EP0161962B1 - Waffensystem und Rakete zur Zerstörung der Struktur eines Luftzieles mittels einer konzentrierten Ladung - Google Patents

Waffensystem und Rakete zur Zerstörung der Struktur eines Luftzieles mittels einer konzentrierten Ladung Download PDF

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Publication number
EP0161962B1
EP0161962B1 EP85400715A EP85400715A EP0161962B1 EP 0161962 B1 EP0161962 B1 EP 0161962B1 EP 85400715 A EP85400715 A EP 85400715A EP 85400715 A EP85400715 A EP 85400715A EP 0161962 B1 EP0161962 B1 EP 0161962B1
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Prior art keywords
missile
target
instant
charge
duration
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EP85400715A
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French (fr)
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EP0161962A1 (de
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Pierre Laures
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Airbus Group SAS
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Airbus Group SAS
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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

Definitions

  • the present invention relates to a weapon system intended for the structural destruction, that is to say the cutting into two distinct sections, of a target by means of a controlled focused charge and comprising a missile carrying said focused charge .
  • Such structural destruction allows the use of small missiles carrying only a small or medium charge (of the order of three to four times lower than that required by the first two effects mentioned above) and having great maneuverability, for example obtained by force control, that is to say using lateral nozzles whose line of action passes at least approximately through the center of gravity of the carrier missile.
  • a missile known for a weapon system intended for structural destruction further comprises calculation means, first means capable of providing the value of the speed of said missile, second means capable of providing the value of the relative speed of the target relative to the missile, third means capable of providing the angle between the longitudinal axis of the missile and said relative speed, as well as fourth proximity detection means capable of indicating the instant of detection of an end of said missile target, said missile being provided with a system for triggering said charge activated with a certain delay after detection of the target.
  • Structural destruction would therefore seem to constitute the most effective method vis-à-vis fast targets with great maneuverability.
  • it is not used in practice, because it requires, for the interception to be successful, that the impact area of the focused burst of shrapnel corresponds to a vulnerable area of the target. So far, it does not seem that we have managed to control the impact zone, on a target, of the fragments of a focused spray.
  • the object of the present invention is to remedy this drawback.
  • the object of the present invention relates to a weapon system making it possible to send the shards of a focused charge into a zone of the target, specified in advance and chosen for its vulnerability.
  • a vulnerable zone corresponds, for example, to the part of the fuselage which is between the wing and the tail.
  • the explosion of the focused charge is controlled, from said instant of detection of one end of the target, with a delay time which is calculated as a function of the real parameters of the interception of the target by the missile and which, in reality, corresponds to a predetermined length of said target from its end detected by said fourth means.
  • the fragments of the focused charge can reach the predetermined region of said target in order to achieve structural destruction of the latter.
  • this calculated duration is zero or negative, the firing will be carried out immediately.
  • the known missiles as described for example in the patents US-A-3,933,097 and DE-A-2,527,368, are generally provided with a charge trigger system actuated with a certain delay, after detection of the target; however, in this case, this delay is foreseen by construction or possibly introduced during the launching of the missile, taking into account the supposed speed of the target and the type of attack carried out by the missile on the target (attack from the front or rear).
  • the delay in the explosion of the focused charge is determined according to the circumstances of the interception, in order to optimize the effects of said charge and to obtain the structural destruction of the target.
  • said first, second and third means are provided to be able to supply their information continuously and then said additional calculation means calculate said duration continuously to provide a series of values, and, from said detection instant provided by said fourth means, said additional calculation means count down the last value of this duration available before said detection instant.
  • said additional calculation means and / or said proximity detection means exhibit an inherent delay in the exposure of said focused charge and in the detection of a target, respectively. If all of these known delays inherent in the system are equal to (To), said additional calculation means send the focused load a firing signal after a period of time (T I ), which is equal to the difference between the duration (T), at the end of which the explosion of the focused charge is desired, and the delay duration (To).
  • said additional calculation means possibly correct the duration (T) of the value (To) of the inherent delays to provide a firing signal at the expiration of the duration (T,).
  • the system according to the invention includes means capable of indicating this constant.
  • Such means may be display means actuated manually when the missile is launched.
  • they consist of automatic means for recognizing the target, either carried by the missile itself, or arranged at a fixed station.
  • these automatic recognition means are advantageously linked to the missile launching and remote control station, which transmits to it by electromagnetic waves the value of to of the target to be destroyed, together with the other information. usual.
