公开(公告)号：WO1990005888A1

公开(公告)日：1990-05-31

申请号：PCT/US1989004486

申请日：1989-10-12

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  SCHOTTER, Daniel, K.

IPC: F41G07/32

CPC classification number: G02B6/4478 ,  F41G7/32 ,  F42B15/04

Abstract: A fiberoptic leader (20) connected between a missile (10) and a launch tube is laid out upon missile launch with a controlled degree of bend in the fiberoptic filament (50), and is furthermore protected from blast effects in the launch. The fiberoptic filament (50) is stiffened within a leader (30) comprised of a Teflon R sleeve (52) insulating the fiberoptic filament (50). A protective sheathing of high tensile strength longitudinally wires (54) are disposed about and encase the Teflon R sleeve (52), and in turn are encased within an outer sleeve. The stiffened leader is led along the longitudinal length of a retainer (20) attached to the side of the missile. The retainer (20) is disposed upon a longitudinal portion of the missile in a channel. The stiffened leader (20) is laid against and under one of the retainer arms from the aft end of the missile (10), where the fiberoptic leader (30) is fed out during launch, to a forward end of the missile (10) and retainer (20). The leader (30) is then led across the width of the channel to the opposing arm of the channel. The stiffened leader (30) is then led partly aft along the opposing arm of the retainer (20) and then out to an open longitudinal slot defining the ends of the channel and is coupled to a fixed point within the launch tube from which point optical communications are provided to the missile (10) during flight. As the missile (10) is launched, the bend propagates down the retainer (20) tearing the stiffened leader from a longitudinally perforated tape which secures the leader (30) into and under one of the arms of the retainer (20).

公开(公告)号：WO1990006893A1

公开(公告)日：1990-06-28

申请号：PCT/US1989004901

申请日：1989-11-06

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  SCHOTTER, Daniel, K.

IPC: B65H57/12

CPC classification number: B65H57/12 ,  B65H2701/31

Abstract: A fiber guide (10) includes a sleeve (12) having a longitudinal slot (14) therealong, a first member (16) having a notch (26) is fixed in the sleeve with the notch substantially aligned with the slot (14). A second member (20), also having a notch (28), is rotatably disposed in the sleeve (12). Thus, a fiber can be positioned in the notches (26, 28) of the first and second members (16, 20) and secured therein by rotating the second member (20). The fiber can also be readily removed from the guide (10), without damage or impediment, by reversing the rotation of the second member (20).

公开(公告)号：EP0400140A1

公开(公告)日：1990-12-05

申请号：EP90901142.0

申请日：1989-11-06

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： SCHOTTER, Daniel, K.

IPC: B65H ,  B65H57

CPC classification number: B65H57/12 ,  B65H2701/31

Abstract: Un guide (10) pour une fibre comprend une gaine (12) ayant une fente longitudinale (14) le long de la gaine, un premier élément (16) ayant une entaille (26) est fixé dans la gaine avec l'entaille sensiblement alignée avec la fente (14). Un second élément (20) ayant également une entaille (28) est disposé de manière rotative dans la gaine (12). Ainsi, on peut positionner une fibre dans les entailles (26, 28) des premier et second éléments (16, 20) et la fixer à l'intérieur par rotation du second élément (20). On peut retirer aisément la fibre du guide (10) sans provoquer de dommage en inversant la rotation du second élément (20).

公开(公告)号：EP0400140B1

公开(公告)日：1993-01-13

申请号：EP90901142.1

申请日：1989-11-06

Applicant: Hughes Aircraft Company

Inventor： SCHOTTER, Daniel, K.

IPC: B65H57/12

CPC classification number: B65H57/12 ,  B65H2701/31

Abstract: A fiber guide (10) includes a sleeve (12) having a longitudinal slot (14) therealong, a first member (16) having a notch (26) is fixed in the sleeve with the notch substantially aligned with the slot (14). A second member (20), also having a notch (28), is rotatably disposed in the sleeve (12). Thus, a fiber can be positioned in the notches (26, 28) of the first and second members (16, 20) and secured therein by rotating the second member (20). The fiber can also be readily removed from the guide (10), without damage or impediment, by reversing the rotation of the second member (20).

