EP0655599B1 - Flugabwehrsystem und Flugabwehrkörper dafür - Google Patents

Flugabwehrsystem und Flugabwehrkörper dafür Download PDF

Info

Publication number
EP0655599B1
EP0655599B1 EP94402386A EP94402386A EP0655599B1 EP 0655599 B1 EP0655599 B1 EP 0655599B1 EP 94402386 A EP94402386 A EP 94402386A EP 94402386 A EP94402386 A EP 94402386A EP 0655599 B1 EP0655599 B1 EP 0655599B1
Authority
EP
European Patent Office
Prior art keywords
missile
defence
interception
trajectory
airborne
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.)
Expired - Lifetime
Application number
EP94402386A
Other languages
English (en)
French (fr)
Other versions
EP0655599A1 (de
Inventor
Pierre Laures
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.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0655599A1 publication Critical patent/EP0655599A1/de
Application granted granted Critical
Publication of EP0655599B1 publication Critical patent/EP0655599B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2273—Homing guidance systems characterised by the type of waves
    • F41G7/2286—Homing guidance systems characterised by the type of waves using radio waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2206—Homing guidance systems using a remote control station
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2213—Homing guidance systems maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22—Homing guidance systems
    • F41G7/2246—Active homing systems, i.e. comprising both a transmitter and a receiver

