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A deliming and sanitizing process which includes injecting a liquid delimer composition into a pre-mix reservoir, and substantially simultaneously injecting a second liquid sanitizing composition into a pre-mix reservoir wherein the liquid delimer composition and the liquid sanitizing composition fo

A deliming and sanitizing process which includes injecting a liquid delimer composition into a pre-mix reservoir, and substantially simultaneously injecting a second liquid sanitizing composition into a pre-mix reservoir wherein the liquid delimer composition and the liquid sanitizing composition form a mixture which is then transported from the pre-mix reservoir into a water circulation system such as in an automatic ice machine for cleaning and sanitizing the system.

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A deliming and sanitizing process which includes injecting a liquid delimer composition into a pre-mix reservoir, and substantially simultaneously injecting a second liquid sanitizing composition into a pre-mix reservoir wherein the liquid delimer composition and the liquid sanitizing composition fo

A deliming and sanitizing process which includes injecting a liquid delimer composition into a pre-mix reservoir, and substantially simultaneously injecting a second liquid sanitizing composition into a pre-mix reservoir wherein the liquid delimer composition and the liquid sanitizing composition form a mixture which is then transported from the pre-mix reservoir into a water circulation system such as in an automatic ice machine for cleaning and sanitizing the system. embly coupled to the case, the nozzle assembly comprising a nozzle passageway and a throat-barrier member for obstructing the nozzle passageway; a primary propellant grain contained in the case and having an auto-ignition temperature at which the primary propellant grain auto-ignites, the primary propellant grain formulated to undergo thermal expansion in response to being heated to temperatures below the auto-ignition temperature thereof so as to fill free volume, if any, inside the case and to apply an internal pressure to the case that is less than the internal pressure burst level; an igniter assembly positioned within the nozzle assembly and operational between an inactive state, in which the igniter assembly is situated in the nozzle passageway and the throat-barrier member obstructs the nozzle passageway, and an activated state, in which the igniter assembly ignites the primary propellant grain and the nozzle passageway is substantially unobstructed by the throat-barrier member to permit flow through the nozzle passageway; and an insensitive munitions charge located inside the case and having an insensitive munitions auto-ignition temperature at which the insensitive munitions charge auto-ignites to release gas, the insensitive munitions auto-ignition temperature being below the primary propellant grain auto-ignition temperature, the insensitive munitions charge being present in an effective amount such that the gas released by auto-ignition of the insensitive munitions charge combines with the internal pressure applied by the thermal expansion of the primary propellant grain when the igniter assembly is in the inactive state to raise the internal pressure inside the case above the internal pressure burst level for rupturing the case before the primary propellant grain reaches the auto-ignition temperature thereof. 3. The rocket motor of claim 2, further comprising a rubber insulator comprising a radially extending portion and an axial extension, the radially extending portion of the rubber insulator being situated between the primary propellant grain and the aft assembly, the axial extension being situated between the primary propellant grain and the cylindrical region of the case. 4. The rocket motor of claim 3, wherein the axial extension of the rubber insulator is spaced radially from the cylindrical region of the case to form a cylindrical void area therebetween. 5. The rocket motor of claim 2, wherein the propellant grain thermal expansion temperature range is selected to fill the free volume of the case with the primary propellant grain at about 66° C. 6. The rocket motor of claim 2, wherein the primary propellant grain auto-ignition temperature is about 238° C. 7. The rocket motor of claim 2, wherein the throat-barrier member comprises an erosive nozzle piece. 8. The rocket motor of claim 2, wherein the insensitive munitions auto-ignition temperature is at least about 56° C. below the auto-ignition temperature of the primary propellant grain. 9. The rocket motor of claim 2, wherein internal pressure of the gas released by auto-ignition of the insensitive munitions charge is not more than 25 percent of the internal pressure applied by the thermal expansion of the primary propellant grain. 10. The rocket motor of claim 2, wherein the insensitive munitions charge is situated between the aft closure member and the primary propellant grain. 11. The rocket motor of claim 2, further comprising a rubber insulator comprising a radially extending portion situated between the primary propellant grain and the aft assembly, wherein the insensitive munitions charge is situated in contact with the radially extending portion of the rubber insulator. 12. The rocket motor of claim 2, further comprising a secondary insensitive munitions charge positioned in close proximity to an aft surface of the primary propellant grain, the second insensitive munitions charge having an auto-ignition temperature at which the second insen