FR2701558A1 - Method and device for attacking targets with submunitions - Google Patents

Abstract

Method of attacking targets (10) with submunitions (24) provided in a warhead (22), released by means of a thruster (20) on a ballistic trajectory (28), on which the thruster (20) is first separated from the head (22) at a height (Ha) then the sub-munitions (24) are released from the head (22), at a height (Hf). Prior to the separation of the warhead (22) from the thruster (20), the current atmospheric pressure, depending on the altitude, is measured and converted to the corresponding current height. The calculated height is adapted to the sum of the determined pre-programmed release height (Hf) and the drop height of the head (22), separated from the thruster (20) until the release of the submunitions (24) by determination of the corresponding fall height (Ha-Hf).

Description

In addition to the results of this study, we will be able to provide you with the information you need.

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  In this known device to be dropped by means of an aircraft, each sub-munition is preferably equipped with a microprocessor which can be programmed, with regard to the trigger height, so that, by example, an explosion occurs at 10 m in height, at 3 m from

  height, at a height of 0,5 m and at a height of 0 m above

above ground

  A method and device for targeting targets by means of submunition, ejected over a target territory, are described in DE 33 26 877 Ai of the applicant in this latter, to increase the probability from kick to goal and improve

  the offensive effect, the military head containing the sub-

  ammunition, or the cluster munitions container, is equipped with a parachute and a target detection device. A target attack method using a miniature bomb and a miniature bomb vector for carrying out this method are described in FIG.

  DE 33 19 824 Ai from the applicant.

  A method and a device of the aforementioned type are known from DE 37 39 370 C 2 of the applicant in this document, the release height or the optimum height above the target territory, which may be a few tens of meters. , is given according to the instant of entry into action of an ejection igniter, determined by an ignition control apparatus, that is to say according to the height of ejection of the bomb miniature, by setting the running time of a timed igniter of the miniature bomb The release time controlled in time depends in this case on the ballistic trajectory of the device consisting of the thruster and the warhead or the trajectory of the military head separate from the thruster, so that it is hardly possible to avoid a certain range of dispersion of the ejection height and therefore a range of

  corresponding dispersion in the battlefield.

  The object of the invention is to provide a method and a device of the aforementioned type which makes it possible to considerably reduce the dispersion range on the field of

battle, with simple means.

  This object is achieved with a method of the aforementioned type in that before the separation of the military head of the thruster, the current atmospheric pressure, depending on the altitude, is measured by means of a pressure sensor provided in the head. and converted, by means of a processor provided in the military head, into the corresponding current height, and in that the respective calculated height is adapted, by means of the processor, to the sum of the determined preprogrammed release height and from the height of fall of the warhead, separated from the thruster until the liberation of the submunitions of the warhead, by

  determination of the corresponding drop height.

  The desired purpose of the device is achieved in that the warhead comprises a pressure sensor, a processor and a time measuring device, the pressure sensor being designed to determine the current atmospheric pressure before separation of the thruster warhead. , the processor is used to convert the current atmospheric pressure measured in the corresponding current altitude of the warhead, and the device

  time measurement is planned so that the sub-

  ammunition be released from the warhead at a specified release time corresponding to a defined release height preprogrammed in the processor by means of an intended ignition device

in the military head.

  The advantage of the invention is that the release height at which the submunitions are released from the warhead can be accurately and relatively accurately met with simple means. The altitude recorded indirectly using the sensor. of pressure, by the barometric pressure measured and converted by the processor into the corresponding height and thus defining the expected release height, depends only on the accuracy and timeliness of the local barometric pressure pressure profile, the measurement accuracy of the pressure sensor, relatively simple design, as well as the kinetic behavior of the military head performing a nutation between the separation height and the release height According to the invention, the measurement of the current barometric pressure is carried out just

  before the separation of the military head from the thruster.

  In this phase of flight, the device is still in a stable state, which, when measuring the atmospheric pressure mentioned, makes it possible to suppress the measurement of a dynamic pressure component. The current data relating to the atmospheric pressure depending on the altitude are introduced into the processor, before the launch of the device, so that it is possible to determine the current altitude by the respective measured barometric pressure. Another advantage lies in the fact that the defect deportation of the submunition under the influence of the wind is reduced because a relatively low release height, determined, is imposed Since the warhead in nutation, the along its trajectory from the separation height to the release height, the wind speed becomes much slower than would be the case

  for submunitions, the lateral shift of the sub-munitions

  ammunition, conditioned by the dispersion in height, is relatively small Thanks to the measurement of the barometric pressure at a current flight time of the device, an increase of the longitudinal dispersion which would result if the atmospheric pressure was measured was avoided. the corresponding current release height is reached and if the thruster was separated and the sub-munitions released only at that moment In addition a measure of the atmospheric pressure during the flight phase of the warhead between the separation height and the release height, during which the warhead performs nutation, would contain a dynamic pressure component which would distort the conversion to the corresponding height or whose elimination by calculation would represent a

  considerable complexity or is hardly possible.

  Various other features and benefits

  of the invention result from the detailed description

  The process according to the invention and an embodiment of the device for carrying out this process are represented by way of non-limiting examples.

  and schematically in the drawings.

  FIG. 1 is a graphical representation of the operation of the device intended to attack targets with submunitions, FIG. 2 is a view in principle similar to that of FIG. 1 of different ballistic device trajectories according to the invention and FIG. 3 is a basic drawing of a

device according to the invention.