Definitions

  • the present invention relates to an anti-aircraft defense system suitable for intercepting aircraft, for example ballistic, flying at high speed (for example in the range from Mach 3 to Mach 10), as well as a defense missile for such a system.
  • the seeker is located at the front of the defense missile, inside a radome forming the front point of said missile, the axis central of said seeker being confused with the axis longitudinal of said missile, while the trajectory interception tracked by said defense missile is such attack the aerial target from the front or by the back.
  • the air target is very fast, only the frontal attack is realistic.
  • the relative speed between the defense missile and the target is then practically parallel to the axis of the target, so that only the sheaf portion aimed at said target can eventually reach this and that in this case the direction that said shards arrive on the target is slightly tilted on the axis of said target.
  • the speed VE of the defense missile is equal to 1000 m / s and that speed VI fragments is equal to 1500 m / s
  • it is easy to verify that the angle of inclination of the fragments reaching the target is inclined by about 26 degrees on the axis thereof.
  • the object of the present invention is to remedy the drawbacks mentioned above and relates to a system of air defense of the type described above for which the interception trajectory and interception time are short, so interception can occur at low altitude and that said system may be distant from a site to protect, while leaving enough time to prepare and fire a defense missile.
  • the air defense system according to the invention allows to obtain, when it implements the projection lateral flake, a direction of impact transverse to the axis of the target.
  • the defense missile observes laterally (not forward, like defense missiles known) and attacks the aerial target transversely (and not from the front or from behind, like missiles from known defense), so the intercept trajectory and interception time are greatly shortened, which provides the benefits mentioned above.
  • the seeker of the defense missile can hang said aerial machine while it describes the interception trajectory, we ensure that, at most late at the estimated time of hanging, the central axis of said seeker is in the plane defined by the position of the defense missile, the said common point and the location at this instant of said aerial vehicle, and that this latter plane is used reference plane for the stabilization in roll of said defense missile.
  • the essential characteristic of the defense missile anti-aircraft according to the present invention resides in that the central axis of its seeker is inclined laterally with respect to the axis of said defense missile.
  • the value of the lateral tilt angle of the central axis of said seeker with respect to the axis of said missile is chosen so that its tangent is at less approximately equal to the ratio between the speed of the spacecraft to be intercepted and the speed of said missile from defense. In the event that said defense missile must intercept a very fast ballistic missile, this angle can be close to 60 degrees.
  • said central axis of the seeker is orientable around the position median corresponding to the angle defined above, by example inside a cone whose half angle at the top can be approximately 40 degrees.
  • the missile according to the present invention can be provided to destroy the aerial target by direct impact or again by blast effect by the explosion of the charge military he wears when said target is at immediate proximity.
  • the defense missile in accordance with the present invention may include a proximity rocket for detect the air craft in the vicinity of the point common to approach and interception trajectories and to command said military charge.
  • a proximity rocket could, as is usual, generate a front of conical detection centered on the axis of the defense missile.
  • the said proximity rocket forms a detection front in the form of flat sheet, inclined laterally relative to the axis of said missile, on the same side as the central axis of said seeker.
  • the angle of lateral inclination of said detection front can be approximately 30 degrees.
  • said seeker is arranged in a intermediate part of said defense missile. So, this may no longer have a front radome, so that its front part can be pointed, elongated and tapered to communicate to said defense missile good properties aerodynamics.
  • Figure 1 is a general schematic view illustrating the implementation of the air defense system in accordance with the present invention.
  • FIG. 2 shows the block diagram of the installation of fixed control of the air defense system of the invention.
  • Figure 3 shows schematically a defense missile according to the present invention.
  • Figure 4 is a schematic perspective view illustrating determining the interception trajectory followed by a defense missile.
  • Figure 5 shows the parameters defining the trajectory interception.
  • Figure 6 schematically illustrates the start of the phase final of the interception, upon detection of said aerial missile by the proximity missile of the defense missile.
  • FIG. 7 is a diagram of the speeds at the time of detection illustrated in Figure 6.
  • Figure 8 schematically illustrates the impact of the sheaf of fragments on said air vehicle.
  • the anti-aircraft defense system illustrated schematically in Figure 1, includes an installation monitoring and control 1, arranged on the ground G, thus than a set of air defense missiles 2.
  • an installation monitoring and control 1 arranged on the ground G, thus than a set of air defense missiles 2.
  • a enemy air craft including a ballistic missile to high speed, is detected and identified by the installation 1 (arrow E), this determines, using radars and calculators it includes, the opportunity and the conditions interception of the device 3.
  • the installation 1 determines the speed VB of the enemy machine 3, which then becomes the target to be shot down, as well as the approach trajectory T followed by said machine 3, and calculates a trajectory of interception t to be followed by a defense missile 2, awaiting launch at a location A, to intercept the missile 3 at a point F, at which said trajectories T and t intersect at an angle at least substantially equal to 90 degrees.
  • the installation 1 then proceeds to launch said defense missile 2, at an instant such that, taking into account the speed possibilities of a defense missile 2, the latter and said missile 3 are at the same instant at point F, or at least in the vicinity of this point.
