EP0547391A1 - Verfahren zur Erhöhung der Erfolgswahrscheinlichkeit bei der Flugkörperabwehr mittels eines fernzerlegbaren Geschosses - Google Patents

Verfahren zur Erhöhung der Erfolgswahrscheinlichkeit bei der Flugkörperabwehr mittels eines fernzerlegbaren Geschosses Download PDF

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Publication number
EP0547391A1
EP0547391A1 EP92119673A EP92119673A EP0547391A1 EP 0547391 A1 EP0547391 A1 EP 0547391A1 EP 92119673 A EP92119673 A EP 92119673A EP 92119673 A EP92119673 A EP 92119673A EP 0547391 A1 EP0547391 A1 EP 0547391A1
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EP
European Patent Office
Prior art keywords
projectile
time
target
fragments
probability
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP92119673A
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German (de)
English (en)
French (fr)
Inventor
Peter Toth
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rheinmetall Air Defence AG
Original Assignee
Oerlikon Contraves AG
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Filing date
Publication date
Application filed by Oerlikon Contraves AG filed Critical Oerlikon Contraves AG
Publication of EP0547391A1 publication Critical patent/EP0547391A1/de
Ceased legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/04—Proximity fuzes; Fuzes for remote detonation operated by radio waves
    • F42C13/047—Remotely actuated projectile fuzes operated by radio transmission links

