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.

An aerial vehicle includes a body and an antenna assembly mounted to the body. The antenna assembly includes a fairing component comprising a hollow body, a conductive coating formed on at least an inner surface of the fairing component, a plurality of antenna elements formed in the conductive coating, each antenna element including a first slot line defining a first transmission line and a second slot line defining a second transmission line, an insulator sleeve disposed within the fairing component, wherein an outer surface of the insulator sleeve at least substantially matches an inner surface of the fairing component, and a plurality of cable assemblies operably coupled to the plurality of antenna elements, wherein each cable assembly is coupled to a respective antenna element.

A composite material manufacturing method includes: laminating a first sheet (210) including a first slurry (214) and a third sheet (230) including a third slurry (234); and heating the first sheet (210) and the third sheet (230) that are laminated to a temperature of transforming to ceramics by pyrolysis to form an intermediate body (300). The manufacturing method further includes impregnating the intermediate body (300) with a slurry and heating at a temperature lower than a temperature of transforming to ceramics by pyrolysis.

A radar-absorbing material projectile system including a projectile with an outer layer of radar-absorbing material (RAM). A carrier or armature is disposed around the projectile, protecting the layer of RAM during the firing sequence. In some embodiments the carrier is a discarding carrier which falls away after firing, rendering the projectile low-observable with regard to radar detection due to the layer of RAM.

A radar-absorbing material projectile system including a projectile with an outer layer of radar-absorbing material (RAM). A carrier or armature is disposed around the projectile, protecting the layer of RAM during the firing sequence. In some embodiments the carrier is a discarding carrier which falls away after firing, rendering the projectile low-observable with regard to radar detection due to the layer of RAM.

An aerial vehicle includes a body and an antenna assembly mounted to the body. The antenna assembly includes a fairing component comprising a hollow body, a conductive coating formed on at least an inner surface of the fairing component, a plurality of antenna elements formed in the conductive coating, each antenna element including a first slot line defining a first transmission line and a second slot line defining a second transmission line, an insulator sleeve disposed within the fairing component, wherein an outer surface of the insulator sleeve at least substantially matches an inner surface of the fairing component, and a plurality of cable assemblies operably coupled to the plurality of antenna elements, wherein each cable assembly is coupled to a respective antenna element.

A radar-absorbing material projectile system including a projectile with an outer layer of radar-absorbing material (RAM). A carrier or armature is disposed around the projectile, protecting the layer of RAM during the firing sequence. In some embodiments the carrier is a discarding carrier which falls away after firing, rendering the projectile low-observable with regard to radar detection due to the layer of RAM.

A radar-absorbing material projectile system including a projectile with an outer layer of radar-absorbing material (RAM). A carrier or armature is disposed around the projectile, protecting the layer of RAM during the firing sequence. In some embodiments the carrier is a discarding carrier which falls away after firing, rendering the projectile low-observable with regard to radar detection due to the layer of RAM.

Thermally-sensitive hardware is at least partially enclosed within a container in which reactants for a solid-solid endothermic chemical reaction are disposed, surrounding at least a portion of the thermally-sensitive hardware. The reactants or a structure including the reactants are positioned between the thermally-sensitive hardware and a heat source, such as an external surface of a missile traveling through atmospheric gases at extremely high speed and experiencing extreme frictional heating. The reactants absorb heat during the solid-solid endothermic reaction to thermally protect the thermally-sensitive hardware. The reactants are preferably selected to absorb heat of at least 5 kilo-Joules per gram (kJ/g) during the solid-solid endothermic chemical reaction.