  • each defense missile 2 includes electronic guidance means capable of cooperate with installation 1 and a seeker associated with an inertial unit.
  • a missile 2 follows a launching trajectory (which may not coincide with the trajectory t ) entirely determined by the cooperation of installation 1 and electronic guidance means on board said missile 2. Then, always thanks to this cooperation via a radio transmission symbolized by the arrows f , the installation 1 obliges the defense missile 2 to follow the interception trajectory t in the direction of the interception point F. Finally, when the missile 2 is close enough to missile 3 and the latter has been hooked by the seeker of said missile 2, the latter is guided on said missile by the action of said seeker.
  • the example of defense missile 2 of axis L-L shown schematically in Figure 3, has a system propellant 20 disposed at the rear; at least one charge flashing military 21; an equipment compartment 22 enclosing an inertial unit, a computer and a transmitter radioelectric; 23 aerodynamic control surfaces fitted movable at the end of wings 24; a device 25 for the control of mobile aerodynamic control surfaces 23; a seeker adjustable in orientation 26; electronics 27 associated with said seeker 26; a side window 28 for the passage of the seeker beam 26; a proximity rocket 29; and a pointed front end 30 and tapered.
  • defense missile 2 could be provided with a force piloting system, comprising in known manner side nozzles supplied by controllable gas jets.
  • the seeker has been illustrated.
  • orientable 26 in the form of an aerial seeker mobile. It is of course possible to use antennas electronically controlled, said static antennas then being pressed against the side wall of missile 2 at the location of the side window 28, which then no more object.
  • the devices 4, 6 and 10 of installation 1 can be similar to known devices and work identically to these.
  • the tracking device 6 address to the information calculation device concerning the approach path T, the positions of the aerial vehicle 3 on the trajectory T and the speed VB of said air vehicle. From this information, as well as maneuverability and location Defense missile 2 (and other factors, such as drop point of debris from intercepted device 3), the calculation device 7 determines a point F of the trajectory of approach T favorable to interception.
  • the missile 2 must intercept the air vehicle 3 crosswise, the tangent tg to the trajectory t at point F is orthogonal to the trajectory T. It is therefore in the normal plane ⁇ in F to the trajectory T. This tangent tg thus happens to be the intersection of the vertical plane AHF and the plane ⁇ .
  • the interception trajectory t in the AHF plane is perfectly defined by the initial tangent ti, for example vertical, at point A, by the horizontal distance X separating the points A and H, by the vertical distance Z separating points F and H, and by the angle a made by the tangent tg with the horizontal, at the interception point F.
  • the interception time DI (duration between the launch firing and the arrival at point F of the missile 2 along the trajectory t ) is therefore defined by the three parameters X, Z and ⁇ .
  • the latter can advantageously be tabulated a priori so that the firing parameters (instant of departure of the missile and guidance orders by the device 8) are established in a very short time.
  • this algorithm determines the point C of the trajectory t from which the seeker of the missile of defense is able to hang the airship and the point D of the trajectory T corresponding to the estimated position of said aerial vehicle at the moment of attachment (see figure 4).
  • the computer 7 calculates at at all times the DV flight time required by the craft aerial 3 to reach point F following the trajectory T.
  • the flight time DV of craft 3 is greater than DI.
  • the DV flight time is constantly decreasing and, from that its value becomes equal to DI, the launch device 10, controlled by the computing device 7 (by the link 13), fire said defense missile 2.
  • the device 4,5 informs the launching device 10 (by the link 12), as well as the tracking device 6. Consequently, a defense missile 2 is prepared for launch fire by the device 10 (by the link 11), while the calculation device 7 determines, as described above, the approach trajectory T, the point of interception F, interception trajectory t , interception time DI and flight time DV.
  • the launching device 10 launches said defense missile 2, for example vertically.
  • the radio link (arrows f) between the guidance device 8,9 and the defense missile 2 the latter is then guided on the interception trajectory t , in a manner similar to the known technique.
  • the device 8, 9 checks the trajectory of the defense missile 2 and, optionally, modifies the acceleration of said missile 2 around said interception trajectory, according to the most recent data of the trajectory of the air vehicle and of the missile. of defense, so that the interception of said aerial vehicle 3 can take place at a point F, which is then re-specified by the computing device 7.
  • the guidance device 8, 9 then controls the missile 2 by rolling, so that the central axis AD of the seeker 26 remains in a plane passing through the interception point F and the positions of the missile 2 and the air vehicle 3 at least from the moment when the missile 2 has reached point C .
  • the seeker 26 performs the space scan directed towards the air vehicle by moving the axis AD in the corner cone at the top ⁇ .
  • the guidance of the missile 2 is taken over by said seeker and the associated electronics, which maintain said missile 2 on the interception trajectory t .
  • the front of FP detection of the proximity rocket 29 of the missile of defense 2 detects a point Q from the front of air craft 3.
  • the proximity rocket 29 commands the military flash charge 21 and it projects its sheaf of shards in direction I, substantially perpendicular to the L-L axis of missile 2 and directed towards the side opposite the FP detection front (see Figure 6).
  • the shards penetrate inside the aerial vehicle 3, following the direction IR, at an angle ⁇ j important favorable to the destruction of said machine (see the figure 8).
  • the impact of the splinters is close to the front end of air craft 3 due to the high value of the angle ⁇ j (sixty degrees in the example described above).
  • the chips reach the latter in a direction IR ', substantially parallel at IR, but more towards the rear of said aerial vehicle (figure 8).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Claims (13)

