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for full image The largest of the facility vacuum chambers it has a usable volume of 6ft.8in. X 14 ft. and vacuum levels of 1 X 10-6 Torr.(mm Hg) are attainable using cryopump vacuum system to simulate orbital altitudes. This chamber utilizes a stainless steel internal LN2 shroud system and a circumferentially mounted 36Kw quartz heater array to produce a symmetrical thermal radiance. Thermal controls are PC intergrated allowing precise control of complex thermal profiles or quadrants about user selectable parameters. Test data and chamber thermal profiles are continually displayed and archived on a PC or storage disks. Thirty two (32) thermocouple channels are currently available to monitor customer payload thermal gradients. This facility can meet cleanliness criteria for space flight hardware, including a TQCM (Temperature-Controlled Quartz Crystal Microbalance) and Residual Gas Analyzer (RGA) to monitor and identify contamination spectra. A class 10,000 portable downflow provides a clean area for test preparation or transition from the Class 1000 clean room, prior to insertion into the test chamber.
OPERATION: Test items are normally configured on the stainless steel tray, which has the capability to be rolled out chamber door by an overhead trolley to a portable support frame for external access to the test item and tray. Thermocouple, electrical or fluid intergration to the payload are normally performed external to the chamber when possible. The tray is then rolled into the chamber for any final connections with chamber feedthrough penetrations and functional checks to support equipment are performed. Isolation valves provide for payload setup during cryopump cooldown (~2 Hr.). The chamber evacuation is achieved with 2 rotary piston mechanical pumps and crossover to ultimate pressure with the high-vacuum cryopumps.
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for full image This medium sized, thermal vacuum chamber is capable of simulating altitude and thermal environments to orbital conditions. This facility is especially useful for qualifying payloads that may be sensitive to IR radiant heat sources. Use of 2 large capacity cryogenic pumps and a unique optically baffled, thermal shroud enables this facility to achieve vacuum pressures of 1 x 10E-7 Torr. (mm Hg). An external plenum tube is used to condition gaseous nitrogen within the range of -300deg.(F) to +250deg.(F). Thermal transfer to a payload is accomplished by pushing conditioned nitrogen through a closed loop, conductive platen and radiant thermal shrouds. Chamber control and data acquisition features can be automated to customer test parameters. There are normally 18 thermocouple channels available for monitoring payload temperatures. Numerous electrical and fluid, feedthrough penetrations are available for GSE (Ground support equipment) integration. The high vacuum capability, extreme cleanliness, TQCM and RGA instrumentation enable this facility to be used for low-level outgassing and mass loss measurement studies.
OPERATION: A class 10,000 portable downflow provides a clean area at test chamber
door for payload preparation prior to insertion in chamber. The payload is placed
on the chamber platten and instrumented with thermocouples, data and ground
support equipment are connected with chamber feedthrough flanges. An overhead
railway provides for optional mounting support. The cryopumps require 2 hour
cool down time prior to chamber pump down, isolation valves provide for payload
preparation during this period. The data acquisition and control system, can
be programmed to customer setpoints, ramps and dwell period.
CHAMBER INSTRUMENTATION:
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for full imageA 5 by 5 foot thermal vacuum chamber
which is capable of providing altitude vacuum and thermal simulation to approximately
10 E-7 Torr. A stainless steel Ln2 shroud provides a cold radiant source and
a quartz heater array provides unidirectional radiant heating. Control and data
acquisition systems are uniquely tailored for each application. This chamber
does not meet stringent contamination requirements for space flight hardware.
It is used primarily to qualify research or developmental components and for
material outgassing or bakeouts.
OPERATTION: Test items are configured
in the chamber and instrumented with thermocouples and connected with ground
support equipment. Isolation value and door interlocks provide for test preparation
in chamber during 2 hour cryopump cooldown. Control programs are suitable for
atmospheric and space flight testing. Two rotary piston pumps with a cold trap
provide roughing pressure for crossover to high vacuum with the cyropump.
Bell Jar thermal vacuum facilities used to qualify components and small subsystems include two glass and one stainless steel Bell Jar. They are all similar in function and size and able to accommodate components up to approximately 1foot^3. Each has a cryogenic pumping system capable of attaining vacuum pressures of 1 by 10^-5mm (hg). Heating sources are uniquely configured to satisfy testing requirements and include both conductive and radiant sources. Conductive cold plates are available to produce temperatures as low as 250(F). When configured in conjunction with an appropriate heat source, a complex thermal profile can be established and maintained. Control and data acquisition features are automated and include both hardware and software fail-safe functions to allow continuous testing over extended periods. Fluid and electrical penetrations are available to meet interface requirements.
The vibration test facility is equipped to perform vibration testing, of aerospace components, subsystems, and small payloads.
LING
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Equipment and trained personnel are available to conduct comprehensive modal
analysis to identify resonant characteristics of complex structures and systems.
Modal Contact : Dr. Kenny B. Elliott
(Kenny.B.Elliott@nasa.gov)
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| 5ft x 5ft |
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| <8 x 10-7 Torr(mm Hg.) |
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| <5 x 10-7 Torr(mm Hg.) |
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| Glass |
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| w/ 4" glass veiwport |
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Ln2 source, -185deg C(-300deg F)
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| 40 Foot |
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(High bay) 26ft. x 16ft. (Medium bay) |
Class 1000
Class 1000 |
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