Missile spiralling mechanism -2

Abstract

A missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiralling motion without the missile rolling. Two fins 3 and 4 are attached to a tube 5 that is able to rotate around the encircled part of the missile fuselage. The fins 3, 4 are able to rotate in a pivoting manner on the rotatable tube 5 with respect to the rotatable tube 5, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 5. Fin 3 is larger than fin 4. The difference in sizes between the fins makes the larger fin 3 exert a greater force on the rotatable tube 4 than the smaller fin 4 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus causes the rotatable tube 5 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 3, 4 would exert a lateral force on the rotatable tube 5. Thus, as well as forcing the rotatable tube 5 to rotate, the fins 3, 4 would also push the rotatable tube sideways. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion of the missile when in flight.

The claims defining this invention are as follows:  
     
         1 . A missile comprising a missile fuselage and a spiral inducing assembly, which said spiral inducing assembly is capable of forcing the missile to travel in a spiralling motion during flight of the missile, and which said spiral inducing assembly consists of a tube, and which said tube encircles part of the missile fuselage of the missile and is able to rotate relative to the encircled part of the missile fuselage, with a plurality of fins connected to the said tube, which said fins are connected to the tube such that the fins protrude laterally outward from the tube and such that the said fins can be rotated in a pivoting manner relative to the tube, and such that the said fins can be rotated in the said pivoting manner in the same direction, and which said spiral inducing assembly comprises a fin rotating mechanism by which fin rotating mechanism the 
 said fins can be rotated in the said pivoting manner, and by which said fin rotating mechanism the said fins can be rotated in the said pivoting manner and simultaneously in the same direction as each other such that during flight of the missile    one of the said fins connected to the tube can continuously exert a greater magnitude of force on the said tube than can another of the said fins that is connected to the said tube.    
     
     
         2 . A missile comprising a missile fuselage and a spiral inducing assembly, which said spiral inducing assembly is capable of forcing the missile to travel in a spiralling motion during flight of the said missile, and which said spiral inducing assembly consists of a tube, and which said tube encircles part of the missile fuselage of the missile and is able to rotate relative to the encircled part of the missile fuselage, with a plurality of fins connected to the said tube, which said fins are connected to the tube such that the fins protrude laterally outward from the tube and such that the said fins can be rotated in a pivoting manner relative to the tube, and 
 which said spiral inducing assembly comprises a fin rotating mechanism by which fin rotating mechanism the said fins can be rotated in the said pivoting manner such that during flight of the said missile one of the said fins connected to the tube can continuously exert a greater magnitude of force on the said tube than can another of the said fins that is connected to the said tube.    
     
     
         3 . A missile comprising a missile fuselage and a spiral inducing assembly, which said spiral inducing assembly is capable of forcing the missile to travel in a spiralling motion during flight of the missile, and which said spiral inducing assembly consists of a tube, and which said tube encircles part of the missile fuselage of the missile and is able to rotate relative to the encircled part of the missile fuselage, with a plurality of fins connected to the said tube, which said fins are connected to the tube such that the fins protrude laterally outward from the tube and such that the said fins can be rotated in a pivoting manner relative to the tube, and such that the said fins can be rotated in the said pivoting manner in the same direction, and which said spiral inducing assembly comprises a fin rotating mechanism by which said fin rotating mechanism the said fins can be rotated in the said pivoting manner and in the same direction as each other and by which said fin rotating mechanism the said fins thus can be rotated in the said same direction relative to the tube such that one of the said fins connected to the tube can be rotated to a greater degree relative to the tube than can another of the said fins that is connected to the said tube.  
     
     
         4 . A missile comprising a missile fuselage and a spiral inducing assembly, which said spiral inducing assembly is capable of forcing the missile to travel in a spiralling motion during flight of the said missile and which said spiral inducing assembly consists of a tube, and which said tube encircles part of the missile fuselage of the missile and is able to rotate relative to the encircled part of the missile fuselage, with a plurality of fins connected to the said tube, which said fins are connected to the tube such that the fins protrude laterally outward from the tube and such that the said fins can be rotated in a pivoting manner relative to the tube, and such that the said fins can be rotated in the said pivoting manner in the same direction, and which said spiral inducing assembly comprises a fin rotating mechanism by which said fin rotating mechanism the said fins can be rotated in the said pivoting manner and in the same direction as each other, and with the said fins being such that one of said fins connected to the tube is of larger size than is another of the said fins.  
     