  1. Luftabwehrsystem zum Abfangen von Flugkörpern mit hoher Fluggeschwindigkeit (3), mit einer stationären Steueranlage (1) und Abwehrraketen (2), wobei die stationäre Anlage (1) umfaßt:
    Mittel (4,5) zur Erfassung der Flugkörper (3);
    Mittel zur Bahnvermessung (6), um die Anflugbahn (T) und die Geschwindigkeit eines derartigen Flugkörpers (3), der von den Erfassungsmitteln (4,5) erfaßt wurde, zu bestimmen;
    Rechenmittel (7) zur Bestimmung einer Abfangflugbahn (t), die eine der Abwehrraketen (2) zum Abfangen des erfaßten Flugkörpers (3) einhalten muß;
    Mittel (10) zum Starten der Abwehrrakete (2);
    Mittel (8) zum Lenken der Abwehrrakete (2); und
    Mittel (9,11) zur Verbindung mit der Abwehrrakete (2), während jede Abwehrrakete (2) ein Antriebssystem (20), mindestens eine militärische Ladung (21), eine Trägheitsanlage (22), einen Zielsucher (26), Lageregelungsorgane (23), Verbindungsmittel (22) mit der stationären Steueranlage (1) und einen Geber von Lageregelungsbefehlen (25) hat, der die Lageregelungsbefehle aus den Informationen der Lenkmittel (8) in der stationären Steueranlage und aus den Informationen des Zielsuchers (26) erarbeitet,
    dadurch gekennzeichnet, daß:
    im gemeinsamen Punkt (F) der Anflugbahn (T) des Flugkörpers (3) und der Abfangflugbahn (t) der Abwehrrakete (2) die Abfangflugbahn quer zur Anflugbahn verläuft;
    die mittlere Achse (AD) des Zielsuchers (26) seitlich gegenüber Achse (L-L) der Abwehrrakete (2) geneigt ist;
    die Rechenmittel (7) den Zeitpunkt einschätzen, zu dem der Zielsucher (26) den Flugkörper erfaßt;
    die Abwehrrakete (2) rollstabilisiert ist, so daß sich die mittlere Achse (AD) des Zielsuchers auf der Seite des Flugkörpers (3) befindet; und
    sich die mittlere Achse (AD) des Zielsuchers (26) spätestens zum geschätzten Erfassungszeitpunkt des Flugkörpers (3) durch den Zielsucher (26) der Abwehrrakete (2) in der Ebene (CFD) befindet, die von der Position (C) der Rakete (2) in diesem Augenblick, dem gemeinsamen Punkt (F) und dem Punkt (D) gebildet wird, der der Position des Flugkörpers (3) zu diesem Zeitpunkt entspricht, wobei diese Ebene (CFD) als Referenzebene für die Rollstabilisierung der Abwehrrakete (2) dient.
  2. Luftabwehrsystem nach Anspruch 1, dadurch gekennzeichnet, daß die Rechenmittel (7), die die Abfangflugbahn (t) der Abwehrrakete (2) bestimmen:
    damit beginnen, den gemeinsamen Punkt (F) der Abfangflugbahn und der Anflugbahn (t,T) zu bestimmen; und dann
    in der vertikalen Ebene (AHF), die durch den gemeinsamen Punkt (F) und durch den Standort (A) der Abwehrrakete (2) am Boden verläuft, die Abfangflugbahn (t) der Abwehrrakete (2) aus den folgenden drei Parametern bestimmen:
    der vertikalen Entfernung (Z) zwischen dem gemeinsamen Punkt (F) und seiner Horizontalprojektion (H) auf den Boden (G);
    der horizontalen Entfernung (X) zwischen dem Bodenstandort (A) der Abwehrrakete (2) und der Horizontalprojektion (H) des gemeinsamen Punkts (F) ; und
    dem Winkel (α) zwischen der Horizontalen und dem Schnittpunkt (tg) der vertikalen Ebene (AHF) und der Ebene (π) senkrecht zur Anflugbahn (T) des Flugkörpers (3) im gemeinsamen Punkt (F).
  3. Luftabwehrsystem nach Anspruch 2, dadurch gekennzeichnet, daß die Rechenmittel (7):
    mit Hilfe der drei Parameter (Z, X, α) die Abfangzeit (DI) bestimmen, die die Abwehrrakete (2) benötigt, um die Abfangstrecke (t) zwischen dem Bodenstandort (A) der Abwehrrakete (2) und dem gemeinsamen Punkt (F) der Abfang- und Anflugbahn (t,T) zurückzulegen;
    kontinuierlich die Flugzeit (DV) berechnen, die der Flugkörper (3) benötigt, um ausgehend von seiner gegenwärtigen Position nach der Anflugbahn (T) den gemeinsamen Punkt (F) zu erreichen; und
    die Mittel (10) zum Starten der Rakete (2) betätigen, so daß diese von den Mitteln (10) gestartet wird, wenn der Flugkörper (3) den Punkt (B) der Anflugbahn erreicht, an dem der Wert der Flugzeit (DV) gleich der Abfangzeit (DI) ist.
  4. Luftabwehrrakete, die an das Abwehrsystem von Anspruch 1 angepaßt wurde, um Flugkörper mit hoher Fluggeschwindigkeit quer abfangen zu können, mit einem Antrieb (20), mindestens einer militärischen Ladung (21), einer Trägheitsanlage (22), einem Zielsucher (26), Lageregelungsorganen (23) und einem Geber von Lageregelungsbefehlen (25),
    dadurch gekennzeichnet, daß die mittlere Achse (AD) des Zielsuchers (26) seitlich gegenüber der Achse (L-L) der Rakete (2) geneigt ist und der Wert (1) des seitlichen Neigungswinkels der mittleren Achse (AD) des Zielsuchers (26) gegenüber der Achse (L-L) der Rakete so gewählt wird, daß seine Tangente tg mindestens annähernd gleich dem Verhältnis zwischen der Geschwindigkeit des abzufangenden Flugkörpers und der Geschwindigkeit der Abwehrrakete ist.
  5. Rakete nach Anspruch 4,
    dadurch gekennzeichnet, daß der Wert (1) des seitlichen Neigungswinkels der mittleren Achse (AD) des Zielsuchers mindestens annähernd gleich 60 Grad ist.
  6. Rakete nach einem der Ansprüche 4 oder 5,
    dadurch gekennzeichnet, daß die mittlere Achse (AD) des Zielsuchers um ihre mittlere Position, die dem Wert (1) entspricht, schwenkbar ist.
  7. Rakete nach Anspruch 6,
    dadurch gekennzeichnet, daß die mittlere Achse (AD) des Zielsuchers (26) innerhalb eines Kegels, dessen Achse aus der mittleren Position besteht, schwenkbar ist.
  8. Rakete nach einem der Ansprüche 4 bis 7,
    dadurch gekennzeichnet, daß die militärische Ladung (21) auf der entgegengesetzten Seite der mittleren Achse (AD) des Zielsuchers (26) seitlich eine Splittergarbe auswerfen kann.
  9. Rakete nach Anspruch 8,
    dadurch gekennzeichnet, daß die mittlere Richtung (I) der Splittergarbe mindestens etwa senkrecht zur Achse der Rakete verläuft.
  10. Rakete nach einem der Ansprüche 4 bis 9, die darüber hinaus einen Näherungszünder (29) zur Erfassung eines derartigen Flugkörpers und zur Steuerung der militärischen Ladung hat,
    dadurch gekennzeichnet, daß der Näherungszünder (29) eine Erfassungsfront (FP) in Form einer ebenen Fläche bildet, die auf der gleichen Seite wie die mittlere Achse (AD) des Zielsuchers (26) seitlich gegenüber der Achse (L-L) der Rakete geneigt ist.
  11. Rakete nach Anspruch 10,
    dadurch gekennzeichnet, daß der seitliche Neigungswinkel (2) der Erfassungsfront (FP) des Näherungszünders gegenüber der Achse der Rakete mindestens annähernd 30 Grad beträgt.
  12. Rakete nach einem der Ansprüche 4 bis 11,
    dadurch gekennzeichnet, daß der Zielsucher (26) in einem Zwischenteil der Rakete (2) angeordnet ist.
  13. Rakete nach Anspruch 12,
    dadurch gekennzeichnet, daß sie kein Vorderradom hat und daß das Vorderteil spitz und langgezogen ist.
EP94402386A 1993-11-25 1994-10-24 Flugabwehrsystem und Flugabwehrkörper dafür Expired - Lifetime EP0655599B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9314082 1993-11-25
FR9314082A FR2712972B1 (fr) 1993-11-25 1993-11-25 Système de défense antiaérien et missile de défense pour un tel système.

