Abstract: Embodiments of a flight vehicle including a scribed frangible seal are provided, as are embodiments of a scribed frangible seal and a method for equipping a flight vehicle with a scribed frangible seal. In one embodiment, the flight vehicle includes a vehicle body having a deployment opening therein, and a deployable element residing in a stowed position within the vehicle body and movable into a deployed position. At least a potion of the deployable element passes through the deployment opening when moving from the stowed position into the deployed position. The flight vehicle further includes a scribed frangible seal, which is sealingly disposed over the deployment opening and which is positioned so as to be contacted by the deployable element during deployment thereof. The scribed frangible seal fractures along at least one scribe line when contacted by the deployable element to permit movement of the deployable element from the stowed position to the deployed position.

Abstract: A two-piece adapter for mounting a guidance system on unguided rockets allows for the existing designs and stores of unguided rockets to be retrofitted with guidance capability to provide a “guided rocket”. The adapter provides the external mounting features for mounting the guidance system and does so in a manner that transfers the steering loads of the guidance system to the rocket airframe and maintains the proper preloading and relationship of the fuze-to-warhead to detonate the warhead. The two-piece adapter comprises an inner adapter and an outer adapter. The inner adapter is secured between the fuze and warhead without requiring modifications of either part and provides the external mounting feature. The outer adapter is secured to the inner adapter and effectively moves the external mounting feature forward in front of the fuze where the guidance system is attached.

Abstract: A two-piece adapter for mounting a guidance system on unguided rockets allows for the existing designs and stores of unguided rockets to be retrofitted with guidance capability to provide a “guided rocket”. The adapter provides the external mounting features for mounting the guidance system and does so in a manner that transfers the steering loads of the guidance system to the rocket airframe and maintains the proper preloading and relationship of the fuze-to-warhead to detonate the warhead. The two-piece adapter comprises an inner adapter and an outer adapter. The inner adapter is secured between the fuze and warhead without requiring modifications of either part and provides the external mounting feature. The outer adapter is secured to the inner adapter and effectively moves the external mounting feature forward in front of the fuze where the guidance system is attached.

Abstract: Carbon fiber material and carbon fiber material that is saturated with hydrocarbon solid-liquid phase change material may be used as thermal management materials for providing a thermally conductive interface between a heat source and its housing. Such carbon fiber material may also be used for mechanical isolation of the heat source from its housing. Carbon fibers used in the carbon fiber material may be unidirectionally oriented to provide for low friction, thus optimizing critically controlled friction tolerances. Additionally the carbon fiber material saturated with hydrocarbon solid-liquid phase change material may be used to transfer heat into the an inherently nonconductive medium.