A projectile configured for operating at least in a launch phase and in a post-launch phase, 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; and 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; wherein said projectile head is configured for being freely aerodynamically aligned with a velocity vector of the projectile independently of said projectile body when said support is terminated; the projectile is characterized in that: in said load bearing relationship, said support structure externally supports said projectile head with respect to said projectile body; 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; and said support structure is a fairing 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. 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; and 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; wherein said projectile head is configured for being freely aerodynamically aligned with a velocity vector of the projectile independently of said projectile body when said support is terminated; the projectile is characterized in that: in said load bearing relationship, said support structure externally supports said projectile head with respect to said projectile body; 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; and said support structure is a fairing 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. in said load bearing relationship, said support structure externally supports said projectile head with respect to said projectile body; 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; and said support structure is a fairing 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.