A flow deflector for an aerial vehicle system has a flow deflector body, a clip arranged in an interior of the flow deflector body, and a spring within the clip. The flow deflector body includes a first portion at a forward end shaped to engage a surface of an aerial vehicle body and a second portion at an aft end shaped to engage a surface of a booster engine. The flow deflector body can include a plurality of body segments arranged to form the flow deflector body. The clip may be configured to fit around and engage a portion of an aft flange of the aerial vehicle body. The spring can be preloaded and arranged to press on the aft flange when the clip engages the portion of the aft flange.

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.

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 bolt catcher and extractor for use with a separation nut and an attaching preloaded bolt that secure a payload to a launch vehicle or spacecraft. The bolt catcher extracts the attaching bolt from the separation nut, pulls it clear of the interface between the launch vehicle or spacecraft and the released payload, and captures it within the bolt catcher housing. The released bolt may have kinetic energy due to the strain energy stored by the pre-release bolt preload. The bolt catcher may have a magnetic eddy current damper that controls the bolt velocity during bolt extraction and dissipates the bolt kinetic energy as heat. The bolt may be magnetically non-impact captured within the bolt catcher. Bolt momentum at the end of the bolt extraction is less than 2% of that of bolt catchers of the prior art. Shock to the released payload or deployable equipment is near zero.

A system for separating composites of a space launch vehicle, comprising non-pyrotechnic separating modules distributed between the composites to be separated and a device for activating the separation modules, which can generate the simultaneous activation of all of the separating modules. The activation device consists of a source of compressed gas, the outlet of which is connected to each separation module.

A system for separating composites of a space launch vehicle, comprising non-pyrotechnic separating modules distributed between the composites to be separated and a device for activating the separation modules, which can generate the simultaneous activation of all of the separating modules. The activation device consists of a source of compressed gas, the outlet of which is connected to each separation module.

An assembly and method for assembling a projectile with a compact low friction high temperature shaft seal is provided. The assembly includes an outer shell, a rotating shaft inside the outer shell, and a seal attached to the rotating shaft. The rotating shaft can rotate independently of the outer shell. The seal can seal a gap between the outer shell and the rotating shaft.

Rocket armament launchable from a tubular launcher with an outside launcher non-ignition securing and motor separation during flight and a method to prevent the ignition of the armaments rocket even in the event of actuation of the armaments pyrotechnic assembly, which normally serves to eject the armament from the launcher and to ignite its rocket motor, wherein the armament comprises a gas dispersion assembly, which when the armament is not encased in the tubular launcher, prevents the ignition of the rocket motor even if the armaments pyrotechnic assembly is actuated; and a cutting and separation assembly that is actuated by the pressure of the rocket motor gases for mechanically cutting a structural connection between the rocket motor and the armaments effective payload and separate them during their flight.

Rocket armament launchable from a tubular launcher with an outside launcher non-ignition securing and motor separation during flight and a method to prevent the ignition of the armaments rocket even in the event of actuation of the armaments pyrotechnic assembly, which normally serves to eject the armament from the launcher and to ignite its rocket motor, wherein the armament comprises a gas dispersion assembly, which when the armament is not encased in the tubular launcher, prevents the ignition of the rocket motor even if the armaments pyrotechnic assembly is actuated; and a cutting and separation assembly that is actuated by the pressure of the rocket motor gases for mechanically cutting a structural connection between the rocket motor and the armaments effective payload and separate them during their flight.