Survey of large space chambers - vacuum chambers to simulate space environmen

Hollingsworth, R. T.

English

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NASA TN D-16' 
TECHNICAL NOTE 
0-1673 
A SURVEY OF LARGE SPACE CHAMBERS 
R. T. Hollingsworth 
Goddard Space Flight Center 
Greenbelt, Maryland 
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 
WASHINGTON April 1963 
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https://ntrs.nasa.gov/search.jsp?R=19630004750 2020-03-24T05:53:25+00:00Z
A SURVEY OF LARGE SPACE CHAMBERS 
by 
R. T. Hollingsworth 
Goddard Space Flight Center 
SUMMARY 
Construction has been authorized for a number of large thermal- 
vacuum chambers to simulate orbital altitudes in the environmental 
testing of complete spacecraft. The proposed facilities shall be capa- 
ble of simulating the low temperatures, solar and earth radiation, and 
vacuum of outer space. 
We have outlined in this report the individual specifications and 
capabilities of each of the proposed space simulation facilities. Since 
the field of space simulation is growing rapidly, it is recognized that 
this survey will be out of date upon issue. 
1 
i 
A SURVEY OF LARGE SPACE CHAMBERS 
by 
R. T. Hollingsworth 
Goddard Space Flight Center 
The need for ground-test facilities which simulate environments encountered at orbital altitudes 
has caused the government and private industry to authorize and construct large thermal-vacuum 
chambers for testing complete spacecraft in many combined environments. 
Since the major portion of a spacecraft's operational life is spent in a vacuum, high reliability 
must be assured by ground testing in a similar environment prior to launching. Some of the princi- 
pal space environment factors are: the low temperatures, solar and earth radiation, ionizating radi- 
ation, meteoritic impacts, and zero gravity. Current technological limitations preclude the simula- 
tion of the last three factors in large space chambers. The remaining factors a r e  chiefly concerned 
with the thermal cycles, heat balance, and temperature extremes experienced by the spacecraft. 
While scientific theory and analytical procedures permit design calculations, the many simpli- 
fying assumptions must be verified by testing of the final complex structure. It is often necessary to 
control the spacecraft temperature within a few degrees centigrade for proper operation of scientific 
instruments and experiments; this is achieved by regulation and ejection of the heat generated by 
internal power sources. The complexity of this problem with large spacecraft is so great that experi- 
mental verification must be made under test conditions simulating outer space. 
The current thermal-vacuum techniques employed at the Goddard Space Flight Center include the 
following: 
1. Uniform soak temperature. - For spinning satellites of simple geometric configuration, 
with very low power dissipation, a uniform soak test may be sufficient. Even for complex systems, 
it is felt that a soak test  is required as a preliminary test to provide a well defined datum plane. 
2. Predicted temperature contour reproduction. - This method involves using a combination 
of cold walls and lamps to reproduce the temperatures predicted (by the thermal design) in several 
important regions of the spacecraft. Usually the spacecraft is brought to "power-off" temperatures, 
and the inputs are held constant when the power is turned on. This technique was  employed with 
Explorer XII. In this test, realistic temperature gradients are produced to verify performance. 
The following will briefly illustrate the above: The solar aspect for Explorer XII was 150 de- 
grees  in September, 1961. The solar aspect for March, 1962 (shown in position 2 on Figure l) was 
1 
/ 
/ 
I 
I 
\ 
\ '\ 
POSITION 1 
/ 
PATH OF SATELLITE 
IN ORBIT 
AROUND THE EARTH . . 
-- - -- -*- 
POSITION 2 
(6  MONTHS AFTER POSITION 1) 1 
\ 
PATH OF EARTH , 
IN ORBIT ---+,I 
AROUND THE SUN,/ 
* .. 
,.I _- --- 
EARTH 
Figure 1-Relative positions of sun and satellite 
at different times of year. 
