Abstract: An explosive cord is disclosed. In various embodiments, the explosive cord includes a tube having a tube inner surface and a tube outer surface, the tube inner surface defining a hollow interior that extends along a length of the tube; a carrier fiber disposed within the hollow interior of the tube, the carrier fiber having a carrier fiber exposed surface area; and a reactive material disposed on the carrier fiber exposed surface area.

Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. The force may be applied by moving a liquid into the perforation. This process may be performed over time to determine a lifespan 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: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying, via a gas, a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and measuring a pressure of the gas. This process may be performed over time to determine a lifespan of the propellant grain.

Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. This process may be performed over time to determine a lifespan of the propellant grain.

Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. This process may be performed over time to determine a lifespan 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 explosive cord is disclosed. In various embodiments, the explosive cord includes a tube having a tube inner surface and a tube outer surface, the tube inner surface defining a hollow interior that extends along a length of the tube; a carrier fiber disposed within the hollow interior of the tube, the carrier fiber having a carrier fiber exposed surface area; and a reactive material disposed on the carrier fiber exposed surface area.

Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. The force may be applied by moving a liquid into the perforation. This process may be performed over time to determine a lifespan of the propellant grain.

Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. This process may be performed over time to determine a lifespan of the propellant grain.

Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and calculating a value of the mechanical property of the solid rocket motor propellant grain based on the deformation. This process may be performed over time to determine a lifespan of the propellant grain.

Abstract: A method for non-destructively determining a mechanical property of a solid rocket motor propellant grain may comprise applying, via a gas, a force to a surface of the solid rocket motor propellant grain, wherein a deformation is formed on the surface of the solid rocket motor propellant grain in response to the applying, and measuring a pressure of the gas. This process may be performed over time to determine a lifespan of the propellant grain.

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).