FR2572514A1 - OPTO-ELECTRONIC IMPACT DETECTOR FOR MISSILES, ROCKETS AND THE LIKE - Google Patents

Abstract

OPTO-ELECTRONIC OPERATION TARGET IMPACT DETECTOR, FOR MISSILES, ROCKETS AND SIMILAR MACHINERY, CHARACTERIZED IN THAT IT INCLUDES A 6-9 OPTICAL FIBER SYSTEM COUPLED TO A TRANSMIT-RECEPTION SYSTEM 7 TRANSMITTING THE FOCUS A FIRE OF THE MILITARY LOAD OF THE MACHINE, THE OPERATION BEING OBTAINED BY DETECTION OF THE VARIATION OF THE LUMINOUS FLOW IN THIS FIBER SYSTEM.

Description

The present invention relates to an impact detector for

missiles and

similar gear.

  We know that most missiles, rockets or other devices use electric fires to initiate their military charge. These fires are triggered by impact detectors of various kinds: warhead of

  contact for establishing or breaking a circuit, inertia contact, piezo sensor

  electrical, or any other electrical device.

  All of these known systems have a major drawback: they are

  sensitive to electromagnetic attack. They are, moreover, often com-

  folded, expensive, bulky or poorly performing.

  The object of the impact detector of the present invention is to alleviate

all of these drawbacks.

  To this end, the invention relates to an opto-electronic impact detector

  which detects the impact of a machine, missile, rocket or other pro-

  jectile on a target, and the transmission of the impact signal, optically.

  The impact detector according to the invention is essentially characterized

  in that it includes a fiber optic system coupled to an emission system

  Zion-reception which transmits the firing signal to the rocket circuit of the missile. According to an exemplary embodiment of this invention, the optical fiber system consists of a network of optical fibers forming a set of several closed branches on a light emission-reception device,

  said branches having a continuity solution constituted by an over-

  reflecting surface, so that it ensures, depending on its position by

  with respect to optical fibers, either continuity or interruption of the light flux

neux issued.

  According to another characteristic of the invention, the link between the network

  of optical fibers and the firing circuit is carried out by an opto-

  electronic, ensuring both the emission and the reception of the light signal from the electrical supply of the machine; the variation of the luminous flux is

  transformed into an electrical signal, by this device according to the invention.

  The various other characteristics of the invention follow from the examples

  described below, with reference to the accompanying drawings. It is clearly stated, however

  dant, that they are only examples, and that all other arrangements, forms, proportions, modes of construction, can also be used,

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  without departing from the scope of the invention.

  In the attached drawings: - Figure 1 is a perspective view of an opto-electronic impact detector according to the invention, for projectile, missile, rocket with head comprising a self-director; - Figure 2 is a longitudinal sectional view of a deployable antenna for projectile warhead, missile or missile object of the applicant's patent No. 79 09 696, filed April 18, 1979, said warhead assembly being equipped, according to l invention, an opto-electronic impact detector. The upper half-view represents the antenna in the deployed position. The lower half-view represents the antenna in the storage position; and, - Figure 3 is a longitudinal sectional view of an antenna, deployable by borrowing gas, for projectile warhead, equipped, according to the invention, with a

  opto-electronic impact detector. The upper half view represents the year

  in the deployed position. The lower half-view shows the antenna in posi-

tion storage.

  Figure 1 shows a nonlimiting example of a detector

impact according to the invention.

  A missile 1 is equipped with a Z warhead with a search or self-directing head

  3, comprising a window 4. The edge of the window is provided with a reflective surface.

chissant 5 according to the inventi on.

  Along the walls of the warhead 2, and at the base thereof, is arranged the

  fiber optic system 6 according to the invention, connected to a transmission boot

  reception 7, in electrical connection with the firing circuits 8 of the missile.

  In this nonlimiting exemplary embodiment, the fiber system 6 is in the form of a network of six pairs of optical fibers such as 9,

  which come to the reflecting surface 5 of the window 4, by means of

  diary of an optical device 10. Each pair of optical fibers comprises a

  "outward" fiber, such as 9 ', and a "return" fiber, such as 9 ".

