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US3647924A - High-temperature furnace for melting materials in space - Google Patents

High-temperature furnace for melting materials in space Download PDF

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Publication number
US3647924A
US3647924A US114848A US3647924DA US3647924A US 3647924 A US3647924 A US 3647924A US 114848 A US114848 A US 114848A US 3647924D A US3647924D A US 3647924DA US 3647924 A US3647924 A US 3647924A
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crucible
plates
furnace
space
bolts
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US114848A
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John R Rasquin
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National Aeronautics and Space Administration NASA
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National Aeronautics and Space Administration NASA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F27—FURNACES; KILNS; OVENS; RETORTS
    • F27D—DETAILS OR ACCESSORIES OF FURNACES, KILNS, OVENS OR RETORTS, IN SO FAR AS THEY ARE OF KINDS OCCURRING IN MORE THAN ONE KIND OF FURNACE
    • F27D11/00—Arrangement of elements for electric heating in or on furnaces
    • F27D11/02—Ohmic resistance heating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G4/00—Tools specially adapted for use in space

Definitions

  • ABSTRACT An electrically powered furnace for melting high-melting point materials in the vacuum and zero gravity environment of space comprising an alumina crucible, cylindrical in shape,
  • the crucible is surrounded by concentric cylindrical enclosures made of polished sheet molybdenum.
  • the sample holder is clamped between a pair of round plates and a pair of alignment bolts are joined to the circular plates and extend along the longitudinal axis of the furnace through the end covers of the crucible and surrounding concentric enclosures.
  • furnace devices capable of melting the materials under study will be needed aboard the orbitingzspace vehicles.
  • Such a furnace device should be highly efticientso as not to require undue power, andthe furnace must be constructed so as to not be impaired by.the high 'gforces experienced during certain phases of a space flight, for example, the launch phase.
  • the invention comprises an electrically powered furnace for melting materials in the vacuum and zero gravity environment of space.
  • Thefurnace includes a crucible of refractory material enclosing a sample holder adapted for containing the sample to be melted.
  • the crucible is surrounded by a plurality of spaced, concentrically related, polishedsheet enclosures, preferably of molybdenum, for preventing radiation loss from the'crucible.
  • FIG; I is a vertical sectional view of a high temperature furnace embodying the invention.
  • FIG. 2 is a sectional view taken along line 2-2 of FIG. 1.
  • FIGS. 1 and 2 therein is shown a high tempera ture furnace 11 particularly adapted for installation on a spacecraft for melting samples of high-melting point materials in the vacuum and zero gravity environment of space.
  • the furnace 11 comprises an alumina cylindrical crucible 13 located centrally of the furnace.
  • the crucible has an integral bottom 15 and a separate cover 17 fitted and joined to the main body of the crucible at the upper end.
  • Formed in the opposite end edges of the crucible 13 are a series of vertical slots ⁇ 19 arranged in spaced pairs to receive tungsten electric resistance heating wire 23 that is looped around spaced supports 25 between the slots 19.
  • the wire supports 25 are provided every radially and the supports at one end of the crucible are staggered relative to the supports vat the other end thereof.
  • the wire is. arranged around the crucible 13 extending diagonally between upper and lower ends and being looped aroundthe supports 25, alternately, at the upperrand lower ends.