SOLAR CELLED 
PADDLE NUMBER 
SINGLE 150W 
LAMP FOR HEATING OF 
LIGHT RING NUMBER 1 LIGHT RING NUMBER 2 
(8- 150W LAMPS ) FIXTURE (8- 150W LAMPS) 
Figure 2-Thermal-vacuum aspect tests. Numbers 
designate thermalcouple stations. 
30 degrees. Figure 2 shows the position- 
ing of the lamps for the thermal-vacuum 
testing of Explorer XII. The two aspect 
tests were chosen because the main instru- 
mentation compartment is located in  the 
octagon, while the transmitter section is 
near the base of the spacecraft. Since 
these two locations will  alternately "see" 
the direct solar radiance and the cold of 
space, the thermal-vacuum test was de- 
signed to observe the thermal gradients 
through the spacecraft and their effect, i f  
any, on the subsystems. 
As spacecraft become more sophisti- 
cated, more accurate simulation of the 
expected environment will  be required. 
Thus, many facilities now planned or 
under construction will include solar simu- 
lation and cryogenic wall temperatures. 
In light of the foregoing, it is inter- 
esting to review the facilities under con- 
sideration for the spacecraft of the future. 
The following pages present illustrations 
and tabular summaries of a number of 
such facilities. 
2 
SPACE SIMULATION FACILITY 
REPUBLIC AVIATION CORPORATION 
FARMINGDALE, LONG ISLAND, NEW YORK 
Construction: 
Overal I dimensions: 13 f t  diameter x 30 f t  long. 
Construction material: 
Shell: 304 Stainless Steel. 
Work space dimensions: 
Entry lock: 13 f t  diameter x 8 f t  long. 
Operating lock: 13 f t  diameter x 18 ft long. 
Pressure: 
Ultimate pressure: 8.8 x lo-’ mm-Hg. 
Time to achieve ultimate pressure: 3 hours. 
Pumping system: Electronic gettering and blower 
s ys te m . 
Temperature : 
. Temperature range: Under evaluation. 
Thermal system: Under evaluation. 
Cryogenics: 
Solar Simulation: 
Area illuminated: 10 f t  diameter 
Maximum intensity: 250 watts/ft * 
System type: Xe lamps. 
Other Environment Capabi I ities: 
A sinusoidal vibration system with a 30,000- 
pound force output i s  being installed. 
Svstems Contractor: 
Design: Tenney Engineering, Inc. 
Fabrication: Tenney Engineering, Inc. 
Operationa I Dote: 
September, 1961 (vacuum). 
LN, panel area: Under evaluation. 
He panel area: Under evaluation. 
3 
H IV (HIGH VACUUM ORBITAL SIMULATOR) 
LOCKHEED AIRCRAFT CORPORATION 
SUNNYVALE, CALIFORNIA 
Construction : 
Overal I dimensions: 
Construction materials: 
18 ft inside 
diameter x 20 ft high. 
Shell: 304 Stainless Steel. 
Shroud: extruded aluminum. 
Init ial configuration for 5 ft diameter x 15 ft 
vert i ca I I y mounted vehicle. 
Work space dimensions: 
Pressure: 
Ultimate pressure: 1 x lo-' mm-Hg. 
Time to achieve ultimate pressure: 4 hours. 
Pumping system: Twenty-two 32-inch o i l  diffusion 
pumps backed by diffusion ejector and mechanical 
pumps. 
Tempera tu re: 
Temperature range: Shell - 273"F, ambient to +375"F. 
Thermal system: Circulating Dowtherm-A. 
Crvoaenics: 
LN, panel area: 5800 square feet. 
Heat Flux: 
Present configuration: 5 ft diameter x 15 ft 
with 1000 Btu/hr/ft2. 
System type: Quartz lamps backed by alum. 
reflectors, computer programmed 
for simulated orbital motion. 
Svstems Contractor: 
Design: Consolidated Vacuum Corporation. 
Fabrication: Consolidated Vacuum 
Corporation (prime). 
Operational Date: 
February 1, 1962. 
4 
Construction : Cryogenics: 
Overall dimensions: 30 f t  diameter x 34 ft high. 
Construction materials: 
Work space dimensions: 24 f t  diameter x 20 ft. 
