A low gravity exothermic heating/cooling apparatus is disclosed for processing materials in space which includes an insulated casing and a sample support carried within the casing which support a sample container. An exothermic heat source includes a plurality of segments of exothermic material stacked one upon another to produce a desired temperature profile when ignited. The sample container is arranged within the core of the stacked exothermic heating material. Igniters are spaced vertically along the axis of the heating material to ignite the exothermic material at spaced points to provide total rapid burn and release of heat. To rapidly cool and quench the heat, a source of liquid carbon dixoide is provided which is conveyed through a conduit and a metering orifice into a distribution manifold where the carbon dioxide is gasified and dispersed around the exothermic heating material and the sample container via tubes for rapidly cooling the material sample

Poorman, R. M.

English

NASA Technical Reports Server

United States Patent E191 [ i i ]  Patent Number: 4,513,810 
Poorman r451 Date of Patent: Apr. 30, 1985 
LOW GRAVITY EXOTHERMIC 
HEATING/COOLING APPARATUS 
Inventor: Richard M. Poorman, Huntsville, 
Assignee: 
Ala. 
The United States of America as 
represented by the Administrator of 
the National Aeronautics and Space 
Administration, Washington, D.C. 
Appl. NO.: 359,627 
Filed: Mar. 18, 1982 
Int. Cl.3 ................................................. F24J 1/00 
U.S. c1. ...................................... 165/61; 126/263; 
244/163; 165/64; 165/48 R 
Field of Search .................................... 165/61-66, 
165/48 R; 244/163; 126/263 
References Cited 
US. PATENT DOCUMENTS 
2,283,832 5/1942 
2,449,874 9/1948 
2,558,794 7/1951 
2,616,269 11/1952 
3,527,201 9/1970 
3,536,132 10/1970 
3,725,153 4/1913 
3 3 1  1,422 5/1914 
4,193,388 3/1980 
4,246,955 1/1981 
4,346,154 SA982 
4,349,333 9/1982 
4,351,385 9/1982 
Thomas ............................ 165/61 X 
Bruning ............................ 165/65 X 
Stark 165/63 X 
Reyn 165/61 X 
Epstein ................................ 126/263 
Imig et al. ........................ 165/61 X 
Bowles .............................. 165/65 X 
Amey .................................... 165/61 
Primaly Examiner-Albert W. Davis, Jr. 
Attorney, Agent, or Firm-Joseph H. Beumer; John R. 
Manning; Leon D. Wofford, Jr. 
P I  ABSTRACT 
A low gravity exothermic heating/cooling apparatus is 
disclosed for processing materials in space which in- 
cludes an insulated casing (10) and a sample support 
(16), (18) carried within the casing which supports a 
sample container (14). An exothermic heat source (A) 
includes a plurality of segments (20) of exothermic ma- 
terial stacked one upon another to produce a desired 
temperature profile when ignited. The exothermic ma- 
terial segments are constructed in the form of an annular 
element having a recess opening (22) which defines an 
open central core (23) throughout the vertical axis of 
the stacked exothermic material (A). The sample con- 
tainer (14) is arranged within the core (23) of the 
stacked exothermic heating material. Igniters (24) are 
spaced vertically along the axis of the heating material 
to ignite the exothermic material at spaced points to 
provide total rapid burn and release of heat. To  rapidly 
cool and quench the heat, a source (30) of liquid carbon 
dioxide is provided which is conveyed through a con- 
duit (32) and a metering orifice (36) into a distribution 
manifold (34) where the carbon dioxide is gasified and 
dispersed around the exothermic heating material and 
the sample container via tubes (38) for rapidly cooling 
the material sample. 
2 Claims, 3 Drawing Figures 
https://ntrs.nasa.gov/search.jsp?R=19850020902 2020-03-22T19:39:52+00:00Z
US. Patent Apr. 30,1985 Sheet 1 of2 4,513,810 
U.S. Patent Apr. 30,1985 Sheet2 of2 4,513,810 
50 g,J 
4.5 13,8 10 
LOW GRAVITY EXOTHERMIC 
HEATINGKOOLING APPARATUS 
ORIGIN OF THE INVENTION 
The invention described herein was made by an em- 
ployee of the United States Government and may be 
manufactured and used by or for the Government for 
governmental purposes without the payment of any 
royalties thereon or therefor. 
