FR2534370A1 - DEVICE INTENDED FOR ATTACK ON OVERVIEW OF OBJECTIVES SUCH AS ESPECIALLY ARMORED - Google Patents

Abstract

MACHINE INTENDED FOR THE OVERFLIGHT ATTACK OF OBJECTIVES SUCH AS IN PARTICULAR ARMOR AND WHOSE MILITARY HEAD CONTAINS A HOLLOW LOAD, CHARACTERIZED IN THAT IT IS ORGANIZED IN A WAY THAT, AT THE DESIRED POINT OF ITS OVERFLIGHT TRAJECTORY OF THE 'OBJECTIVE, ONLY HIS MILITARY HEAD IS DIRECTED TOWARDS THE OBJECTIVE.

Description

The present invention relates to improvements in gear

  intended for the fight against armored vehicles.

  We have been moving for some time, in the fight against armored vehicles, towards the use of devices whose attack is no longer, like that of conventional devices, a direct attack, in taut shooting, of the faces, frontal or lateral

  armored, hypothetically strongly or skillfully defended, but an attack

  that when flying over the blind, to reach surfaces, much more vulnerable

  by construction, of such a target.

  The machines of this new generation are therefore fired, or launched, following a trajectory which leads them to fly over the armored vehicle on the surface

  from which they are then directed, at the desired time and distance.

  In accordance with the present invention, liengin, the characteristics of which

  mass, launch, propulsion, military head design, can be very diverse and as they can make the anti-tank weapon of a foot combatant, is arranged so that, at desired point of its trajectory over the target, only its military head

is aimed at this target.

  According to a first embodiment of the invention, the device is organized in two parts, one of which contains or constitutes the military head and is provided with at least one means such as an impeller causing, to the point

  wanted from the trajectory, the attachment of the machine to the armored vehicle, the body of the

  gin being produced or provided with at least one means for causing the separation of the two parts of the machine, the military head being alone directed towards the armored vehicle.

  According to another embodiment of the invention, the mili-

  shutter is pivotally mounted in the body of the machine so as, at the desired point of its trajectory and under the action of an impeller, to protrude out

  of the machine, in the direction of the target constituted by the armored vehicle.

  The various characteristics and advantages of the invention will emerge

  of the description which follows of two of its possible forms of realization

  It is clearly stated that these are only examples and that all

  other provisions could be adopted without departing from the scope of the invention

tion. -2-

  During this description, reference is made to the attached drawings.

  which show: Fig 1 a schematic view in longitudinal section of a machine according to the invention in a first embodiment, Fig 2 a schematic view of its operating mode, Fig 3 and 4 similar to Fig 1 and 2, of a second embodiment

of such a craft.

  4 In the example treated in Fig 1 and 2, the body I of the machine is organized in two parts, a rear part A (see Fig 2) and a front part B, assembled to each other in such a way that, under the conditions which will be described later, they can separate For example in the case treated, they are connected by a zone of weakening represented

schematically has a body 1.

  The rear part A has a tail 2, a thruster

  acceleration or cruising 3.

  The front part B is provided with a hollow charge 4, initiated by a rocket 5 to which is coupled a verticality detector 6 and an opto-electronic detector 7 associated with a reflector 8 In the warhead la, connected to the body 1 of the machine, are housed a radial impeller 9 and a generator 10 linked

  to the impeller and capable of supplying all or part of the energy required

  fit the various electrical equipment of the machine The generator is

  trafficked in rotation thanks to the rotation printed on the machine to stabilize it

on trajectory.

  However, the radial impeller 9 and the sighting system (reflector 8) are isolated in rotation, thanks in the example treated to mounting on bearings

  (11) They are stabilized in a vertical position by their own unbalance.

  The hollow charge 4 is initiated by the pyrotechnic rocket 5 at the instant when the front part of the machine A is turned towards the target in a substantially vertical direction. This direction can be defined by a

  system linked to the rocket such as, in the example treated, the vertical

cality 6.