Shell: 304 Stainless Steel. 
Pressure: 
Ultimate pressure: lo-' or better, 5 x mm-Hg 
Time to achieve ultimate pressure: 24 hours. 
Pumping system: Sixteen 32-inch o i l  diffusion 
pumps backed by booster and 
mechan i ca I pumps. 
with test vehicle. 
Temperature: 
Forecasted for 1962: Operational LN, open 
cycle. 
Solar S i  mu lat i  on: 
Forecasted for 1963. 
Other environment capabilities of this chamber: 
28,000 vibration potential. 
Systems Contractor: 
Design: RCA Major Systems Division. 
Fabrication: Chicago Bridge and Iron Company. 
Temperature range: -100' F to +250° F. 
Thermal system: Cascade Freon 13 brine 
system and immersion 
e I ectri c heaters. 
Operational Date: 
November, 1961. 
5 
Construction: 
Overall dimensions: 20 ft  diameter x 27 ft  long. 
Construction materials: 
Shell: 304 Stainless Steel. 
Shroud: 304 Stainless Steel. 
Work space dimensions: 18 ft diameter 
x 20 ft long. 
Pressure: 
Ultimate pressure: 4.8 x lO-*mm-Hg with 
cold wall. 
Time to achieve ultimate pressure: 
Pumping system: Six 32-inch o i l  diffusion 
pumps backed by blower 
pumps and rotary gas pumps. 
1 1  -12 hours. 
Temperature: 
Temperature range: -300' F to +2000° F. 
Thermal system: Quartz lamps and nitrogen 
curtain wal I. 
SPACE SIMULATION CHAMBER 
THE BENDIX CORPORATION 
ANN ARBOR, MICHIGAN 
Cryogenics: 
LN, panel area: 1600 square feet. 
Solar Simulation: 
Area illuminated: 7 ft  diameter 
Maximum intensity: 140 watts/f?. 
System type: Carbon arc. 
Other Environment Capabilities: 
Structural loading, shock and vibration 
provisions. 
Systems Contractor: 
Design: Bendix Systems Division. 
Fabrication: Chicago Bridge and Iron Company. 
Opera t iona I Date : 
Vacuum: November, 1961. 
Complete system: January, 1962. 
6 
25-FOOT SPACE ENVIRONMENT FACILITY 
JET PROPULSION LABORATORY 
PASAD EN A, CALI FOR N I A 
Construction: 
Overall dimensions: 27 ft diameter x 80 ft high. 
Construction materials: 
Shell: 304 Stainless Steel. 
Shroud: Aluminum. 
Work space dimensions: 25 ft diameter 
x 25 ft high. 
Pressure: 
Ultimate pressure: 1 x 10-6mm-Hg. 
Time to achieve ultimate pressure: 3-1/4 hours. 
Pumping system: Ten 36-inch o i l  diffusion 
pumps backed by blowers and 
the wind tunnel compressors. 
Temperature: 
Tempqrature range: -320' F to ambient 
Thermal system: LN, panels and solar 
simulation. 
(possible). 
Cryogenics: 
L N ,  panel area: 4200 square feet. 
R 1 1  
Solar Simulation: 
Area illuminated: 1 1  ft diameter. 
Maximum intensity: 75 watts/ft2 (or 5 f t  
diameter 130 watts/ft, 
future 15 ft diameter 
275 watts/ft*). 
System type: Hg-Xe lamps. 
Other Environment CaDabilities: 
Provision i s  made to use electrodynamic 
shakers in the chamber with force ratings up 
to approximately 30,000 pounds. 
Systems Contractor (Prime): 
Design: Consolidated Vacuum Corp. 
Fabrication: Consolidated Vacuum Corp. 
Operationa I Date: 
December, 1962. 
0 
SPACE ENV I RON M E NT SI M U LATO R 
CHANCE VOUGHT CORPORATION 
DALLAS, TEXAS 
Construct ion: 
Overall dimensions: 12 ft diameter x 15 ft  long. 
Construction materials: 
Shell: 304 Stainless Steel. 
