Projectile

Abstract

A projectile ( 100 ) is provided for operating at least in a launch phase and in a post-launch phase. The projectile includes a projectile body ( 10 ), a projectile head ( 50 ), and a support structure ( 80 ). The projectile head is non-rigidly mounted to the projectile body via a joint structure ( 70 ). The support structure is configured for selectively supporting the projectile head with respect to the projectile body in a load bearing relationship independently of the joint structure during at least a portion of the launch phase, and for selectively terminating the support during at least a portion of the post-launch phase. A method for operating a projectile and a method for retrofitting a projectile are also provided.

1 - 42 . (canceled) 
     
     
         43 . A projectile configured for operating at least in a launch phase and in a post-launch phase, the projectile comprising:
 a projectile body;   a projectile head; and   a support structure;   wherein said projectile head is non-rigidly mounted to said projectile body via a joint structure;   wherein said support structure is configured for selectively supporting said projectile head with respect to said projectile body in a load bearing relationship independently of said joint structure during at least a portion of said launch phase, and for selectively terminating said support during at least a portion of said post-launch phase; and   wherein at least during said portion of said post-launch phase, said projectile head is freely pivotable with respect to said projectile body in at least two rotational degrees of freedom.   
     
     
         44 . The projectile according to  claim 43 , wherein said projectile head is at least one of:
 pivotably mounted to said projectile body via said joint structure;   axially movable with respect to said projectile body via said joint structure at least in when said support is terminated; or   configured for being freely aerodynamically aligned with said velocity vector of the projectile independently of said projectile body when said support is terminated.   
     
     
         45 . The projectile according to  claim 43 , wherein said support structure is configured for preventing at least a majority of loads between said projectile head and said projectile body associated with said launch phase being channeled via said joint structure. 
     
     
         46 . The projectile according to  claim 43 , wherein at least one of the following:
 said projectile body comprises a front end, an aft end and a first longitudinal axis extending therebetween, and wherein said projectile head comprises a second longitudinal axis, wherein in said load bearing relationship, said first longitudinal axis is substantially coaligned with said second longitudinal axis;   in said load bearing relationship, said support structure externally supports said projectile head with respect to said projectile body;   in said load bearing relationship, said support structure reversibly interconnects said projectile head with said projectile body and is configured for supporting said loads between said projectile head and said projectile body when thus interconnected;   said support structure is configured for being removed from said projectile body and said projectile head at least during said portion of said post-launch phase for selectively terminating said support; or   said loads are induced responsive to an acceleration of the projectile during said launch phase.   
     
     
         47 . The projectile according to  claim 43 , wherein said support structure is further configured for preventing aerodynamic loads being directly applied to said projectile head during said portion of said launch phase. 
     
     
         48 . The projectile according to  claim 43 , wherein said support structure comprises a load bearing member, wherein in said load bearing relationship said load bearing member is in load bearing contact with said projectile body and in load bearing contact with an external part of said projectile head. 
     
     
         49 . The projectile according to  claim 43 , wherein said support structure comprises a housing having an open aft end and a cavity in communication therewith, wherein said aft end is configured for reversibly connecting to said projectile body, and wherein said cavity is configured for accommodating said projectile head therein in load bearing contact therewith. 
     
     
         50 . The projectile according to  claim 43 , wherein at least during said portion of said post-launch phase, said projectile head is freely pivotable with respect to said projectile body in three rotational degrees of freedom. 
     
     
         51 . The projectile according to  claim 43 , wherein at least one of:
 said joint structure is configured for permitting relative angular movement between said projectile head and said projectile body, said projectile head being configured for self-alignment with a free stream fluid flow direction, of a fluid through which said projectile is traveling, via said joint structure in said post-launch phase wherein said projectile head is exposed to the fluid flow;   said projectile head is gimbaled freely to said projectile body via said joint structure or wherein said joint structure comprises a flexible hose;   said projectile head comprises an aft portion comprising an annular tail airfoil configured for providing said self-alignment; or   said projectile head is configured for homing said projectile to a target.   
     
