz EMI receiver system (ESU8/40 and ESIB40) for data acquisition, processing, and data reduction.

Associated electric and magnetic field antennas and line conduction transducers are provided for testing in the 20 Hz to 40 GHz frequency range. The receiver system is controlled by the Rohde and Schwarz EMC32E/S measurement software package. Line conducted and radiated susceptibility tests are performed using a variety of signal generators, amplifiers, and transducers or antennas for injection and/or radiation of the test signals. Frequency range is 20 Hz to 400 MHz for signal injection; 10 kHz to 40 GHz for signal radiation. Radiated field strengths up to 200 V/m can typically be provided. Programmed swept frequency test signals, appropriately modulated, are provided over portions of the test spectrum.

Data Acquisition: The Rohde and Schwarz EMC32E/S EMC measurement software can be used for all Electromagnetic Interference (EMI) and Electromagnetic Susceptibility (EMS) measurements. The software is a modern and powerful tool for controlling and monitoring devices/equipment. Susceptibility test data relating to the susceptibility test signal can be time synchronized with the test item performance test data which is typically recorded as a function of the type of ground support equipment furnished with the test item. Failure modes are test project defined and susceptibility thresholds determined whenever the test item responds to the susceptibility test signal.

Electrical power: Test item power is normally provided by project-furnished, current and/ or voltage limited power supplies. An Elgar 5250 Switching Amplifier can be supplied for power quality tests that desire spacecraft specific power ripple tests. Each anechoic chamber is supplied with 100W of filtered power and can be modified to handle higher power applications with the proper amount of preparation.

16 Environmental Test and Integration Facilities Handbook

1.2.1.1 Small EMC Facility

Description: This facility is located in Building 7, and is designed for either small satellite or sub-assembly tests. This facility consists of three contiguous electromagnetically shielded enclosures that meet or exceed shielding enclosure requirements stated in Mil-Std-285 and IEEE-299. The individually shielded enclosures include the anechoic Test Room, the EMC Control Room, and a Ground Support Equipment (GSE) Room.

Inside the Test Room is a free standing faraday cage that is lined with ferrite tiles with TDK IP-090, carbon impregnated Styrofoam wedge absorbers to handle RF energy absorption up to 200 V/m (70 mW/cm2) from 20 Hz to 40 GHz. The Control and GSE Rooms consist of standard modular shielded panels constructed of ¾” plywood paneling, sandwiched by an inner and outer layer of 10 mil galvanized steel. A cable penetration plate, located on the same wall as the test bench, separates the Test Room from the GSE Room and acts as a Single Point Ground for both the spacecraft and GSE. The standard penetration plate consists of four “Pi” filters and three 3” diameter Wave-Guide-Below cutoffs that can be used to feed cables through. When desired a penetration plate can be made to mount existing TVAC cables to reduce cable costs and to reduce common mode currents.

Mode of Operation: The test article is installed in the EMC chamber and bonded to the copper test bench that is certified to hold a 250 pound payload (5:1 tested to 1250 lbs). The test bench is bonded to the anechoic panels via a copper ground strap which maintains a 5:1 (L:W) ratio. Interconnecting cables between the test article and its ground support equipment are connected through an access panel mounted either on the cleanroom or GSE side, allowing for greater flexibility and acting as a single point ground. The test enclosure maintains relative humidity between 30% and 70% and temperature at 68°F ±5° (20°C ±2.8°).

Physical Characteristics:

Experimenter’s area: 4 m (L) x 2 m (W) x 3 m (H) Personnel door: 1 m (W) x 1.7 m (H)

Control room: 7.3 m (L) x 3.7 m (W) x 3 m (H) Personnel door: 1.3 m (W) x 2.1 m (H)

Test area room: 5.5 m (L) x 5 m (W) x 3 m (H) Equipment door: 2 m (W) x 2.2 m (H)

Test Area Anechoic Characteristics: Ferrite tiles and Carbon impregnated Styrofoam wedge absorbers combine to make the facility a broadband anechoic chamber capable of absorbing electromagnetic waves over the frequency range of 20 Hz to 40 GHz. Field measurement accuracy is thereby enhanced compared to shield room facilities that lack the anechoic material, and radiated susceptibility test signals are controlled with improved signal-to-noise ratios. The test facility also has web based video camera system and Fiber Optic lighting capable of withstanding 200 V/m that keeps the facility RF emissions to a minimum.

Fire Protection: Fire protection is provided in the Test Area using retractable sprinkler heads and an auto-cutoff ventilation system for toxic smoke exhaust to the outside of the building. The TDK IP-090 Carbon impregnated Styrofoam wedge absorbers release CO2 and water vapors when ignited. Personnel safety features include a radiation hazard warning and monitoring system. The facility is also equipped with electrostatic discharge testing and prevention capabilities and a large copper test bench for mounting and earth-bonding test items.