Definitions

  • the invention is in the field of missile defense by means of cannon projectiles and relates to a method for increasing the probability of success by deliberately disassembling a specially designed projectile.
  • Missiles are unmanned aerial objects such as missiles, guided missiles, projectiles, drones.
  • the spectrum of possible movements of such objects is very diverse.
  • the means to combat them are correspondingly varied; they range from simple anti-aircraft guns to complex air-to-air weapons with homing heads.
  • Systems for combating and destroying enemy missiles by means of projectiles, which are at stake, essentially comprise at least one cannon for firing the projectiles and a fire control device for measuring the movement of the missile and for calculating the direction of fire and the time of the fire initiation.
  • An automatic fire control system is essential to combat fast and agile missiles, i.e.
  • the target is pursued - in this case the missile - and the direction of the shot is calculated on the basis of the results of the measurement and the cannon is continuously readjusted. If desired, the time and duration of the burst of fire can also take place automatically when the fire barrier is lifted.
  • the general problem of air defense or missile defense is to bring a sufficiently large destruction potential in good time to the current location of the object to be defended and to make it effective there.
  • the potential for destruction is the moving mass of a ballistic projectile, that is to say kinetic energy.
  • the projectile or at least one Part of it hit the target.
  • Another option is an explosive device. This carries an explosive, i.e. bound chemical energy, which detonates in the event of a direct hit or with the help of a proximity fuse if the target is approached sufficiently and exerts its destructive effect through heat radiation and pressure waves.
  • the defense task is to render the object harmless, i.e.
  • a known measure to increase the likelihood of success consists in tempering the floor. Immediately upon firing, the projectile is tempered, that is, it is impressed with a time after which it is exploded or disassembled. Such a projectile acts through the fragments or the pressure waves of the explosive, which are distributed within a cone in the room. The time of the decomposition is chosen so that the fragments or the pressure waves cover the area of uncertainty of the target's stay at the calculated hit time.
  • the imprinted time is the calculated floor flight time to the ideal meeting point minus the advance time. The latter can be constant or can be calculated in an optimized manner based on the current conditions.
  • the described method has the disadvantage that the available destruction potential must be distributed over the relatively large area of the target uncertainty zone, which reduces the impact of a hit.
  • An improvement in this regard is achieved with a projectile with a proximity fuse.
  • the relative speed the target to the floor determined by Doppler measurement. It is ignited when the relative speed that falls near the target falls below a predetermined value. A direct hit is not anticipated.
  • the projectile is disassembled closer to the object than with the templating process, which results in a higher probability of destruction.
  • the proximity fuse requires measurement and signal processing on the floor.
  • DE-A-2348365 describes a weapon system that can affect the detonator of a projectile in flight. It includes a pulse transmitter that can transmit data to the detonator on the floor via a transmitting antenna. The detonator on the floor has, among other things, an electronic receiver device for this data.
  • the data contains the individual address, which means that only one particular detonator is addressed at a time, and correction values for a running counter.
  • the detonation occurs when a certain counter reading is reached.
  • the ignition timing can thus be advanced or postponed. This procedure results in a smaller target uncertainty zone and an adjusted advance in time. If, however, it turns out that the target and the projectile will cross each other at a relatively large distance, there is no other option than to disassemble the projectile early, so that fragments can still reach the target. The The destruction potential of these few fragments will then hardly be sufficient to render the target harmless.
  • the method is based on a projectile, the fragments of which are concentrated on a cone shell when dismantled, for example according to EP-A-0 328 877, but with a remote-controlled detonator.
  • the target is measured further after the projectile has been shot down. Towards the predicted meeting time, the location of the destination is then increasingly known. It will generally not match what was originally calculated.
  • the dismantling order will be communicated to the projectile in flight as late as possible.
  • the time of disassembly is chosen so that the fragments diverging in the cone shell hit the target on the new target path.
  • the projectile dismantling thus acts as a one-off redirection of the projectile trajectory by half the opening angle of the cone for part of the projectile mass. This has the great advantage that the existing destructive potential remains more concentrated than in the conventional temp. Projectile and in the proximity fuse. An active measurement from the floor, as inevitable with the latter, is not necessary.
  • the starting point is a system 30 for combating missiles 31 by means of projectiles 32, with at least one fire control device 33 and at least one gun 34.
  • the aim is to launch the missile 31 with the cannon 35 fired floor 32 to hit directly.
  • the fire control device 33 continuously measures the target, ie the path 1 of the missile 31. Together with the knowledge of the type of the missile 31 and thus its maneuverability, the expected trajectory 1 of the target is determined from this in the near future.
  • the ballistics of the projectile 32 used in conjunction with the cannon 35 are known.
  • the trajectory 3 of the projectile 32 can thus be specified for a predetermined firing direction.
  • the cannon 35 is continuously directed by the automatic fire control system so that a projectile 32 can be fired at any time and then takes the desired trajectory.
  • the fire control device 33 and the gun 34 are combined in one device or connected to one another via the necessary lines 36.
  • the calculated target trajectory 1 is symbolized by a directional straight line, the calculated projectile trajectory 3 by a similar straight line.
  • the two lanes intersect at meeting point 11, which is calculated according to the calculation Should meet target and floor at meeting time t3. It is a mixed representation of spatial and temporal elements.
  • An uncertainty zone 6 is sketched as an example in FIG.
  • time t3 when the target is most likely to be in meeting point 11, there is an area (not shown) within which the target is located with a probability that is close to one.
  • a spatial area (not shown) can be specified within which the floor is with a probability close to one.
  • the overlay Both areas result in the sketched uncertainty zone 6 around the common point 11, the shape of which is given here as a model.
  • the proportion of the target uncertainty predominates considerably. It is not difficult to determine that there is a considerable probability that the projectile will miss the target.
  • FIG. 2 shows the corresponding conditions.
  • the ignition or disassembly time t0 is earlier than the calculated meeting time t3.
  • the projectile is at the disassembly point 4.
  • the fragments of the projectile spread out conically.
  • This cone 14 is indicated in FIG. 2 - it opens towards the viewer.
