公开(公告)号：WO1987002764A1

公开(公告)日：1987-05-07

申请号：PCT/US1986001981

申请日：1986-09-22

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  HERRMANN, Werner ,  MALIS, Albert

IPC: F42B15/027

CPC classification number: F16B2/14 ,  F16B2200/30 ,  F42B10/06 ,  Y10T403/1641 ,  Y10T403/595 ,  Y10T403/61

Abstract: A coupling mechanism for quick attach/disconnect of a control fin to a missile which does not require the use of a separate tool to make the attachment. A first coupling member 24 is mounted on the control fin actuator rod 16. A force regulating means comprised of a spring 28 and retainer bracket 58 are attached to the first coupling member. A second coupling member 26 and a pivotable lever arm 38 are formed as part of the control fin. When the second coupling member is loosly fitted upon the first coupling member, rotation of the lever arm will engage the force regulating means thereby deflecting the spring 28. The reactive force of the spring is exterted through the lever arm, through the control fin, and causes the second coupling member to firmly and securely engage the first coupling member. A means is provided to lock the lever arm in place so as to retain the first and second coupling members in the firmly engaged position even through extreme aerodynamic maneuvers. The lock is easily disengaged manually should it be necessary to remove a control fin from the missile.

公开(公告)号：EP0250454A1

公开(公告)日：1988-01-07

申请号：EP86906141.0

申请日：1986-09-22

Applicant: Hughes Aircraft Company

Inventor： HERRMANN, Werner ,  MALIS, Albert

IPC: B64C9 ,  F16B2 ,  F42B10

CPC classification number: F16B2/14 ,  F42B10/06 ,  Y10T403/1641 ,  Y10T403/595 ,  Y10T403/61 ,  Y10T403/7094

Abstract: Mécanisme de couplage pour la fixation/séparation rapide d'une ailette de direction de roquette ne nécéssitant pas l'emploi d'un outil séparé pour effectuer la fixaton. Un premier organe de couplage (24) est monté sur la tige d'actionnement (16) de l'ailette de direction. Un organe régulateur de force comprenant un ressort (24) et un support de retenue (58) est fixé sur le premier organe de couplage. Un deuxième organe de couplage (26) et un bras de levier pivotant (38) font partie de l'ailette de direction. Lorsque le deuxième organe de couplage est monté avec du jeu sur le premier organe de couplage, la rotation du bras de levier actionne l'organe régulateur de force, ce qui provoque le fléchissement du ressort (28). La force de réaction du ressort s'exerce par l'intermédiaire du bras de levier, de l'ailette de direction et produit l'engagement fixe et fiable du deuxième organe de couplage dans le premier organe de couplage. Un autre organe permet de verrouiller en place le bras de levier afin de retenir les premier et deuxième organes de couplage dans la position d'engament fixe même en cas de sollicitations aérodynamiques extrêmes. Le verrou peut être dégagé aisément manuellement lorsqu'il est nécessaire de démonter une ailette de direction de la roquette.

公开(公告)号：EP0250454B1

公开(公告)日：1990-10-24

申请号：EP86906141.6

申请日：1986-09-22

Applicant: Hughes Aircraft Company

Inventor： HERRMANN, Werner ,  MALIS, Albert

IPC: F42B10/06

CPC classification number: F16B2/14 ,  F42B10/06 ,  Y10T403/1641 ,  Y10T403/595 ,  Y10T403/61 ,  Y10T403/7094

Abstract: A coupling mechanism for quick attach/disconnect of a control fin to a missile which does not require the use of a separate tool to make the attachment. A first coupling member (24) is mounted on the control fin actuator rod (16). A force regulating means comprised of a spring (28) and retainer bracket (58) are attached to the first coupling member. A second coupling member (26) and a pivotable lever arm (38) are formed as part of the control fin. When the second coupling member is loosly fitted upon the first coupling member, rotation of the lever arm will engage the force regulating means thereby deflecting the spring (28). The reactive force of the spring is exerted through the lever arm, through the control fin, and causes the second coupling member to firmly and securely engage the first coupling member. A means is provided to lock the lever arm in place so as to retain the first and second coupling members in the firmly engaged position even through extreme aerodynamic maneuvers. The lock is easily disengaged manually should it be necessary to remove a control fin from the missile.