18 Environmental Test and Integration Facilities Handbook

1.2.1.2 Large EMC Facility

Description: This facility is located in Building 7, and is designed for testing large spacecraft that require Class 10k contamination protection. This facility consists of three contiguous electromagnetically shielded enclosures that meet or exceed shielding enclosure requirements stated in Mil-Std-285 and IEEE-299. The enclosures consist of Test Room (Rm. 108A), the EMC Control Room (Rm. N115), and a Ground Support Equipment (GSE) Room (Rm. N117). Inside the enclosure is a free standing faraday cage that is lined with ferrite tiles with Panashield HYB-NF12, fibrous composite material with carbon impregnated within wedge absorbers to handle RF energy absorption up to 200 V/m (70 mW/cm2) from 20 Hz to 40 GHz. The Control and GSE Rooms consist of standard modular shielded panels constructed of ¾” plywood paneling, sandwiched by an inner and outer layer of 10 mil galvanized steel. A cable penetration plate, located on the same wall as the test bench, separates the Test Room from the GSE Room and acts as a Single Point Ground for both the spacecraft and GSE.

Mode Of Operation: The test article is installed inside the faraday cage and bonded to the penetration plate ensuring a single point ground for project and EMI test equipment. Grounding for larger spacecraft, that can’t fit onto the test bench, can connect to either an 18” or 36” wide copper strap for a better RF ground and maintaining a 5:1 (L:W) ratio. Interconnecting cables between the test article and its ground support equipment are connected through an access panel mounted either on the cleanroom or GSE side, allowing for greater flexibility and acting as a single point ground. The test enclosure maintains a relative humidity at a value between 30% and 70% and temperature at 68°F ±5° (20°C ±2.8°).

Physical Characteristics:

Test Enclosure Size: Expandable from basic 6.5 m cubed. Max Height: 6.7 m

Ferrite-Tiled Anechoic Enclosure Door Size: 6.5 m (W) x 6.2 m (H)

Ground Support Equipment Enclosure: Room Size: 6.7 m (L) x 5.2 m (W) x 3.2 m (H Door Size: 2 m (W) x 2.5 m (H)

Test Area Anechoic Characteristics: Ferrite tiles with Panashield HYB-NF12, fibrous composite material with carbon impregnated within, absorbers handle RF energy absorption up to 200 V/m (70mW/cm2) from 20 Hz to 40 GHz are mounted on the interior walls of the test area combine to make the facility a broadband anechoic chamber capable of absorbing electromagnetic waves over the frequency range of 20 Hz to 40 GHz.

Field measurement accuracy is thereby enhanced compared to shield room facilities that lack the anechoic material, and radiated susceptibility test signals are controlled with improved signal-to-noise ratios. The test facility also has web based video camera system capable of withstanding 200 V/m and just like the Fiber Optic lighting, keeps and facility RF emissions to a minimum.

Safety Features: The Test Enclosure is equipped with flashing warning lights at all entrance doors to warn personnel not to enter whenever electromagnetic waves are being propagated within the room. Internal humidity and temperature alarms, as well as a fire alarm and dry sprinkler system, are also features of this facility.

22 Environmental Test and Integration Facilities Handbook

Spacecraft Magnetic Test Facility

Data Acquisition: An array of three state-of-the-art triaxial fluxgate magnetometers is used for magnetic field testing. A field mapping of the test item is performed, the resultant data is automatically provided as input into the facility’s “near field analysis” software, and an equivalent dipole moment is calculated.

Measurements are taken for various magnetic field conditions including: perm, deperm, induced and stray field (test item powered) measurements.

24 Environmental Test and Integration Facilities Handbook

1.3.1 Capabilities Summary (English Units)

Facility Nominal Specifications (English Units)

Type Number Test Volume (ft) Operating Pressure

(psi)

Temperature Range (°F)

Unique Capabilities

Temperature 204 1.67 x 1.00 x 1.34 Ambient -274 to 392 Temp / Humid

232 4 x 4 x 4 Ambient -157 to 302 Humidity <5% to 95% RH (±5%) 233 4 x 4 x 4 Ambient -94 to 302 Humidity <5% to 95% RH (±5%)

Thermal Vacuum

225 9 Dia x 14 L <2x10-7 -310 to 302 2 Cryopumps, Turbopump, C/F, 2 TQCMs, RGA

237 7 Dia x 8 L <2x10-7 -310 to 257 Diffusion Pump, C/F, TQCM, RGA 238 12 Dia x 15 H <2x10-7 -310 to 239 3 Cryopumps, Turbopump, C/F, 2 TQCMs, RGA 239 7 Dia x 8 L <2x10-7 -310 to 257 Cryopump, C/F, 2 TQCMs, RGA 240 3 Dia x 3 L <2x10-7 -220 to 230 Diffusion Pump, C/F, TQCM, RGA 241 3 Dia x 3 L <2x10-7 -220 to 230 Cryopump, C/F, TQCM, RGA 245 2 Dia x 3 L <2x10-7 75 to 302 Turbopump, C/F, TQCM, RGA 246 3.5’ Dia x 5.5’ L <1x10-5 torr 140 to +150 Mechanical Pump, Cryopump, C/F 281 3 Dia x 4 L <2x10-7 -310 to 302 Cryopump, C/F, TQCM, RGA 290 27 Dia x 40 H <2x10-7 -292 to 212 7 Cryopumps, Turbopump, He Shroud, C/F, 4 TQCMs, RGA Rapid Pump

