An actuation device for ejecting a removable part of a missile includes a pyrotechnic actuator having a pyrotechnic charge configured to generate an overpressure and a piston configured to act on the removable part of the missile, at least one retaining rod, and at least one thermal insulation element configured to thermally insulate at least the pyrotechnic charge. The pyrotechnic actuator is configured to break the retaining rod.

A mitigation control system, for performing an active hazard mitigation method, is arranged in an environment containing an energetic material and includes an abnormal temperature sensor for detecting an abnormal temperature of the environment, a power source that is mechanically actuated by the abnormal temperature sensor when the abnormal temperature exceeds a predetermined abnormal temperature threshold, a mitigation controller that is actuated by the power source, and a plurality of local temperature sensors that are communicatively coupled to the mitigation controller and are arranged for detecting critical temperatures in specific regions of the environment. The mitigation controller executes a mitigation action when one of the critical temperatures exceeds a predetermined critical temperature threshold for the corresponding specific region.

A mitigation control system, for performing an active hazard mitigation method, is arranged in an environment containing an energetic material and includes an abnormal temperature sensor for detecting an abnormal temperature of the environment, a power source that is mechanically actuated by the abnormal temperature sensor when the abnormal temperature exceeds a predetermined abnormal temperature threshold, a mitigation controller that is actuated by the power source, and a plurality of local temperature sensors that are communicatively coupled to the mitigation controller and are arranged for detecting critical temperatures in specific regions of the environment. The mitigation controller executes a mitigation action when one of the critical temperatures exceeds a predetermined critical temperature threshold for the corresponding specific region.

A separation device includes: an outer case; a pillar-shaped separation member including an engaging portion; a support member including a swinging portion and an engageable portion, the swinging portion being swingably supported by the outer case, the engageable portion supporting the separation member; an inner case including a fitting hole restricting swinging of the support member; and an operation-enabling element, which supports the inner case and which is fusion-cut when an electric current is applied thereto. When the operation-enabling element is fusion-cut, the inner case is displaced, such that: the engageable portion of the support member detaches from the fitting hole; the swinging portion swings; and the engageable portion moves away from the engaging portion to release the separation member.

A separation device includes: an outer case; a pillar-shaped separation member including an engaging portion; a support member including a swinging portion and an engageable portion, the swinging portion being swingably supported by the outer case, the engageable portion supporting the separation member; an inner case including a fitting hole restricting swinging of the support member; and an operation-enabling element, which supports the inner case and which is fusion-cut when an electric current is applied thereto. When the operation-enabling element is fusion-cut, the inner case is displaced, such that: the engageable portion of the support member detaches from the fitting hole; the swinging portion swings; and the engageable portion moves away from the engaging portion to release the separation member.

The invention relates to a device and a method for the connection and linear separation of two elements, such as the two stages of a spacecraft, consisting in using a tube containing a pyrogenic-type material and a glue arranged around the tube, particularly in contact with the elements. The pyrotechnic triggering of the pyrogenic material causes heating and the melting or carbonisation of the glue and the separation of the two elements.

A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.

A missile or other flight vehicle has a stage separation mechanism for separating a downstream stage from an upstream portion of the missile. The mechanism includes one or more holes in fluid communication with a cavity between the upstream and downstream portions of the missile. The holes are located downstream of one or more shocks produced by one or more local variations in the outer surface shape of the missile. The one or more local variations in outer surface shapes produce the one or more shocks as the missile is flown at supersonic speeds. These shock(s) produce downstream pressure rises, and these pressure increases are communicated to the cavity by the hole(s). The increased pressure in the cavity provides a mechanism for separating the downstream stage from the upstream portion of the missile, after release of a mechanical coupling between the upstream portion and downstream stage.

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.

A networked electronic ordnance system is provided. The system includes a first plurality of pyrotechnic devices connected to a first network bus. The system further includes a first bus controller connected to the first network bus. The system further includes a second plurality of pyrotechnic devices connected to a second network bus. The system further includes a second bus controller connected to the second network bus. The system further includes a bus interface circuit connected to the first bus controller by a first electrical connection and connected to the second bus controller by a second electrical connection.