  • Lead wires 27 for the heating wire 23 extend from a power source .(not shown) and enter the crucible l3;through a double-bore alumina tube 29 that is bonded in an opening 33 by a temperature-resistant cement.
  • Another tube 29 is sealed in an opening 34 at the lower end of the crucible for receiving lead wires 35 of athermocouple 37 associated with an indicator (not shown)for indicating temperaturewithinthe crucible .13.
  • the crucible '13 are fourconcentrically related cylinders 41, 43,45 and 47 of uniformly increasing diameter and length.
  • the cylinders are provided, respectively, with circular end covers 49, 51, 53 and 55 that fit telescopically over the ends of the cylinders.
  • the cylinders and covers are made of polished :sheet molybdenum .that reflect heat to prevent radiationlossafrom the crucible 13.
  • the covers are not sealed to the cylindersso.that gas-trapped within each of the cylinders will escapewhenthe furnace is placedin a vacuum en- -vironment..and:thereby assure against convection heat loss .betweenthe cylinders and the crucible.
  • the alumina tubes 29 material'such as .glass for example.
  • the sample is indicated in phantom linesin;its.solid .state and a spherical mass 67 represents the sample after being melted.
  • Surrounding the sample 65 is a carbon cylinder 69 and end covers 71.
  • Each of "the;carbon end covers71 has-a central pointed projection 73 tthabengagesthe sample 65-to support the sample until it is meltedfiwhen the sample is melted itwill have no tendency to adhere tosthe carbon but will. readily-"pull away from the carbon projections 73,.and form the sphere 67 without contamination-ofithe sample.
  • The-sample holder 61 is clamped-between a lower circular plate' 75 and anpupper'circular plate 77.
  • Each of the plates are made of molybdenum andwthe lower plate 75 hasa circular -recess79therein that receives the lower end of the sample holder6l.
  • Three molybdenum. clamping'bolts8l each have threaded. end portions :83 of reduced diameter extending through vertically alignedholes' 85 -in the upper and lower plates. Nuts 91 are used in clamping thesample holder 61 firmlybetween-theplates'75 and-77.
  • a molybdenum bolt 93 Joined to eachof the plates'75 and 77 is a molybdenum bolt 93.
  • the bolts 93 are'locatedonthe vertical orlongitudinal axis of the furnace l 1 .and have athreaded portion 95 screwed into athreaded hole 97in the center of the plates75and 77.
  • Each bolt 93 has an unthreaded portion 101 of increased diameter that provides a spacer between the respective plates 75 and 77 and the upper and lower ends of the crucible 13.
  • Spacers in the form of molybdenum nuts 103 threaded on the bolts 93 are also provided between the upper and lower ends of the crucible l3 and between the respective adjacent covers 49, 51, 53 and 55. Nuts 103 are also threaded on the bolts 93 against the outer surfaces of the covers 55.
  • the furnace 11 may be mounted in a spacecraft in the manner desired and may be enclosed in a chamber 105 (indicated in phantom line) that is put in communication, selectively, with the vacuum environment of space.
  • Mounting elements 107 may be attached to the bolts 93 and to the chamber 105.
  • the high temperature furnace disclosed herein is extremely efficient in that heat losses from the crucible are minimal and the described structure of the furnace makes it uniquely sturdy and resistant to damage from subjection to high g forces.
  • a furnace for melting materials in the vacuum and zero gravity environment of space comprising:
  • said container being disposed between two clamping plates
  • adjustable means extending between said plates for clamping said plates against said container
  • electrical conducting means disposed in the vicinity of said enclosed container for electrically heating a sample of material to be melted.
  • said concentrically related enclosures comprise a plurality of cylinders having separable end covers, said cylinders and said covers comprising polished sheet molybdenum.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Sampling And Sample Adjustment (AREA)