Publications (2)

Publication Number Publication Date
EP0655599A1 EP0655599A1 (de) 1995-05-31
EP0655599B1 true EP0655599B1 (de) 1998-07-08

Family

ID=9453208

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94402386A Expired - Lifetime EP0655599B1 (de) 1993-11-25 1994-10-24 Flugabwehrsystem und Flugabwehrkörper dafür

Country Status (8)

Country Link
US (1) US5464174A (de)
EP (1) EP0655599B1 (de)
JP (1) JP3630181B2 (de)
CA (1) CA2134578C (de)
DE (1) DE69411514T2 (de)
ES (1) ES2119983T3 (de)
FR (1) FR2712972B1 (de)
IL (1) IL111419A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106643298A (zh) * 2016-11-29 2017-05-10 北京宇航系统工程研究所 一种基于预置命中点的大气层内反导拦截器中制导方法

Families Citing this family (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4442134A1 (de) * 1994-11-26 1996-05-30 Bodenseewerk Geraetetech Lenkschleife für Flugkörper
US6279482B1 (en) 1996-07-25 2001-08-28 Trw Inc. Countermeasure apparatus for deploying interceptor elements from a spin stabilized rocket
US5710423A (en) * 1996-09-27 1998-01-20 Mcdonnell Douglas Corporation Exo-atmospheric missile intercept system employing tandem interceptors to overcome unfavorable sun positions
US5862496A (en) * 1996-10-01 1999-01-19 Mcdonnell Douglas Corporation Method of computing divert velocity for the ground-based interceptor using numerical partial derivatives
US5866837A (en) * 1997-06-18 1999-02-02 Mcdonnell Douglas Corporation Method for safe flight testing of high velocity interceptor missiles
IL125455A (en) 1998-07-22 2003-12-10 Rafael Armament Dev Authority System for destroying enemy ballistic missiles
DE19847091A1 (de) * 1998-10-13 2000-04-20 Diehl Stiftung & Co Verfahren zum Schützen eines Objektes gegen die Einwirkung eines schnellen Projektiles
AUPQ524000A0 (en) * 2000-01-24 2000-06-15 Metal Storm Limited Anti-missile missiles
DE10024320C2 (de) * 2000-05-17 2002-09-05 Diehl Munitionssysteme Gmbh Radareinrichtung für den Objekt-Selbstschutz
KR20020083049A (ko) * 2001-04-25 2002-11-01 서정수 요격용 미사일
US6677571B1 (en) * 2001-04-26 2004-01-13 The United States Of America As Represented By The Secretary Of The Air Force Rocket launch detection process
GB2380244B (en) * 2001-08-13 2006-02-15 Joseph Zabrana Michael Automated Sound Missile and Associated Defence System
US6527222B1 (en) * 2001-09-18 2003-03-04 Richard T. Redano Mobile ballistic missile detection and defense system
US6584879B2 (en) * 2001-11-14 2003-07-01 Northrop Grumman Corporation System and method for disabling time critical targets
EP1314949B1 (de) * 2001-11-23 2004-12-08 Oerlikon Contraves Ag Verfahren und Vorrichtung zum Beurteilen von Richtfehlern eines Waffensystems und Verwendung der Vorrichtung
DE50204935D1 (de) * 2001-11-23 2005-12-22 Contraves Ag Verfahren und Vorrichtung zum Beurteilen der Richtfehler eines Waffensystems und Verwendung der Vorrichtung
IL149683A0 (en) * 2002-05-15 2003-07-31 Rafael Armament Dev Authority Method and system for detecting and determining successful interception of missiles
US6738012B1 (en) * 2003-05-02 2004-05-18 Honeywell Industrial Inc. Protecting commercial airliners from man portable missiles
US6796213B1 (en) * 2003-05-23 2004-09-28 Raytheon Company Method for providing integrity bounding of weapons
US6980152B2 (en) * 2003-07-03 2005-12-27 Textron Systems Corporation Externally cued aircraft warning and defense
US6825792B1 (en) 2003-10-06 2004-11-30 Howard Letovsky Missile detection and neutralization system
US7104496B2 (en) * 2004-02-26 2006-09-12 Chang Industry, Inc. Active protection device and associated apparatus, system, and method