  FIG. 1 represents targets to be attacked, which may be, for example, tanks

  shielded, which are within a region-

  determined target At some distance from it is a lancemissile 14 with a weapons system 16 from which can be drawn non-guided devices 18 These devices are missiles with a thruster 20 and a military head 22 (see also

  Figure 3), in which are placed sub-

  During the launch phase, which is designated in Figure 1 by reference 26, one of the

  devices 18 is first temporarily accelerated.

  The device 18 moves along a stable ballistic trajectory, until it reaches the separation height Ha, for the separation of the warhead 22 from the thruster 20. The thruster 20 then moves, for example, along the trajectory 30, represents dashed lines, and the warhead 22 moves along a trajectory 32, the warhead 22 twisting along the trajectory 32, which has the effect of reducing the rotation and the speed Independently of the separation height Ha, the submunitions 24 are ejected from the warhead 22, as shown in FIG. 2, at a release height Hf quite determined. This release height is, for example, less than 600 m, this which causes the submunitions to fall within a given target zone 12 and can attack the targets at that location. The free flight phase of the submunitions 24, from the top eur Hf release until the impact on

  the ground, can be of the order of 15 seconds or less.

  FIG. 2 represents three different trajectories 28, 28 'and 28 ", each of which corresponds to a separation height Ha, Ha' or Ha ', the separation height Ha corresponding to the separation time t 0 at which the thruster 20 is separated. of the warhead 22 (see FIG. 3), after measurement of the barometric atmospheric pressure, corresponding to the separation height Ha The separation height Ha '> Ha corresponds to a moment of separation ta'> ta or to a barometric pressure pal <pa The same is true for the separation height Ha "> Ha '> Ha and for the corresponding barometric pressure pa' <pa '<pa The corresponding intersection points of the height lines Ha, Ha' or Ha" l with the corresponding ballistic trajectories 28, 28 'or 28 ", lie on a geometric curve which is designated by the reference 34 Starting from these points of intersection or the geometric curve 34, the trajectories 32, 3 have been indicated. Corresponding 2 'or 32 "of the nutary warhead irrespective of the trajectory 32, 32' or 32 '" of the nutary warhead 22, the submunitions 24 are released by the warhead at time t 1, at a given release height Hf At time t 1, an ignition device 36, provided in the military head 22, is initialized (see FIG. 3). FIG. 3 furthermore shows schematically a processor 38 provided for in FIG. military head 22, and a pressure sensor 40 provided in the military head 22 with which the current pressure, depending on the height, is measured before separation of the warhead 22 of the thruster 22 and therefore during the steady trajectory 28 of the device 18 and is converted into the height H

  corresponding current, using the processor 38.

  By computer-assisted correction of ta and in particular ti, it is therefore possible to size the fall time of each submunition 24, from the release height Hf to the zero height, less than the time of self-destruction of the corresponding submunition 24, which reliably excludes self-destruction of submunitions 24 in the air.

sinks into the ground.

  Just before the warhead 22 is separated from the thruster 20, it therefore occurs, using the pressure sensor 40, a measurement of the atmospheric pressure depending on the height At this time, the device 10 is as it is. has been said in a stable flight state, which makes a measurement of a dynamic pressure component superfluous The current data relating to the altitude-dependent atmospheric pressure are introduced into the processor 38, before the launching of the device 18, so that by the atmospheric pressure depending on the altitude, measured, we have information

  relative to the current altitude of the device 10.

  Knowing the release height Hf thus preprogrammed, the height of fall of the warhead is thus known between the separation height Ha and the release height Hf mentioned. The fall time corresponding to this difference in height, necessary for the warhead 22 , is either determined by a preprogrammed table of values, or if necessary determined by simulation, with the current measured data At the expiration of the determined fall time, the ignition device 36 of the head

  Military 22 is initialized, which means that the sub-

  ammunition 24 are released at the given constant Hf release height, required, and are distributed in the target zone 12, within a given ideal dispersion model. Given that according to the invention the release height Hf is within a very narrow dispersion range, a specific dispersion model can be relatively accurately

in the target area 12.

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  processor with the current pressure data

  measured by means of the pressure sensor (40).

  4 Process according to any one of

  Claims 1 to 3, characterized in that

  the flow of the falling time (Ha-Hf) of the warhead (22), calculated by means of the processor (38), is measured by means of a time measuring device provided in the warhead (22), and an ignition device (36), mounted in the military head and connected to the time measuring device, is illuminated to eject the submunitions (24) from the warhead

  (22) at the predetermined release height (Hf).

  Device for attacking targets (10) with submunitions (24), which are provided in a warhead (22), which can be released by means of a propellant (20) on a ballistic trajectory (28) and can being separate from the thruster (20), characterized in that the warhead (22) comprises a pressure sensor (40), a processor (38) and a time measuring device, the pressure sensor (40) being provided for determining the current atmospheric pressure before separation of the thruster (22) from the thruster (20), the processor (38) is used to convert the current measured atmospheric pressure into the corresponding current height of the warhead (22), and the time measurement is provided for the submunitions (24) to be released from the warhead (22) at a determined release time corresponding to a defined release height (Hf) preprogrammed in the processor (38), by means of in an ignition device

  (36) provided in the military head (22).

  6 Device according to claim 5, characterized in that the processor (38) comprises a memory for a table of pre-programmed fall times. Device according to Claim 51, characterized in that the ignition device (36) intended for the release of the submunitions (24),

  has a pyrotechnic self-destruction unit.