Abstract

An electrically powered furnace for melting high-melting point materials in the vacuum and zero gravity environment of space comprising an alumina crucible, cylindrical in shape, and enclosing a cylindrical tantalum sample holder that contains the sample to be melted. The crucible is surrounded by concentric cylindrical enclosures made of polished sheet molybdenum. The sample holder is clamped between a pair of round plates and a pair of alignment bolts are joined to the circular plates and extend along the longitudinal axis of the furnace through the end covers of the crucible and surrounding concentric enclosures.

Description

United States Patent Rasquin 1151 3,647,924 1 51 Mar.7, 1972 [72] inventor:
[54] HIGH-TEMPERATURE FURNACE FOR MELTING MATERIALS IN SPACE John R. Rasquin, Madison, Ala.
[73] Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration 221 Filed: Feb. 12,1971
211 Appl.No.: 114,848
. [52] US. Cl ..l3/20, 13/31 [5 1] Int. Cl. [58] Field otSearch ..l3/20, 21; 219/343, 349, 424
[56] References Cited UNITED STATES PATENTS 3,170,018 2/l965 Lewis ..l3/3l 3,456,935 7/1969 Bornor ..l3/3l X Primary Examiner-Bernard A. Gilheany Assistant Examiner-Roy N. Envall, .l r.
Attorney-L. D. Wofi'ord, Jr., W. H. Riggins and John R. Manning [57] ABSTRACT An electrically powered furnace for melting high-melting point materials in the vacuum and zero gravity environment of space comprising an alumina crucible, cylindrical in shape,
and enclosing a cylindrical tantalum'sample holder that contains the sample to be melted. The crucible is surrounded by concentric cylindrical enclosures made of polished sheet molybdenum. The sample holder is clamped between a pair of round plates and a pair of alignment bolts are joined to the circular plates and extend along the longitudinal axis of the furnace through the end covers of the crucible and surrounding concentric enclosures.
8 Claims, 2 Drawing Figures HIGH-TEMPERATURE FURNACE FOR MELTING MATERIALS IN SPACE ORIGIN OF THE INVENTION The invention described herein was made by an employee 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 aboard earth-orbiting workshops, laboratories and space stations that will remain in earth orbit for long periods. I
Included in the projects to be undertaken in earth orbit are experiments relating to manufacturing .in space. The advantages of using the space environment for carrying out certain manufacturing processes is well recognized andit is anticipated that some day many unique products will be made in space. These products will be made by processing materials in the fluid-state since itis in this state thatmaterials will be affected by the vacuum and zero gravity condition in space.
In conducting experiments to observe and analyze the behavior of various materials in space and thereby gain knowledge that will contribute to the developmentof space manufacturing, furnace devices capable of melting the materials under study will be needed aboard the orbitingzspace vehicles. Such a furnace device should be highly efticientso as not to require undue power, andthe furnace must be constructed so as to not be impaired by.the high 'gforces experienced during certain phases of a space flight, for example, the launch phase. v
Although high temperature fumacesof various'designs are known, they are not deemed to have thestructural rigidity and performance efficiency required for use in a space facility.
SUMMARY OF THE INVENTION The invention comprises an electrically powered furnace for melting materials in the vacuum and zero gravity environment of space. Thefurnace includes a crucible of refractory material enclosing a sample holder adapted for containing the sample to be melted. The crucible is surrounded by a plurality of spaced, concentrically related, polishedsheet enclosures, preferably of molybdenum, for preventing radiation loss from the'crucible. To provide firm support for'all the partsof the furnace and insure'thatthe'fumace will'withstand high 3" forces the sample holder is clamped between a pair of opposed plates and a pair of alignment bolts are joinedtothe plates and extend along the longitudinal axis of the furnace'through opposite ends of the crucible *andpolishedsheet enclosures.'The
perature furnace for installation on *aspace vehicle and con-' structed sothat itwill withstand the high g" forcesattendant to certain phases of space flight.
These and other objects and advantages of the invention will become apparent upon-reference to the following specification, attendant claims-and drawing.
BRIEF DESCRIPTION OF THE DRAWING FIG; I is a vertical sectional view of a high temperature furnace embodying the invention.
FIG. 2 is a sectional view taken along line 2-2 of FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT :Referringto FIGS. 1 and 2, therein is shown a high tempera ture furnace 11 particularly adapted for installation on a spacecraft for melting samples of high-melting point materials in the vacuum and zero gravity environment of space. The furnace 11 comprises an alumina cylindrical crucible 13 located centrally of the furnace. The crucible has an integral bottom 15 and a separate cover 17 fitted and joined to the main body of the crucible at the upper end. Formed in the opposite end edges of the crucible 13 are a series of vertical slots\19 arranged in spaced pairs to receive tungsten electric resistance heating wire 23 that is looped around spaced supports 25 between the slots 19. In the embodiment illustrated the wire supports 25 are provided every radially and the supports at one end of the crucible are staggered relative to the supports vat the other end thereof. The wire is. arranged around the crucible 13 extending diagonally between upper and lower ends and being looped aroundthe supports 25, alternately, at the upperrand lower ends. Lead wires 27 for the heating wire 23 extend from a power source .(not shown) and enter the crucible l3;through a double-bore alumina tube 29 that is bonded in an opening 33 by a temperature-resistant cement.