     
         5 . The missile of  claim 1  wherein the said fin that is able to exert a greater magnitude of force on the tube can be pivotly rotated to a greater degree than the said other fin by means of the fin rotating mechanism, such that when the said fin that can be rotated to greater degree is rotated to a greater degree than the said other fin the fin that is rotated to a greater degree exerts a greater magnitude of force on the tube during flight of the missile than the said other fin.  
     
     
         6 . The missile of  claim 1  wherein the said fin that is able to exert a greater magnitude of force on the tube is of larger size than the said other fin such that by being of larger size the fin that is of larger size can exert a greater magnitude of force on the tube than the said other fin during flight of the missile.  
     
     
         7 . The missile of  claim 2  wherein the said fin that is able to exert a greater magnitude of force on the tube can be pivotly rotated to a greater degree than the other said fin by means of the fin rotating mechanism, such that when the said fin that can be rotated to greater degree is rotated to a greater degree than the said other fin the fin that is rotated to a greater degree exerts a greater magnitude of force on the tube during flight of the missile than the said other fin.  
     
     
         8 . The missile of  claim 2  wherein the said fin that is able to exert a greater magnitude of force on the tube is of larger size than the said other fin such that by being of larger size the fin that is of larger size can exert a greater magnitude of force on the tube than the said other fin during flight of the missile.  
     
     
         9 . A missile comprising a missile fuselage and a spiral inducing assembly, which said spiral inducing assembly is capable of forcing the missile to travel in a spiralling motion during flight of the said missile, and which said spiral inducing assembly consists of a tube, and which said tube encircles part of the missile fuselage of the missile and is able to rotate relative to the encircled part of the missile fuselage, with a plurality of fins connected to the said tube, which said fins are connected to the tube such that the fins protrude laterally outward from the tube and such that the said fins can be rotated in a pivoting manner relative to the tube, and such that the said fins can be rotated in the said pivoting manner in the same direction and in unison relative to the tube and which said spiral inducing assembly comprises a fin rotating mechanism by which said fin rotating mechanism the said fins can be rotated in the said pivoting manner in the same direction as each other and in unison relative to the tube and with the said fins being such that during flight of the said missile one of the said fins connected to the tube can continuously exert a greater magnitude of force on the said tube than can another of the said fins that is connected to the said tube.  
     
     
         10 . The missile of  claim 9  wherein the said fin that is able to exert a greater magnitude of force on the tube is of larger size than the said other fin such that by being of larger size the fin that is of larger size can exert a greater magnitude of force on the tube than the said other fin during flight of the missile.  
     
     
         11 . The missile of  claim 1  wherein the spiral inducing assembly can force the said missile to travel in a continuous spiralling motion while the said fins are continuously maintained in a rigid position with respect to the said tube.  
     
     
         12 . A missile comprising a missile fuselage and a spiral inducing assembly, which said spiral inducing assembly is capable of forcing the missile to travel in a spiralling motion during flight of the said missile, and which said spiral inducing assembly consists of a tube, which said tube encircles part of the missile fuselage of the missle and which said tube is able to rotate relative to the encircled part of the missile fuselage, with a plurality of fins connected to the said tube, which said fins are connected to the tube such that the fins protrude laterally outward from the tube and such that the said fins can be rotated in a pivoting manner relative to the tube, and such that the said fins can be rotated in the said pivoting manner in the same direction, with a stem connected to one fin and another stem connected to another fin, and with an additional tube encircling part of the missile fuselage of the missile, which missile fuselage comprises a fore end and an aft end, and which said additional tube is able to move between the fore end and the aft end of the missile fuselage, with at least one hydraulic actuator connected to the missile fuselage, which hydraulic actuator is connected to the missile fuselage such that the hydraulic actuator is able to push the additional tube and force the additional tube to move between the fore end and the aft end of the missile fuselage, such that as the additional tube is moved the additional tube can be pressed against the said stems, such that as the additional tube presses against the stems, the respective fins are rotated in a pivoting manner with respect to the tube that is able to rotate relative to the missile fuselage, with the stems of such relative lengths with respect to one another and with the stems connected to the respective fins such that the said fins can be rotated in the said pivoting manner and in the same direction as each other such that one of the said fins can be pivotly rotated to a greater degree relative to the tube that is able to rotate relative to the missile fuselage than can another of the said fins be rotated relative to tube that is able to rotate relative to the missile fuselage.  
     