  • the tip of the cone 14 is at the location of the projectile at the ignition, the axis lies in the direction of movement of the projectile and the opening angle and the density distribution of the fragments is a characteristic of the projectile; typically the density decreases towards the outside.
  • the fragments are essentially distributed in a circularly delimited plane and form a fragment disk 5.
  • the plane is orthogonal to the projectile trajectory 3 and contains the calculated meeting point 11.
  • the radius of the fragment disk 5 is ideally just so large that the greatest extent the uncertainty zone 6 finds space in it.
  • the advance in time that is the time difference t3-t0, by which the projectile is disassembled before the calculated point of impact t3, is advantageously chosen in knowledge of the projectile characteristics, in particular the opening angle of the cone, so that at time t3 the fragment disk 5 extends the extent of the Uncertainty zone 6.
  • the uncertainty zone 6 is significantly larger for long storey flight times than for short ones.
  • the advantage of a temping only becomes apparent when it is shot down when the conditions are known.
  • the time advance can then be adjusted to the present situation.
  • the likelihood of a hit can therefore be significantly increased by the temping process.
  • the probability of success does not increase to the same extent.
  • the fragment density decreases quadratically.
  • the probability of destruction also decreases with density. For a given total weight, this basically applies regardless of the optimization between the number of fragments and the weight of the fragments.
  • the uncertainty zone 6 is smaller in its dimensions (and somewhat changed in shape) and the distance of the decomposition point 4 from the calculated meeting point 11 is shorter.
  • the density of the fragment disk 5 is correspondingly higher. If the probability of a hit remains approximately the same, the probability of destruction and thus the probability of success can be increased if the projectile is "on the right track".
  • the invention now remedies this.
  • the additional information is used to increase the likelihood of destruction compared to the method with the fragmentary bullet in flight, and thus to improve the chances of success.
  • a projectile is used which can also be temped in flight through the fire control system or, preferably, remotely ignited, the fragments of which, however, spread out in the shape of a cone after being dismantled.
  • the destructive potential in the form of kinetic energy in the fragments is concentrated on an expanding ring.
  • FIG. 3 shows in the same way as FIG. 2, in a mixed representation of spatial and temporal elements, the conditions after the dismantling of such a conical shell bullet.
  • the projectile is at the point of disassembly 9.
  • the fragments of the projectile continue to fly in space at approximately the same axial speed, and all of them spread uniformly in all directions with approximately the same radial speed.
  • fragments sweep over a conical shell 19 of finite strength, as is sketched in FIG. 3.
  • the viewer looks into the narrowing funnel.
  • the calculated bullet trajectory 3 which in turn is indicated by a directed straight line, forms the axis of the cone, the point of decomposition 9 the tip.
  • the projectile would have been in trajectory 3 at point 12. Now it is divided into a circular fragment ring 10, which lies approximately in the orthogonal plane to path 3 through point 12. It is easy to see that the fragment density in this ring is considerably higher than that when the same number of fragments is distributed over the entire circular area.
  • FIG. 3 also shows the conditions for successful missile defense using the inventive method.
  • the target trajectory 1 calculated at the time the projectile was fired intersects the projectile trajectory 3 at the meeting point 11, which was then calculated in advance, at the theoretical hit time t3.
  • the probable target trajectory around the time t3 can be determined more precisely during the projectile flight time, but before the projectile has reached point 9. This is shown as the corrected target trajectory 2.
  • the location of the target is known at time t2 except for an uncertainty zone 7, which is generally much smaller than that Uncertainty zone 6 shown in FIG. 2 for the location of the target around the theoretical meeting point 11 at time t3, as is determined when the projectile is fired.
  • the location 13 of the destination at time t3 after the updated calculation naturally lies within the uncertainty zone 6.
  • the most important floor exit measurement is that of the initial speed, which latter has a significant influence on the floor trajectory.
  • the directional errors due to control deviations can also be measured well and can be used to determine the uncertainty zone.
  • the system is also supplemented by a tracking and measuring device 37 (FIG. 1) for the projectiles fired.
  • a tracking and measuring device 37 for the projectiles fired.
  • This is advantageously on the gun, but can also be combined with the fire control device 33.
  • the probable location of each individual storey 32 ' can be continuously and precisely determined in the pre-calculated meeting time, which contributes to a further shrinking of the uncertainty zone.
  • the target is at time t2 within the uncertainty zone 7 around point 8, which in turn lies in the middle of the wall thickness of the fragment ring 10.
  • This is the hit situation, with the projectile being disassembled at time t1, so that the fragment ring 10 meets the target at time t2. Thanks to the relatively high fragment density, the likelihood of destruction is high for such a hit.
  • FIG. 4 shows, over the radius r, the different fragment densities d for the two types of storey at two different times.
  • Curve 23 shows the conditions for the conventional fragmentary bullet at the time 2 * T1 after disassembly, curve 24 that of the conical jacket bullet.
  • a simplifying approach is used, which is based on linear equations.
  • those skilled in the art can increase the accuracy to a more detailed level Fall back on model.
  • a Cartesian coordinate system is used as the basis for the calculations, the axis directions of which are defined as follows: x-axis in the direction of the projectile trajectory 3, y-axis in the orthogonal plane thereto horizontally; The z-axis thus has the direction of the intersection line between a vertical plane through the projectile trajectory and the orthogonal plane to the projectile trajectory.
  • the axis directions are indicated in FIG. 3 at point 12.
  • the projectile moves along the x-axis with the velocity vg> 0, the fragments also have a radial component vr.
  • the ratio vr / vg determines the opening angle of the cone.
  • the current target location p (t) is given by the components xf (t), yf (t) and zf (t), the target speed by the components vfx, vfy and vfz. It does not matter where the origin of the coordinate system is selected on the cone axis, that is to say the floor trajectory 3.
  • T t2-t3 .
  • T can be positive or negative - in Figure 3, T is obviously negative.
  • xf (t2) xf (t3) + vfx ⁇ T
  • the method according to the invention thus ensures a high probability of a hit paired with a high concentration of the fragments of the projectile and thus ensures a high probability of success.
  • the method can also be used to combat other moving targets, namely the defense against aircraft and combat helicopters.
  • the person skilled in the art it is readily possible for the person skilled in the art to make the necessary adaptations to the characteristic task.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP92119673A 1991-12-18 1992-11-19 Verfahren zur Erhöhung der Erfolgswahrscheinlichkeit bei der Flugkörperabwehr mittels eines fernzerlegbaren Geschosses Ceased EP0547391A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH375591 1991-12-18
CH3755/91 1991-12-18