Down 208 NA 2x10-4 NA Rough down Facilities

237 & 239 in 2 minutes

Thermal Conditioning

Units

201 NA NA -220 to 284, LN2

GN2 transfer medium, circulating with LN2 bypass mode

203 NA NA -220 to 284 GN2 transfer medium, single pass with LN2 bypass mode

205 NA NA -148 to 212, LN2 GN2 transfer medium, single pass with LN2 bypass mode

209 NA NA -148 to 248 GN2 transfer medium, single pass 230 NA NA -238 to 302 GN2 transfer medium, circulating

Heater Racks

242 NA NA -148 to 212 Harrel rack 315 NA NA -328 to 752* Max temp based upon heater type 316 NA NA -328 to 1112* Max temp based upon heater type

Solar Simulator Portable

211 NA NA NA 61 cm dia, 1 SC

Emergency Power

253 NA NA NA 250 kVA, 480 V, 3-phase 254 NA NA NA 350 kVA, 480 V, 3-phase

High Pressure

GN2

257 NA NA NA 2000 psi 258 NA NA NA 2000 psi

Environmental Test and Integration Facilities Handbook 29

1.3.3 Thermal Vacuum

1.3.3.1 Facility 225 – 2.7 m x 4.3 m (9’ x 14’) Vacuum Chamber

Description: This is a horizontal loading thermal vacuum test chamber used for thermal vacuum and thermal balance testing, and baking out large test items. Electrical feedthroughs and liquid and gas penetrations are provided at locations on the sides and rear of the chamber. A clean tent covering the door opening provides a Class 10,000 clean area for integrating hardware prior to loading it into the chamber.

Mode of Operation: Test items are loaded by crane onto a load cart, which is rolled into the chamber on a rail system. Payload weight can be as high as 2,268 kg (5,000 lb). Access to the chamber is through a clean tent. The use of cleanroom procedures and the wearing of clean garments are required when working in the chamber.

Chamber evacuation is provided by two cryopumps and one turbomolecular pump. Roughing is provided by a blower and rotary piston mechanical pump. Shroud temperature conditioning is accomplished by a recirculating GN2 thermal system, or it may be flooded with LN2.

Parameters:

Test pressure: <1x10-5 Torr (<2x10-7 psi) Shroud temperature:

GN2 mode: -140°C to +150°C (-220°F to +302°F) LN2 mode: -190°C (-310°F) Pumping speeds for N2:

2 Cryopumps: 60,000 l/s (127,000 cfm) Turbomolecular pump: 1,000 l/s (2,120 cfm)

Physical Characteristics:

Test volume: 2.74m dia x 4.27m L (9’ x 14’) Payload support: 76” x 144” cart - 1,361 kg (3,000 lb) capacity Crane capacity: 4,536 kg (5 ton) Instrumentation ports: 6 each 25.4 cm dia (10”), 6 each 12.7 cm dia (5”) Std. electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF

Integral Instrumentation:

Pressure: Convectron - atm to 10-3 Torr Ion gauge - 10-3 Torr to ultimate Payload temperature: 320 channels Contamination: TQCM, scavenger plate, cold finger, residual gas analyzer

Auxiliary Equipment: Portable thermal systems are available to control baseplates, the thermoelectric quartz crystal microbalance (TQCM) and contamination control mirrors.

Environmental Test and Integration Facilities Handbook 31

1.3.3.2 Facility 237 – 2.1 m x 2.4 m (7’ x 8’) Diffusion Pumped Vacuum Chamber

Description: This is a horizontal loading thermal vacuum test chamber equipped with a viewport to accommodate an external solar simulator. An overhead rail is available for mounting purposes and stainless steel tubes are available for hanging thermal blankets. The facility is used for thermal vacuum and thermal balance testing, and baking out test items.

Mode of Operation: The test item is craned or hand carried onto the payload cart positioned at the chamber door. Typically, the payload is instrumented and connected to GSE prior to rolling it into the chamber.

Ground support equipment cabling is connected through the penetration plates and ambient functional checks are performed. Prior to solar testing, it is normal to perform an alignment check of the test item with the external simulator.

Chamber evacuation is provided by a rotary piston mechanical pump and an oil diffusion pump. Rapid pump down can also be performed. A sliding gate main valve allows chamber access while the pumping systems are established.

