TRANSPARENT POLYCRYSTALLINE BODY WITH HIGH ULTRAVIOLET TRANSMITTANCE, PROCESS FOR MAKING, AND APPLICATIONS THEREOF

Abstract: A transparent polycrystalline body having high ultraviolet transmissivity is provided. The body is preferably a sintered magnesia-alumina spinel body having a transmittance of at least 85 percent in the wavelength range from 0.4 microns to 0.8 microns and a transmittance at some wavelength in the wavelength range between about 0.2 and about 0.4 microns of at least about 86 percent and a porosity of less than about 0.001 percent. The sintered body is produced by a two-step method comprising forming a closed porosity body from a spinel powder and subjecting the closed porosity body to a hot isostatic pressure treatment. The resulting body has high transmissivity of electromagnetic radiation in the range between about 0.2 microns and about 6 microns, is resistant to abrasion or erosion, does not substantially deteriorate after exposure to ultraviolet light, and has high strength. The sintered body is useful in a variety of applications, including as a dome and window for missiles and launch tubes.

Description: TRANSPARENT POLYCRYSTALLINE BODY WITH HIGH ULTRAVIOLET TRANSMITTANCE, PROCESS FOR MAKING, AND APPLICATIONS THEREOF Field Of The Invention The present invention relates to a transparent polycrystalline body with high transmittance and, par¬ ticularly, a polycrystalline body of sintered spinel with high transmittance in the ultraviolet wave lengths. The present invention further relates to a method of producing such a body by a closed porosity formation step, followed by a hot isostatic pressing step. The present invention further relates to mis¬ siles and missile launch tubes and certain components used therewith and, in particular, to a missile dome and a launch tube window having high ultraviolet trans¬ mittance properties comprising the sintered spinel. Background Information In a number of applications, there is need for a strong, tough, transparent window material having a high transmissivity throughout a wide range of electro¬ magnetic radiation. Such a window material is useful, for example, for covering a port used in connection with instrumentation for detecting electro-magnetic radiation. Materials which have been used for producing a transparent body include metal fluorides, particu¬ larly magnesium fluoride (U.S. Patent No. 3,589,880 issued June 29, 1971 to Clark; U.S. Patent No. 3,294,878 issued December 27, 1966 to Carnall, Jr., et al.; U.S. Patent No. 3,431,326 issued March 4, 1969 to Letter), aluminum oxynitride (U.S. Patent No. 4,520,116 issued May 28, 1985 to Gentilman, et al. ) , aluminum niobate or tantalate (U.S. Patent No. 4,047,960 issued September 13, 1977 to Reade), and solid solutions of alumina, silica and other oxides (U.S. Patent No. 4,009,042 issued February 22, 1977 to Wittier) and alumina, with minor amounts of spinel (U.S. Patent No. 3,026,210 issued March 20, 1962 to Coble). Previous methods of ceramic preparation which have included a hot-press or closed-porosity step followed by a hot isostatic press step have included U.S. Patent No. 4,461,750 issued July 24, 1984 to Chess, et al., U.S. Patent No. 4,524,138 issued June 18, 1985 to Schwetz, et al., and U.S. Patent No. 3,853,973 issued December 10, 1974 to Hardtl, et al. Such methods, how¬ ever, do not address the problems involved in producing a body which is transparent in the ultraviolet region and has the desired hardness and strength characteris¬ tics. Methods have also been developed for production of transparent bodies substantially from a magnesia- alumina spinel. U.S. Patent No. 3,974,249 issued August 10, 1976 to Roy, et al., U.S. Patent No. 3,768,990 issued October 30, 1973 to Sellers, et al. , U.S. Patent No. 3,531,308 issued September 29, 1970 to Bagley. Polycrystalline bodies of spinel are, in general, more easily formed than single-crystal or fusion-cast spinel or sapphire. Previous materials and methods for production of a sintered transparent window have suffered from a number of difficulties. These materials have been deficient in transmittance in certain wavelength ranges, par- ticularly ultraviolet ranges, for example, wave lengths from about 0.2 micrometers (microns) to about 0.4 microns, as well as visible and infrared wave lengths up to about 6 microns. Previous materials were susceptible to abrasion or erosion, for example, from high velocity impaction of dust or sand particles or rain or cloud droplets. Previous materials were often unstable under con¬ ditions of long exposure to ultraviolet light, such that exposure to sunlight or to ultraviolet light with an intensity of about 700 microwatts/cm 2 , on the order of 0.25 hours or more caused a reduction of the trans¬ mittance properties of the material. Previous materials have been difficult to form with the desired structural strength. In some applica¬ tions it is desired to produce a transparent window which can withstand mechanical stress on the order of a pressure of about 15 psi (0.1 MPa), but which will preferably rupture when subjected to a pressure of about 25 psi (0.17 MPa) or more. Certain previous materials, e.g. MgO, are hygro¬ scopic and become cloudy upon exposure to moisture, rendering the optical qualities of the material unac¬ ceptable. A number of missiles and missile-related hardware items use transparent dome or window components. For example, the missile uses a dome component which acts as a port for radiation sensing instruments such as infrared sensors or ultraviolet sensors. The missile is commonly launched from a launch tube which includes a sealing window intended to rupture upon launch but which should be transparent to infrared or ultraviolet ratiation. Materials used in the past for such domes and windows, particularly MgF 2 , have a degree of trans¬ mittance in the infrared region, but are somewhat defi¬ cient in transmittance in ultraviolet wavelengths. Additionally, MgF 2 is, for some purposes, so wehat deficient in certain mechanical properties. In this regard, MgF 2 domes and launch windows have a Knoop hardness of about 576 kg mm - and a flexure strength of about 12.5 kpsi. A material for a launch tube window or a missile dome preferably is also relatively stable under condi¬ tions of high temperature, corrosive environments, such as oxidizing environments, or acidic environments, is substantially insoluble in water, can be polished to a high degree of polish, is stable under prolonged ex- posure to ultraviolet light, and is resistant to abra- sion or erosion, particularly when subjected to dust, sand, or water droplets at a velocity of about 500 meters per second. Launch tube windows have an additional constraint in that the launch tube window should have sufficient strength and hardness to retain its integrity and transparency during odrinary storage and transport con¬ ditions, but which will rupture at a desired over¬ pressure level, so that the window will disintegrate during launch of the missile. Previous production methods have been costly to practice and have required a number of difficult steps making the windows impractical to produce in quantity. Accordingly, a number of advantages would be real- ized by methods and materials for producing a trans¬ parent window having high transmissivity, particularly in the ultraviolet spectral region, as well as in the infrared region (e.g., about 3 to 5 microns), high resistance to erosion, abrasion or thermal or chemical degradation, elevated strength and hardness charac¬ teristics, low susceptibility to deterioration from ultraviolet light, low cost and ease of manufacture. Summary Of the Invention According to the present invention, a polycrystal¬ line body is produced having a high in-line transmit¬ tance and, particularly, a transmittance greater than that depicted by line A in Fig. 1. The body preferably comprises magnesia-alumina spinel. The body preferably has, in its uncoated state, and with a thickness of about 1.88 mm, a transmittance not less than about 60 percent, preferably not less than about 72 percent, and