  The operation is as follows: The opto-electronic device 7 emits a light signal as soon as it is energized by the arming boot. The luminous flux passes through the fibers

optics 6.

  If we consider a pair of optical fibers 9, the light flux emitted by the device 7 travels through the "go" fiber 9 'and reaches the reflecting surface

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  by means of the optical device 10. It is reflected by this surface 5, and returns, by the "return" fiber 9 ", to the emission-reception device 7, which

turns into current.

  On impact, the reflecting surface 5 is displaced relative to the arrangement

  sitive 10. A variation in the luminous flux then takes place, which is transformed into a variation in current by the transmission-reception device.

  emitted is returned to circuit 8 firing the military charge of the missile.

  Another embodiment of the invention is shown in Fig.

gure 2.

  This example shows the principle and the deployment mode of an antenna

  according to the patent filed by the applicant on April 18, 1979 under No. 79 09 696.

  In this Figure 2, there is shown the missile 11 equipped with a warhead 12 which has in its axis a channel 13 in which slides, according to the invention, an antenna 14 of composite material, preferably. At the rear part of this antenna 14 there is, on the external wall, a reflecting ring 15 according to the invention, preferably of small size. The end of the antenna 14 ends in a tip 16 of cellular material, preferably rigid. This

  antenna 14 is held in place by a pin 17. The antenna 14 according to the in-

  vention can slide in a guide sleeve 18, preferably made of a material

  posite. This sleeve 18 contains a rod 19. Along the walls of the warhead 12 is

  find, according to the invention, pairs of optical fibers 20, 20 'which abou-

  weave into the sleeve 18. The antenna 14, in the folded position, keeps it energized

a spring 21.

  The operation is as follows At the start of the blow, the acceleration of the machine drives, according to the invention, the antenna 14 towards the rear, shearing the pin 17. When the acceleration ceases, the spring 21 relaxes, and it feeds the antenna forward, until the

  rod 19 is placed in a housing 22, provided in the antenna 14.

  The reflecting ring 15 is placed opposite the pairs of fibers

  optics 20, 20 '. The detection system is then armed according to the invention.

  tion. On impact, the movement of the antenna 14 in the guide sleeve 18, thanks to the shape of the housing 22 which allows a certain play, for example, causes the misalignment of the reflecting ring 15 and the pairs of optical fibers 20 , 20 ′ and the interruption of the luminous flux, according to the invention, which causes the

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  functioning of the military charge.

  Another embodiment of an impact detector according to the invention

is shown in Figure 3.

  In this variant, the missile comprises a warhead 12 ', provided, along its axis, with a channel 13'. In this channel slides a hollow antenna 14 ', preferably

made of composite material.

  At the rear part of this antenna 14 ′ is located, on the external part, the reflecting ring 15 ′ according to the invention, preferably of small dimensions,

  placed opposite the pairs of optical fibers 20, 20 '. On the inner wall of the an-

  A tenne according to the invention is a detonating cord 23 wound in a spiral and

  linked, at the base of the antenna, to a transmission relay 24. The end of the antenna

  14 ′ tenne is terminated by a 16 ′ point made of cellular material, rigid of pre-

  ference. This antenna is pinned, in the retracted position, by a pin 17 ',

as previously described.

  The pairs of optical fibers 20, 20 ′ end up at the guide sleeve

18 'from the antenna.

  Along the channel 13 'are a transmission cord 25 and its

relay 26.

  The operation, according to the invention, is as follows At the time of launching the missile, the antenna 14 ′ is deployed outside the warhead 12 ′, for example by a gas borrowing system using the gases of the cruise thruster , for example acting on the bottom 27 of the antenna

  14, shearing the retaining pin 17 '.

  When the antenna 14 'is in the deployed position, there is alignment of the pyrotechnic hinge, constituted by the detonating cord 23 and its relay 24, and the transmission cord 25 and its relay 26. The reflecting ring 15' comes place, according to the invention, opposite the pairs of optical fibers 20, 20 ′, and

  and there is arming of the detection system according to the invention.

