Device with remote motor for controlling an aerodynamic control surface of a missile

Abstract

An aircraft comprising at least one aerodynamic control surface ( 26 ) controlled using a remote motor ( 4 ), through a transmission comprising a linear device ( 7 ) rigid in torsion but flexible in bending and in tension and compression, to absorb thermomechanical deformations. This transmission comprises small clearances, good flexibility, does not require any additional support and makes favourable use of a reduction gear ( 9 ) located near the control surface ( 26 ) rather than near the motor ( 4 ).

1 . Device for controlling a missile aerodynamic control surface also comprising a motor element ( 1 ) performing a rotation movement and a transmission element ( 2 ) extending between the motor and the control surface ( 26 ) to transfer a movement correlated to the motor rotation movement to the control surface, device characterised in that the transmission element comprises a linear device ( 7 ) rigid in torsion, but flexible in tension, compression and bending, in that it comprises a reduction gear ( 9 ) located between the linear device and the control surface, and in that the linear device is limited by at least one sliding connecting element.  
   
   
       2 . Device for controlling a missile aerodynamic control surface according to  claim 1 , characterised in that the transmission element comprises a movement conversion jack ( 10 ) for converting the rotation movement into a translation movement, comprising a portion ( 11 ) subject to the translation movement and articulated to a lever ( 15 ) for controlling the control surface ( 26 ), and a portion ( 18 ) subject to the rotation movement and coupled to the linear device.  
   
   
       3 . Device for controlling a missile aerodynamic control surface according to  claim 1 , characterised in that the linear device comprises shaft segments ( 20 ,  21 ,  22 ) assembled together through universal joints ( 23 ,  24 ).  
   
   
       4 . Device for controlling a missile aerodynamic control surface according to  claim 1 , characterised in that the linear device comprises a flexible shaft.  
   
   
       5 . Device for controlling a missile aerodynamic control surface according to  claim 1 , characterised in that the sliding connecting element is a coupling with a grooved pin and bushing ( 16 ,  17 ).  
   
   
       6 . Device for controlling a missile aerodynamic control surface according to  claim 1 , characterised in that the reduction gear comprises an associated ball screw ( 11 ) and a nut ( 18 ) assembly.  
   
   
       7 . Device for controlling an aerodynamic control surface according to  claim 2 , characterised in that the reduction gear is a bevel reduction gear located between the jack ( 10 ) and the linear device ( 7 ).  
   
   
       8 . Device for controlling an aerodynamic control surface according to  claim 1 , characterised in that the motor is a brushless electric motor.