Parameters:

Test pressure: <1x10-5 Torr (<2x10-7 psi) Shroud temperature:

GN2 mode: -140°C to +125°C (-220°F to +257°F) LN2 mode: -190°C (-310°F)

Diffusion pump speed for N2: 25,000 l/s (53,000 cfm)

Physical Characteristics:

Test volume: 2.13 m dia x 2.44 m L (7’ x 8’) Payload support: 44” x 76” cart – 584 kg (1288 lb) capacity 43.5” x 80” cart – 729 kg (1607 lb) capacity Crane capacity: 4,536 kg (5 ton) Viewport dimensions: 31cm dia (12”) quartz window Std. electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF

Integral Instrumentation:

Pressure: Convectron - atm to 10-3 Torr Ion gauge - 10-3 Torr to ultimate Payload temperature: 126 channels Contamination monitors: TQCM, scavenger plate, cold finger, residual gas analyzer

Auxiliary Equipment: Heater racks and thermal conditioning units (TCUs) are available to control auxiliary heater panels, cryopanels and baseplates. The portable solar simulator can be used with this chamber.

Environmental Test and Integration Facilities Handbook 33

1.3.3.3 Facility 238 – 3.7 m x 4.6 m (12’ x 15’) Cryo & Turbo Vacuum Chamber

Description: This is a vertical loading thermal vacuum test chamber used for thermal vacuum and thermal balance testing, and baking out spacecraft hardware. A bracket containing stainless steel tubes is available for hanging thermal blankets. Ports for electrical feedthroughs, liquid/gas feedthroughs, and viewing are located around the perimeter of the chamber. A clean tent at the chamber entrance provides class 10,000 cleanliness conditions.

Mode of Operation: Test articles are normally loaded through the top of the chamber using the building crane; however, small payloads can be transported through the personnel entrance. In some cases, special fixtures must be designed due to the uniqueness of the test article support system. Once installed, the payload is connected to the ground support equipment via feedthroughs. Access to the chamber is through a clean tent. The use of cleanroom procedures and the wearing of clean garments are required when working in the chamber.

Initial chamber evacuation is provided by two rotary piston mechanical pumps, with three cryopumps and a turbomolecular pump for high vacuum pumping. All four pumps are isolated from the chamber by sliding gate main valves.

Parameters:

Test pressure: <1x10-5 Torr (<2x10-7 psi) Shroud temperature:

GN2 mode: -120C to +115°C (-184°F to +239°F) LN2 mode: -190°C (-310°F) Pumping speeds for N2:

3 cryopumps 90,000 l/s (190,700 cfm) Turbomolecular pump 2,000 l/s (4,237 cfm)

Physical Characteristics:

Test volume: 3.4 m D x 4.3 m H (11’2” x 14’2”) Personnel door: 1.5 m (5’) diameter Payload support: Floor level - 1.2 m (4’) square platform – 1950 kg (4300 lb) capacity Side wall - hard points at 1.8 m and 3.7 m (6’ and 12’) levels Crane capacity: 4,536 kg (5 ton) Crane hook height: 4.06 m (13’4”) to dome stop, 4.16 m (13’8”) to top flange Viewport dimensions: 23 cm (9”) diameter Std. electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF

Integral Instrumentation:

Pressure: Convectron - Atm to 10-3 Torr Ion gauge - 10-3 Torr to ultimate Payload temperature: 360 channels Contamination monitors: TQCM, scavenger plate, cold finger, residual gas analyzer

Auxiliary Equipment: Heater racks and thermal conditioning units (TCUs) are available to control auxiliary heater panels, cryopanels and baseplates.

Environmental Test and Integration Facilities Handbook 35

1.3.3.4 Facility 239 – 2.1 m x 2.4 m (7’ x 8’) Cryopumped Vacuum Chamber

Description: This is a horizontal loading thermal vacuum test chamber equipped with a viewport to accommodate an external solar simulator. An overhead rail is available for mounting purposes and stainless steel tubes are available for hanging thermal blankets. The facility is used for thermal vacuum and thermal balance testing, and baking out test items. A clean tent at the chamber entrance provides class 10,000 cleanliness conditions.

Mode of Operation: The test item is craned or hand carried onto the payload cart positioned at the chamber door. Typically, the payload is instrumented and connected to gse prior to rolling it into the chamber. Ground support equipment cabling is connected through the penetration plates and ambient functional checks are performed. Prior to solar testing, it is normal to perform an alignment check of the test item with the external simulator. Access to the chamber is through a clean tent. The use of cleanroom procedures and the wearing of clean garments are required when working in the chamber.

Parameters:

Test pressure: <1 x 10-5 Torr (<2x10-7 psi) Shroud temperature:

GN2 mode: -138°C to +125°C (-216°F to +257°F) LN2 mode: -190°C (-310°F) Cryopump speed for N2: 30,000 l/s (63,560 cfm)

Physical Characteristics:

Test volume: 2.13 m diameter x 2.44 m L (7’ x 8’) Payload support: 44” x 76” cart – 584 kg (1288 lb) capacity 43.5” x 80” cart – 729 kg (1607 lb) capacity Crane Capacity: 4,536 kg (5 ton) Viewport dimensions: 30 cm (12”) diameter quartz window Std. electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF

Integral Instrumentation:

Pressure: Convectron - Atm to 0.13 Pa (10-3 Torr) Ion gauge - 10-3 Torr to ultimate Payload temperature: 126 channels Contamination monitors: TQCM, cold finger, scavenger plate, residual gas analyzer

Auxiliary Equipment: Heater racks and thermal conditioning units (TCUs) are available to control auxiliary heater panels, cryopanels and baseplates. The portable solar simulator can be used with this chamber.