more preferably not less than about 77 percent, at some wavelength from about 0.2 to about 0.3 microns. The body preferably has, in its uncoated state and with a thickness of about 1.88 millimeters, a transmittance greater than about 80 percent, preferably greater than about 82 percent, and more preferably greater than about 85 percent at a wavelength of about 0.4 microns to about 0.5 microns. The body preferably has, in its uncoated state and with a thickness of about 1.88 mil¬ limeters, a transmittance greater than about 84.5 per- cent, preferably greater than about 85 percent, and more preferably greater than about 86 percent, in the wavelength range between about 0.5 microns and about 1.0 microns. The body preferably has a transmittance, in its uncoated state and with a thickness of about 1.88 millimeters, a transmittance greater than about 78 percent, preferably greater than about 81 percent, and more preferably greater than about 83 percent, at all wavelengths in the wavelength range from about 3 microns to about 4 microns and a transmittance greater than about 50 percent, preferably greater than about 76 percent, at a wavelength between about 4 microns and about 5 microns. The material retains at least about 90 percent and preferably at least about 99 percent of its original transmissivity after as much as 240 hours or more of exposure to ultraviolet light of a wave length between about 0.2 and about 0.4 microns. The sintered body has a flexural strength of at least about 15,000 psi (about 100 MPa) and preferably at least about 20,000 psi (about 140 MPa), most preferably at least about 28,000 psi (about 200 MPa) . The sintered transparent body can be produced by a two-step process involving forming a closed porosity body in a first step and reducing residual porosity in a second step. The method comprises forming a powder of spinel, and preferably having less than 0.005 weight percent of certain impurities. The powder is formed into a closed porosity body. The closed porosity body can be formed by, e.g., hot pressing or pressureless sintering. The closed porosity body is then hot isos¬ tatic pressed at a temperature of at least about 1400°C under a pressure of at least about 15,000 psi (about 100 MPa) . The sintered body produced by this method has a grain size less than about 150 microns, a poros¬ ity less than about 0.001 percent, and, in a thickness of about 1.88 mm, an in-line transmittance greater than or equal to that depicted by line A in Fig. 1. In general, increased hardness and strength char¬ acteristics are associated with smaller grain sizes. A body which is fcransparatent in the ultraviolet region as well as having the desired strength in general in¬ volves producing a body with grain sizes of about 150 microns. Substantially larger grain sizes in general result in reduced strength, while substantially smaller grain sizes in general result in unacceptable ultra¬ violet transmission. Brief Description Of The Figures Fig. 1 illustrates a preferred and a more pre¬ ferred in-line transmission of polycrystalline bodies made according to the present invention; Fig. 2 depicts the transmission curves of Fig. 1 in greater detail; Fig. 3 illustrates spectral transmission curves of single crystal and hot-pressed spinel bodies made by methods other than those of the present invention; Fig. 4 illustrates spectral transmission curves of calcium aluminate glasses; Fig. 5 illustrates spectral transmission curves of quartz crystal and silica and fused silica glass; Fig. 6 illustrates spectral transmission curves of MgO and MgF 2 ; Fig. 7 illustrates spectral transmission curves of zinc alumino ger anate and germanare glassses; Fig. 8 illustrates spectral transmission curves of SrF 2 , BaF 2 , and zinc εulfide; Fig. 9 illustrates spectral transmission curves of sapphire, A10N, and yttria; Fig. 10 illustrates spectral transmission curves of a number of samples of material made according to the present invention; Fig. 11 depicts a phase diagram for the MgO-Al 2 0 3 - spinel system; Fig. 12 illustrates a relationship between optical transmission and porosity used to obtain porosity from measurements of optical transmission; Fig. 13 is a schematic perspective view of a mis- sile dome produced in accordance with the present invention; Fig. 14 is a cross-sectional view taken along Line 14-14 of Fig. 13; Fig. 15 is a top plan view of the dome depicted in Fig. 13; Fig. 16 is a perspective view of a launch tube window formed in accordance with the present invention; Fig. 17 is a cross-sectional view taken along Line 17-17 of Fig. 16; Fig. 18 is a top plan view of the launch tube win¬ dow of Fig. 16; and Fig. 19 is a schematic cross-sectional view of a missile having a dome and residing in a launch tube having a window. Detailed Description Of The Preferred Embodiments According to the present invention, there is provided a sintered polycrystalline body which is highly transparent, particularly in the ultraviolet region between about 0.2 and about 0.4 microns wave¬ length. The sintered bodies produced according to the present invention have an in-line transmittance greater than or equal to the transmittance depicted by line A in Figs . 1 and 2. The materials of the present inven- tion are capable of a transmittance even greater than that depicted by line A in Figs. 1 and 2 and, accord¬ ingly, the present invention also includes producing a sintered body with a transmittance greater than or about equal to that depicted by line B in Figs. 1 and 2. The sintered body of the present invention also has good transmittance in the infrared wavelength region, having an in-line transmittance per 1.88 mm thickness at all wavelengths from 3 microns to 5 microns of not less than about 73 percent, preferably not less than about 76 percent, and, at all wavelengths from about 3 microns to 4 microns of not less than about 81 percent, preferably not less than about 84 percent. The body preferably has, in its uncoated state and with a thickness of about 1.88 mm, a transmittance not less than 85 percent in all wavelengths from 0.3 to 0.8 microns and not less than about 72 percent at some wavelength from 0.2 to 0.3 microns. Further, the body preferably has a transmittance not less than about 73 percent in all wavelengths from about 3 microns to about 5 microns and has a transmittance of at least about 86 percent at some wavelength from about 0.2 to about 0.4 microns. The body preferably has, in its un- coated state and with a thickness of about 1.88 mm, a transmittance greater than about 30 percent, preferably greater than 40 percent, and most preferably greater than about 45 percent, at a wavelength of about 0.2 microns and a transmittance greater than about 84 per- cent and perferably greater than about 85 percent at a wavelength of about 0.4 microns. Lines C through E of Fig. 3, provided for purposes of comparison, depict transmittance reported for spinel bodies produced by previous methods. Lines F through W of Figs. 4-9 depict transmittances reported for sin¬ tered bodies made of non-spinel materials as described in Table 1, and are provided for comparison purposes. Table 1 Curve Fig. Material Thickness (mm) C 3 single-crystal 1.6 spinel D 3 hot-pressed spinel E 3 hot-pressed 4.9 spinel F 4 calcium-aluminate 2 glass G 4 calcium-aluminate 2 glass H 4 calcium-aluminate 2 glass I 5 high-silica glass 1 J 5 fused silica 10 K 5 quartz crystal 10 L 6 MgF 2 2 M 6 MgF 2 N 6 MgO 2.5 0 7 zinc alumino 1 germanate P 7 germanate glass 2 Q 7 Ge-mullite 0.76 62% A1 2 0 3 R 8 SrF 2 2.9 S 8 BaF 2 2.9 T 8 zinc sulfide U 9 sapphire 1.5 V 9 A10N 1.5 w 9 yttria 1.5 A sintered body produced according to the present invention comprises spinel ana preferably contains more than about 99.9 weight percent spinel. Spinel is a useful material for optical applications such as in- strument ports because, among other reasons, spinel is non-birefringent, has a cubic structure, and is sub¬ stantially non-hygroscopic. The sintered transparent body has a porosity of less than 0.01 percent, preferably less than about 0.001 percent by volume and an