A venting device for a projectile includes a first part comprising a body containing an explosive charge and a second part comprising an actuating element for triggering the explosive charge, the first and second parts forming an assembly able to confine the explosive charge when they are connected, the venting device comprising: a sealing means configured to render the projectile gastight and fluidtight when the first and second parts are connected; an opening means able to allow the projectile to open, the opening means being able to be triggered when the internal pressure in the projectile is higher than or equal to a given pressure threshold; a pushing means able to enlarge the opening of the projectile once the opening means has been triggered.

Embodiments described herein include layered mesh containers and methods for using the containers to safely transport and dispose of airbag inflators having ammonium-nitrate-based propellant. For example, a container with at least two single-layer sidewalls is provided that can hold multiple airbag inflators and withstand up to 4 moles of matter being deployed from an inflator having ammonium-nitrate-based propellant. The container can contain the inflator and any shrapnel associated with the explosion while also venting gases expelled as a result of the explosion. Various container designs are provided, along with methods for using these containers.

Embodiments described herein include layered mesh containers and methods for using the containers to safely transport and dispose of airbag inflators having ammonium-nitrate-based propellant. For example, a container with at least two single-layer sidewalls is provided that can hold multiple airbag inflators and withstand up to 4 moles of matter being deployed from an inflator having ammonium-nitrate-based propellant. The container can contain the inflator and any shrapnel associated with the explosion while also venting gases expelled as a result of the explosion. Various container designs are provided, along with methods for using these containers.

Multistage thermal trigger devices disclosed herein may include a first stage and a second stage, wherein the first stage activates at a first temperature, and wherein the second stage activates at a second temperature. The first stage activates an arming assembly so that the second stage is armed. The second stage may then activate the output of the multistage thermal trigger device, via the arming assembly, when the second temperature is reached. An autoignition material (AIM) capsule is also disclosed herein. The AIM capsule may be deployed in connection with the disclosed multistage thermal trigger devices.

An electronic thermally-initiated venting system (ETIVS) for rocket motors includes at least one linear-shaped charge attached to a rocket motor housing. At least one exploding foil initiator (EFI) is attached to the linear-shaped charge. At least one electronic thermally-initiated venting system circuit is electrically-connected to the EFI. The EFI is configured to auto-fire when the electronic thermally-initiated venting system circuit relays a current pulse through the EFI. The linear-shaped charge is configured to initiate when the current pulse is relayed through the EFI.

A shape charge venting apparatus and method for venting gases generated during deflagration. The venting apparatus and method including vent grooves inside the shape charge providing a pathway for deflagration gases to escape the shape charge. The venting apparatus and method also may include using a retainer ring in addition to the vent groove in order to hold the components of the shape charge in place. The venting of the gases during deflagration facilitates pressure relief within the shape charge and increases safety from accidental detonation during a fire.

A shape charge venting apparatus and method for venting gases generated during deflagration. The venting apparatus and method including vent grooves inside the shape charge providing a pathway for deflagration gases to escape the shape charge. The venting apparatus and method also may include using a retainer ring in addition to the vent groove in order to hold the components of the shape charge in place. The venting of the gases during deflagration facilitates pressure relief within the shape charge and increases safety from accidental detonation during a fire.

Embodiments are directed to a shock mitigation device including a hollow fuze well having an inner surface and an outer surface. A plurality of vents are axially spaced at equal distance about the outer surface. A shock dampening liner is affixed to the inner surface. A shock dampening ring is concentric about the hollow fuze well.

Embodiments are directed to a shock mitigation device including a hollow fuze well having an inner surface and an outer surface. A plurality of vents are axially spaced at equal distance about the outer surface. A shock dampening liner is affixed to the inner surface. A shock dampening ring is concentric about the hollow fuze well.

A thermally initiated variable venting system may comprise a first linear shape charge (LSC) coupled to a first sensor and a second LSC coupled to a second sensor. An upper apex of the second LSC may be disposed within a lower apex of the first LSC. The output of the system may vary depending on whether the event is fast cook-off (FCO) or slow cook-off (SCO).