Publications (1)

Publication Number Publication Date
EP0547391A1 true EP0547391A1 (de) 1993-06-23

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EP92119673A Ceased EP0547391A1 (de) 1991-12-18 1992-11-19 Verfahren zur Erhöhung der Erfolgswahrscheinlichkeit bei der Flugkörperabwehr mittels eines fernzerlegbaren Geschosses

Country Status (4)

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US (1) US5322016A (ja)
EP (1) EP0547391A1 (ja)
JP (1) JPH05312497A (ja)
CA (1) CA2084318A1 (ja)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008098562A1 (de) * 2007-02-12 2008-08-21 Krauss-Maffei Wegmann Gmbh & Co. Kg Verfahren und vorrichtung zum schutz gegen fliegende angriffsmunitionskörper
WO2008098561A1 (de) * 2007-02-12 2008-08-21 Krauss-Maffei Wegmann Gmbh & Co. Kg Verfahren und vorrichtung zur fernauslösung eines geschosses
CN101435684A (zh) * 2008-08-03 2009-05-20 赵明 气动能连散射炮防御导弹
CN102313484A (zh) * 2010-06-30 2012-01-11 葛泓杉 霰弹反导航炮
DE102011109658A1 (de) * 2011-08-08 2013-02-14 Rheinmetall Air Defence Ag Vorrichtung und Verfahren zum Schutz von Objekten
EP2989408B1 (de) 2013-04-26 2021-03-17 Rheinmetall Waffe Munition GmbH Verfahren zum betrieb eines waffensystems

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL1001556C2 (nl) * 1995-11-02 1997-05-13 Hollandse Signaalapparaten Bv Fragmenteerbaar projectiel, wapensysteem en werkwijze.
US6279482B1 (en) 1996-07-25 2001-08-28 Trw Inc. Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket
US6945088B2 (en) * 2002-05-14 2005-09-20 The United States Of America As Represented By The Secretary Of The Navy Multi-fragment impact test specimen
CN100463835C (zh) * 2004-12-21 2009-02-25 西昌卫星发射中心 液体火箭爆炸碎片散布范围的确定方法
US20100030519A1 (en) * 2008-07-31 2010-02-04 Collier Jarrell D System for Real-Time Object Damage Detection and Evaluation
US20100030520A1 (en) * 2008-07-31 2010-02-04 Collier Jarrell D System for Real-Time Object Detection and Interception
US10677758B2 (en) * 2016-10-12 2020-06-09 Invocon, Inc. System and method for detecting multiple fragments in a target missile
JP6383817B2 (ja) * 2017-01-13 2018-08-29 株式会社Ｓｕｂａｒｕ 飛しょう体位置計測装置、飛しょう体位置計測方法及び飛しょう体位置計測プログラム