average pore radius less than about 0.1 microns. Porosity in such low range is difficult to measure by ordinary displacement methods. Porosity can be measured using electron micrographs of the sintered body. Another method of determining porosity is to calculate porosity from measured light transmittance, e.g. by using the graphical relationship depicted in Fig. 12, which applies generally to material such as the material which is the subject of this invention. The polycrystalline body of the present invention has a scatter of less than about 9xl0 ~3 , preferably less than about 8xl0 _3 , and most preferably less than 7xl0 ~3 at a wavelength of about 0.6471 microns. The sintered body can be polished to a scratch-dig size of less than about 20-20. The scratch-dig size of 20-20 represents a maximum scratch size of 0.020 mm (0.0008 inches) in width and a maximum dig size of 0.20 mm (0.008 inches) in diameter. In this context, a scratch is a defect which is long and thin in nature and a dig is a defect which is basically round. The meaning of scratch-dig size is explained fully in Mil- 0-13830, pp. 32-34, incorporated herein by reference. Mil-0-13830 states: Surface quality is specified by two numbers separated by a hyphen, e.g., 60-20. The first number is the maximum "scratch number" and the second number is the maximum "dig number." Scratches are classified as defects which are long and thin in nature, and digs are defects which are basically round. The smaller the number in both instances, the better the sur¬ face quality. Surface quality specifications should also integrate defects over the surface of the part. Therefore, looser tolerances should be considered for larger parts. The sintered body has an average grain size less than about 150 microns. The sintered body has an average defect radius of less than about 0.005 inches (about 0.12 mm) . The sintered body of the present invention pro¬ vides a relatively low emissivity in the infrared wave¬ length regions at elevated temperatures. High emis- sivities interfere with optics measurements and can be detrimental to optical guidance systems such as situa¬ tions in which missile nose cones are aerodynamically heated during flight. Table 2 provides a comparison of emissivities of hot-pressed spinel with those of sap- phire at various temperatures. Although the hot- pressed spinel represented in Table 2 is not made ac¬ cording to the claimed invention, since emissivities are primarily material-dependent, it is believed emis¬ sivities of spinel material made in accordance with the - present invention has emissivities no greater than about those shown in Table 2 for hot-pressed spinel. Table 2 Emissivity at 4.5 and 5 .0 Microns Temp. Emissivity at 4.5 microns Emissivity at 5.0 micro (°C) spinel sapphire spinel sapphire 30 0.078 0.051 0.157 0.199 200 0.091 0.074 0.203 0.268 400 0.118 0.119 0.280 0.370 600 0.151 0.168 0.361 0.477 800 0.194 0.229 0.461 0.587 1000 0.247 0.311 0.559 0.686 1200 0.303 0.381 0.664 0.777 1400 0.381 0.468 0.788 0.848 The sintered body of the present invention has a flexural strength, measured according to the ASTM F417 test, measured at 25°C, of at least about 15,000 psi (100 MPa), preferably at least about 20,000 psi (140 MPa), and most preferably at least about 23,000 psi (about 150 MPa) . The sintered body has a tensile strength, measured according to the ACMA #4 test of at least about 12,000 psi (about 80 MPa). The material, however, is not so strong that it will resist bursting at a desired level. The sintered body of the present invention, when provided in a 3 inch (7.5 cm) diameter disk having a thickness of about 0.06 inches (1.5 mm), bursts when subjected to a pressure of more than about 25 psi (about 0.17 MPa). The sintered body of the present invention is resistant to abrasion or erosion, and particularly, when subjected to dust, sand or water droplets at a velocity of about 500 meters per second, undergoes sub- stantially no degradation of transmittance properties. The sintered body of the present invention has a Knoop hardness, measured according to the ASTM E18 test of greater than 1350 kg/mm 2 , preferably greater than 1500, and most preferably about 1700. The sintered body of the present invention is resistant to degradation under high temperature condi¬ tions and, in particular, has a high melting point, preferably above 2000°C. The sintered body of the present invention is stable undar exposure to ultraviolet light, and par¬ ticularly, experiences a loss of transmissivity of less than about 1 percent after being subjected to sunlight or at a distance of about 6 inches (15 cm) to ultraviolet radiation of an intensity of about 700 microwatts/cm 2 having a wave length of about 0.254 microns for about 240 hours. The sintered body of the present invention is chemically and thermally stable. The polycrystalline material of the present invention has a solubility of less than 10 ~3 g/100 g water at room temperature. The polycrystalline body has substantially no solubility in an acidic aqueous solution having a pH of between about 7 and about 2. There is substantially no degradation of the body upon exposure to oxidizing materials and there is substantially no degradation of the body upon exposure to temperatures of about 500°C. In this con¬ text, substantially no degradation means that the strength, hardness and optical qualities of the material are substantially preserved. In particular, upon exposure to oxidizing materials or to temperatures of about 500°C, the body possesses a Knoop hardness of at least about 1038, a flexure strength of at least about 15,00 psi, and in-line transmittance per 1.88 mm thickness in all wavelengths in the wavelength range from about 0.2 microns to about 0.4 microns of not less than the transmittance shown by Line A in Fig. 2. For comparison purposes, Table 3 shows a number of physical properties reported for other optical materials. Tabli__..._. 550- 450°C 750°C Resis¬ Resis¬ Thermal tance tance Conduc¬ Melting 4-point Knoop to to tivity or Flexure Hardness Fracture Thermal Thermal Tensile (10-4 cal. Softening Strength 20oC Strength Stress Shock Strength /cm sec Temperature (MPa) (kg/mm*) (MPa) ( K/ E) (w/cm) (MPa) °C) (°C) Previous 103 .1.390 193 11 10 110 330 2135 hot-pressed spinel MgF ; , 100 576 151 3,2 9 1255 MgO 140 900 158 8 • 11 600 2800 A1 ? 0„ 2200 344 21 600 2030 Y-,0, 160 800 193 7 Znϋ 35b 103 6 Fusion- 175 1750 cast, spinel Alplia 2400 AION 305 1950 206 2140 Germinate 460 glass For purposes of comparison, absorption coeffi¬ cients of other materials are given in Table 4, in which "HP" indicates hot-pressed. Table 4 Absorption Coefficients (cm -1 ) Wavelength (microns) Material 3.0 4.0 4.5 5.0 5.5 6. Temperature = 17 -25°C Spinel (HP) .0007 .0332 .135 .465 1.16 3.07 -.8 - 2 Sapphire .0013 .061 .252 .81 2.07 5.66 A10N .5 1.6 Zirconia 0.5 1.5 Yttria .0001 .0003 .0021 .001 .037 .11 -.15 Temperature = 127°C Spinel (HP) .0010 .046 .186 .614 1.51 3.38 Sapphire .0019 .083 .333 1.6 2.63 6.95 Yttria .001 .0006 .0038 .0017 .061 .18 Temperature = 227-250°C Spinel (HP) .0015 .0646 .243 .7- 1.95 4.74 .802 --2.3 Sapphire .0028 .113 .437 1.3- 3.3 8.48 1.4 -3.4 A10N 0.9 2.4 Zirconia 0.9 2.4 Temperature = 477-500°C Spinel (HP) .0038 .135 .475 1.3- 3.4 7.68 1.46 -3.7 Sapphire .0069 .233 .826 2.1- 5.1 : L3.38 2.46 -5.65 A10N 1.3 3.7 Zirconia 2.0 4.5 Yttria .0001 .003 .019 .072 .23 0.6 Table 4 ( cont . ) Absorption Coefficients (cπr 1 ) Wavelength (microns) Material 3.0 4.0 4.5 5.0 5.5 6.0 Temperature = 727°C Spinel (HP) .008 .244 .809 2.35 5.3 11.19 Sapphire .014 .417 1.38 2.93 8.6 19.15 Yttria .00011 .009 0.42 .15 .45 1.13 The method preferred for producing the transparent sintered body will now be described. According to- the method of the present invention, a magnesia-alumina spinel powder is provided. The spinel powder is of high purity, and particularly, has less than about 5 ppm by weight, preferably less than 3 ppm, of oxides of any of the following elements: Cr, Cu, Fe, Ga, Mn, Pb, Ti, V, Zn, and has less than 50 ppm, preferably less than 30 ppm of the total of all the above