Novel test mounts are defined for a radar cross section testing apparatus that allows a supported object to be tested without interference from the test mount. This includes prescribing a diameter of about 0.61 wavelengths for a cylindrical test mount; maintaining a ratio for the test mount's characteristic dielectric constant and magnetic permeability of about one; and/or installing a frequency transposing apparatus to convert the frequency of radar pulses directed toward the test mount to off-frequency echoes.
This application is a continuation in part of my earlier filed application, Ser. No. 08/273,576, filed Jul. 11, 1994, still pending, entitled Synthetic Aperture Radar Smearing, copending herewith, for which the benefit of 35 U.S.C. 120 is claimed.
Low power magnetoelectronic device structures and methods for making the same are provided. One magnetoelectronic device structure (100) comprises a programming line (104), a magnetoelectronic device (102) magnetically coupled to the programming line, and an enhanced permeability dielectric material (106) disposed adjacent the magnetoelectronic device. The enhanced permeability dielectric material has a permeability no less than approximately 1.5. A method for making a magnetoelectronic device structure is also provided. The method comprises fabricating a magnetoelectronic device (102) and depositing a conducting line (104). A layer of enhanced permeability dielectric material (106) having a permeability no less than approximately 1.5 is formed, wherein after the step of fabricating a magnetoelectronic device and the step of depositing a conducting line, the layer of enhanced permeability dielectric material is situated adjacent the magnetoelectronic device.
A missile adapted for flight at hypersonic velocities includes an engine operable in rocket and ramjet modes of operation, the engine having an inlet opening, a fuel combustion chamber in the engine housing a boost fuel and a cruise fuel, an axially movable plug located at the engine inlet opening for opening and closing the inlet opening, and a mechanism, coupled with the plug and the engine, for switching between the two modes of operation of the engine during flight of the missile. In this way, when the missile reaches a target location in its flight trajectory, the plug can be moved to close the inlet opening and shut down the ramjet operation, while also minimizing the missile radar cross section properties. The switching mechanism includes sensors for determining flight parameters and a computer for processing the flight parameters to determine when to move the plug. To achieve low weight and improved thermal protection properties, the outer skin and internal structural components of the missile are made from a cured carbon/carbon slurry.