Citations (5)

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US3955069A (en) * 1972-09-28 1976-05-04 General Electric Company Presettable counter
US4267776A (en) * 1979-06-29 1981-05-19 Motorola, Inc. Muzzle velocity compensating apparatus and method for a remote set fuze
DE3123339A1 (de) * 1981-06-12 1982-12-30 Wegmann & Co, 3500 Kassel Verfahren zur fernzuendung eines sprenggeschosses, insbesondere eines hubschrauberabwehrgeschosses sowie einrichtung und geschoss zur durchfuehrung des verfahrens
EP0161962A1 (fr) * 1984-04-13 1985-11-21 AEROSPATIALE Société Nationale Industrielle Système d'arme et missile pour la destruction structurale d'une cible aérienne au moyen d'une charge focalisée
EP0309734A1 (de) * 1987-09-29 1989-04-05 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Verfahren zum Zünden eines Geschosses G in der Nähe eines Zieles Z

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Publication number Priority date Publication date Assignee Title
US4168663A (en) * 1954-12-01 1979-09-25 The United States Of America As Represented By The Secretary Of The Army Computer fuzes
US3844217A (en) * 1972-09-28 1974-10-29 Gen Electric Controlled range fuze
EP0328877A1 (de) * 1988-02-18 1989-08-23 Oerlikon-Contraves AG Geschoss mit Splittermantel

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3955069A (en) * 1972-09-28 1976-05-04 General Electric Company Presettable counter
US4267776A (en) * 1979-06-29 1981-05-19 Motorola, Inc. Muzzle velocity compensating apparatus and method for a remote set fuze
DE3123339A1 (de) * 1981-06-12 1982-12-30 Wegmann & Co, 3500 Kassel Verfahren zur fernzuendung eines sprenggeschosses, insbesondere eines hubschrauberabwehrgeschosses sowie einrichtung und geschoss zur durchfuehrung des verfahrens
EP0161962A1 (fr) * 1984-04-13 1985-11-21 AEROSPATIALE Société Nationale Industrielle Système d'arme et missile pour la destruction structurale d'une cible aérienne au moyen d'une charge focalisée
EP0309734A1 (de) * 1987-09-29 1989-04-05 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Verfahren zum Zünden eines Geschosses G in der Nähe eines Zieles Z

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Title
NAVY TECHNICAL DISCLOSURE BULLETIN Bd. 2, Nr. 2, Februar 1977, Seiten 1 - 4 H. A. BULGERIN 'Command detonate fuze' *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008098562A1 (de) * 2007-02-12 2008-08-21 Krauss-Maffei Wegmann Gmbh & Co. Kg Verfahren und vorrichtung zum schutz gegen fliegende angriffsmunitionskörper
WO2008098561A1 (de) * 2007-02-12 2008-08-21 Krauss-Maffei Wegmann Gmbh & Co. Kg Verfahren und vorrichtung zur fernauslösung eines geschosses
CN101435684A (zh) * 2008-08-03 2009-05-20 赵明 气动能连散射炮防御导弹
CN102313484A (zh) * 2010-06-30 2012-01-11 葛泓杉 霰弹反导航炮
DE102011109658A1 (de) * 2011-08-08 2013-02-14 Rheinmetall Air Defence Ag Vorrichtung und Verfahren zum Schutz von Objekten
WO2013020911A1 (de) 2011-08-08 2013-02-14 Rheinmetall Air Defence Ag Vorrichtung und verfahren zum schutz von objekten
EP2989408B1 (de) 2013-04-26 2021-03-17 Rheinmetall Waffe Munition GmbH Verfahren zum betrieb eines waffensystems

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JPH05312497A (ja) 1993-11-22
US5322016A (en) 1994-06-21
CA2084318A1 (en) 1993-06-19

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