Compositions, devices, and methods for destroying chemical warfare agents, independent of their chemical make-up, include (i) at least one reactive metal; (ii) at least one oxidizer; and (iii) a binder. In one embodiment, the self-sustaining reactive composition includes magnesium powder, iron oxide powder, potassium perchlorate powder, and silicone gel. In another embodiment, the self-sustaining reactive composition includes manganese powder, lithium perchlorate powder, lithium peroxide powder, and silicone gel. The reactive metal(s), oxidizer(s), binder, and their respective amounts, are selected such that, following ignition of the composition, the composition is capable of producing a solid mass of ash (wicking composition) that increases the surface area of the chemical agent material and provides a site for combustion and/or thermal degradation of the chemical agent to occur.

Compositions, devices, and methods for destroying chemical warfare agents, independent of their chemical make-up, include (i) at least one reactive metal; (ii) at least one oxidizer; and (iii) a binder. In one embodiment, the self-sustaining reactive composition includes magnesium powder, iron oxide powder, potassium perchlorate powder, and silicone gel. In another embodiment, the self-sustaining reactive composition includes manganese powder, lithium perchlorate powder, lithium peroxide powder, and silicone gel. The reactive metal(s), oxidizer(s), binder, and their respective amounts, are selected such that, following ignition of the composition, the composition is capable of producing a solid mass of ash (wicking composition) that increases the surface area of the chemical agent material and provides a site for combustion and/or thermal degradation of the chemical agent to occur.

A spark generating tube includes a single tube and a pyrotechnical mixture. The single tube only has a single layer of plastic material, such as ethylene vinyl acetate (EVA) and polyethylene. The pyrotechnical mixture has formed a thin layer in contact with the single layer of the single tube. The pyrotechnical contains an oxidizer, a reducing agent, a substance with low temperature of Tammann and an agent for lubricating and adhering, wherein the agent for lubricating and adhering is either talc or graphite, and the reducing agent can be an aluminum powder in microscale. During the process for manufacturing a spark generating tube, the mixture of the oxidizers and additives is formed separately from the reducing agent. The final mixture is obtained only in the single tube formed with an extruder. In this way, only a very small amount of pyrotechnic mixture is formed at any instant.

A spark generating tube includes a single tube and a pyrotechnical mixture. The single tube only has a single layer of plastic material, such as ethylene vinyl acetate (EVA) and polyethylene. The pyrotechnical mixture has formed a thin layer in contact with the single layer of the single tube. The pyrotechnical contains an oxidizer, a reducing agent, a substance with low temperature of Tammann and an agent for lubricating and adhering, wherein the agent for lubricating and adhering is either talc or graphite, and the reducing agent can be an aluminum powder in microscale. During the process for manufacturing a spark generating tube, the mixture of the oxidizers and additives is formed separately from the reducing agent. The final mixture is obtained only in the single tube formed with an extruder. In this way, only a very small amount of pyrotechnic mixture is formed at any instant.

The present invention relates to propellant composition free from Activated Copper Chromite (ACR) having a high burn rate comprising only 0.1-0.25% of Iron oxide (Fe.sub.2O.sub.3) as burn rate catalyst. Particularly, it relates to the use of propellant composition for use in pyrogen igniters for large rocket motors. The propellant composition is devoid of Activated Copper Chromite catalyst, achieves a high burn rate, fulfils requirements of physical, mechanical and ballistic properties, has stable combustion and ensures reliable performance of the pyrogen igniters of large Rocket Motors.

The present invention relates to propellant composition free from Activated Copper Chromite (ACR) having a high burn rate comprising only 0.1-0.25% of Iron oxide (Fe.sub.2O.sub.3) as burn rate catalyst. Particularly, it relates to the use of propellant composition for use in pyrogen igniters for large rocket motors. The propellant composition is devoid of Activated Copper Chromite catalyst, achieves a high burn rate, fulfils requirements of physical, mechanical and ballistic properties, has stable combustion and ensures reliable performance of the pyrogen igniters of large Rocket Motors.