Environmental Test and Integration Facilities Handbook 37

1.3.3.5 Facility 240 – 0.9 m x 0.9 m (3’ x 3’) Diffusion Pumped Vacuum Chamber

Description: : This diffusion pumped facility is a horizontal loading thermal vacuum test chamber used for thermal vacuum testing and bakeout of test articles. The payload is mounted on a plate which is supported by rails welded to the chamber wall.

Mode of Operation: After the test article is instrumented with thermocouples and placed in the chamber, ground support equipment cabling is connected through the penetration plates, and ambient functional checks are performed. Placing the test article on a baseplate or suspending it from the overhead rail is an acceptable mounting method. Chamber evacuation is provided by rotary piston mechanical pumps and an oil diffusion pump. A main valve allows test set up while the pumping system is being established.

Parameters:

Test pressure: <1 x 10-5 Torr (<2x10-7 psi) Shroud temperature: -140°C to +110°C (-220°F to +230°F) Pumping speed for N2: 1,600 L/sec (3,400 cfm)

Physical Characteristics:

Test volume: 0.91 m D x 0.91 m L (3’ x 3’) Std. electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF Max P/L weight: 840 kg (1854 lbs)

Integral Instrumentation:

Pressure: Convectron - atm to 0.13 Pa (10-3 Torr) Ion gauge - 10-3 Torr to ultimate Payload temperature: 36 channels Contamination monitors: TQCM, cold finger, scavenger plate

Auxiliary Equipment: Portable thermal systems are available to control baseplates, the thermoelectric quartz crystal microbalance (TQCM), and contamination control mirrors.

Environmental Test and Integration Facilities Handbook 39

1.3.3.6 Facility 241 – 0.9 m x 0.9 m (3’ x 3’) Cryopumped Vacuum Chamber

Description: This cryopumped facility is a horizontal loading thermal vacuum chamber used for thermal vacuum testing and bakeout of test articles. The payload is mounted on a plate which is supported by rails welded to the chamber wall..

Mode of Operation: After the test article is instrumented with thermocouples and placed in the chamber, ground support equipment cabling is connected through the penetration plate, and ambient functional checks are performed. After roughing down the chamber with the rotary piston mechanical pump, ultimate pressure is achieved with the cryopump. A main valve allows test set up while the pumping system is being established.

Parameters:

Test pressure: <1 x 10-5 Torr (<2x10-7 psi) Shroud temperature: -140°C to +110°C (-220°F to +230°F) Pumping speed for N2: 1,500 L/sec (3,200 cfm)

Physical Characteristics:

Test volume: 0.91 m diameter x 0.91 m L (3’ x 3’) Std. electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF Max P/L weight: 840 kg (1854 lbs)

Integral Instrumentation:

Pressure: Convectron - Atm to 0.13 Pa (10-3 Torr) Ion gauge - 10-3 Torr to ultimate Payload temperature: 36 channels Contamination monitor: TQCM, cold finger, scavenger plate

Auxiliary Equipment: Portable thermal systems are available to control base plates, the thermoelectric quartz crystal microbalance (TQCM), and contamination mirrors.

Environmental Test and Integration Facilities Handbook 43

1.3.3.9 Facility 281 – 0.9 m x 1.2 m (3’ x 4’) Cryopumped Vacuum Chamber

Description: This cryopumped facility is a horizontal loading thermal vacuum chamber used for thermal vacuum testing and baking out test articles. The payload is mounted on a plate which is attached to rails in the chamber.

Mode of Operation: After the test article is instrumented and installed in the chamber, it is connected to the ground support equipment and data acquisition system via electrical feedthroughs. After roughing down the chamber with the mechanical pump, ultimate pressure is achieved with a cryopump. A main valve allows test set up while the pumping system is being established.

Parameters:

Test pressure: <1 x 10-5 Torr (<2x10-7 psi) Shroud temperature:

GN2 mode: -148°C to +150°C (-234°F to +302°F) LN2 mode: -190°C (-310°F) Pumping speed for N2: 1,500 L/sec (3,200 cfm)

Physical Characteristics:

Test volume: 0.91m diameter x 1.22m L (3’ x 4’) Payload support: Plate on support rails Std. electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF

Integral Instrumentation:

Pressure: T/C gauge - atm to 0.13 Pa (10-3 Torr) Convectron - Atm to 0.13 Pa (10-3 Torr) Ion gauge - 10-3 Torr to ultimate Payload temperature: 72 channels Contamination monitor: TQCM, cold finger, scavenger plate

Auxiliary Equipment: Portable thermal systems are available to control base plates, the thermoelectric quartz crystal microbalance (TQCM), and contamination mirrors.