     
         52 . The projectile according to  claim 43 , wherein:
 said projectile body further comprises a steering arrangement configured for steering the projectile responsive to suitable control input; and   said projectile head is further configured for providing said control input at least during said portion of said post launch phase.   
     
     
         53 . The projectile according to  claim 52 , wherein said projectile head comprises a sensor arrangement configured for sensing a control parameter wherein to generate said control input in response thereto. 
     
     
         54 . The projectile according to  claim 52 , wherein said steering arrangement comprises an aerodynamic control surface arrangement configured for generating aerodynamic moments suitable for steering said projectile, responsive to said control input. 
     
     
         55 . The projectile according to  claim 43 , wherein said support structure comprises a casing having an aerodynamically contoured outer wall, and an internal seat for seating an aft portion of said projectile head in said load bearing relationship. 
     
     
         56 . The projectile according to  claim 55 , wherein at least one of;
 in said load bearing relationship, said projectile head is immobilized in said casing; or   in said load bearing relationship, said casing prevents axial displacement between said projectile head and said projectile body and/or wherein in said load bearing relationship, said projectile head and said projectile body are longitudinally aligned.   
     
     
         57 . The projectile according to  claim 55 , wherein said casing comprises a first casing half reversibly joined to a second casing half, and wherein said support structure is removable from said projectile head and said projectile body by separating said first casing half from said second casing half 
     
     
         58 . The projectile according to  claim 43 , wherein said projectile is configured as a mortar shell configured to be launched via a mortar. 
     
     
         59 . A method for operating a projectile, comprising:
 (a) providing a projectile as defined in  claim 43 ;   (b) operating said projectile during at least said portion of said launch phase wherein to selectively support said projectile body with respect to said projectile head via said support structure in a load bearing relationship independently of said joint structure; and   (c) selectively terminating said load bearing relationship and subsequently operating said projectile during at least said portion of said post-launch phase.   
     
     
         60 . The method according to  claim 59 , wherein step (c) comprises removing said support structure from said projectile head and said projectile body while said projectile is traveling in the atmosphere, and allowing said projectile body to become freely aerodynamically aligned with a velocity vector of the projectile independently of said projectile body. 
     
     
         61 . The method according to  claim 59 , further comprising homing said projectile to a target. 
     
     
         62 . The method according to  claim 61 , further comprising illuminating said target with an illuminating radiation, detecting with said projectile head said illuminating radiation reflected from the target, and steering said projectile to said target wherein to maintain said reflected illuminating radiation in the boresight of said projectile head. 
     
     
         63 . A method for retrofitting a projectile, comprising:
 (a) providing the projectile, the projectile comprising a projectile body and a projectile head, wherein the projectile head is non-rigidly mounted to the projectile body via a joint structure; and   (b) providing a selectively removable support structure, wherein said support structure is configured for selectively supporting said projectile head with respect to said projectile body in a load bearing relationship independently of said joint structure during at least a portion of said launch phase, and for selectively terminating said support during at least a portion of said post-launch phase, wherein at least during said portion of said post-launch phase said projectile head is freely pivotable with respect to said projectile body in at least two rotational degrees of freedom.   
     
     
         64 . The method according to  claim 63 , wherein said support structure is configured for preventing at least a majority of loads between said projectile head and said projectile body associated with said launch phase being channeled via or supported by said joint structure, and optionally wherein said majority of said loads is otherwise damaging if applied to said joint structure. 
     
     
         65 . A projectile, comprising:
 a projectile body; and   a projectile head;   wherein said projectile head is non-rigidly mounted to said projectile body via a joint structure at a forward end of the projectile body; and   wherein said projectile is configured for permitting limited relative axial movement between said projectile body and said projectile head via said joint structure.   
     
     
         66 . The projectile according to  claim 65 , wherein said joint structure comprises a forward portion configured for pivotingly mounting said projectile head thereto, and an aft portion comprising a shaft slidingly mounted to said projectile body. 
     
     
         67 . The projectile according to  claim 66 , wherein said shaft is axially reciprocably movable with respect to said projectile body within a displacement range, and wherein optionally a resilient member may be provided for biasing said shaft with respect to said projectile body.