oxides. The powder preferably has less than 1,000 ppm, preferably less than 10 ppm of carbon, less than 10 ppm, preferably less than 5 ppm of calcium, less than 30 ppm, preferably less than 5 ppm of sodium, less than 500 ppm, preferably less than 100 ppm of sulfur, less than 1,000 ppm, preferably less than 50 ppm of silicon. The magnesia-alumina powder is a mixture of a pow¬ der of MgO and a powder of A1 2 0 3 . The mixture can be in any weight ratio of Al 2 0 3 to MgO approximately fall¬ ing in the range indicated by "spinel SS" in Fig. 11. Preferably, the molar ratio of Al 2 0 3 to MgO in the pow¬ der is about 1:1 plus or minus about 5 M/0. The powder preferably has a surface area of between about 10 and about 25 m 2 /g, preferably between about 15 m 2 /g and about 20 m 2 /g. The average particle size of the powder is substantially submicron and preferably between 40 and 50 weight percent of the particles have a diameter less than about 1 micrcn. The powder is used to form a closed porosity body. The formation of a closed porosity body is used in con¬ nection with the subsequent hot isostatic pressing step because hot isostatic pressing requires the ability to establish an elevated isostatic (usually gas) pressure outside the body, compared to the pressure in the body, e.g., the pressure of gas in the pores of the body. It is usually inconvenient to envelope or coat the body with a gaε-impermeable material before hot isostatic pressing. Therefore, formation of a closed porosity body (i.e., a body in which substantially no internal pores are in communication with the external atmos ¬ phere) is used to permit establishing an external pres¬ sure substantially in excess of internal pressure during the hot isostatic pressing step, as described below. The " formation of a closed porosity body can be ac¬ complished by hot pressing or pressureless sintering. According to the hot pressing method, the powder is mixed with an amount of hot-pressing aid, e.g., between about 0.5 weight percent and about 3 weight percent, preferably about 1-1/2 weight percent of LiF. A suitable powder can be obtained by processing in a mortar and pestal or milling, for example, in a vibroenergy mill. Total mortar and pestal or mill time is preferably about 1 to 10 hours with the MgAl 2 0 Δ and LiF added in batches. The mortar and pestaled or milled MgAl 2 0 4 is screened preferably through a non- metallic screen at about a 35 to 100 mesh screen size. The mixed powder is loaded in a hot press die. The powder compacts substantially upon pressing. The thickness desired for the hot pressed parts preferably will include an allowance for grinding. For example, a finished 0.3 inch (8 mm) thick disk may require the ad- dition of about 0.015 inch (about 0.3 mm) for grind al¬ lowance. The hot press die may be made of graphite, for ex¬ ample, in the form of a cylindrical annulus. A cylindrical bottom die is placed in the bottom of the hot press die. All surfaces of the dies which will be exposed to the spinel are coated with a graphite foil. According to one method of hot pressing, a single window is produced for each hot pressing operation. According to another hot pressing method, a number of windows are hot pressed simultaneously such as by ver¬ tically stacking two or more layers of spinel powder, separated by a parting medium such as graphite or boron nitride. When several windows are hot pressed simul¬ taneously, the spinel layers are preferably separated by graphite spacers sufficiently thick to prevent frac¬ ture of the spacers. Spacers of about 1/2 inch (1.2 cm) thickness layered with 0.3-1.1 mm graphite foil are operable, although thinner spacers may also be oper¬ able. Products can be produced in a number of shapes including disks and domes. After the powder and any parting medium is placed into the die, a top punch is placed into the top of the die. For disks, the top punch is a cylindrically- shaped punch and for domes, the top punch is preferably a male punch. The prepared and filled die is cold pressed at about 100 psi (0.7 MPa). The cold-press pressure must be sufficient to provide for ease of handling and also assists in slightly compacting the powder prior to placing the die in the main press. The cold press pres¬ sure must not, however, be so high that closed porosity results. The cold-pressed body can be treated to fully or partially remove volatile impurities by heating the body (at about 20°C per minute) to about 1100°C to about 1300°C, preferably about 1200°C at a reduced pressure, preferably less than 100 microns Hg pressure, for about 30 minutes. Alternatively, the impurities can be removed during the step of forming closed porosity. After cold pressing, the die is placed in a quartz cylinder, separated therefrom by an insulating material such as graphite felt. The cold pressed bodies in the die are then subjected to hot pressing. The hot press step can be achieved in an inert gas atmosphere, but is preferably conducted under a vacuum. The actual vacuum which is achieved during hot pressing will depend in part upon the rate at which impurities or other materials out-gas. Apparatus capable of producing about 60 microns of vacuum will suffice. Note that in the discussion that follows with regard to the hot press step, the temperatures are those measured at the top surface of the die by a direct optical method. These temperatures are not necessarily equal to the tempera¬ tures of the spinel. Before any pressure is applied, the die is first heated to about 1125°C. Heating is preferably achieved by an induction heating method. The spinel is held at about 1125°C for about 30 minutes. The pressure and temperature are then both linearly increased over a period of about 1 to 5 hours. The rate of temperature rise and the rate of pressure rise are approximately 5°C per minute and 0.07 MPa (10 psi) per minute, respectively, and are selected such that the target temperature is never reached substan¬ tially before the target pressure is reached. For disks, the target temperature is at least about 1400°C, preferably about 1410°C and normally not above about 1480°C. The target pressure is at least about 2000 psi (about 13 MPa), preferably about 2200 psi (about 15 MPa). For domes, ' the target temperature is at least about 1395°C and preferably about 1460°C, and the tar- get pressure is at least about 2000psi (about 13 MPa), preferably about 3200 psi (about 22 MPa) . A tempera¬ ture which is too high will result in a substantial amount of sublimation of the spinel. A temperature which is too low may result in decreased transparency of the product. Pressures higher than the target pres¬ sure are believed to be operable but cause excessive wear cf the dies . Pressures lower than the target pressure result in compaction less than that desired and inferior optical clarity. During hot pressing, the spinel normally loses about 3 1/2 weight percent to sublimation. The spinel is held at the target pressure and tem- perature for a period of time. The period of time for disks is about 2 to 5 hours. The period of time for domes is about 4 hours. Following holding at the target temperature and pressure, the heating and pressure are reduced. Cool- ing occurs in about 12 to 14 hours. When domes are being pressed, after the die has cooled to about 1000°C, it is preferred to reduce the vacuum and to fill the die with a noble gas such as argon. Another method for producing a closed porosity body is by pressureless sintering. Pressureless sin¬ tering, as compared to a hot press process, permits easier control of grain growth during the closed poro¬ sity formation step and is more useful in formation of parts having complex geometry. Hot-pressing is, in general, not as suitable for formation of complex- geometry parts. According to this method, the spinel powder is mixed with an amount of binder such as about 5 weight percent of carbowax, and may optionally also be mixed with materials such as surfactants, or lubricants, such as neofat. The powder mix is then compressed at substantially room temperature or is slip cast at room temperature