Environmental Test and Integration Facilities Handbook 45

1.3.3.9 Facility 290 – 8.2 m x 12.2 m (27’ x 40’) Cryopumped Vacuum Chamber

Description: Facility 290, also known as the Space Environment Simulator (SES) is a very large vertical loading thermal vacuum chamber capable of achieving ultra-low pressure and a wide range of thermal conditions. In addition to the 27’D x 40’H nitrogen shroud, two auxiliary helium shroud configurations are available (25’D x 15’H and 25’ x 27’H). A 1 kW at 20K helium refrigerator is used to cool the helium shrouds and/or other auxiliary equipment. An integrated HEPA filtration system provides a Class 10,000 environment in the chamber and anteroom. The chamber is used for thermal vacuum and thermal balance testing, and baking out very large test articles.

Mode Of Operation: To load large test articles the chamber dome is rolled back to allow loading with the overhead crane. Small test articles and equipment are brought in through the personnel entrance located in the basement. Wearing of clean garments is required. Entry to instrument the payload, connect ground support equipment cabling, and install hardware is through a cleanroom air shower at the personnel door.

Scaffolding may be erected to provide access to the payload. An area adjacent to the main facility control console is reserved for the experimenter’s ground support equipment.

Chamber evacuation is provided by eight rotary piston mechanical pumps with Roots blowers, seven cryopumps and a turbomolecular pump. Thermal control is provided by an aluminum tube-in-sheet cylindrical shroud with both liquid nitrogen and gaseous nitrogen operational modes. The dome and bottom shrouds are also connected to the thermal skid. Helium shrouds, resistance heater arrays and gaseous nitrogen panels are available for special thermal requirements. Thermoelectric quartz crystal microbalances (TQCMs) and a residual gas analyzer (RGA) provide both quantitative and qualitative monitoring of molecular contamination and gaseous constituents within the chamber. Closed circuit television coverage is available for monitoring the test article.

Helium Skid: A 1.0 kW helium refrigeration system is piped to 2.54 cm (1”) VCR fittings inside the chamber that may be connected to manifolds providing the capability of achieving 20K on those surfaces.

This is enough cooling energy to cool and maintain large thermal shrouds at cryogenic temperatures.

Vibration Isolation Table: The pneumatic isolation system and payload platform (with counter weights) is designed to support and provide vibration isolation to delicate spacecraft and component payloads during testing in Facility 290. The isolation system consists of three constant-effective-area pneumatic isolators controlled by three height sensing servo valves with an adjustable deadband. The isolation system will support any load up to its maximum capacity of 6032 kg (13,300 lbs).

The isolation system is configured with heaters to maintain the system above 0°C during cold wall testing in Facility 290. The maximum operating temperature for the system is +50°C.

Natural Frequencies Vertical: 0.7- 0.9 Hz Horizontal: 0.4- 0.5 Hz Dimensions: 43” High 120” Diameter

46 Environmental Test and Integration Facilities Handbook

Parameters:

Test pressure: 13.3 μPa (10-7 Torr) Shroud temperature:

GN2 mode: -130°C to +80°C (-202°F to +176°F) LN2 mode: -180°C (-292°F) Chamber pumping speed:

7 cryopumps: 2.1 x 105 L/sec (4.5 x 105 cfm) @ 133 μPa (10-6 Torr) Turbomolecular pump: 6,000 L/sec (12,700 cfm) @ 133 μPa (10-6 Torr)

Physical Characteristics:

Test volume: 8.23 m diameter x 12.19 m H (27’ x 40’) Payload support: 11794 kg (26000 lb) Viewport: 30 cm (12”) Standard electrical feedthroughs: 61-pin, 37-pin, 7-pin, 4-pin, RF Personnel door: 1.8 m H x 1.5 m H (6’ H x 5’ W) Crane capacity: 13,608 (15 ton) Crane hook height: 12.8 m (42’) to I-beam structure

Integral Instrumentation:

Pressure: Convectron (2) - Atm to 0.13 Pa (10-3 Torr) Ion gauge (3) 0.13 Pa to 13.3 μPa (10-3 to 10-7 Torr) Payload temperature: 760 channels of thermocouples Contamination monitor: TQCM, cold finger, scavenger plate, residual gas analyzer TQCM frequencies: 15 MHz (4); 10 MHz (2)

Auxiliary Equipment: Portable thermal systems are available to control base plates, the thermoelectric quartz crystal microbalances (TQCMs), and contamination mirrors.

48 Environmental Test and Integration Facilities Handbook

1.3.4 – Solar Simulator (Facility 211)

Description: This portable solar simulator projects a divergent beam. The unit is mounted on a castered platform to provide alignment with the windows of the medium-sized thermal vacuum chambers. The power supply and controls are incorporated in a separate castered console.

Mode of Operation: The intensity is adjusted to the desired level, and uniformity of the beam at the target plane is measured before the test article is installed in the facility. The lamp is then aligned at the quartz window at the required distance from the target plane. The lamp is ignited and the payload illuminated in accordance with the test procedure.

Parameters:

Beam size: 61 cm (24”) across flats Intensity: 90 to 270 mW/cm2 (0.16 in2);

0.6 to 1.0 S.C.

