Abstract: A ceramic material for radome is illustrated comprising: -about 80-95% (wt %) of Si3N4; about 5-15% (wt %) of magnesium aluminosilicates including 2.5-12.5% (wt %) of Si02, 0.5-3% (wt %) of MgO and 2-6% (wt %) of Al2O3; and having a density not lower than 2.5 g/cm3 and a dielectric constant not exceeding 6.5. A process for producing a radome is also illustrated.

Abstract: A ceramic material for radome is illustrated comprising: —about 80-95% (% wt) of Si3N4; about 5-15% (wt %) of magnesium aluminosilicates including 2.5-12.5% (wt %) of SiO2, 0.5-3% (wt %) of MgO and 2-6% (wt %) of Al2O3; and having a density not lower than 2.5 g/cm3 and a dielectric constant not exceeding 6.5. A process for producing a radome is also illustrated.

Abstract: A ceramic material for radome is illustrated comprising: —about 80-95% (% wt) of Si3N4; about 5-15% (wt %) of magnesium aluminosilicates including 2.5-12.5% (wt %) of Si02, 0.5-3% (wt %) of MgO and 2-6% (wt %) of Al203; and having a density not lower than 2.5 g/cm3 and a dielectric constant not exceeding 6.5. A process for producing a radome is also illustrated.

Abstract: A method to process a radar echo signal is described. The method determines the value of at least one target motion parameter by selecting from a plurality of possible test values (VR1, . . . , VRN) one value (VR) which maximizes a functional defined over the radar echo signal. The method further performs a correction of the radar echo signal based on the value (VR) which is determined by the at least one motion parameter. The functional is the time derivative of the radar echo signal or a function dependent from the derivative.

Abstract: In a ground launcher, two or more housing-transportation-launch assemblies for respective missiles are placed one on top of the other and connected releasably and interchangeably to each other; each housing-transportation-launch assembly has a respective outer casing, which in turn has longitudinal end walls breakable from inside the casing, and a deflecting body for deflecting the exhaust gas of the engine of the missile; a guide and protection assembly being interposed between the casing and the missile to guide the missile in the set launch direction, and to protect the missile against shock or vibration.