  • the value of the duration (T or T i ) applicable at a given instant is calculated from measurements of the speed (Ve) of the missile, of the target relative speed - missile (V R ) and of the angle (D) carried out at an earlier instant and said additional calculation means generate an additional delay time t which is counted from the instant of said measurements and whose expiration allows the start from the countdown of the delay (T or T 1 ) to the ignition of the charge, as soon as the proximity detection means have detected the target.
  • Ve, V R and D are measured and the calculations necessary are carried out at a rate controlled by time t and a delay T, periodically renewed, which is used after detection of the target by the detection means, is developed. proximity, to trigger the charge at the optimal time.
  • said additional delay time t is calculated by said additional calculation means and is proportional to the inverse of the square root of the relative speed (V R ).
  • the weapon system according to the invention shown in FIG. 1 and intended for air defense, comprises a detection and guidance device 1, arranged on the ground, as well as a set of air defense missiles 2.
  • a detection and guidance device 1 arranged on the ground, as well as a set of air defense missiles 2.
  • an air enemy 3 missile, plane, helicopter, etc.
  • the device 1 determines using the computer and the radar that it includes the opportunity and the conditions for an interception of the enemy 3.
  • each air defense missile 2 comprises electronic guide means 4 capable of cooperating with the device 1 and a seeker 5 provided with an inertial unit 5 '. Also, initially, a missile 2 follows a launch trajectory entirely determined by the cooperation of the device 1 and on-board guidance means 4. Then, again thanks to this cooperation, the device 1 directs the missile 2 towards the target 3 by making it follow a trajectory 7. Finally, when the missile 2 is sufficiently well oriented, its guidance towards the target 3 is taken care of by its seeker 5.
  • FIG. 1 we have illustrated the case where the missile 2 goes against the target 3 to attack it from the front, which corresponds to the diagrams of FIGS. 4 and 5. It goes without saying that missile 2 can also attack target 3 from the rear, chasing and catching it, as shown in the diagrams in Figures 6 and 7.
  • the object of the invention is to control the explosion of the focused charge 10 at an instant following the detection of the target 3 by the proximity detection means 8, such as the fragments of said charge 10 reach a structurally fragile region of said target, in order to cut the latter in two.
  • the front and middle parts of an attacking machine 3 are structurally resistant because they include navigation and measuring devices, fuel tanks, military load, etc., so that, in order to obtain structural destruction of said machine 3, it is preferable to project the fragments of the load 10 into a zone 14 of the rear part thereof (see FIGS. 4 and 6).
  • the object of the invention is to determine a time T of delay in the explosion of the charge 10, after the detection of the target 3 by the proximity detection means 8, such as the bursts of said focused charge 10 can reach zone 14, placed at a distance from the first point 15 of the target 3 detected by the front 9 of said proximity detection means 8.
  • the explosion of the charge 10 after firing by the calculation means 13 is not instantaneous and that, moreover, there is a delay in the detection of a target 3 by the detection means of proximity 8; as a result, the delay time T to the explosion must be corrected by a time To, known for a charge 10 and proximity detection means 8 given and corresponding to the explosion delays after ignition and detection by proximity detection means 8.
  • Io is a constant, having the dimension of a length and independent of the parameters Ve, V B and P; lo is attached to each type of target 3 and characteristic of it.
  • the detection and guidance device 1, which performs an at least partial image recognition of the target 3, knows the type of the latter and can therefore send to the calculation means 13 of the missile 2, the value lo suitable for the target 3 being intercepted.
  • the different values 10 respectively correspond to the different types of possible targets are preferably predetermined and stored in the device 1.
  • Each type of target 3 can be associated with a value of 10 for a forward attack and another value lo for a rear attack.
  • the missile 2 may include the means for detecting the type of the target 3 and determining the value to be adopted for the constant lo;
  • Dl 1 ⁇ V B ⁇ te, term in which te is the time taken by the bursts of the focused charge 10 to reach zone 14 of the target 3.
  • the + sign is used for a forward attack and the sign - for a rear attack.
  • the detection and guidance device 1 knows the type of attack (from the front or from the rear) that the missile 2 will carry out on the target 3 and it is therefore able to communicate to the calculation means 13 the sign appropriate.
  • te is an implicit function of h, a and T;
  • DI 2 is a variation in length due to the parameters h and a.
  • Condition (1) is easy to achieve by construction, since it involves only parameters available to the manufacturer of missile 2. If this condition (1) is met, the delay time T is given by the formula that is to say if it is an attack from the front (see Figures 4 and 5), or by the formula: that is to say if it is a rear attack (see Figures 6 and 7).
  • condition (1) is respected and if the time T has been chosen according to the appropriate relation (2 1 ) or (2 2 ), the zone 14 reached by the splinters will be defined from point 15, by the relationship :
  • Circuit 16 controls the measurements and performs the calculations.
  • the up-down counter 17 determines. the instant from which the explosion delay time can be used, while the up-down counter 18 allows the exploitation of this delay.
  • the measurement authorization signal (input 23) is initialized at the time of launching or during the search for seeker 5.