Target plane: 191 cm (75”) from exit optics Uniformity: ± 10% max of average intensity Subtense angle: 7° half angle Spectrum: Filtered to air mass zero solar spectrum

Physical Characteristics:

Source: One 6.5 kW Xenon arc lamp Lamphouse: 76 cm x 137 cm x 122 cm (30” x 54” x 48”) Control console: 76 cm x 76 cm x 183 cm (30” x 30” x 72”) Platform: 173 cm x 76 cm x 127 cm (68” x 30” x 50”) Exhaust fan: 8.5 m3/min (300 ft3/min)

Utility requirement:

Power: 480 V, 60 Hz, 3 phase, 35 A 110 V, 60 Hz, 1 phase, 25 A

Cooling water: 15°C to 30°C (59°F to 86°F) 11 to 19 L/min (3 to 5 gal/min)

Integral Instrumentation:

Lamp voltage: 0-150 VDC, Lamp current: 0-200 A Lamp intensity: 0-200 mW/cm2 (0.16 in2) DC System alarms: Klaxon and lights

60 Environmental Test and Integration Facilities Handbook

1.3.11.4 Contamination Control Mirror

Description: These aluminum coated mirrors are used primarily to collect outgassed materials in the thermal vacuum chambers; however, they may be placed anywhere to collect condensable matter. To determine the quantity of material on the mirror, reflective ultraviolet measurements are made prior to test, and then compared to post-test measurements for a loss of reflectivity.

Mode of Operation: The mirror is placed in the thermal vacuum chamber (or other environment) and allowed to remain in that location for the duration of the test. In most cases, the mirror’s temperature follows the thermal vacuum chamber temperature profile; however, the mirror’s temperature can be controlled if desired. For large accretions (greater than 10% change in reflectivity) the mirror is sent to the Materials Assurance Branch for chemical analysis of the nonvolatile residue.

Parameters:

Temperature: -190°C to +100°C (-310°F to +212°F) Measurement error: ± 2% Measurement wavelength: 1216 Å, 1608 Å, and 2000 Å Mirror size: 5 cm x 5 cm (2” x 2”), coated on one side Coating: Al - 600 to 800Å thick Over coating: MgFl - 250Å thick

62 Environmental Test and Integration Facilities Handbook

2.1 MECHANICAL INTEGRATION

The Center possesses both the facilities and personnel necessary for mechanically integrating spaceflight hardware, including instruments, ground support equipment, and complete spacecraft. This integration effort is provided from the inception of the program through launch and recovery. Integration is performed either in the cleanrooms or in the general laboratories, as appropriate. Contamination-sensitive flight hardware and systems are integrated in the cleanrooms, while non-sensitive hardware is completed in the general integration facilities.

2.1.1 Handling of Spacecraft

Typical spacecraft handling tasks include preparation of procedures, use of hydrasets, crane operations, proof testing and verification of lifting devices and handling carts. The Center has extensive facilities, hardware, and trained personnel for both routine and quick reaction handling tasks. Logistics for shipping, receiving, and packaging are also provided at GSFC and other offsite locations.

2.1.2 Fabrication Support

Frequently, quick reaction machining operations need to be performed so that spacecraft integration tasks will remain on schedule. Trained personnel, using precision equipment and facilities, are available to modify or fabricate critical components and hardware as required.

2.1.3 Assembly

Both Center and project-supplied hardware is used by the integration group in the assembly of flight systems. Precision assembly tools, measuring instruments, and trained personnel are used to ensure precise alignment and installation of flight hardware. Precision optical transit squares, interferometers, surface tables, inclinometers, electronic levels, height gauges, laser trackers and helio-precision measuring tools are some of the instruments used for this effort.

2.1.4 Functional Checks of Spacecraft Mechanisms

Center personnel perform weight, moment of inertia, center of gravity, and product of inertia measurements on flight hardware. Functional checks of hinged doors, solar panel deployment mechanisms, payload ejection systems, and boom deployments are routinely conducted in accordance with the designer’s and experimenter’s specifications. Integration personnel also work closely with electronics personnel when installing electronic packages and routing electrical harnesses.

2.1.5 Field Support

When required, Center personnel are available for field support at contractor sites, launch sites, and other NASA installations. Typical operations performed during field support tasks are covered above.

Environmental Test and Integration Facilities Handbook 63

2.1.6 Purge Systems

Spacecraft and shipping containers typically require a regulated flow of clean, dry gas to maintain a safety barrier to reduce contamination. Large and small systems can be designed to customer specifications, fabricated and certified. Existing systems can be refurbished and brought up to current NASA specifications

64 Environmental Test and Integration Facilities Handbook

2.2 THERMAL SYSTEM SUPPORT FACILITY

Description: From the facilities the Thermal System Support Group provides personnel and production support for the development, design, procurements, and implementation of unique processes in layout, fabrication, and installation of mutli-layer insulation (MLI) for GSE and space flight equipment.

Applications include flight spacecraft, instrumentation, optical components, mock-ups, and test fixtures.

