Method of correcting the trajectory of a spin-stabilised projectile and projectile implementing one such method

Abstract

The invention relates to a process to correct the trajectory of a spin-stabilised projectile, process in which at least one correction is made to the axial position of the projectile's centre of aerodynamic thrust, such process wherein the correction of the axial position of the centre of thrust is obtained by modifying at least once the length of the projectile in flight, such modification being triggered by control means.

1 . A process to correct the trajectory of a spin-stabilised projectile ( 1 ), process in which at least one correction is made to the axial position of the projectile's centre of aerodynamic thrust (F), such process wherein the correction of the axial position of the centre of thrust (F) is obtained by modifying at least once the length of the projectile ( 1 ) in flight, such modification being triggered by control means ( 3 ,  7 ).  
   
   
       2 . A correction process according to  claim 1 , wherein the modification of the projectile's length ( 1 ) in flight is obtained by ejecting one section ( 4 ) of the projectile.  
   
   
       3 . A correction process according to  claim 2 , wherein the section to be ejected is positioned at the front part of the projectile.  
   
   
       4 . A correction process according to  claim 1 , wherein the modification of the projectile's length ( 1 ) in flight is obtained by the relative translation of a front part of the projectile with respect to a rear part.  
   
   
       5 . A correction process according to  claim 4 , wherein at least one correction of the projectile's ( 1 ) trajectory is also made by deploying the projectile's aerodynamic braking means ( 17 ).  
   
   
       6 . A correctable trajectory projectile implementing the process according to  claim 1 , wherein it incorporates at least one section ( 4 ,  8 ,  11 ) made integral with a body ( 2 ) of the projectile ( 1 ) by releasable linking means ( 12 ,  16 ,  19 ).  
   
   
       7 . A correctable trajectory projectile according to  claim 6 , wherein the section releasable on trajectory is a cap ( 4 ) placed at the front part of the projectile ( 1 ).  
   
   
       8 . A correctable trajectory projectile implementing the process according to  claim 4 , wherein it incorporates a telescopic nose cone ( 11 ) mounted able to slide with respect to the projectile ( 1 ) body ( 2 ), such nose cone constituting a front part of the projectile able to move with respect to a rear part formed by the projectile body ( 2 ), the nose cone being made integral with the body by releasable linking means ( 12 ,  16 ).  
   
   
       9 . A correctable trajectory projectile according to  claim 8 , wherein the nose cone ( 11 ) encloses a gas generator ( 13 ) to be initiated on trajectory by the control means ( 3 ,  7 ), the gas pressure causing the nose cone/body linking means ( 12 ) to shear and the nose cone ( 11 ) to translate forwards up to an abutment and thus elongating the projectile.  
   
   
       10 . A correctable trajectory projectile according to  claim 8 , wherein the releasable linking means ( 16 ) are activated by the control means ( 3 ) and the release of the nose cone ( 11 ) allows it to translate to the rear with respect to the body ( 2 ) under the effect of the aerodynamic pressure, thereby shortening the projectile.  
   
   
       11 . A correctable trajectory projectile implementing the process according to  claim 4 , wherein it incorporates a base ( 8 ) mounted able to slide with respect to the projectile body ( 2 ), such base constituting a rear part of the projectile and able to move with respect to a front part formed by the projectile body ( 2 ), said base being made integral with the body by releasable linking means ( 19 ).  
   
   
       12 . A correctable trajectory projectile according to  claim 8 , wherein it incorporates at least one flap ( 17 ) whose radial deployment is triggered by the control means ( 3 ), such flap ensuring the aerodynamic braking of the projectile ( 1 ) and the shortening of its range.  
   
   
       13 . A correctable trajectory projectile implementing the process according to  claim 2 , wherein it incorporates at least one section ( 4 ,  8 ,  11 ) made integral with a body ( 2 ) of the projectile ( 1 ) by releasable linking means ( 12 ,  16 ,  19 ).  
   
   
       14 . A correctable trajectory projectile implementing the process according to  claim 3 , wherein it incorporates at least one section ( 4 ,  8 ,  11 ) made integral with a body ( 2 ) of the projectile ( 1 ) by releasable linking means ( 12 ,  16 ,  19 ).  
   
   
       15 . A correctable trajectory projectile implementing the process according to  claim 5 , wherein it incorporates a telescopic nose cone ( 11 ) mounted able to slide with respect to the projectile ( 1 ) body ( 2 ), such nose cone constituting a front part of the projectile able to move with respect to a rear part formed by the projectile body ( 2 ), the nose cone being made integral with the body by releasable linking means ( 12 ,  16 ).  
   
   
       16 . A correctable trajectory projectile implementing the process according to  claim 5 , wherein it incorporates a base ( 8 ) mounted able to slide with respect to the projectile body ( 2 ), such base constituting a rear part of the projectile and able to move with respect to a front part formed by the projectile body ( 2 ), said base being made integral with the body by releasable linking means ( 19 ).  
   
   
       17 . A correctable trajectory projectile according to  claim 9 , wherein it incorporates at least one flap ( 17 ) whose radial deployment is triggered by the control means ( 3 ), such flap ensuring the aerodynamic braking of the projectile ( 1 ) and the shortening of its range.  
   
   
       18 . A correctable trajectory projectile according to  claim 10 , wherein it incorporates at least one flap ( 17 ) whose radial deployment is triggered by the control means ( 3 ), such flap ensuring the aerodynamic braking of the projectile ( 1 ) and the shortening of its range.  
   
   
       19 . A correctable trajectory projectile according to  claim 11 , wherein it incorporates at least one flap ( 17 ) whose radial deployment is triggered by the control means ( 3 ), such flap ensuring the aerodynamic braking of the projectile ( 1 ) and the shortening of its range.