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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)
  • Radar Systems Or Details Thereof (AREA)
  • Piezo-Electric Or Mechanical Vibrators, Or Delay Or Filter Circuits (AREA)

Claims (7)

1. Waffensystem für die strukturelle Zerstörung, d. h. die Zerlegung in zwei verschiedene Teilstücke, eines Zielobjekts (3) mittels einer gesteuerten, gezielten Ladung (10) und mit einem Tragflugkörper (2) für die gezielte Ladung und für Mittel zur Berechnung, erste Mittel (5') zum Bestimmen des Werts für die Geschwindigkeit (Ve) des Flugkörpers (2), zweite Mittel (5) zum Bestimmen des Werts für die Geschwindigkeit (VR) des Zielobjekts (3) relativ zu der des Flugkörpers (2), dritte Mittel (12) zum Bestimmen des Winkels (D) zwischen Längsachse des Flugkörpers (2) und der genannten Relativgeschwindigkeit sowie vierte Mittel (8) zur Näherungserfassung, mit denen der Zeitpunkt der Erfassung eines Vorsprungs des Zielobjekts (3) angezeigt werden kann, wobei der Flugkörper (2) mit einem System zur Freigabe der Ladung unter einer gewissen Verzögerung nach Erfassung des Zielobjekts versehen ist, dadurch gekennzeichnet, daß es zusätzliche Mittel zum Berechnen (13) umfaßt, die an Bord des Flugkörpers (2) angebracht sind und die aus den Werten für die Geschwindigkeit (Ve) des Flugkörpers und für die relative Geschwindigkeit Zeilobjekt-Flugkörper (VR) sowie aus dem Winkel (D) zwischen der , Längsachse des Flugkörpers (2) und der Relativgeschwindigkeit (VR) in einem Zeitpunkt nahe dem von den vierten Mitteln (8) bestimmten Zeitpunkt eine Zeitdauer (T) berechnen, die dann von den zusätzlichen Mitteln zum Berechnen (13) vom Zeitpunkt der Erfassung an abwärtsgezählt wird und wobei an deren Ende die zusätzlichen Mittel zum Berechnen (13) die gezielte Ladung (10) steuern, wobei die Mittel zum Berechnen (13) die Zeitdauer nach den folgenden Formeln berechnen :
Figure imgb0014
wobei:
T = Zeitdauer vom Zeitpunkt der Erfassung eines Vorsprungs des Zielobjekts (3) durch die vierten Mittel (8), wobei an deren Ende die Explosion der gezielten Ladung gewünscht ist, damit deren Sprengsplitter einen verletzbaren, vorher bestimmten Teil des Zielobjekts (3) erreichen ;
d = Abstand längs der Achse X-X des Flugkörpers (2) zwischen dem Mittelpunkt F der vierten Mittel (8) zur Näherungserfassung und dem Mittelpunkt 0 der gezielten Ladung ;
lo = Konstante in der Art einer Länge, kennzeichnend für das zu zerstörende Zielobjekt ;
Ve = Geschwindigkeit des Flugkörpers (2) ;
VR = Relativgeschwindigkeit des Zielobjekts (3) bezüglich des Flugkörpers (2) ;
D = Winkel zwischen der Achse des Flugkörpers (2) und VR :
2. Waffensystem nach Anspruch 1, wobei die ersten, zweiten und dritten Mittel ihre Informationen kontinuierlich abgeben dadurch gekennzeichnet, daß die zusätzlichen Mittel zum Berechnen (13) die Dauer (T) kontinuierlich berechnen, was in einer Folge von Werteb resultiert, und daß die zusätzlichen Mittel zum Berechnen den letzten Wert dieser verfügbaren Dauer, ausgehend vom durch die vierten Mittel gelieferten Zeitpunkt der Entdeckung, abwärts vor dem Zeitpunkt der Entdeckung zählen.