to produce a green body. The green body is then exposed to a temperature, such as greater than about 1800°C preferably at substantially sub-atmospheric pressure, e.g., about 100 psi (0.7 MPa) . The atmosphere during said pressureless sintering can be hydrogen or vacuum. The closed porosity body typically has some amount of residual porosity. The hot pressed body typically has a porosity of about 0.01 volume percent or more. The pressureless sintered body typically has porosity of about 1 volume percent or more. In order to produce a body with the desired characteristics, the body is subjected to a second treatment step to reduce or eliminate the residual porosity. According to the present invention, the second step is a hot isostatic pressure treatment. The closed-porosity bodies are preferably inspected for visually-apparent defects and for minimum ultraviolet transmission such as about 65- 85 percent transmission of an ultraviolet source having an intensity peak at a wavelength of about 0.25 microns. The parts, preferably separated by graphite spacers, are loaded into a hot-isostatic pressing cham¬ ber. The hot isostatic treatment includes heating the body to a target temperature of about 1500°C to 2000°C, preferably less than about 1800°C, and preferably at least about 1500°C. Heating can be accomplished by a resistance heater furnace. The maximum temperature is achieved in an atmosphere which has been pressurized to at least " about 15,000 psi (about 100 MPa), preferably more than 25,000 psi (about 170 MPa), and most prefer¬ ably at least about 29,500 psi (about 205 MPa). The hot isostatic pressure atmosphere is preferably argon or helium. A number of rates of pressurization and heating and depressurization and cooling are operable. In one preferred embodiment, the chamber is pressurized to about 5,000 psi (about 34 MPa) without heating. The temperature and pressure are then increased linearly such that the target temperature and target pressure are arrived at essentially simultaneously. The heating is at a rate of between about 5°C per minute and about 25°C per minute, preferably about 15°C per minute. The target temperature and target pressure are maintained for a period between about 1/2 hour and about 5 hours, preferably about 2-1/2 hours. In general, there is an inverse relationship between temperature and hold time, i.e., at higher temperatures, ' a shorter hold time will be operable. After the hold time or "soak" period, a controlled cool-down is used. The pressure is decreased linearly during the cool-down period at such a rate that when the temperature reaches 600°C, the pressure will be about 10,000 psi (about 70 MPa). The preferred cooling rate is about 5°C per minute down to the tem¬ perature of 600°C. Too rapid cooling, such as more than about 15°C per minute, may cause thermal shock. After a temperature of 600°C has been achieved, the furnace is turned off. The pressure, during this period, is decreased linearly at a rate such that when the tem¬ perature is 300°C, the pressure is about 7,500 psi (about 50 MPa). At this point, the pressure is allowed to freely vent to the atmosphere and the parts are al¬ lowed to cool to a temperature at which they can be handled. Normally, there will be no weight loss of the spinel parts during the hot-isostatic pressing proce¬ dure. In one embodiment of the process, the two steps of the process are accomplished without substantial cool¬ ing of the body between steps. According to this method, a formed but unfired compact is sintered to a closed porosity state in a vessel at about atmospheric pressure in an H 2 atmosphere or a sub-atmospheric pres¬ sure in a vacuum atmosphere, and at a temperature of about 1400°C. Because this process does not require a hot-press step to form the closed porosity body, it can be used in formation of bodies having complex geometry. Hot press techniques are generally not suitable for forming complex geometry bodies. After the compact is sintered to a closed porosity state, the vessel is pressurized to at least about 20,000 psi (about 140 MPa) , without substantial cooling of the body, at a temperature of at least about 1400°C to accomplish the hot isostatic pressure step of the process and reduce or eliminate residual porosity of the body. In this context, "without substantial cooling" includes main¬ taining the temperature above about 1000°C, preferably above about 1300°C. Following the hot isostatic pressing step, the body is cooled and is subjected to further steps ro modify the surface characteristics of the body. These further steps can include grinding and polishing, ap¬ plication of an anti-reflection coating and metalliz¬ ing. The grain size in the finished body is thought to be related to both the strength characteristics and the optical characteristics of the sintered body. The ex¬ act parameters of these relationships and methods for controlling grain size are not well understood. How¬ ever, without wishing to be bound by any theory, it is presently believed that grain size is generally in¬ versely related to the strength of the sintered body but is directly related to transmission characteristics at shorter wavelengths, such as ultraviolet wave¬ lengths, in other words, it is believed that larger grain sizes produce more favorable ultraviolet charac¬ teristics but cause a decrease in the strength charac¬ teristics of the sintered body. It is also believed that the grain size of the finished body is affected by a number of factors, especially including the hot press conditions, such as soak temperature and soak time, but also, it is believed, being influenced by such factors as cooling rates, such as hot isostatic pressing cool¬ ing rates and by powder stoichiometry. It has been found that in spite of the antagonistic constraint ' s j on grain size produced by various desired qualities of the finished product, and in spite of the lack of exact knowledge regarding the numerous factors which effect grain size, a finished sintered body with the desired range of properties, particularly strength properties and transmission properties, can be produced by the described process. The transparent body is particularly useful as an optical element in electro-optical systems that will be exposed to extreme environments such as high-abrasion, high-heat, high-stress or high-corrosion environments. Applications include missile or guided artillery com¬ ponents including guidance system components such as domes, windows, lenses, and prisms, as well as armor and fuse covers. The process of this invention can be used to produce bodies having a number of useful characteristics, including those described above. How¬ ever, it is possible the process of this invention can produce bodies having other characteristics so that the characteristics above may but do not necessary charac¬ terize the process. According to the present invention, there is also provided a missile dome and a launch tube window com- prised of the sintered polycrystalline magnesia-alumina spinel body described above produced by the method described above. The domes and windows produced ac¬ cording to the present invention comprise spinel and preferably contain more than about 99.9 weight percent spinel. The domes and windows of the present invention have the advantages of the various properties discussed above for the sintered polycrystalline magnesia-alumina spinel body. These properties include, but are not limited to, non-birefringence, cubic structure, non- hygroscopicity, low porosity, low scatter, high polish- ability, low grain size, low average defect radius, low emissivity in infrared wavelength regions at elevated temperatures, high flexural strength, high tensile strength, resistance to abrasion and erosion, high Knoop hardness, high melting point, stability under ex¬ posure to ultraviolet light, and chemical and thermal stability. The configuration, i.e., the size and shape of the body produced by the above-described process, will depend on the particular application contemplated. Referring to Fig. 13, a dome 10 can be provided in a number