BACKGROUND OF THE INVENTION 
The invention relates to the processing of material 
samples in space and, particularly, to the rapid heating 
and cooling of a material sample in space by means of a 
controlled temperature profile. 
The environment for heating and cooling processes 
of material samples in space does not lend itself to con- 
ventional heating and cooling techniques. In space, a 
stable and controlled temperature profile must be estab- 
lished from a heat source which is a problem to which 
considerable attention need be given, particularly at 
elevated temperatures of IO00 to 1200 degrees Centi- 
grade. Combustion reactions are too dependent on envi- 
ronmental pressure and tend to be unstable and difficult 
to control for accurate heat processing in space. Exo- 
thermic reactions produce heat reactions fairly indepen- 
dent of environmental pressure and have been utilized 
as heat sources mainly for unsophisticated domestic 
applications, such as for thermal batteries as disclosed in 
US. Pat. No. 4,158,084. 
Accordingly, an important object of the present in- 
vention is to provide a highly controllable and reliable 
means for heating material samples in space experi- 
ments. 
Yet another important object of the present invention 
is to provide apparatus for heating and cooling material 
samples by means of a controlled temperature profile in 
space environments. 
Still another important object of the present inven- 
tion is to provide apparatus for rapidly heating material 
samples and thereafter rapidly quenching the tempera- 
ture for the processing of foamed metals in space envi- 
ronments. 
SUMMARY OF THE INVENTION 
The above objectives are accomplished according to 
the present invention by providing a furnace module 
which includes an insulated casing and a sample support 
carried within the casing which s u ~ ~ o r t s  a ample con- 
2 
liquid carbon dioxide is solidified and gasified in the 
chamber. The gasified carbon dioxide is dispersed 
around the exothermic heating material and the sample 
container for rapidly cooling the material sample. The 
5 gases from the cooling medium and heating reaction are 
vented through a non-propulsive vent on the exterior of 
the module casing which may be exhausted on the out- 
side of the rocket or other vehicle in which the experi- 
ment is being carried such that no reactive forces are 
A very effective heating and cooling furnace is thus 
provided in which the temperature of a material sample 
may be brought to above 1200 degrees Centigrade and 
thereafter cooled to below 900 degrees Centigrade in a 
l 5  manner of a few minutes. This IIS particularly useful in 
space experiments for processing foamed metals such as 
copper . 
DESCRIPTION O F  THE DRAWINGS 
The construction designed to carry out the invention 
will be hereinafter described, together with other fea- 
tures thereof. 
The invention will be more readily understood from 
25 a reading of the following specification and by refer- 
ence to the accompanying drawing forming a part 
thereof, wherein an example of the invention is shown 
and wherein: 
FIG. 1 is an elevation of a sounding rocket vehicle in 
30 which an exothermic furnace module constructed ac- 
cording to the present invention is utilized to carry out 
processing and experimentation of material samples in 
space; 
FIG. 2 is an elevation of exothermic heating appara- 
35 tus constructed according to the present invention with 
parts thereof shown in phantom lines to illustrate the 
cooling of the exothermic material and sample con- 
tainer. 
FIG. 3 is a partially cutaway view illustrating exo- 
40 thermic heating apparatus constructed according to the 
lo produced. 
20 
present invention. 