  On impact, the antenna 14 'begins to retreat relative to the warhead 12' of the missile, and there is a misalignment between the optical fibers 20, 20 'and the reflecting ring 15'. The interruption of the resulting light circuit then causes, according to the invention, the firing order. The detonation is

  transmitted to the transmission line 25, then to the military charge of the missile.

  Relays 26 and 24 being still aligned, the detonation propagates in the cor-

  water 23 and destroys the antenna, which eliminates, according to the invention,

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  an obstacle which could disturb the operation of the military shaped charge,

  at least in the event of impact with incidence.

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Claims (8)

  1 - Target impact detector with opto-electronic operation, for missiles, rockets and similar devices, characterized in that it comprises a system of optical fibers (6-9) coupled to a transmission-reception system (7 ) transmitting the signal for firing the military charge of the machine, the operation being obtained by detecting the variation of the light flux in said fiber system.   2 - Impact detector according to claim 1, characterized in that the optical fiber system consists of a network of pairs of optical fibers (9'-9 ") forming a set of several branches closed on the device emission-reception (7) of the light flux, said branches having a continuity solution (5-10) ensuring, according to its position relative to the fibers   optical, either continuity or interruption of the luminous flux.   3 - Impact detector according to one of claims 1 or 2, characterized   in that the transmission-reception device (7) transforms the variation in the flow   luminous in a variation of electric current, the signal thus emitted being trans-   set to the firing circuit (8) of the military charge.   4 - Impact detector according to any one of the preceding claims.   teeth, characterized in that the pairs of optical fibers comprise forward fibers (9 ') and return fibers (9 "), ensuring the emission and reception of the light flux, these return fibers presenting a solution between them of continuity (10).   - Impact detector according to any one of the preceding claims.   teeth, characterized in that the optical fibers (9) are interconnected by a reflecting system (5).   6 - Impact detector according to claim 5, characterized in that said reflecting system (5) is constituted by the internal face of the warhead (2)   of the craft, so that its deformation or destruction, on impact,   on the interruption, at least partially, of the transmission of the luminous flux   between the forward fiber (9 ') and the return fiber (9 "), causing ignition.   7 - Impact detector according to one of claims 5 or 6, characterized   in that said reflecting system (5) is formed at the periphery of the window   nêtre (4) of the self-director (3) of the machine.   8 - Impact detector according to any one of the preceding claims.   teeth, characterized in that the continuity of the pairs of optical fibers go 7 2572514   (20) and return (20 ') is ensured by transmission through a antenna   foldable (14) comprising reflecting surfaces (15), this antenna (14) being deployed under the effect of a spring (21), and locked in a position   which also ensures the arming of the detector system, by positioning   said reflective surfaces (15) facing the pairs of optical fibers (20-20 '), the misalignment, on impact, of these elements, when the antenna is moved relative to the warhead, causing the interruption luminous flux   and the firing of the military charge of the device.   9 - impact detector according to any one of claims 1 to 7,   characterized in that the continuity of the pairs of optical fibers going (20) and returning (20 ') is ensured by transmission through a deployable antenna (14') comprising reflecting surfaces (15 '), and in that said antenna is   provided with self-destruction means acting after impact detection, the ar-   ment of the detection system, by positioning said reflected surfaces   chissant (15 ') opposite the pairs of optical fibers (20, 20'), taking place   when the antenna is in the deployed position, at the same time as the alignment is   ment of the pyrotechnic firing chain of the antenna self-destruction means, the misalignment, on impact, between the optical fibers (20, 20 ') and the reflective surfaces (15'), during the movement of the antenna in relation to the warhead, causing the interruption of the luminous flux, the ignition of the charge   military, and the destruction of the antenna.   - Impact detector according to claim 9, characterized in that the self-destruction means, on impact, of the deployable antenna, are constituted   a detonating cord (23) wound in a spiral inside the antenna.