.Another tube 29 is sealed in an opening 34 at the lower end of the crucible for receiving lead wires 35 of athermocouple 37 associated with an indicator (not shown)for indicating temperaturewithinthe crucible .13.
*Surroundingthe crucible '13 are fourconcentrically related cylinders 41, 43,45 and 47 of uniformly increasing diameter and length. The cylinders are provided, respectively, with circular end covers 49, 51, 53 and 55 that fit telescopically over the ends of the cylinders. The cylinders and covers are made of polished :sheet molybdenum .that reflect heat to prevent radiationlossafrom the crucible 13. The covers are not sealed to the cylindersso.that gas-trapped within each of the cylinders will escapewhenthe furnace is placedin a vacuum en- -vironment..and:thereby assure against convection heat loss .betweenthe cylinders and the crucible. The alumina tubes 29 :material'such as .glass for example. The sample is indicated in phantom linesin;its.solid .state and a spherical mass 67 represents the sample after being melted. Surrounding the sample 65 is a carbon cylinder 69 and end covers 71. Each of "the;carbon end covers71has-a central pointed projection 73 tthabengagesthe sample 65-to support the sample until it is meltedfiwhen the sample is melted itwill have no tendency to adhere tosthe carbon but will. readily-"pull away from the carbon projections 73,.and form the sphere 67 without contamination-ofithe sample.
The-sample holder 61 is clamped-between a lower circular plate' 75 and anpupper'circular plate 77. Each of the plates are made of molybdenum andwthe lower plate 75 hasa circular -recess79therein that receives the lower end of the sample holder6l. Three molybdenum. clamping'bolts8l each have threaded. end portions :83 of reduced diameter extending through vertically alignedholes' 85 -in the upper and lower plates. Nuts 91 are used in clamping thesample holder 61 firmlybetween-theplates'75 and-77.
Joined to eachof the plates'75 and 77 is a molybdenum bolt 93. The bolts 93 are'locatedonthe vertical orlongitudinal axis of the furnace l 1 .and have athreaded portion 95 screwed into athreaded hole 97in the center of the plates75and 77. The
and 77 through vertically aligned holes 99 in the top and bottom of the crucible 13 and in the top and bottom covers of the cylinders 41, 43, 45, and 47. Each bolt 93 has an unthreaded portion 101 of increased diameter that provides a spacer between the respective plates 75 and 77 and the upper and lower ends of the crucible 13. Spacers in the form of molybdenum nuts 103 threaded on the bolts 93 are also provided between the upper and lower ends of the crucible l3 and between the respective adjacent covers 49, 51, 53 and 55. Nuts 103 arealso threaded on the bolts 93 against the outer surfaces of the covers 55.
The furnace 11 may be mounted in a spacecraft in the manner desired and may be enclosed in a chamber 105 (indicated in phantom line) that is put in communication, selectively, with the vacuum environment of space. Mounting elements 107 may be attached to the bolts 93 and to the chamber 105.
The high temperature furnace disclosed herein is extremely efficient in that heat losses from the crucible are minimal and the described structure of the furnace makes it uniquely sturdy and resistant to damage from subjection to high g forces.
1 claim:
1. A furnace for melting materials in the vacuum and zero gravity environment of space comprising:
an enclosed container for holding a sample of material to be melted;
said container being disposed between two clamping plates;
adjustable means extending between said plates for clamping said plates against said container;
a plurality of concentrically related enclosures surrounding said container;
a bolt connected to each of said plates, said bolts being aligned with each other and extending outwardly and axially of said container and said furnace;
said bolts passing through opposite walls of said concentrically related enclosures;
spacers carried by said bolts between adjacent walls of said concentrically related enclosures;
electrical conducting means disposed in the vicinity of said enclosed container for electrically heating a sample of material to be melted.
2. The invention as defined in claim 1 wherein the innermost of said concentrically related enclosures comprises an alumina crucible, said electrical conducting means comprising electric resistance wire, said wire being arranged within said crucible.
3. The invention as defined in claim 2 wherein said crucible is cylindrical, a plurality of slots circumferentially spaced around each end portion of said crucible, said resistance wire extending diagonally between opposite ends of said crucible and being supported in said slots.
4. The invention as defined in claim 1 wherein said bolts are threadedly joined to said clamping plates in the center of said plates, said spacers threadedly engaging said bolts.
5. The invention as defined in claim 4 wherein said plates and said bolts are molybdenum.
6. The invention as defined in claim 1 wherein said concentrically related enclosures comprise a plurality of cylinders having separable end covers, said cylinders and said covers comprising polished sheet molybdenum.
7. The invention as defined in claim 1 wherein said enclosed container comprises an interior carbon lining.
8. The invention as defined in claim 7 wherein said lining comprises opposite spaced projections for supporting a sample of material prior to melting of the material.