US7066427B2 (en) * 2004-02-26 2006-06-27 Chang Industry, Inc. Active protection device and associated apparatus, system, and method
DE102004037235A1 (de) * 2004-07-31 2006-03-23 Diehl Bgt Defence Gmbh & Co. Kg Verfahren zum Schützen einer Immobilie gegen ein angreifendes Projektil
DE102004038264A1 (de) * 2004-08-06 2006-03-16 Diehl Bgt Defence Gmbh & Co. Kg Selbstschutz-Verfahren gegen die Bedrohung durch ein angreifendes Projektil
IL163450A (en) * 2004-08-10 2009-12-24 Rafael Advanced Defense Sys Guided missile with distributed guidance mechanism
US7264198B2 (en) * 2004-12-13 2007-09-04 Lockheed Martin Corporation Time-to-go missile guidance method and system
US7387060B1 (en) * 2005-05-17 2008-06-17 The United States Of America As Represented By The Secretary Of The Navy Rocket exhaust defense system and method
US8130137B1 (en) 2005-07-26 2012-03-06 Lockheed Martin Corporation Template updated boost algorithm
US7511252B1 (en) * 2006-05-09 2009-03-31 Lockheed Martin Corporation Multihypothesis threat missile propagator for boost-phase missile defense
US7473876B1 (en) * 2006-05-09 2009-01-06 Lockheed Martin Corporation Boost phase intercept missile fire control system architecture
US7755011B2 (en) * 2006-06-23 2010-07-13 Lockheed Martin Corporation Target maneuver detection
WO2008029392A2 (en) * 2006-09-03 2008-03-13 E.C.S. Engineering Consulting Services-Aerospace Ltd. Method and system for defense against incoming rockets and missiles
US8134103B2 (en) * 2006-12-27 2012-03-13 Lockheed Martin Corporation Burnout time estimation and early thrust termination determination for a boosting target
US8288696B1 (en) * 2007-07-26 2012-10-16 Lockheed Martin Corporation Inertial boost thrust vector control interceptor guidance
DE102007049438B4 (de) * 2007-10-16 2018-10-31 Mbda Deutschland Gmbh Verfahren zur Abwehr von ballistischen Geschossen mit Hilfe von Lenkflugkörpern
US7875837B1 (en) * 2008-01-09 2011-01-25 Lockheed Martin Corporation Missile tracking with interceptor launch and control
US7953524B1 (en) * 2008-02-29 2011-05-31 Rockwell Collins, Inc. Navigation through reception of a remote position fix via data link
JP2009300063A (ja) * 2008-06-10 2009-12-24 Haruo Wakabayashi 飛行体捕捉システムおよび飛行体捕捉方法
JP5224934B2 (ja) * 2008-06-25 2013-07-03 株式会社東芝 飛翔体、飛翔体の飛翔方法及びコンピュータプログラム
US8173946B1 (en) * 2008-08-26 2012-05-08 Raytheon Company Method of intercepting incoming projectile
US8063347B1 (en) * 2009-01-19 2011-11-22 Lockheed Martin Corporation Sensor independent engagement decision processing
US8380367B2 (en) * 2009-03-26 2013-02-19 The University Of North Dakota Adaptive surveillance and guidance system for vehicle collision avoidance and interception
GB2479211B (en) * 2010-03-31 2014-07-23 Qinetiq Ltd System for the detection of incoming munitions
CN101982720B (zh) * 2010-09-29 2012-11-14 北京机械设备研究所 一种低空慢速小目标的拦截方法
CN102087082B (zh) * 2010-11-22 2013-05-08 北京机械设备研究所 一种基于射表拟合的低空慢速小目标拦截方法
US8963765B1 (en) * 2010-12-14 2015-02-24 Lockheed Martin Corporation System and method for detecting use of booster rockets by ballistic missiles
CN103134387B (zh) * 2011-11-29 2014-10-15 北京航天长峰科技工业集团有限公司 一种低空慢速小目标探测与拦截系统标定方法
US9316733B2 (en) * 2012-01-04 2016-04-19 Farrokh Mohamadi W-band, ultra-wide band (UWB) trajectory detector
CN103575167B (zh) * 2013-11-07 2014-12-03 北京机械设备研究所 一种民用拦截弹弹道修正方法
RU2611683C2 (ru) * 2014-12-12 2017-02-28 Николай Евгеньевич Староверов Система преодоления противоракетной обороны противника, алгоритм её работы и боеголовка для неё
CN111369832B (zh) * 2019-12-27 2021-07-16 中国人民解放军海军大连舰艇学院 一种单艘区域舰空导弹舰艇纵横向水平机动掩护单艘邻舰方法