Shroud: Finned aluminum tubing. 
Work space dimensions: 10 ft diameter x 10 ft. 
Pressure: 
Ultimate pressure: 1 x l(r7 mm-Hg. 
Time to achieve ultimate pressure: 2-1/2 hours. 
Pumping system: Three 32-inch o i l  diffusion 
pumps backed by a booster 
and mechanical pump. 
Temperature: 
Temperature range: -320' F to ambient. 
Thermal system: LN, heat sink and solar 
s i  mu I at ion. 
Cryogen i cs : 
Solar Simulation: 
Area illuminated: 6 ft  diameter. 
Maximum intensity: 130 watts/ft2. 
System type: Hg-Xe lamps with external 
e l  l iptical reflectors. 
Other Environmental Capabilities: 
Two-axis orbital rotation of specimen 
of 1 000-pound maximum weight. Maximum 
envelope of 8-foot diameter sphere. Slip 
rings on motion gimbal for power in/data out. 
Systems Contractor: 
Design: Tenney Engineering, Inc. 
Fabrication: Tenney Engineering, Inc. (prime). 
Ope rat i ona I Date : 
December, 1961 (partial operation). 
LN, panel area: 460 square feet. 
8 
Construct ion: 
SPACE SIMULATION SYSTEM 
GRUMMAN AIRCRAFT ENGINEERING CORPORATION 
BETHPAGE, LONG ISLAND, NEW YORK 
Overall dimensions: 19 ft diameter (30 ft at 
bustle) x 28 ft high. 
Construction materials: 
Shell: 304 Stainless Steel. 
Shroud: Stainless steel. 
Work space dimensions: 15 ft diameter x 20 ft 
high. 
Pressure: 
Ultimate pressure: 5 x lo-' mm-Hg with cryo. 
Time to achieve ultimate pressure: 6 hours. 
Pumping system: Eight 32-inch oi l  diffusion 
pumps backed by roughing 
system. 
Tempe rat ure : 
Temperature range: -320" F to +300° F. 
Thermal system: Liquid or gaseous N in shroud. 
Cryogenics: 
LN, panel area: 2200 square feet. 
Solar Simulation: 
Provisions made for heat flux simulation tailored 
to specific project. 
Other Environment Capabilities of this Chamber: 
Backfilling with N, gas 1 to 3 tor. 
Svstems Contractor (Prime): 
Design: Chicago Bridge and Iron Co. 
Fabrication: Chicago Bridge and Iron Co. 
Operational Date: 
March 1, 1962. 
Construction: 
Overall dimensions: 
Construct ion mater io Is : 
Shell: 304 Stainless Steel. 
Shroud : A I umi num. 
32 ft diameter x 54 ft high. 
Work space dimensions: 20-ft diameter sphere. 
Pressure: 
Ultimate pressure: 1 x lo-' mm-Hg. 
Time to achieve ultimate pressure: 6 hours. 
Pumping system: Cryogenic pumping and two 
32-inch a i l  diffusion pumps 
backed by booster and 
mechanical pumps. 
Temperature : 
Temperature range: Function of experiment design. 
Thermal system: Solar simulation and 100°K walls. 
Cryogenics: 
L N  panel area: 5400 square feet. 
He panel area: 725 square feet. 
Solar Simulation: 
Area illuminated: 20 ft diameter. 
Maximum intensity: 140 watts/ft2. 
System type: Off axis parabolic collimating 
reflector with xenon arc-lamp 
source. 
Other Environment Capabilities: 
Provision for future addition of vibration 
foci I i t ies. 
Systems Contractor: 
Design: General Electric Company. 
Fabrication: General Electric Company (prime). 
Operational Date: 
March, 1962. 
November 1962 for Solar. 
10 
30-FOOT THERMAL-VACUUM AND SPACE 
SIMULATION TEST FACILITY 
SPACE 
Construct ion: 
TECHNOLOGY I 
LOS ANGELES, 
Overal I dimensions: 30-ft diameter sphere. 
