EP0655599B1 - Système de défense antiaérien et missile de défense pour un tel système - Google Patents

Système de défense antiaérien et missile de défense pour un tel système Download PDF

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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
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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
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German (de)
English (en)
French (fr)
Other versions
EP0655599A1 (fr
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
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Airbus Group SAS
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Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0655599A1 publication Critical patent/EP0655599A1/fr
Application granted granted Critical
Publication of EP0655599B1 publication Critical patent/EP0655599B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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).

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  • 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)
EP94402386A 1993-11-25 1994-10-24 Système de défense antiaérien et missile de défense pour un tel système Expired - Lifetime EP0655599B1 (fr)

Applications Claiming Priority (2)

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

Publications (2)

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

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

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Also Published As

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

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