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH401703A (de) * 1961-09-08 1965-10-31 Siemens Ag Albis Einrichtung zur selbsttätigen Regelung der Bewegung eines selbstgelenkten Flugkörpers nach einem Ziel
US4087061A (en) * 1972-05-08 1978-05-02 The United States Of America As Represented By The Secretary Of The Navy Wide angle seeker
US3964695A (en) * 1972-10-16 1976-06-22 Harris James C Time to intercept measuring apparatus
US3924826A (en) * 1974-12-20 1975-12-09 Us Air Force Rotatable window means
US5112006A (en) * 1975-03-12 1992-05-12 The Boeing Company Self defense missile
US4098191A (en) * 1976-07-09 1978-07-04 Motorola, Inc. Passive optical proximity fuze
US4848239A (en) * 1984-09-28 1989-07-18 The Boeing Company Antiballistic missile fuze
DE3608108C1 (de) * 1986-03-12 1990-06-07 Diehl Gmbh & Co Verfahren zur Abwehr von Flugobjekten
US4925129A (en) * 1986-04-26 1990-05-15 British Aerospace Public Limited Company Missile defence system
US5080300A (en) * 1989-12-07 1992-01-14 Hughes Aircraft Company Launcher control system for surface launched active radar missiles
DE4018198C2 (de) * 1990-03-12 2000-04-20 Daimlerchrysler Aerospace Ag Lenkverfahren für Geschosse und Anordnungen zur Durchführung des Verfahrens
FR2671193B1 (fr) * 1990-12-28 1994-03-25 Thomson Brandt Armements Procede et dispositif de detection de proximite sectorielle d'une cible, et munition utilisant le dispositif.
US5368254A (en) * 1993-03-16 1994-11-29 Hughes Aircraft Company Optical imaging system including generally conical, transparent protective dome and optically refractive fixed corrector for reversing conical deformation created by viewing through the dome

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106643298A (zh) * 2016-11-29 2017-05-10 北京宇航系统工程研究所 一种基于预置命中点的大气层内反导拦截器中制导方法