3. Waffensystem nach einem der Ansprüche 1 oder 2, wobei die zusätzlichen Mittel zum Berechnen (13) und/oder die Mittel zur Näherungserfassung eine Eigenverzögerung für die Explosion der gezielten Ladung und für die Entdeckung eines Zielobjekts (3) aufweisen, dadurch gekennzeichnet, daß, falls die Gesamtheit der bekannten Eigenverzögerungen des Systems gleich (To) ist, die zusätzlichen Mittel zum Berechnen (13) zur gezielten Ladung (10) ein Signal zum Abschießen nach Ablauf einer Zeitdauer (T1) senden, die gleich der Differenz zwischen der Zeitdauer (T), nach der die Explosion der gezielten Ladung (10) gewünscht ist, und der Verzögerungszeit (To) ist.
4. Waffensystem nach Anspruch 1, dadurch gekennzeichnet, daß es Mittel (1) zum Erkennen der Art des Zielobjekts (3) umfaßt und die Konstante lo bestimmen kann.
.5. Waffensystem nach einem der Ansprüche 1 oder 4, dadurch gekennzeichnet, daß der Wert für die Zeit (T oder T) für einen gegebenen Zeitpunkt aus den Meßwerten für die Geschwindigkeit (Ve) des Flugkörpers, für die relative Geschwindigkeit Zeilobjekt-Flugkörper (VR) und für den Winkel (D) zu einem früheren Zeitpunkt berechnet wird, und daß die zusätzlichen Mittel zum Berechnen (13) eine zusätzliche Verzögerungszeit t erarbeiten, die vom Zeitpunkt der Messungen an abwärtsgezählt wird und deren Ablauf den Beginn des Abwärtszählens der Verzögerung (T oder T1) für das Abschießen der Ladung (10) erlaubt, sobald die Mittel zur Näherungs-erfassung (8) das Zielobjekt (3) entdeckt haben.
6. Waffensystem nach Anspruch 5, dadurch gekennzeichnet, daß die zusätzliche Verzögerungszeit t von den zusätzlichen Mitteln zum Berechnen (13) berechnet wird und proportional zum Kehrwert der Quadratwurzel aus der relativen Geschwindigkeit (VR) ist.
7. Waffensystem nach einem der Ansprüche 5 oder 6, dadurch gekennzeichnet, daß die zusätzlichen Mittel zum Berechnen (13) aus einem ersten, die Messungen der verschiedenen Parameter bestimmenden und die notwendigen Berechnungen bewirkenden Kreis (18), einem zweiten, den Zeitpunkt, von dem an die Dauer der Verzögerung (T oder T1) ausgewertet werden soll, bestimmenden Kreis (19) und einem dritten, die Dauer der Verzögerung (T oder T1) selbst auswertenden Kreis (20) bestehen.
EP85400715A 1984-04-13 1985-04-10 Waffensystem und Rakete zur Zerstörung der Struktur eines Luftzieles mittels einer konzentrierten Ladung Expired EP0161962B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT85400715T ATE36066T1 (de) 1984-04-13 1985-04-10 Waffensystem und rakete zur zerstoerung der struktur eines luftzieles mittels einer konzentrierten ladung.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8405913A FR2563000B1 (fr) 1984-04-13 1984-04-13 Systeme d'arme et missile pour la destruction structurale d'une cible aerienne au moyen d'une charge focalisee
FR8405913 1984-04-13

