초록 ▼

A non-ablative heat sensitive nose cap uses a highly conductive solid forward ogive and rear segmented ogive member, in contact with a low melting point locking ring which is thermally isolated from the main projectile body. The locking ring holds the rear ogive segments together until the desired t

A non-ablative heat sensitive nose cap uses a highly conductive solid forward ogive and rear segmented ogive member, in contact with a low melting point locking ring which is thermally isolated from the main projectile body. The locking ring holds the rear ogive segments together until the desired time for projectile-break. Break-up occurs when a zinc alloy locking ring fails under the combined influence of decreasing yield strength and centrifugal force due to launch and free flight imposed spin.

대표청구항 ▼

A heat sensitive nose cap assembly for limiting the range of a fin-stabilized, hypervelocity, anti-armor training projectile which has passed a target which comprises: a projectile body having a centrally positioned boss located on a front end and an axially alligned screw member integrally connecte

A heat sensitive nose cap assembly for limiting the range of a fin-stabilized, hypervelocity, anti-armor training projectile which has passed a target which comprises: a projectile body having a centrally positioned boss located on a front end and an axially alligned screw member integrally connected to said boss; first thermal conductive means releaseably connected to said screw member of said projectile for maintaining an ogive geometry for said projectile during flight toward said target and for transferring aerodynamically generated heat which includes; a pair of rear ogive members, having a centrally disposed forward threaded cavity therein, a centrally disposed rear threaded cavity, a semi-annular shaped groove operatively disposed in a front end of said rear ogive members, and a rear locking ring groove positioned in an aft end of said rear ogive members; second thermal conductive means fixedly connected to said first thermal conductive means for preventing premature break-up of said projectile which includes; a conically shaped forward ogive member threadedly attached to said rear ogive members, said forward ogive member having a semi-annular shaped groove operationally disposed opposite to the semi-annular grooves of said rear ogive members; a forward locking ring positioned in said semi-annular grooves of said rear and forward ogive members; and a threaded axially aligned rear end for fixedly engaging the centrally disposed forward threaded cavity of said rear ogive members, said forward ogive preventing the premature opening of said pair of rear ogive members during projectile setback; a zinc alloy locking ring internally positioned in said projectile and operatively disposed in said rear locking ring groove under compressive radial stress approximately equal to the yield stress of said zinc alloy locking ring, for releaseably holding said first thermal conductive means attached to said projectile body for a specified period of time after launch of said projectile, said first thermal conductive means heating said zinc alloy locking ring and thereby changing the yield strength of said locking ring in response to the aerothermodynamic heating of said rear and forward ogive members, and breaking in response to the centrifugal forces generated by said fin stabilized projectile; and insulator means, operatively disposed intermediate said projectile boss and said zinc alloy locking ring for thermally isolating said zinc alloy locking ring from said projectile boss.