DESCRIPTION O F  A PREFERRED 
EMBODIMENT 
Referring now in more detail to the drawings, appa- 
ratus for heating material samples in a low gravity space 
environment by means of an exothermic reaction is 
illustrated as including a casing having a generally 
_ _  closed interior and a samde S U D D O ~ ~  means carried 
45 
. I  
5" within the casing for supp&ting the sample. Exother- 
mic heating means A is provide'd for rapidly releasing tainer. An exothermic heat source &&des a pluiality of segments of exothermic material stacked one upon an- heat having an open core in which the sample is sup- other to produce a desired temperature profile when 
ignited. The exothermic material segments are con- ported to be heated. Ignition means activates the exo- 
strutted in the form of an annular element having a 55 thermic material A to release the heat. After heating, 
throughout the vertical axis of the stacked exothermic of the sample material at a desired cooling rate for con- 
material. The sample container is arranged the trolled cooling. Insulation is carried within the casing 
of the stacked exothermic heating material. surrounding the exothermic heating means and the sam- 
tion means are spaced vertically along the axis of the 60 ple Suppod. The sample material is rapidly heated and 
heating material to ignite the exothermic material at cooled by means of a controlled temperature Profile. 
spaced points to provide total rapid bum and release of In reference to FIG- 3, it can be Seen that the casing 
heat. To rapidly cool and quench the heat, a source of includes a cylindrical casing 10 having a removable top 
liquid carbon dioxide is provided which is conveyed 12 which may be secured to casing 10 in any suitable 
through a conduit and a metering orifice into a distribu- 65 manner such as by screws. Within the interior of the 
tion chamber. A pressure drop across the metering casing, the means for supporting a sample container 14 
orifice is such that the temperature and pressure of the is provided in the form of a lower container support 16 
liquid carbon dioxide is reduced to a point where the and an upper container support 18. The sample con- 
recess opening which defines an open central core quenching means c quenches the temperature 
43 13,8 10 
3 4 
tainer 14 is held by its ends between the upper and The segments 20 of exothermic material are stacked 
lower sample supports. upon a lower base 40 on the bottom of casing 10. An 
The exothermic heating means A includes a plurality upper retaining cap 42 is resiliently biased toward base 
of segments 20 of an exothermic material which are 40 such that the stack of segments 20 are resiliently held 
stacked one upon another to produce the desired tem- 5 between base 40 and cap 42. For this purpose, a biasing 
perature profile for the heating process. When acti- spring 46 is provided at the top of the casing which 
vated, the exothermic material produces a certain urges the cap 42 and segments 20 against the bottom 
amount of heat depending on the number of segments base support 40. The cooling gas difuses in and around 
and hence m~~ount  of material whereby the temperature exothermic material normally exiting the top through 
Profile (temperature versus time) of the sample heating 10 gap 44 between the upper container support 18 and cap 
may be reliably controlled. The segments may be made 42. In one experimentation, for example, foamed copper 
from any suitable exothermic m a t e d  characterized by is processed in space aboard a sounding rocket vehicle 
being ignitable to give off heat such as iron oxide and by heating carbon, copper oxide, and copper in con- 
aluminum which is mixed with water in powdered form tainer 14 to about 1200 degrees Centigrade in approxi- 
and then cast in the desired shape. Each segment in- 15 mately one minute. After the material reacts for approx- 
cludes a central recess 22 which defines open core 23 imately one minute, the temperature is quenched by 
when the segments are stacked One another. The cooling fluid and gases to about 900 degrees Centigrade 
recess 22 is defined by a first generally vertical surface in one minute. The entire process takes less than five 
20u extending from a top surface 20b of the segment minutes. 
which terminates in a generally horizontal ledge surface 20 is provided in the conduit 32 for 
from the ledge surface 2oc and terminates at a bottom the source 30 and hence the cooling temperature profile 
stacked one upon another, the continuous central core motely by conventional means. opening 23 is provided along the axis of the vertically 25 A non-propulsive vent 50 is carried by the casing 10 stacked exothermic heating material in which the sam- which communicates with the interior of the casing. ple container 14 and material sample contained therein The exhaust gases from the heating and cooling disperse are received. 