Also Published As

Publication number Publication date
DE69411514D1 (de) 1998-08-13
JPH07190695A (ja) 1995-07-28
JP3630181B2 (ja) 2005-03-16
DE69411514T2 (de) 1998-12-10
IL111419A (en) 1998-02-22
CA2134578C (fr) 2005-05-24
EP0655599A1 (de) 1995-05-31
FR2712972B1 (fr) 1996-01-26
FR2712972A1 (fr) 1995-06-02
US5464174A (en) 1995-11-07
ES2119983T3 (es) 1998-10-16
IL111419A0 (en) 1995-01-24
CA2134578A1 (fr) 1995-05-26

Similar Documents

Publication Publication Date Title
EP0655599B1 (de) Flugabwehrsystem und Flugabwehrkörper dafür
EP0081421B1 (de) Verfahren zur Endphasenlenkung und dieses Verfahren verwendender Lenkflugkörper
EP1891393B1 (de) Verfahren zum schutz von fahrzeugen gegen lenkflugkörper und vorrichtung dafür
US20090314878A1 (en) Method and system for defense against incoming rockets and missiles
EP0273787B1 (de) Geschoss zum indirekten Angriff auf Panzerfahrzeuge
FR3041744A1 (fr) Projectile d'artillerie ayant une phase pilotee.
FR2695467A1 (fr) Procédé de neutralisation de cible aérienne évoluant à l'aide de pales et système et projectile pour la mise en Óoeuvre de ce procédé.
FR2940246A1 (fr) Dispositif de tir de munition a partir d'un drone arme
FR2657687A1 (fr) Munition anti-char et son procede d'utilisation.
EP0800054A1 (de) Geschoss dessen Sprengladung durch einen Zielanzeiger ausgelöst wird
EP1600728B1 (de) Flugkörper zur Geländeaufklärung
EP1093561B1 (de) Passive selbstschutzvorrichtung für bewegliche objekte wie zum beispiel einen helikopter
FR2679023A1 (fr) Procede et dispositif pour combattre un objectif immerge.
FR2583868A1 (fr) Sous-munition a tete d'allumage chercheuse.
FR2567993A1 (fr) Munition a charge explosive
FR2492966A1 (fr) Perfectionnements aux projectiles a trajectoire corrigee
FR2578665A1 (fr) Procede de pilotage d'un missile a faible vitesse, systeme d'arme et missile pour la mise en oeuvre du procede
EP0062563B1 (de) Verfahren zum Steuern der Seitwärtsbeschleunigung eines Flugkörpers und entsprechendes Waffensystem
EP0610129B1 (de) Verfahren zum Abschuss und zur Steuerung von einem bewegbaren Fahrzeug eines nicht vertikal gelenkten Geschosses mit gebremstem Flugweg
EP0482970B1 (de) Einrichtung zur Verleihung einer Flugbahnabweichung an einen aus einem Fluggerät abgeschossenen Flugkörper
FR2716966A1 (fr) Système de défense anti-aérienne à très courte portée, de type missile sol-air.
JP5506581B2 (ja) 航空機防御装置
KR20230171331A (ko) 비행체 후방 방어 시스템
BE901258A (fr) Methode d'acquisition d'une cible par un projectile guide et projectile operant selon cette methode.
FR2674952A1 (fr) Guidage pour obus stabilise par rotation non empenne ni aile avec stabilisation de la trajectoire par tuyere tractrice a effet differentiel.

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): BE CH DE ES GB GR IT LI NL PT SE

17P Request for examination filed

Effective date: 19950619

17Q First examination report despatched

Effective date: 19961220

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): BE CH DE ES GB GR IT LI NL PT SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 19980708

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: JOHN P. MUNZINGER INGENIEUR-CONSEIL

Ref country code: CH

Ref legal event code: EP

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19980710

REF Corresponds to:

Ref document number: 69411514

Country of ref document: DE

Date of ref document: 19980813

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 19981008

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2119983

Country of ref document: ES

Kind code of ref document: T3

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCAR

Free format text: JOHN P. MUNZINGER C/O CRONIN INTELLECTUAL PROPERTY;CHEMIN DE PRECOSSY 31;1260 NYON (CH)

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20070920

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 20071016

Year of fee payment: 14

Ref country code: ES

Payment date: 20071025

Year of fee payment: 14

Ref country code: DE

Payment date: 20070928

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20071029

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20071008

Year of fee payment: 14

Ref country code: BE

Payment date: 20071011

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20071024

Year of fee payment: 14

BERE Be: lapsed

Owner name: *AEROSPATIALE SOC. NATIONALE INDUSTRIELLE

Effective date: 20081031

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

EUG Se: european patent has lapsed
GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20081024

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 20090501

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090501

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081024

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090501

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081031

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081024

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20081025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081025

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20081025