A missile including an upper stage and at least one lower stage is provided. The upper stage includes a primary flight computer configured to control a flight of the upper stage along a missile flight path such that, for example, it reaches a predetermined target. The lower stage is mounted to the upper stage and includes a propellant for initially propelling the upper stage along the missile flight path. The lower stage is configured to be jettisoned from the upper stage when the propellant is spent. The lower stage includes a secondary flight computer configured to receive data from the primary flight computer prior to the propellant of the lower stage being spent, and to control a flight of the lower stage along a jettisoned stage flight path of the jettisoned lower stage such that, for example, the jettisoned lower stage glides to a predetermined safe landing zone.

Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

A pipeline separation device for liquid-propellant rocket comprising a first flange pipeline, a second flange pipeline, a clamping unit, a push-and-pull unit and an actuation unit. The first flange pipeline and the second flange pipeline dock along a first direction, a docking end surface docking with each other is limited by the clamping unit, and end surfaces opposite to each other after docking of the first flange pipeline and the second flange pipeline are respectively used for connecting with different medium pipelines; the actuation unit is used for pushing the push-and-pull unit so that the clamping unit relieves limit on the docking end surface. Being provided with a clamping unit and an actuation unit, the pipeline separation device for liquid-propellant rocket is capable of quickly pushing the clamping unit out when the actuation unit works, thereby relieving the limit on the first flange pipeline and the second flange pipeline.

A pipeline separation device for liquid-propellant rocket comprising a first flange pipeline, a second flange pipeline, a clamping unit, a push-and-pull unit and an actuation unit. The first flange pipeline and the second flange pipeline dock along a first direction, a docking end surface docking with each other is limited by the clamping unit, and end surfaces opposite to each other after docking of the first flange pipeline and the second flange pipeline are respectively used for connecting with different medium pipelines; the actuation unit is used for pushing the push-and-pull unit so that the clamping unit relieves limit on the docking end surface. Being provided with a clamping unit and an actuation unit, the pipeline separation device for liquid-propellant rocket is capable of quickly pushing the clamping unit out when the actuation unit works, thereby relieving the limit on the first flange pipeline and the second flange pipeline.

Embodiments of a system and method for carrying an aeronautical or launch vehicle to altitude for release to flight are disclosed. The system may comprise a multiplicity of mounting elements configured to be affixed to a carrier aircraft in distributed fashion along a mounting axis. Each mounting element may include a cradle and a retention strap. Each retention strap may be suspendedly attached to a respective said cradle, and actuatable from a retention configuration to a release configuration. The retention configuration may enable the retention straps to clampingly secure the vehicle to the respective cradles. The actuation of the retention straps from the retention configuration to the release configuration may disable the clamping securement and thereby release the vehicle to drop away from the cradles. For one or more of the retention straps, the actuation may be by way of detonating at least one corresponding pyrotechnic fastener.

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.

A separation device assembly with efficiency that allows for multi-fault-tolerance. The separation device assembly comprising an inflation device that applies force to a shear plate assembly which in turn applies focused force to a frangible portion. The assembly further comprising a means for limiting excess movement after fracture so that residual energy from the inflation device is applied to non-fractured portions of the assembly.

A separation device assembly with efficiency that allows for multi-fault-tolerance. The separation device assembly comprising an inflation device that applies force to a shear plate assembly which in turn applies focused force to a frangible portion. The assembly further comprising a means for limiting excess movement after fracture so that residual energy from the inflation device is applied to non-fractured portions of the assembly.

A sabot including a first casing petal having at least one coupling feature and at least one disengagement feature; a second casing petal having at least one coupling feature and at least one disengagement feature; and a cap insertable within a forward receiver formed by coupling the first casing petal with the second casing petal, wherein the first casing petal and the second casing petal and the cap are configured to cooperatively attach to a forward assembly of a missile and cooperatively detach from the forward assembly of the missile responsive to a missile launch.