Products include thermal blanketing for space environments and adverse heat loads, attenuating Electromagnetic Interference (EMI), micrometeorite shields, and support for EVA crew tools and aids.

These services are provided to all NASA centers and aerospace vendors and are not limited to the Goddard Space Flight Center facilities.

Mode of Operation: Technical support is provided to ensure thermal design, performance, fabrication, and installation requirements meet all NASA and Project instructions and guidelines, and adherence to ISO and Quality procedures possess the proper documentation. Technicians work with a variety of metalized and non-metalized thin films (ex. Mylar, GBK, Kapton, and Al FEP), fabrics (ex. Betacloth, E-glass, and Kevlar), foils (ex. titanium, stainless steel, and aluminum), tapes and adhesives, as well as a variety of buttons and fasteners. Technicians work from drawing, models, and direct from the flight hardware to produce templates for the thermal blanketing. From approved templates GSE and Flight blanketing is produced. Work is performed primarily in one of the production labs, but is also done in integration or test areas, contamination-controlled areas, and offsite locations. Technicians are trained in clean room operations, secondary bonding, Electrostatic Discharge precautions and procedures, and working on flight hardware and instrumentation. Work performed includes patterning, fabrication, modification, refurbishment, repair, and installation of thermal blanketing and EVA Tools and Aids.

Technicians provide test, integration, and launch support world-wide.

Physical Characteristics:

• Production Lab 1 (Room 019) is ~ 1800 square feet.

• Production Lab 2 (Room N107) is ~396 square feet

• Production Lab 3 (coming soon)

• Maintain (2) Heavy Duty Industrial and (1) Light/Medium Sewing Machines.

• Maintain (10) Fabrication Tables (6’ X 7’).

• Maintain ~ 800 square feet bonded storage area for materials, completed MLI, templates, and project documentation.

74 Environmental Test and Integration Facilities Handbook

2.4.12 Portable Particle Counters

There are four 0.028 m3/min (1.0 ft3/min) and two 0.0028 m3/min (0.1 ft3/min) portable automatic particle counters. The particle counters can be used for certifying cleanrooms and other cleanroom devices.

2.4.13 Pressure, Temperature and Humidity Monitoring

Provisions have been made to monitor room air pressure, temperature, and humidity in the CIA, SCA, RFI, and MB C220 vibration test cell. Each area is equipped with temperature and humidity chart recorders and a Magnehelic differential pressure gauge. These are direct reading instruments whose displays are monitored by viewing them near the front windows of the cleanrooms.

2.4.14 Contamination Monitoring and Analysis Lab

The Contamination Monitoring and Analysis Laboratory is located in the SSDIF Precision Cleaning Room.

The lab is equipped with microscopes and an image analysis system for qualitative and quantitative analyses.

A typical sample is taken to the lab in a clean container, the container is opened in the cleanroom, and the sample is placed under a microscope for a particulate count. When identification of the particles is required, the sample is studied using the image analysis system or the polarizing light microscope. Photographs may be taken and saved. After the contaminant has been identified, it can be traced to its origin, and steps can be taken to eliminate the source.

2.4.15 Spacecraft Systems Development and Integration Facility (SSDIF), Bldg 29

Description: The SSDIF is a 7,989 m2 (86,000 ft2) facility designed to provide support for the integration and testing of spacecraft hardware. It is unique in the fact that it contains a 36,816 m3 (1.3 million ft3) horizontal, unidirectional flow cleanroom. Additional features include: Automated Data Processing Area, Shipping/Receiving Area, Flight Hardware Storage Area, and Precision Cleaning facilities.

SSDIF High Bay Cleanroom

Description: The High Bay Cleanroom is a 1,161 m2 (12,500 ft2), class 10,000 (M5.5), horizontal unidirectional flow cleanroom. It has been designed to support the integration and testing of flight hardware and has the capacity to accommodate two full-sized shuttle payloads simultaneously. A cable tray provides data cable access to the Automated Data Processing Room. Access to the cleanroom is via a 7.6 m x 12.2 m (25’ x 40’) overhead roll up door. Two 31,752 Kg (35 ton) cranes, with hook heights of 21.0 m (69’) and 24.4 m (80’), provide lift and transport capabilities. Materials of construction have been selected, and procedures designed, to minimize molecular and particulate contamination levels within this facility.

Mode of Operation: A computer-based automatic control system monitors and controls environmental parameters on a 24-hour basis. Only approved personnel and materials are allowed to enter the cleanroom, and procedures are strictly enforced to maintain cleanliness of the facility. On-site contamination control personnel provide cleanroom support services such as: certification, monitoring, facility cleaning, maintenance of the change room, and precision cleaning.

78 Environmental Test and Integration Facilities Handbook

3.0 FACILITY SUPPORT SERVICES

3.1 ELECTRICAL POWER

3.1.1 Normal House Power (Commercial)

Normal house power in buildings 7, 10, 15, & 29 complex consists of the following circuits:

Voltage (AC) Hz Phase Current (Amp)

120/208 60 3 Up to 100 277/480 60 3 Up to 100

The…