Construct ion materials: 
Shell: 304 Stainless Steel. 
Shroud: Aluminum. 
Work space dimensions: 28-ft diameter sphere. 
Pressure: 
Ultimate pressure: 3 x mm-Hg. 
Time to achieve ultimate pressure: 
Pumping system: Four 32-inch o i l  diffusion 
pumps backed by blower and 
mechanical pumps. 
12 hours. 
Temperature: 
Temperature range: -320" F to +275" F. 
Thermal system: Gaseous N within shroud. 
Cryogenics: _~ 
LN, panel area: 2450 square feet. 
Solar Simulation: 
Area illuminated: 7 f t  x 4 f t  expandable to 
1 1  f t x  1 1  ft. 
Maximum intensity: 260 watts/ft*, current 
System type: Carbon arc source. 
system 130 watts/ft2. 
Systems Contractor: 
Design: Chicago Bridge and Iron Co. 
Fabrication: Chicago Bridge and Iron Co. 
Ope rational Date: 
November, 1962; with solar January 1, 1963. 
11 
MARK I AEROSPACE SIMULATOR 
ARNOLD ENGINEERING DEVELOPMENT STATION 
ARNOLD AIR FORCE STATION, TENNESSEE 
Construction: 
Overall dimensions: 42 ft diameter x 82 ft high. 
Construct ion materia I s  : 
Shell: 304 Stainless Steel. 
Shroud: Copper. 
Work space dimensions: 35 ft diameter x 65 ft. 
Pressure: 
Ultimate pressure: 1 x lo-* mm-Hg. 
Time to achieve ultimate pressure: 24 houn. 
Pumping system: Forty-eight 32-inch o i l  
diffusion pumps and a 20" K 
cryogenic system backed by 
roughing pumps and wind 
tunnel facilities. 
Temperature : 
Thermal system: Solar simulation and LN, 
panels. 
Cryogenics: 
LN, panel area: 13,376 square feet. 
He panel area: 8160 square feet. 
Solar Simulation: 
Area illuminated: 5 ft x 32 ft. 
Maximum intensity: 130 watts/ft2. 
System type: Carbon arc lamps in optical system. 
Other Environment Capabilities: 
Vibration: Up to 200,000-pound force from 
10 to 600 cps. 
Up to 5,000-pound force from 600 
to 2000 cps. 
Ascent simulation: Sea level to 80,000 feet in 
90 seconds. 
Systems Contractor: 
Design: Radio Corporation of America. 
Fabrication: Compudyne Corp. 
Operationo I Date: 
August, 1963. 
12 
3 r A L t  t N V l K U N M t N l  3 I M U L A l U K  
Construct ion: 
Overall dimensions: 35 ft diameter x 60 ft high. 
Construction materials: 
Shell: 304 Stainless Steel. 
Shroud: AI umi num. 
Work space dimensions: 28 ft diameter x 40 ft. 
Pressure: 
Ultimate pressure: 2 x mm-Hg. 
Time to achieve ultimate pressure: 24 houn. 
Pumping system: Cryogenic and seventeen 32- 
inch o i l  diffusion pumps backed 
by mechanical booster pumps. 
Temperature: 
Temperature range: -320OF to +215"F. 
Thermal system: Liquid and gaseous N. 
Cryogenics: 
LN, panel area: 8000 square feet. 
He panel area: 2000 square feet. 
NASA-Langley, 1963 G-290 
Solar Simulation: 
Area illuminated: 20 ft diameter. 
Maximum intensity: 275 watts/ft2. 
System type: Multimodular, He-Xe lamps. 
Svstems Contractor: 
Design: Minneapolis-Honeywell Regulator 
Company (Prime). 
F. J. Stokes Corp. - Vacuum and 
Cryogenics. 
Fabrication: Minneapol is-Honeywel I Regulator 
Company (Prime). 
F. J. Stokes Corp. - Vacuum and 
Cryogenics. 
Operational Date: 
December, 1962. 
Solar Simulation - early 1963. 
13 


A SURVEY OF LARGE SPACE CHAMBERS

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