     
         13 . The missile of  claim 12  wherein the said stems are positioned such that they extend longitudinally with respect to the missile fuselage of the missile.  
     
     
         14 . The missile of  claim 12  wherein the additional tube is in the form of a ring.  
     
     
         15 . The missile of  claim 12  wherein an additional hydraulic actuator is connected to the missile fuselage, which additional hydraulic actuator is connected to the missile fuselage such that as hydraulic pressure is applied to the additional hydraulic actuator, the additional hydraulic actuator is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the additional hydraulic actuator and the tube that is able to rotate around the missile fuselage.  
     
     
         16 . The missile of  claim 12  wherein a lever is connected to the missile fuselage, which lever is connected to the missile fuselage such that the lever is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the lever and the tube that is able to rotate around the missile fuselage.  
     
     
         17 . The missile of  claim 1  wherein an additional hydraulic actuator is connected to the missile fuselage, which additional hydraulic actuator is connected to the missile fuselage such that as hydraulic pressure is applied to the additional hydraulic actuator, the additional hydraulic actuator is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the additional hydraulic actuator and the tube that is able to rotate around the missile fuselage.  
     
     
         18 . The missile of  claim 1  wherein a lever is connected to the missile fuselage, which lever is connected to the missile fuselage such that the lever is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the lever and the tube that is able to rotate around the missile fuselage.  
     
     
         19 . The missile of  claim 2  wherein an additional hydraulic actuator is connected to the missile fuselage, which additional hydraulic actuator is connected to the missile fuselage such that as hydraulic pressure is applied to the additional hydraulic actuator, the additional hydraulic actuator is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the additional hydraulic actuator and the tube that is able to rotate around the missile fuselage.  
     
     
         20 . The missile of  claim 2  wherein a lever is connected to the missile fuselage, which lever is connected to the missile fuselage such that the lever is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the lever and the tube that is able to rotate around the missile fuselage.  
     
     
         21 . The missile of  claim 3  wherein an additional hydraulic actuator is connected to the missile fuselage, which additional hydraulic actuator is connected to the missile fuselage such that as hydraulic pressure is applied to the additional hydraulic actuator, the additional hydraulic actuator is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the additional hydraulic actuator and the tube that is able to rotate around the missile fuselage.  
     
     
         22 . The missile of  claim 3  wherein a lever is connected to the missile fuselage, which lever is connected to the missile fuselage such that the lever is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the lever and the tube that is able to rotate around the missile fuselage.  
     
     
         23 . The missile of  claim 4  wherein an additional hydraulic actuator is connected to the missile fuselage, which additional hydraulic actuator is connected to the missile fuselage such that as hydraulic pressure is applied to the additional hydraulic actuator, the additional hydraulic actuator is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the additional hydraulic actuator and the tube that is able to rotate around the missile fuselage.  
     
     
         24 . The missile of  claim 4  wherein a lever is connected to the missile fuselage, which lever is connected to the missile fuselage such that the lever is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the lever and the tube that is able to rotate around the missile fuselage.  
     
     
         25 . The missile of  claim 9  wherein an additional hydraulic actuator is connected to the missile fuselage, which additional hydraulic actuator is connected to the missile fuselage such that as hydraulic pressure is applied to the additional hydraulic actuator, the additional hydraulic actuator is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the additional hydraulic actuator and the tube that is able to rotate around the missile fuselage.  
     
     
         26 . The missile of  claim 9  wherein a lever is connected to the missile fuselage, which lever is connected to the missile fuselage such that the lever is able to be pressed against the tube that is able to rotate around the missile fuselage such that friction can be induced between the lever and the tube that is able to rotate around the missile fuselage.