公开(公告)号：EP0396706B1

公开(公告)日：1994-02-02

申请号：EP89912552.0

申请日：1989-10-12

Applicant: Hughes Aircraft Company

Inventor： SCHOTTER, Daniel, K.

IPC: F41G7/32 ,  F42B15/04

CPC classification number: G02B6/4478 ,  F41G7/32 ,  F42B15/04

Abstract: A fiberoptic leader (20) connected between a missile (10) and a launch tube is laid out upon missile launch with a controlled degree of bend in the fiberoptic filament (50), and is furthermore protected from blast effects in the launch. The fiberoptic filament (50) is stiffened within a leader (30) comprised of a Teflon R sleeve (52) insulating the fiberoptic filament (50). A protective sheathing of high tensile strength longitudinally wires (54) are disposed about and encase the Teflon R sleeve (52), and in turn are encased within an outer sleeve. The stiffened leader is led along the longitudinal length of a retainer (20) attached to the side of the missile. The retainer (20) is disposed upon a longitudinal portion of the missile in a channel. The stiffened leader (20) is laid against and under one of the retainer arms from the aft end of the missile (10), where the fiberoptic leader (30) is fed out during launch, to a forward end of the missile (10) and retainer (20). The leader (30) is then led across the width of the channel to the opposing arm of the channel. The stiffened leader (30) is then led partly aft along the opposing arm of the retainer (20) and then out to an open longitudinal slot defining the ends of the channel and is coupled to a fixed point within the launch tube from which point optical communications are provided to the missile (10) during flight. As the missile (10) is launched, the bend propagates down the retainer (20) tearing the stiffened leader from a longitudinally perforated tape which secures the leader (30) into and under one of the arms of the retainer (20).

公开(公告)号：EP0396706A1

公开(公告)日：1990-11-14

申请号：EP89912552.0

申请日：1989-10-12

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： SCHOTTER, Daniel, K.

IPC: F41G7 ,  F42B15 ,  G02B6

CPC classification number: G02B6/4478 ,  F41G7/32 ,  F42B15/04

Abstract: Un guide à fibres optiques (20) relié entre un missile (10) et un tube de lancement est déroulé lors du lancement du missile avec un degré de courbure commandé dans le filament à fibres optiques (50) et est de plus protégé des effets de l'explosion lors du lancement. Le filament en fibres optiques (50) est renforcé à l'intérieur d'un guide (30) comprenant une enveloppe Teflon R (52) qui isole les fibres optiques (50). Des gaines protectrices de forte résistance à la traction longitudinale (54) sont disposées autour de l'enveloppe Teflon R de façon à l'entourer, et à leur tour sont enveloppées par une enveloppe extérieure. Le guide renforcé est amené le long d'une piste de retenue (20) fixée sur le côté du missile. La piste de retenue (20) est placée dans une gorge sur une partie longitudinale du missile. Le guide renforcé (20) est fixé contre et sous l'un des bras de la piste de retenue depuis l'extrémité arrière du missile (10), où le guide à fibres optiques est déroulé pendant le lancement, vers une extrémité avant du missile (10) et de la piste de retenue (20). Le guide (30) traverse la longueur de la gorge jusqu'au bras opposé de celle-ci. Le guide renforcé (30) revient alors partiellement en arrière le long du bras opposé de la piste de retenue (20) et ensuite vers une encoche longitudinale ouverte qui détermine les extrémités de la gorge, et est relié à un point fixe à l'intérieur du tube de lancement à partir duquel des communications optiques sont fournies au missile (10) pendant le vol. Lors du lancement du missile (10), la partie courbée est transmise le long de la piste de retenue (20) en arrachant le guide renforcé d'une bande perforée longitudinalement qui fixe le guide (30) contre un des bras de la piste de retenue (20) et en-dessous dudit bras.