of configurations. As depicted in Figs. 13 and 14, and particularly in contemplation of use of the dome in connection with the stinger-post missile, the dome 10 is preferably in the form of a sector of a spherical shell. The outer radius of the finished dome 10 is preferably about 1.350 inches (about 33 mm) and the inner radius is preferably about 1.297 inches (about 31.7 mm) to provide a dome thickness of about 0.053 inches (about 1.3 mm). As depicted in Fig. 16, the launch tube window 20 is preferably 90 millimeters (3.350 inches) in diameter and 1.57 millimeters (0.064 inches) in thickness. The thickness of the widnow 20 is selected to provide for the desired rupturing of the window upon launch. A thicker window 20 will, in general, withstand a higher over-pressure before rupturing occurs. The window 20 pref rably has rounded edges as depicted in Figs. 17 and 18 or, alternatively, rounded edges. Referring to Fig. 19, the missile 30 is provided with a dome 10 beneath which is mounted sensing instru- mentation (not shown), for example, infrared and/or ultraviolet guidance or tracking sensing instrumenta¬ tion. The launch tube 32 is a generally cylindrically- shaped tube sealed at both ends. The end of the launch tube 34 which is adjacent to the nose end 36 of the missile 30 is sealed by the launch tube window 20. By using the launch tube end 32 to provide a sealed en¬ vironment for the missile 30, the missile components are preserved in relative cleanliness to prevent deterioration of the missile operating parts which would result from exposure to environmental con¬ taminants. The missile 30 is intended to be launched by aiming the launch tube 32 towards the target to al¬ low the optical guidance system of the missile 30 to receive optical radiation from the target through both the launch tube window 20 and the missile dome 10. In connection with this launching mode, the launch tube window 20 must have transmittance properties at the ultraviolet and infrared wavelength regions in order to permit the missile guidance system to receive optical radiation while the missile 30 is still in the launch tube 32. Because the launch tube window 20 and the dome 10 are exposed to sunlight and thus to ultraviolet radia- tion during transport and use, the launch tube window 20 and dome 10 must retain infrared and ultraviolet transparency properties as well as strength and hard¬ ness properties under conditions of exposure to light, such as ultraviolet light. Missile launch includes two phases. During the first phase, gases are released in the launch tube 32, producing over-pressure within the sealed launch tube sufficient to rupture the launch tube window 20. An eject motor launches the missile 30 through the now- opened end 34 of the launch tube 32. When the missile 30 is a safe distance from the gunner, a booster motor accelerates the missile to the desired speed. The mis¬ sile 30 continues its flight, guided towards the in- tended target by the guidance system, which senses radiation through the dome 10. The dome 10 is exposed to great pressure and stress during the launch and flight owing to the accelaration of the launch, spin, abrasion by dust particles, water droplets and the like. The dome 10 produced according to this invention preserves the necessary transmittance characteristics in the face of such erosion and preserves its integrity in the face of the stress and acceleration endured during launch and flight. EXAMPLES Example 1 Three sintered bodies of magnesia-alumina spinel were formed and the properties thereof tested. All three bodies were formed from a powder having less than 5 parts per million by weight of oxides of any of Cr, Cu, Fe, Ga, Mn, Pb, Ti, V, and Zn and having less than 5G ppm cf the total of all the above oxides. The pow¬ der had less than 1000 ppm of carbon and less than 10 ppm cf calcium, less than 30 ppm sodium, less than 500 ppm sulfur, less than 1000 ppm silicon. The molar ratio of A1 2 0 3 to MgO was 1:1. The average particle size was submicron. The powder was mixed with 1 1/2 weight per¬ cent LiF. The powder was loaded in a graphite die and cold-pressed at about 100 psi (0.7 MPa). The cold- pressed body was hot pressed at a temperature of about 1410°C with a uniaxial pressure of about 2200psi (15 MPa) with a "soak" of 5 hours. After cooling, the bodies were hot isostatically pressed at a temperature of 1500°C and a pressure of 29,500 psi. After cooling, the bodies were polished. Transmission spectra charac¬ teristic of the three bodies are shown in Fig. 10. Example 2 Bodies of calcium aluminate glass and bodies of spinel, the latter formed according to the process of the invention, as described in Example 1, were sub¬ jected to sunlight and an artificial ultraviolet light source, Model UVL-56 manufactured by Ultra-Violet, Inc. of San Gabriel, California, for periods of time indi- cated in Table 5. The transmission of the bodies at a wavelength of about 0.254 microns is also shown in Table 5 before such exposure to ultraviolet light and after such exposure to ultraviolet light. Table 5 Length of Transmission Transmission Type of Exposure Light Before After Body (hours) Source U.V. Exposure U.V. Exposure Calcium- 2 Sunlight 70 45 aluminate glass 1/4 Artificial* 70 68 244 Sunlight 78 78 Spinel 115 Artificial* 78 76 Example 3 To assess the damage from sand erosion, samples of material formed according to the present invention, along with plexiglass and window glass were mounted on a rotating table and blasted with 10 pounds of abrasive grit. The percent haze after the test was measured using an integrating sphere. The results are shown in Table 6. Table.6 Percent Haze Material After Sandblast Test Spinel - Hot press + HIP 8 Plexiglass - 1 79 Plexiglass - 2 74 Window Glass 82 Example 4 The Agile Rain Erosion Test, as described in Memo REG. 4062-137-72 "Rain Erosion Test of Proposed Dome Materials" was performed on the material produced ac¬ cording to the present invention as well as a number of other materials including MgF 2 , CaF 2 , Yttrium-Aluminum- Garnet, MgO, and two glasses, Vycor 7913 and Corning 1723. The materials were placed in a sample holder and attached to an accelerated sled achieving the velocities indicated in Table 7. Results of the test are shown in Table 7. Table 8 shows the resistance to damage of the materials tested in order of relative ef¬ fectiveness. Table 7 Thickness of A1 2 0 3 Velocity Coating Run (km per Material (microns) No. hr/fps) Description Spinel- None 29/1600 No appreciable hot-press damage + HIP None 3 25.5/1400 No damage None 4 29/1600 No damage MgF 2 None 1 29/1600 Completely shattered None 2 29/1600 Completely shattered None 3 25.5/1400 One surface crack None 4 29/1600 Complete breakage 2.1 4 29/1600 Surface cracks with coating deterioration 3.9 4 29/1600 Coating slightly deteriorated CaF- None 1 29/1600 Slight pitting with surface cracks & fractures throughout although sample intact None 2 29/1600 Surface cracks with pitting None 4 29/1600 Surface cracks with slight pitting 2.1 4 29/1600 Coating gone - slight pitting ' with surface cracks MgO None 1 29/1600 Surface cracks None 2 29/1600 Complete breakage Table 7 ( cont . ) Thickness of A1 2 0 3 Velocity Coating Run (km per Material (microns) No. hr/fps) Description Sapphire None 2 29/1600 Single line fracture None 3 25.5/1400 No damage Yttrium- None 1 29/1600 Single line Aluminum- fracture Garnet None 3 25.5/1400 No damage Corning 2 29/1600 Completely 1723 shattered 3 25.5/1400 Pitting with surface cracks VyCor 2 29/1600 Completely 7913 shattered 3 25.5/1400 Surface pitting with one surface crack Table 8 Agile Rain Erosion Test Resistance To Damage (In Order Of Relative Effectiveness) 1 Spinel; Hot-press + HIP 2 Sapphire 3 Yttrium-Aluminum-Garnet 4 MgF 2 with coating 5 CaF 2 with coating 6 MgO 7 CaF 2 8 MgF 2 9 VyCor 7913 10 Corning 1723 Although the present invention has been described with reference to certain embodiments, it should be ap¬ preciated that further modifications can be effected within the spirit ana scope of the invention as limited only by the appended claims.

