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Details
Inventors: Brazel, James P.;
Assignee: General Electric Company (Philadelphia, PA)
Primary Examiner: Hille; Rolf
Assistant Examiner: Johnson; Doris J.
Attorney, Agent or Firm: Amgott; Allen E., Checkovich; Paul

A cover for an elongated antenna window of a nose cone of a reentry type missile includes a four directional composite material. A respective portion of a plurality of fibers are disposed in each of the four directions. The directions are oriented so that the fibers provide increased resistance to expected aerodynamic pressure-induced shear forces, especially during reentry, in the plane of the longitudinal axis of the window. The fibers comprise a refractory ceramic such as silica, boron nitride, alumina, aluminum nitride or a combination thereof having a filler material including a refractory ceramic disposed in the interstices between the fibers.

DETAILED DESCRIPTION Referring to FIG.
1, a plan view of a portion of a reentry-type missile in accordance with the present invention is shown.
Nose cone 10, having a generally aerodynamic, such as conical, outer surface 11 and central axis 15, includes an elongated window, or aperture, 12 having a cover 14 sealingly engaging the margin thereof.
Nose tip 18 is disposed forward nose cone 10.
Window 12 facilitates electromagnetic flow communication between a hollow volume, or cavity, 20 disposed within nose cone 10 and the surroundings external nose cone 10.
Window 12 may be oval or elliptical with longer axis 17 disposed coincident with a meridian 16 on surface 11, or alternatively disposed substantially parallel to central axis 15.
Shorter axis 19 is perpendicular or transverse longer axis 17.
Of course, window 12 may be disposed in a lateral surface of any portion of the missile, which includes any circumferential position about central axis 15.
If the radius of curvature of surface 11 is large with respect to the dimension of shorter axis 19, then cover 14 may be substantially planar.
Typically, electronic equipment (not shown) such as a radio frequency (RF) antenna, RF receiver and/or RF transmitter, and guidance and control electronics, may be disposed in cavity 20.
These electronic components tend to be fragile and must be protected during the course of missile flight, while still permitting undistorted and adequate uni- or bilateral electromagnetic flow through oblong aperture 12.
For cases when the missile is maintained in a preferred orientation or attitude (i.
e.
predetermined roll, pitch and yaw) and is not rotating, so that the focal axis of a nose cone antenna (not shown) through window 12 may be directed in a predetermined direction, like toward a passive terrestial, or perhaps a stellar or solar, reference, expected mechanical forces on window cover 14 may be readily determined.
On the reentry portion of a trajectory, aerodynamic pressure loads will be exerted on window 14 which will generally be found on the earthward side (i



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