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EP0161962A1 EP0161962A1 (de) 1985-11-21
EP0161962B1 true EP0161962B1 (de) 1988-07-27

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US (1) US4625647A (de)
EP (1) EP0161962B1 (de)
JP (1) JPH0785000B2 (de)
AT (1) ATE36066T1 (de)
AU (1) AU570778B2 (de)
DE (1) DE3564030D1 (de)
FR (1) FR2563000B1 (de)

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DE3617487C1 (en) * 1986-05-24 1990-03-01 Messerschmitt Boelkow Blohm Warhead detonator for guided missile - compares radius vector valve with threshold signal as target is approached
EP0309734A1 (de) * 1987-09-29 1989-04-05 Werkzeugmaschinenfabrik Oerlikon-Bührle AG Verfahren zum Zünden eines Geschosses G in der Nähe eines Zieles Z
US4972775A (en) * 1989-12-18 1990-11-27 General Electric Company Electrostatic passive proximity fuzing system
EP0547391A1 (de) * 1991-12-18 1993-06-23 Oerlikon Contraves AG Verfahren zur Erhöhung der Erfolgswahrscheinlichkeit bei der Flugkörperabwehr mittels eines fernzerlegbaren Geschosses
SE508651C2 (sv) * 1995-10-05 1998-10-26 Bofors Ab För eldrörsvapen avsedd granat
FR2775341B1 (fr) * 1998-02-20 2000-06-23 Tda Armements Sas Procede de calcul de l'instant de mise a feu d'une charge d'un mobile
US6279478B1 (en) * 1998-03-27 2001-08-28 Hayden N. Ringer Imaging-infrared skewed-cone fuze
US6298787B1 (en) 1999-10-05 2001-10-09 Southwest Research Institute Non-lethal kinetic energy weapon system and method
US7827900B2 (en) * 2004-10-07 2010-11-09 Innovative Survivability Technologies, Inc. Explosive round countermeasure system
US9849785B1 (en) * 2012-12-10 2017-12-26 The United States Of America, As Represented By The Secretary Of The Navy Method and apparatus for state space trajectory control of uncertain dynamical systems
CN103837868B (zh) * 2013-12-12 2016-05-25 江南机电设计研究所 一种侧向探测天线引信信号处理装置及其方法
KR102063293B1 (ko) * 2018-11-12 2020-01-07 국방과학연구소 파편화 가능한 직격 방식의 요격 미사일
CN110645843B (zh) * 2019-08-16 2020-08-14 北京理工大学 针对高速机动目标的高动态补偿制导控制系统及方法
CN114763980A (zh) * 2020-12-31 2022-07-19 深圳市卫飞科技有限公司 驱赶弹

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US4168663A (en) * 1954-12-01 1979-09-25 The United States Of America As Represented By The Secretary Of The Army Computer fuzes
US3858207A (en) * 1966-09-29 1974-12-31 Us Navy Range sensing target detecting device
US3933097A (en) * 1968-01-04 1976-01-20 The United States Of America As Represented By The Secretary Of The Navy Device to determine effective target size for fixed angle fuzes
DE2347374C2 (de) * 1973-09-20 1982-05-13 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Abstandszünder für einen Gefechtskopf
DE2527368C2 (de) * 1975-06-19 1982-05-13 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Annäherungszünder
JPS58195800A (ja) * 1982-05-10 1983-11-15 株式会社東芝 誘導飛翔体

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FR2563000B1 (fr) 1986-06-06
FR2563000A1 (fr) 1985-10-18
JPH0785000B2 (ja) 1995-09-13
EP0161962A1 (de) 1985-11-21
US4625647A (en) 1986-12-02
AU3981885A (en) 1985-10-17
DE3564030D1 (en) 1988-09-01
ATE36066T1 (de) 1988-08-15
JPS6141900A (ja) 1986-02-28
AU570778B2 (en) 1988-03-24

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