Claims: What Is Claimed Is: 1. A sintered polycrystalline ceramic body comprising: magnesia-alumina spinel; said body having an in-line transmittance per 1.88 mm thickness in all wavelengths in the wavelength range from about 0.2 microns to about 0.4 microns of not less than the transmittance shown by line A in Fig. 2. 2. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has a flexural strength at 25°C of at least about 15000 psi. 3. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has a Knoop hardness of at least about 1350 kg mrrr 2 . 4. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has a tensile strength of at least about 12,000 psi. 5. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has an average grain size less than about 150 microns. 6. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has an average defect radius of less than about 0.1 microns. 7. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has a scatter at a wavelength of about 0.6 microns of less than about 9xl0 ~3 percent. 8. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body can be polished to a scratch-dig size of less than about 20-20. 9. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has sufficient chemical stability that there is substantially no solubility of said body in an acidic aqueous solution having a pH of between about 2 and 7. 10. A sintered polycrystalline body, as claimed in Claim 1, wherein: said body has sufficient thermal stability that there is substantially no degradation of said body upon exposure to temperatures of about 500°C. 11. A sintered polycrystalline body, as claimed in Claim 1, wherein: said polycrystalline body has an in-line transmit¬ tance per 1.88 mm thickness in all wavelengths in the wavelength range from 3 microns to 5 microns of not less than about 73 percent. 12. A sintered polycrystalline ceramic body, comprising: magnesia-alumina spinel; said body having a porosity of less than about 0.001 volume percent. 13. A sintered polycrystalline body, as claimed in Claim 12, wherein: said body has a flexural strength at 25°C of at least about 15000 psi. 14. A sintered polycrystalline body, as claimed in Claim 12, wherein: said body has a Knoop hardness of at least about 1350 kg mm ~ 2 . 15. A sintered polycrystalline ceramic body, as claimed in Claim 12, wherein: said body has a flexural strength at 25°C of at least abo ' ut 21000 psi. 16. A sintered polycrystalline body, as claimed in Claim 15, wherein: said body has a maximum strength such that a 3 inch diameter disk having a thickness of about 0.06 inches bursts when subjected to a pressure of more than about 25 psi. 17. A sintered polycrystalline body, as claimed in Claim 15, wherein: said body has a Knoop hardness of at least about 1350 kg mm- 2 . 18. A sintered polycrystalline ceramic body comprising: magnesia-alumina spinel; said body having an in-line transmittance per 1.88 mm thickness in all wavelengths in the wavelength range from about 0.2 microns to about 0.4 microns of not less than the transmittance shown by line B in Fig. 2. 19. A sintered, polycrystalline body, as claimed in Claim 18, wherein: said body has a flexural strength at 25°C of at least about 15000 psi; and said body has a Knoop hardness of at least about 1350 kg mm- 2 . 20. A sintered polycrystalline ceramic body, comprising: magnesia-alumina spinel; said body having an in-line transmittance per 1.88 mm thickness in all wavelengths from about 0.3 microns to about 0.8 microns of not less than about 85 percent; and said body retaining at least about 99 percent of its original transmissivity after 200 hours of exposure at a distance of about 15 cm to ultraviolet light of a wavelength of about 0.254 microns and an intensity of about 700 microwatts/cm 2 . 21. A sintered polycrystalline body, as claimed in Claim 20, wherein: said body has a flexural strength at 25°C of at least about 15000 psi; and said body has a Knoop hardness of at least about 1350 kg mm- . 22. A sintered polycrystalline ceramic body comprising: magnesia-alumina spinel; said body having an in-line transmittance per 1.88 mm thickness at some wavelength in the wavelength range from about 0.2 microns to about 0.3 microns of not less than about 72 percent. 23. The sintered polycrystalline body, as claimed in Claim 22, wherein: said body has an in-line transmittance of not less than about 86 percent at some wavelength within the wavelength range between about 0.2 microns and about 0.4 microns. 24. A body, comprising: a sintered polycrystalline ceramic; said body having an in-line transmittance per 1.88 mm thickness in all wavelengths from about 0.3 microns to about 0.8 microns of not less than about 85 * percent; said body having a Knoop hardness of at least about 1350 kg mm ~2 ; and said body having a flexural strength at 25°C of at least about 20000 psi. 25. A body, as claimed in Claim 24, wherein: said body comprises magnesia-alumina spinel. 26. A body, as claimed in Claim 24, wherein: said body has an in-line transmittance per 1.88 mm thickness in all wavelengths in the wavelength range from about 0.2 microns to about 0.4 microns of not less than the transmittance shown by Line A in Fig. 2. 27. * A body, as claimed in Claim 24, wherein: said body has a melting point above about 2000°C. 28. A body, as claimed in Claim 24, wherein: said body is substantially non-birefringent. 29. A process for producing a sintered polycrys¬ talline body comprising: providing a powder comprising magnesia-alumina spinel; producing a closed porosity body from said powder; and heating said closed porosity body to at least about 1400°C at elevated pressure of at least about 20,000 psi to reduce residual porosity. 30. A process, as claimed in Claim 29, wherein said providing step comprises: providing a high purity powder having less than about 50 ppm of oxides selected from the group consist«- ing of oxides of chromium, copper, iron, galium, man¬ ganese, lead, titanium, vanadium, and zinc, and com¬ binations thereof. 31. A process, as claimed in Claim 29, wherein said producing step comprises: hot pressing said powder at a temperature of more than about 1400°C and a pressure of more than about 2,000 psi. 32. A process, as claimed in Claim 29, wherein said producing step comprises: pressureless sintering said powder at a tempera¬ ture greater than about 1800°C and at a pressure less than about atmospheric pressure. 33. A process, as claimed in Claim 29, further comprising: reducing impurities content of said powder by heating to a temperature greater than about 1100°C and at a pressure less than about atmospheric pressure. 34. A process, as claimed in Claim 29, further comprising: maintaining said closed porosity body at a temper¬ ature of at least about 1000°C continuously from the completion of said step of producing said closed porosity body until initiating said step of heating of said closed porosity body. 35. A process, as claimed in Claim 29, wherein: said heating step comprises heating at a rate be¬ tween about 5°C per hour and abour 25°C per hour. 36. A process, as claimed in Claim 29, further comprising: maintaining said closed porosity body at a temper¬ ature of at least about 1400°C and a pressure of at least about 20,000 psi for a period of at least one- half hour. 37. A process, as claimed in Claim 29, further comprising: cooling said body, after said heating step, at a rate less than about 15°C per minute to a temperature of about 600°C. 38. A process for producing a sintered polycrys¬ talline body comprising: providing a powder comprising magnesia-alumina spinel; producing a closed porosity body from said powder; and sintering said closed porosity body at an elevated temperature and pressure for a time effective to produce a sintered body having a porosity less than about 0.001 volume percent. 