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An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and decomposition products of the ionic sa

An apparatus and method are provided for decomposition of a propellant. The propellant includes an ionic salt and an additional fuel. Means are provided for decomposing a major portion of the ionic salt. Means are provided for combusting the additional fuel and decomposition products of the ionic salt.

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1. An apparatus comprising:a source of HAN-based propellant; a reactor for dissociating a portion of the HAN in the propellant; and a combustor having an upstream end and a downstream end for combusting products of the dissociation with an additional fuel in the propellant, wherein the reactor is lo

1. An apparatus comprising:a source of HAN-based propellant; a reactor for dissociating a portion of the HAN in the propellant; and a combustor having an upstream end and a downstream end for combusting products of the dissociation with an additional fuel in the propellant, wherein the reactor is located aft of said downstream end. 2. The apparatus of claim 1 wherein:the propellant comprises a mixture of said HAN, said additional fuel comprising alcohol, and water. 3. The apparatus of claim 1 wherein:the source comprises a tank containing the propellant and an automatically-controlled valve governing flow between the tank and the reactor. 4. The apparatus of claim 1 wherein:the reactor comprises a circuitous heated passageway. 5. The apparatus of claim 1 further comprising:means for feeding back heat from the combustor to the reactor. 6. A method for operating a combustion system using a HAN-based propellant, said combustion system having a combustor having an upstream end and a downstream end, comprising:introducing the propellant to a reactor located substantially aft of said downstream end; decomposing the propellant in the reactor to dissociate at least a portion of the HAN in the propellant; directing an output of the reactor to the combustor; and combusting said output of the reactor in the combustor so as to combust dissociation products of said dissociated HAN with unreacted fuel in the propellant. 7. The method of claim 6 wherein:the combusting releases at least 60% of an energy of the propellant. 8. The method of claim 6 further comprising:feeding back heat from the combustor to the reactor in an amount effective to initiate said decomposing. 9. An apparatus comprising:a source of propellant said propellant comprising an ionic salt and an additional fuel; means for decomposing a portion of said ionic salt; and means for combusting additional fuel and decomposition products of said portion, said means for combustion having an upstream end and a downstream end and said means for decomposing located substantially aft of said downstream end. 10. The apparatus of claim 9 wherein:the propellant comprises a mixture of HAN, alcohol, and at least 5% water. 11. The apparatus of claim 9 wherein:the ionic salt is an inorganic ionic salt and the additional fuel includes an organic ionic salt. 12. The apparatus of claim 1 wherein:the reactor comprises a passageway; said propellant flowing along the passageway is decomposed at least in part by heat of exhaust products to produce a decomposed output; and the decomposed output is ignited to produce said exhaust products. 13. The apparatus of claim 12 wherein:the passageway is helical. 14. The apparatus of claim 1 wherein:the reactor lacks a catalyst, the dissociating being noncatalytic thermal dissociating. 15. The apparatus of claim 1 wherein:the propellant is contained in a single tank. 16. The apparatus of claim 1 wherein:the reactor is formed in an upstream portion of a vessel; the combustor is formed in a downstream portion of the vessel; and the combustor has a convergent/divergent nozzle. 17. An apparatus comprising:a source of propellant, said propellant comprising an ionic salt and an additional fuel; a combustor having an upstream end and a downstream end and discharging combustion products; and a heat exchanger located substantially aft of said downstream end and transferring heat from the combustion products to the propellant to thermally decompose a portion of said ionic salt, the combustor combusting decomposition products of said portion with said additional fuel. 18. The apparatus of claim 1 wherein:the reactor comprises a heated passageway. 19. The apparatus of claim 18 wherein:all the propellant passes through the heated passageway to receive heat to promote the dissociating. 20. The apparatus of claim 18 wherein:the heated passageway encircles a combustion products flow path portion. 21. The apparatus of claim 18 being a thruster, combustion products of the combustion exiting a nozzle to produce thrust.22. The apparatus of claim 18 further comprising:an annular space between a combustion chamber outer wall of the combustor and a combustion chamber inner wall for passing the propellant; and an igniter positioned to ignite the propellant reaching an upstream end of the combustion chamber, to discharge the combusting decomposition products downstream through an interior of the chamber inner wall. 23. The apparatus of claim 1 wherein said portion is a major portion.24. The apparatus of claim 4 wherein said portion is a major portion.25. The method of claim 6 wherein said portion is a major portion.26. The apparatus of claim 9 wherein said portion is a major portion.27. An apparatus comprising:a source of HAN-based propellant; a reactor for dissociating a portion of the HAN in the propellant; a combustor having an upstream end and a downstream end for combusting products of the dissociation with an additional fuel in the propellant; and a nozzle downstream of the combustor, wherein the reactor is located between the combustion chamber and a throat of the nozzle. 28. The apparatus of claim 27 wherein said portion is a major portion.