  -3- Fig 2 represents the successive phases of the trajectory

  followed by the vehicle when approaching an armored vehicle The vehicle first follows a trajectory

  overflight approach roof (positions I and II) The optoelectronic detector 7, continuously energized, emits signals at close regular intervals, oriented by the reflector 8 The detection angle is chosen to

  so that the location of the armored vehicle is carried out early enough to remain

pect the timeline.

  The detector must recognize the armored vehicle and must not be influenced

  by any small metal part This is why more

  it needs several successive tops to trigger the following process (positions III and IV): the radial impeller 9 exerts a thrust such that the warhead begins to pivot downwards by breaking the machine in its middle, thanks to the zone weakening of the body 1, the pivoting speed of the head is accelerated by the combined action

  aerodynamic forces exerted on the machine and by that of the impulse

sister 9.

  The military head being then brought into desired position and situation

  (position V) the shaped charge is started and ignited.

  The shaped charge can be initiated in two ways: remotely by a verticality detector or an overdue attack delay system,

  or on impact when the nose of the warhead comes into contact with the armored vehicle.

  It should be noted that a judiciously adapted swivel speed of the warhead makes it possible to increase the time of coincidence of the axis of the load with the center of the armored vehicle. This particularity allows priming.

  of the shaped charge in a longer time interval.

  In the context of the example treated, the non-rotating part of the

  gin, that which contains the impeller and the reflector is considered to be stabilized by its own unbalance, The precision of the stabilization in rotation is directly linked to the moment of inertia of the stabilized element, to the restoring torque exerted by the unbalance , and to the resistant friction and / or rolling torque in the -4-

link her.

  The connection between the non-rotating part of the machine, and its part driven by a rotational movement must achieve a precise angular reference (verticality of the detection plane) and must operate under strong accelerations. This connection can be carried out by means of bearings which must satisfy the following conditions to oppose the angular acceleration to which the vehicle is subjected to launch resist the transverse and axial accelerations to which the vehicle is subjected during the phases of launch and flight, have a very low coefficient of friction and / or rolling,

  have a sufficient rotational damping coefficient for sta-

  quickly mobilize the imbalance, be of a small mass and dimensions so as not to endow the machine

  of an unacceptable mass and dimensions.

  In order to satisfy these conditions, all types of bearings or stops can be used without departing from the scope of the invention: gas fluid bearings, the energy necessary for the flow of the fluid can be generated when the machine is launched, or by the displacement of a mass which by inertia compresses a gas trapped in a chamber, or even by a compressed gas generator initiated at the launch of the machine,

  hydraulic bearings, with hydrostatic or hydrodynamic lubrication

mique,

magnetic bearings.

  It is also possible to use various combinations of mounting on bearings such as thrust ball bearings and ball bearings, thrust bearings

  needles and needle bearings, tapered roller bearings, roller

angular contact elements.

  Furthermore, in the context of the example treated, the connection between the rear part (containing the propellant and the guidance system) and the front part (containing the military charge and the opto-electronic detector)

-2534370

  of the machine must be such as to ensure, under the conditions

  discussed above, the separation between the two parts of the craft.

  This highly requested link must meet the conditions

  following s: transmit the intense accelerations resulting from the thrust of the propellant

  aerodynamic friction, rotation, as well as

  brations to which the craft is subjected during the different phases of the flight, keep the front and rear parts of the craft perfectly aligned throughout the trajectory, be of a mass and dimensions as small as possible,

  offer minimal resistance to the action of the impeller.

  In accordance with the invention, this rupture can be achieved by

  the simple mechanical effect of the impeller shock, an electrical decoupling

  stick or pyrotechnic or any other suitable means.

  In the embodiment shown in Fig 3 the body

  of the machine is in two parts, part C animated by a movement of ro-

  part and part D not rotating The rotating part contains a pro-

  acceleration or cruising blower 12 and is provided with a tail unit 13.

  In the non-rotating part are housed a pyrotechnic rocket

  with safety device 14, a shaped charge 15 and a radial impeller 170

  mment to the invention, the shaped charge 15 is pivotally mounted about an axis 15 a perpendicular to the longitudinal axis of the machine

  rotating also contains an opto-electronic detector 16 and optionally

  LEMENT a generator 18 linked to the impeller 17 and driven in rotation, sus-

  capable of providing all or part of the energy necessary for the different

  equipment placed on board the craft.

