Automatically disintegrating missile
AssigneeRheinmetall GmbH
InventorsDieter Boeder, Christian Jaeneke, Rudolf Romer, Guenter Sikorski
Life of this patent
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Abstract
There is disclosed a missile which automatically disintegrates after a predetermined flight time. The missile is made up of several parts which are positively secured together by a locking means which is released at a predetermined time after the firing of the missile by the action of the air through which the missile passes during its flight. The invention may by used to advantage in both practice missiles and service missiles.
Claims15
A missile having a tip and a tail end, which automatically disintegrates after attaining a predetermined flight time, comprising a missile body formed of at least two parts, a sleeve coaxially mounted with respect to the missile on said two parts thereby gripping said parts and holding them together, said sleeve being formed of a material which softens or melts as a result of the increase of temperature caused by the air flowing around the missile during its flight, at least two parts being formed as identical sector-shaped parts in a longitudinal direction, such parts of the missile body forming a recess at the tail end of the missile, wing tail unit having a stud received and held within the recess, and an annular groove encircling the missile body in a central zone thereof, the sleeve for securing the missile body parts together being disposed in said annular groove.
A missile having a tip and wing tail unit end which automatically disintegrates after attaining a predetermined of flight time, comprising a missile body formed of a plurality of parts, a locking means including a part which forms at least part of the tip of the missile and being coaxial therewith, said tip part being at least partially formed of a material which softens or melts as a result of the increase of temperature caused by the air flowing around the missile during its flight, an axial passage extending through the missile body from adjacent the forward end thereof to the wing tail unit thereon, a rod slidably mounted within said axial passage through the missile body, the rear end of the said rod being secured to the wing tail unit, said rod forming another part of said locking means and locking said parts of said missile together when said rod is in a forward locked position and releasing said parts of said missile when said rod has been shifted rearwardly by the air flowing around said missile during flight after said tip part has molten or softened sufficiently.
A missile which automatically disintegrates after attaining a predetermined flight time, comprising a missile body formed of a plurality of parts, a locking means for positively locking said missile body parts to one another, the locking means being mounted on the missile body and being releasable after a predetermined time delay by the action of the air flowing around the missile in its flight, the locking means includes a securing element which can be shifted by the air flowing around the missile during its flight, the missile body is divided into at least two longitudinally extending identical sector-shaped parts, and the securing element comprises a piston displaceable longitudinally of the missile body and located in one of the parts of the missile body, said piston being capable of being displaced rearwardly of the missile body by the pressure of the air through which the missile travels and by the force of inertia upon the piston after the discharge of the missile.
Dependencies are inferred from the claim text.