Ignition includes an annular heating element through the heating material A and insulation 52 and 
A solenoid valve 2oc* A second generally surface 20d extends controlling the flow and amount of cooling fluid from 
surface 20e Of the segment' Thus, with the segments and rate. In space processing, this may be done re- 
24 which is carried on the ledge surface 2 0 ~  of at least 30 exit through the Opposite vent Ports 54 and 56 Of vent 
two of the segments 20, can best be seen in FIGS. 2 50* The vent Ports 54 and 56 are connected by %litable 
and 3. Electrical leads 26 connect the heating elements tubing to exterior Ports 58 and 60, On the 
24 to an voltage control by of exterior of the rocket which nullify each other and 
which the furnace may be remotely activated by ener- whereby no reactive force is produced on the vehicle. 
and ignite the exothermic material. conventional been described using specific terms, such description is 
remote control may be utilized to energize the heating for illustrative purposes only, and it is to be understood 
elements. Heating elements are provided in number and that changes and variations may be made without de- 
spaced such that total bum ofthe exothermic material is Parting from the spirit or scope of the following claims. 
accomplished to release the total heat therefrom. Ther- 40 What is 
mal couple leads 28 are operatively connected to the 1. Apparatus for heating a material Sample in low- 
container and sample by remote station in a COnven- tion and thereafter cooling said sample, said apparatus 
tional manner. By achieving total burn of the exother- comprising: 
mic material, control of the temperature profile in the 45 
heating process is achieved. 
Cooling means C is illustrated in the form of a source 
of a cooling fluid which is preferably liquid carbon 
dioxide carried externally of the casing 10. Conduit 
means 32 conveys the cooling fluid from the container 50 
30. A manifold 34 is connected to the conduit 32. A 
metering orifice 36 in flow relationship with the conduit 
32 includes a restricted opening which causes the pres- 
sure and temperature of the cooling fluid passing 
through the orifice to drop whereby the cooling fluid is 55 
solidified and gasified in manifold 34. Distribution 
means 38 conveys the gasified coolant for distribution 
to and around the exothermic heating material A and 
the sample container 14. Heat is absorbed by the solidi- 
fied carbon dioxide which causes more gas coolant to be 60 
released. By way of example, conduit 32 may be one- 
eighth of an inch tubing and orifice 36 restricted to 
about 0.0017 of an inch. Liquid carbon dioxide in con- 
tainer 30 is pressurized to approximately 1000 psi. The 
pressure drops to about 1 or 2 psi across the metering 65 
orifice whereby solid and gaseous carbon dioxide are 
formed at a temperature of about minus seventy five 
degrees Centigrade. 
gizing the heating elements 24 which, in turn, activate 35 a preferred embodiment of the invention has 
is: 
sample container 14 to monitor the temperature of the gravity environments by means of an exothermic reac- 
casing n ~ a n S  having a generally closed interior; 
sample support means carried within said casing 
means for supporting said sample; 
exothermic heat means rapidly releasing heat sur- 
rounding said sample supported by said support 
means for heating said sample to a desired tempera- 
ture; 
said exothermic heating means including a plurality 
of individual segments of said exothermic material 
which can be ignited to give off heat, stacked upon 
one another and arranged to provide a desired 
temperature profile for heating said sample; 
each said segment including a central recess there- 
through defining an open core when said segments 
are stacked upon one another, in which core said 
sample material is disposed and surrounded, said 
recess being defined by a first generally vertical 
surface extending from a top surface of said seg- 
ment and terminating in a generally horizontal 
ledge surface, and a second generally vertical sur- 
face extending from said ledge surface terminating 
at a bottom surface of said segment; 
ignition means activating said exothermic heating 
means to release said heat; 
5 
4,5 13,8 10 
6 
cooling means quenching said sample at a desired 
cooling rate for controlled cooling following heat- 
ing to said desired temperature; and 
insulation carried within said casing means surround- 
ing said exothermic heating n ~ a n s  and said sample 
support means; 
after cooled for controlled processing of said sam- 
ple. 
2. The apparatus of claim 1 wherein said ignition 
means includes a heating element carried on said ledge 
surface of at least two of said segments spaced to pro- 
vide total burn and rapid release of heat from said seg- 
ments of exothermic material. 
whereby the sample may be rapidly heated and there- * * * * *  
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Low gravity exothermic heating/cooling apparatus

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