  The operation is that described in connection with the form of reaction

  reading shown in; Fig 1 except that, in position

  of attack of the armored vehicle (position III), the shaped charge 15 under the action of the im

  blower 17 and due to its mounting on axis 15 has pivots, to make

  projection, for example by a hatch formed in the body of the machine, per-

  thus putting a jet of hollow charge carried out under optimal conditions.

  -6 - What was said above about the connection between the rotating and non-rotating parts of the machine also applies to this embodiment, the same means can be used to achieve this

link her.

  In both embodiments the example treated relates

  to an individual anti-tank infantry weapon It is quite obvious that the Pinven-

  tion is not limited to such an example and that it can be applied to any device capable of being used in the fight against armored vehicles.

  constructive measures described are of course not the only ones that can

  see be adopted and the invention can give rise to many variants without departing from its scope. This is for example the case that the machine may not be driven in a rotational movement It may be of a constant caliber and also be equipped with a military head of a caliber different from that of the propellant The non-rotating part of the machine stabilized by its own unbalance can be maintained in a fixed direction by any other mechanical, aerodynamic or electrical device As detector, can

  be used, instead of the opto-electronic detector, a magnetic detector

  tick, or Doppler effect, or a laser detector.

  radial sor, positioned at the end of the warhead can be placed in another place

  allowing the pivoting of the military head.

7 2534370

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Claims (7)

  1 Machine intended for attack on overflight of objectives such as in particular   armored vehicles, the military head of which contains a hollow charge,   characterized in that it is arranged in such a way that, at the desired point of its travel   jectory of overflight of the objectives only its military head is directed towards the   jective. 2 machine according to claim I characterized in that it is organized in two parts, one of which contains or constitutes the military head and is provided with at least one means, such as an impeller, causing to the point   wanted from the trajectory, the apiquing of the machine on the objective, the body of the   gin being organized, or provided with at least one means, to cause separation   tion of the two parts of the machine, the military head being only directed towards the objective. 3 Machine according to claim 1 characterized in that the military head is pivotally mounted in the body of the machine so, at the desired point of its trajectory and under the action of a means such as an impeller,   to protrude from the craft, specially organized for this purpose, directly tion of the objective.   4 machine according to claim 2, gyrostabilized on trajectory characterized in that the military head contains, in addition to the hollow charge and its firing rocket, an opto-electronic detector system and an impeller arranged radially as well as possibly a generator put in rotation by the rotation of the machine and intended to supply energy to the systems of sight and the rocket.   Machine according to claim -4, characterized in that it comprises   door, coupled to the rocket, a verticality detector.   6 Machine according to any one of claims 2, 4 and 5,   characterized in that the connection between the military head and the rest of the device is designed so as to preserve the integrity of the device up to the desired point of its trajectory while allowing their separation only under the effect of the impeller.   7 machine according to claim 6 characterized in that the connection between the military head and the rest of the machine consists of a weakening zone -8 causing the rupture at its level, of the two parts of the machine, by simple effect mechanical shock determined by operation of the impeller.   8 Machine according to any one of claims 2 and 5 to 7,   characterized in that the impeller and the part of the optoelectronic system   directing the pulses supplied by the detector are subtracted from the rotation   tion printed on the machine by means such as hydraulic bearings, magnesium   ticks, fluid, thrust ball bearings and ball bearings.   9 Machine according to claim 3 characterized in that the head te   member of the machine comprising, in addition to the hollow charge and its starter rocket,   çage, the radial impeller and the detection means, is mounted at the height of the top of the hollow charge coating, on an axis perpendicular to   the longitudinal axis of the machine, the body of the latter being arranged to   put the projection, out of the craft, of the military head.   10 Machine according to any one of claims 3, 8 and 9   characterized in that its body is in two parts, a front part forming the military head and a rear part stabilized in rotation, the two parts being connected by one or means according to claim 8, intended to remove the front part from rotation printed on the back of the craft.