Claims (7)

  1. 2. The invention as defined in claim 1 wherein the innermost of said concentrically related enclosures comprises an alumina crucible, said electrical conducting means comprising electric resistance wire, said wire being arranged within said crucible.
  2. 3. The invention as defined in claim 2 wherein said crucible is cylindrical, a plurality of slots circumferentially spaced around each end portion of said crucible, said resistance wire extending diagonally between opposite ends of said crucible and being supported in said slots.
  3. 4. The invention as defined in claim 1 wherein said bolts are threadedly joined to said clamping plates in the center of said plates, said spacers threadedly engaging said bolts.
  4. 5. The invention as defined in claim 4 wherein said plates and said bolts are molybdenum.
  5. 6. The invention as defined in claim 1 wherein said concentrically related enclosures comprise a plurality of cylinders having separable end covers, said cylinders and said covers comprising polished sheet molybdenum.
  6. 7. The invention as defined in claim 1 wherein said enclosed container comprises an interior carbon lining.
  7. 8. The invention as defined in claim 7 wherein said lining comprises opposite spaced projections for supporting a sample of material prior to melting of the material.
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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7594530B1 (en) 2007-11-19 2009-09-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Orbital foamed material extruder
US7807097B1 (en) 2008-05-19 2010-10-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Orbital fabrication of aluminum foam and apparatus therefore
US20130327894A1 (en) * 2012-06-11 2013-12-12 Robert T. Bigelow Spacercraft Shield
US8882048B2 (en) 2011-05-20 2014-11-11 Eugene M. Levin In-space processing and delivery system
US10654596B1 (en) * 2016-09-29 2020-05-19 Northrop Grumman Systems Corporation On-orbit thermal extractions of raw materials from space debris in support of additive manufacturing of new space elements on-orbit

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3170018A (en) * 1960-05-03 1965-02-16 Nuclear Technical Service Corp High temperature furnace
US3456935A (en) * 1967-09-20 1969-07-22 Alco Standard Corp Heat treating furnace with shielding packs

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3170018A (en) * 1960-05-03 1965-02-16 Nuclear Technical Service Corp High temperature furnace
US3456935A (en) * 1967-09-20 1969-07-22 Alco Standard Corp Heat treating furnace with shielding packs

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7594530B1 (en) 2007-11-19 2009-09-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Orbital foamed material extruder
US7807097B1 (en) 2008-05-19 2010-10-05 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Orbital fabrication of aluminum foam and apparatus therefore
US8882048B2 (en) 2011-05-20 2014-11-11 Eugene M. Levin In-space processing and delivery system
US20130327894A1 (en) * 2012-06-11 2013-12-12 Robert T. Bigelow Spacercraft Shield
US9327848B2 (en) * 2012-06-11 2016-05-03 Bigelow Aerospace Method of deploying a spacecraft shield in space
US10654596B1 (en) * 2016-09-29 2020-05-19 Northrop Grumman Systems Corporation On-orbit thermal extractions of raw materials from space debris in support of additive manufacturing of new space elements on-orbit
US11492150B1 (en) 2016-09-29 2022-11-08 Northrop Grumman Systems Corporation System and method for vaporizing space debris in space
US11874061B2 (en) 2016-09-29 2024-01-16 Northrop Grumman Systems Corporation System and method for manufacturing a space-based component

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