Full-caliber, spin-stabilized guided projectile with long range

Abstract

An increased range guided projectile includes overcaliber lateral moment reducing wings ( 10 ) that can be deployed. The lateral moment reducing wings ( 10 ) are designed and arranged behind the center of gravity (S) in the tail direction on the guided projectile ( 1 ) so that the pitching moment derivative coefficient (C mα ) of the guided projectile ( 1 ) is in the range of ±0.5, if the guided projectile ( 1 ) has a speed that is in the speed range of Mach 0.4 to 0.8; the lateral moment reducing wings ( 10 ) are in their deployed position; and, the canard guide device ( 20 ) does not exert any guiding moments.

1 . A guided projectile comprising the following features:
 a) the guided projectile is designed so that it is spin-stabilized over the whole flight trajectory,   b) the guided projectile comprises a nose with a canard guide device with canard guiding wings,   c) the guided projectile is a large-caliber full caliber projectile,   d) the flight path of the guided projectile is influenced by aerodynamic coefficients, such as by a pitching moment derivative coefficient (C mα ),   wherein:   e) the guided projectile comprises overcaliber lateral moments reducing wings that can be deployed,   f) the lateral moments reducing wings are designed and arranged behind the center of gravity in the tail direction on the guided projectile so that the pitching moment derivative coefficient (C mα ) of the guided projectile is in the range of ±0.5, if   the guided projectile has a speed that is in the speed range of Mach 0.4 to 0.8,   the lateral moments reducing wings are in their deployed position, and   the canard guide device does not exert any guiding moments.   
     
     
         2 . The guided projectile according to  claim 1 , wherein the pitching moment derivative coefficient (C mα ) of the guided projectile is in the range of ±0.5 not only if
 the guided projectile has a speed, hereafter referred to as the nominal speed, that is in the speed range of Mach 0.4 to 0.8, but also 
 in a complete speed range extending from the nominal speed minus a speed of Mach 0.1 to the nominal speed plus a speed of Mach 0.1. 
 
     
     
         3 . The guided projectile according to  claim 1 , wherein the lateral moments reducing wings in each case comprise an attachment end, and the axial distance between the lateral moments reducing wings, measured at the center of the attachment end, and the center of gravity is 0.01 times to 1.0 times the caliber. 
     
     
         4 . The guided projectile according to  claim 1 , wherein
 in the deployed position, each lateral moment reducing wing protrudes with a radial extension over the cladding of the guided projectile, so that the radial extension is 0.8 to 2 times the caliber of the guided projectile.   
     
     
         5 . The guided projectile according to  claim 1 , wherein
 the lateral moment reducing wings are twisted like a propeller, and during a section in a descending flight phase, rotation energy is converted into translation energy, wherein at least in this process the lateral moments reducing wings are non-rotatably attached to the guided projectile.   
     
     
         6 . The guided projectile according to  claim 1 , wherein
 the lateral moments reducing wings are mounted in a roll-decoupled manner.   
     
     
         7 . The guided projectile according to  claim 1 , wherein
 the guided projectile comprises no additional wings besides the canard guiding wings and the lateral moments reducing wings.   
     
     
         8 . The guided projectile according to  claim 1 , wherein
 the canard guide device is designed so that the canard guide wings can be deployed and retracted.   
     
     
         9 . The guided projectile according to  claim 1 , wherein the lateral moment reducing wings are twisted so that, at a distance r i  from the symmetry axis of the guided projectile, each cross section of a lateral moment reducing wing forms an angle a i  with respect to the axis according to the following equation: tan a i =r i W/V, where W is the rotation speed (in rad/s) and V is the guided projectile speed.