Highly soluble, non-hazardous hydroxylammonium salt solutions for use in hybrid rocket motors
First Claim
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1. A process for increasing the thrust of a rocket motor comprising a primary combustion chamber, a solid propellant grain within said primary chamber which generates combustion gas when ignited, a secondary combustion chamber aft of said primary chamber, and a passage connecting said primary and secondary chambers for conducting said combustion gas from said primary chamber to said secondary chamber, said process comprising the steps of:
- (a) providing a supply of an aqueous solution comprising from 50% to 90% by weight of a hydroxylammonium salt selected from the group consisting of hydroxylammonium nitrate and hydroxylammonium perchlorate; and
(b) contacting said combustion gas with said solution substantially within one of said passage and said secondary chamber at selected times, thereby reacting said combustion gas and said solution in said secondary chamber to increase thrust during said selected times.
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Abstract
Non-hazardous, highly soluble hydroxylammonium salt solutions are disclosed. These solutions have utility as liquid oxidizers in solid/liquid hybrid rocket motors.
33 Citations
3 Claims
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1. A process for increasing the thrust of a rocket motor comprising a primary combustion chamber, a solid propellant grain within said primary chamber which generates combustion gas when ignited, a secondary combustion chamber aft of said primary chamber, and a passage connecting said primary and secondary chambers for conducting said combustion gas from said primary chamber to said secondary chamber, said process comprising the steps of:
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(a) providing a supply of an aqueous solution comprising from 50% to 90% by weight of a hydroxylammonium salt selected from the group consisting of hydroxylammonium nitrate and hydroxylammonium perchlorate; and (b) contacting said combustion gas with said solution substantially within one of said passage and said secondary chamber at selected times, thereby reacting said combustion gas and said solution in said secondary chamber to increase thrust during said selected times. - View Dependent Claims (2, 3)
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Specification
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Current AssigneeAlliant Techsystems Incorporated (Northrop Grumman Corporation)
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Original AssigneeThiokol Corporation (Howmet Aerospace, Inc.)
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InventorsBiddle, Richard A., Sutton, Ernest S.
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Primary Examiner(s)Miller, Edward A.
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Application NumberUS06/390,570Time in Patent Office1,114 DaysField of Search60/219, 60/220, 60/251, 60/254, 60/207, 149/45, 149/75US Class Current60/207CPC Class CodesC06B 47/02 the components comprising a...C06D 5/00 Generation of pressure gas,...
