Abstract: Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.

Abstract: Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.

Abstract: A transducer assembly configured to convert a pyrotechnic initiation to an electrical signal may comprise a magnet, a hollow tube, and a conductive element. The hollow tube may be wrapped around the magnet in the shape of a coil. The hollow tube may be at least partially filled with a thermite. The conductive element may be coupled to an outlet of the hollow tube. The conductive element may seal the outlet of the hollow tube.

Abstract: An energy conversion system may comprise a substrate including a first conductive trace and a second conductive trace electrically isolated from the first conductive trace. A housing may be coupled to the substrate. An ignition compound may be located in the housing. A solder may be thermally coupled to the ignition compound such that ignition of the ignition compound melts the solder. The housing may be configured to output the solder onto the first conductive trace and the second conductive trace.

Abstract: An obscurant-emitting composition may comprise an oxidizer comprising a cation comprising at least one of an alkali metal or an alkaline earth metal, and an anion comprising at least one of nitrate, chlorate, bromate, iodate, perchlorate, periodate, or chlorite; a fuel; and a hydrated salt composition, wherein the obscurant-emitting composition comprises between 0.001% and 8% by weight hydrated salt composition.

Abstract: An energy conversion system may comprise a connector defining a first chamber and a second chamber. An ignition compound may be located in the first chamber. The ignition compound may comprise a material that produces a conductive combustion product. A first electrode may be coupled to the connector and located in the second chamber. A second electrode may be coupled to the connector and located in the second chamber. The second electrode may be electrically isolated from the first electrode.

Abstract: Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.

Abstract: An energy conversion system may comprise a substrate including a first conductive trace and a second conductive trace electrically isolated from the first conductive trace. A housing may be coupled to the substrate. An ignition compound may be located in the housing. A solder may be thermally coupled to the ignition compound such that ignition of the ignition compound melts the solder. The housing may be configured to output the solder onto the first conductive trace and the second conductive trace.

Abstract: An energy conversion system may comprise a connector defining a first chamber and a second chamber. An ignition compound may be located in the first chamber. The ignition compound may comprise a material that produces a conductive combustion product. A first electrode may be coupled to the connector and located in the second chamber. A second electrode may be coupled to the connector and located in the second chamber. The second electrode may be electrically isolated from the first electrode.

Abstract: A transducer assembly configured to convert a pyrotechnic initiation to an electrical signal may comprise a magnet, a hollow tube, and a conductive element. The hollow tube may be wrapped around the magnet in the shape of a coil. The hollow tube may be at least partially filled with a thermite. The conductive element may be coupled to an outlet of the hollow tube. The conductive element may seal the outlet of the hollow tube.

Abstract: A combustible solid propellant composition is disclosed that includes an oxidizer of the reaction product under vacuum of potassium periodate and isocyanate, a polymer binder, a plasticizer, and a fuel.

Abstract: An obscurant-emitting composition may comprise an oxidizer comprising a cation comprising at least one of an alkali metal or an alkaline earth metal, and an anion comprising at least one of nitrate, chlorate, bromate, iodate, perchlorate, periodate, or chlorite; a fuel; and a hydrated salt composition, wherein the obscurant-emitting composition comprises between 0.001% and 8% by weight hydrated salt composition.

Abstract: An obscurant-emitting composition may comprise an oxidizer comprising a cation comprising at least one of an alkali metal or an alkaline earth metal, and an anion comprising at least one of nitrate, chlorate, bromate, iodate, perchlorate, periodate, or chlorite; a fuel; and a hydrated salt composition, wherein the obscurant-emitting composition comprises between 0.001% and 8% by weight hydrated salt composition.

Abstract: A solid rocket motor propellant grain arrangement may comprise a case, a propellant grain disposed within the case, and an integrated rocket motor aging sensor disposed outward from the propellant grain, wherein the integrated rocket motor aging sensor is configured to measure data corresponding to a plurality of distinct locations of the propellant grain. The integrated rocket motor aging sensor may comprise a resistive screen matrix (RSM).

Abstract: A combustible solid propellant composition is disclosed that includes an oxidizer of the reaction product under vacuum of potassium periodate and isocyanate, a polymer binder, a plasticizer, and a fuel.

Abstract: A combustible solid propellant composition is disclosed that includes an oxidizer of the reaction product under vacuum of potassium periodate and isocyanate, a polymer binder, a plasticizer, and a fuel.

Abstract: A propellant may comprise a primary oxidizer having a density of greater than or equal to 2.7 grams per cubic centimeter; a secondary oxidizer having a density of less than 2.7 grams per cubic centimeter; and/or a fuel comprising at least one of zirconium metal, tin metal, titanium metal, aluminum metal, magnesium metal, or a metal hydride. The propellant may be substantially free of lead.

Abstract: A combustible aerosol composition is disclosed including an oxidizer including potassium bromate, a fuel including potassium cyanurate, and a hydrated mineral composition including potassium hydromagnesite.

Abstract: An obscurant-emitting composition may comprise an oxidizer comprising a cation comprising at least one of an alkali metal or an alkaline earth metal, and an anion comprising at least one of nitrate, chlorate, bromate, iodate, perchlorate, periodate, or chlorite; a fuel; and a hydrated salt composition, wherein the obscurant-emitting composition comprises between 0.001% and 8% by weight hydrated salt composition.

Abstract: A combustible solid propellant composition is disclosed that includes an oxidizer of the reaction product under vacuum of potassium periodate and isocyanate, a polymer binder, a plasticizer, and a fuel.