Abstract: A thermal protection system arrangement and method of manufacture for a carbon-carbon nose tip of a re-entry space vehicle that is expected to encounter very high heat fluxes upon re-entry into the earth's atmosphere. The arrangement includes a carbon-carbon nose tip which has a first sublimatable material infiltrated into the outer portion of the nose tip for release of thermal energy to the environment during the high heat fluxes of re-entry. A second sublimatable material which sublimates at heat fluxes materially less than that of the first sublimatable material is infiltrated into the inner portion of the nose tip so that the nose tip releases energy to the environment and erodes in a controlled manner thereby maintaining the interior of the nose tip at a desired temperature.

Abstract: The invention is a reduced radar detectable runway. In detail, the invention comprises a runway having a plurality of holes randomly orientated and randomly dispersed across and along the surface thereof. The holes are preferably polygons, and ideally square in shape, and filled with a dielectric material. Additionally, the minimum necessary perimeter of the runway should include an extended portion in an irregular pattern about a least a portion of the necessary perimeter. This portion should also incorporate the randomly positioned and orientated holes.

Abstract: Disclosed is a nose piece for a power drill and hand drill with certain modifications made to nose piece and using telescopic bushing having a drill motor, a drill spindle and a drill bit attached to the spindle, the nose piece being capable of macro longitudinal adjustment with respect to the length of the drill bit and rotational adjustment of its position with respect to the drill motor and the work piece.

Abstract: The invention is an all electric environmental control system. The primary power for the system is provided in a first embodiment by a compressor (C.sub.1) driven by an electric motor (14). The system includes the primary heat exchanger (16), an expansion cooling system (20), and a water separator (26). The electric motor (14) may be utilized in another embodiment to drive a compressor (23) within the expansion cooling system (20'). A vapor-cycle cooling system including the freon-compressor (34), the condenser (36) and the evaporator (38) may optionally replace the expansion cooling system (20). To compensate for pressure variations during flight, the electric motor (32) is mounted to a planetary gearbox (44) with a "makeup"/"subtract" differential electric motor (42) such that the compressor (C.sub.1) is run at the desired speed. The compressor (C.sub.