39. A process, as claimed in Claim 38, wherein said step of producing a closed porosity comprises: hot pressing said powder at a temperature more than about 1400°C and a pressure of more than about 2,000 psi. 40. A process, as claimed in Claim 38, wherein said step of producing a closed porosity comprises: pressureless sintering said powder at a tempera¬ ture greater than about 1800°C and at a pressure less than about atmospheric pressure. 41. A process, as claimed in Claim 38, said step of sintering comprises: heating said closed porosity body to at least about 1400°C at elevated pressure of at least about 20,000 psi to reduce residual porosity. 42. A process, as claimed in Claim 38, wherein: said sintered body has a Knoop hardness of at least about 1350 kg irr 2 . 43. A process, as claimed in Claim 38, wherein: said sintered body has a flexural strength at 25°C of at least about 15,000 psi. 44. A sintered polycrystalline body produced by a process comprising: providing a powder comprising magnesia-alumina spinel; producing a closed porosity body from said powder; and heating said closed porosity body to at least about 1400°C at elevated pressure of at least about 20,000 psi to reduce residual porosity. 45. A sintered polycrystalline body, as claimed in Claim 44, wherein: said body has a flexural strength at 25°C of at least about 15,000 psi. 46. A sintered polycrystalline body, as claimed in Claim 44, wherein: said sintered body has a Knoop hardness of at least about 1350 kg mm -2 . 47. A sintered polycrystalline body, as claimed in Claim 44, wherein: said body has a grain size less than about 150 microns. 48. A sintered polycrystalline body, as claimed in Claim 44, wherein: said body has a tensile strength of at least about 12,000 psi. 49. A sintered polycrystalline body, as claimed in Claim 44, wherein: said body has a maximum strength such that a 3 inch diameter disk having a thickness of about 0.06 inches bursts when subjected to a pressure of more than about 25 psi. 50. A dome for a missile guidance system com¬ prising: a sintered polycrystalline body comprising magnesia-alumina spinel having a transmittance per 1.88 mm thickness at all wavelengths in the wavelength region between 0. microns and 0.5 microns cf at least about 82%, having a flexural strength at 25°C of at least about 20,000 psi and having a Knoop hardness of at least about 1350 kg mm -2 ; said body being formed in the shape of a convex shell. 51. A dome, as claimed in Claim 50, wherein: said body is formed in the shape of a sector of a spherical shell. 52. A dome, as claimed in Claim 50, wherein: said body has a transmittance per 1.88 mm thick¬ ness at all wavelengths in the wavelength region be¬ tween 0.5 microns and 1.0 microns of at least about 85%. 53. A dome, as claimed in Claim 50, wherein: said body has a transmittance per 1.88 mm thick¬ ness at all wavelengths in the wavelength region be¬ tween 3 microns and 4 microns cf at least about 81% and all wavelengths in the wavelength region between 4 microns and 5 microns of at least about 76%. 54. A dome for a missile guidance system produced by the process comprising: providing a powder comprising magnesia-alumina spinel; producing a closed porosity body from said powder; and heating said closed porosity body to at least about 1400°C at elevated pressure of at least about 20,000 psi to reduce residual porosity. 55. A missile launch tube window comprising: a transparent, sintered polycrystalline body com¬ prising magnesia-alumina spinel having a transmittance per 1.88 mm thickness at all wavelengths in the wavelength region between 0. microns and 0.5 microns of at least about 82%, having a flexural strength at 25°C of at least about 20,000 psi and having a Knoop hardness of at least about 1350 kg mm -2 ; said launch tube window being formed in the shape of a substantially flat disk. 56. A launch tube window, as claimed in Claim 55, wherein: said body has a transmittance per 1.88 mm thick¬ ness at all wavelengths in the wavelength range between 0.5 microns and 1.0 microns of at least about 85%. 57. A launch tube window, as claimed in Claim 55, wherein: said body has a transmittance per 1.88 mm thick¬ ness at all wavelengths in the wavelength range between 3.0 microns and 4.0 microns of at least about 81%, and at all wavelengths in the wavelength region between 4 microns and 5 microns of at least about 76%. 58. A launch tube window, as claimed in Claim 55, wherein: said window has a thickness such that said window ruptures upon exposure to a pressure of more than about 25 psi. 59. A missile launch tube window comprising: providing a powder comprising magnesia-alumina spinel; producing a closed porosity body from said powder; and heating said closed porosity body to at least about 1400°C at elevated pressure of at least about 20,000 psi to reduce residual porosity. 60. A guided missile comprising: a missile propulsion system for moving the missile in a controllable direction; an optical guidance system operably connected to said propulsion system for controlling said direction of said movement; a dome covering at least a portion of said optical guidance system, the dome comprising a sintered poly¬ crystalline body comprising magnesia-alumina spinel, having a transmittance per 1.88 mm thickness at all wavelengths in the wavelength region between 0.4 microns and 0.5 microns of at least about 82%, at all wavelengths in the wavelength range between 3.0 microns and 4.0 microns of at least about 81%, and at all wavelengths in the wavelength range between 4 microns and 5 microns of at least about 76%, having a flexural strength at 25°C of .at least about 20,000 psi and having a Knoop hardness of at least about 1350 kg mm" 2 . 61. A missile launch tube comprising: a tubular-shaped member having a sealable opening; a window attached to said tubular member in a position to seal said sealable opening, said window comprising a transparent, sintered polycrystalline body comprising magnesia-alumina spinel, having a transmit¬ tance per 1.88 mm thickness at all wavelengths in the wavelength region between 0.4 microns and 0.5 microns of at least about 82%, at all wavelengths in the wavelength range between 3.0 microns and 4.0 microns of at least about 81%, and at all wavelengths in the wavelength range between 4 microns and 5 microns of at least about 76%, having a flexural strength at 25°C of at least about 20,000 psi and having a Knoop hardness of at least about 1350 kg mm -2 .

Inventors: COUBROUGH LAWRENCE E, GREEN KENNETH EDWARD, HASTERT JAMES L, ROY DONALD W, TRUJILLO AURELIO, COUBROUGH, LAWRENCE, E., GREEN, KENNETH, EDWARD, HASTERT, JAMES, L., ROY, DONALD, W., TRUJILLO, AURELIO
Applicants: COORS PORCELAIN CO, COORS PORCELAIN COMPANY DBA COORS CERAMICS COMPANY
Application year: 1988
Main classification: C04B35
IPC codes: C04B35, H01Q1