A dome
assembly (50) adapted for use with a
missile (32) having a longitudinal axis (42) parallel to a thrust vector thereof. The inventive dome (50) includes a
crystal (30, 50) having a crystallographic structure that includes a plurality of planes (12, 14, 16), one of said planes (14) being more susceptible to failure than one or more of the other planes (12, 16). A surface around a
missile sensor provides a place for mounting the
crystal (30, 50) so that said plane susceptible to failure (14) faces approximately opposite to that of a positive
velocity vector (34) of said
missile (32). In a more specific embodiment, the
crystal (30, 50) is a
sapphire crystal (30, 50) having a crystallographic structure that includes positive n-planes (12), positive r-planes (14), and a c-plane (16). By design at nominal conditions, an r-plane (14) is approximately bisected by a plane formed by the normal of the c-plane (16) and a
wind flow vector (36) parallel to a thrust vector of said missile (32). A turntable (not shown) orients the sensor dome (50) so that a first r-plane (14) faces leeward of impinging
airflow (36) corresponding to the
wind flow vector (36). An r-plane normal (38) of a second r-plane forms an angle of approximately 60 degrees with respect to impinging
airflow (36) that is approximately parallel to the thrust vector of the missile (32). The turntable includes a motor (not shown) for strategically orienting the lattice planes (12, 14, 16) of the dome (50) so as to maximize the strength of the dome (50) with respect to applied stresses.