EP0455531A1 - Verfahren zur Selbstlenkung eines Flugkörpers gegen ein Überschallziel - Google Patents

Verfahren zur Selbstlenkung eines Flugkörpers gegen ein Überschallziel Download PDF

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Publication number
EP0455531A1
EP0455531A1 EP91401006A EP91401006A EP0455531A1 EP 0455531 A1 EP0455531 A1 EP 0455531A1 EP 91401006 A EP91401006 A EP 91401006A EP 91401006 A EP91401006 A EP 91401006A EP 0455531 A1 EP0455531 A1 EP 0455531A1
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EP
European Patent Office
Prior art keywords
missile
target
trajectory
supersonic
pressure sensors
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.)
Granted
Application number
EP91401006A
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English (en)
French (fr)
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EP0455531B1 (de
Inventor
Jean Loup Durieux
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.)
Steria SA
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Steria SA
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Publication date
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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
    • F41G7/228—Homing guidance systems characterised by the type of waves using acoustic waves, e.g. for torpedoes

Definitions

  • the present invention relates to a method for homing tactical missiles to a supersonic aim.
  • the guided organ of guided missiles is a sensor sensitive to the electromagnetic or infrared radiation of the target.
  • This sensor is, in general, carried on a mobile pointing system slaved to the goal called seeker.
  • Gyros mounted on the seeker measure the absolute angular speed of the line of sight which is, to the accuracy of the servo, the missile-target line.
  • the sensor can also be linked to the missile.
  • the absolute angular speed of the missile-target line is obtained by combining the direction of the target relative to the missile, measured by the sensor, and the absolute orientation of the missile measured by an inertial unit.
  • the electromagnetic sensor is active or passive, depending on whether or not it emits radiation illuminating the target.
  • the guidance law transforms the absolute angular speed of the line of sight into a missile order. It requires knowledge of the target missile radial speed which is either measured or estimated.
  • shock wave is used here to define the pressure wave induced over a long distance by a supersonic target, comparable to a thin sheet of revolution, propagating according to the laws of acoustics.
  • acoustic wave could be used in an equivalent manner.
  • the subject of the invention is therefore a method of guiding a supersonic anti-air missile towards a supersonic target characterized in that it consists in slaving the trajectory of the missile to the shock wave induced at high speed by said target.
  • the missile is provided with a rustic inertial unit providing at all times a measurement of its position M, its speed vector V M , its acceleration T M and its reference trihedron T M in an inertial reference trie T O.
  • the sensitive guidance member replacing the seeker, consists of one or more pressure sensors placed on board the missile.
  • These sensors may consist of one or more orifices distributed over the missile connected to as many pressure detectors, or to a single detector for all of the orifices. These are simple microphone type detectors. These sensors detect and date, thanks to an internal clock, their passage through the shock wave of the target. Taking into account the stiffness of the front of the shock wave of the target, these passages are dated with very great precision. The bandwidth of the sensors is chosen accordingly.
  • Figure 1 shows possible locations of sensors 1, 2, 3 installed on board missile 4.
  • the order of guidance produces a trajectory of the missile, which, relative to the goal has the appearance of a sinusoid of small amplitude located alternately inside and outside the conical sheet by following a generator of this tablecloth.
  • the measurements contributing to the development of the order are carried out at each crossing of the conical sheet. Interception takes place when the missile arrives at the top of the cone which obviously requires that its speed be higher than that of the target.
  • FIG. 2 shows the target 5, the absolute trajectory 6 of the target, the missile 4, the conical shock wave 7 of the target 5, the average relative trajectory 8 of the missile 5 which is a generator of the cone, the absolute trajectory average 9 of the missile leading to the interception point 10.
  • the guidance law comprises two functional modules programmed on the missile computer.
  • the first called the estimator, determines the speed of the missile relatively to the conical tablecloth at each crossing of it.
  • the second called the controller, develops the missile command according to the estimated relative speed.
  • the estimator estimates the trajectory of the target defined by its position B and its speed vector V B , ie in all six parameters, from the successive positions of the pressure sensors M C (k, i) at the crossing of the wave shock (k the number of the sensor, i number of the crossing), occurring at the instant . These positions are deducted from the position at the missile developed by the inertial unit and the arrangement of the sensors in the missile.
  • the controller prepares the orders ordered with the missile.
  • the missile to which the invention applies can have any organization. It can be stabilized in roll or in natural autorotation. Its lateral movement can be produced by aerodynamic and / or pyrotechnic forces. The taking of incidence can be caused by an aerodynamic (control), pyrotechnic (impeller, transverse jet) or other actuator.
  • the actuator can operate along two transverse axes of maneuver (yaw, pitch) or only one (if the missile is directly in autorotation).
  • the command ordered can be addressed directly to the actuator (s) or to an autopilot, if it exists. It can be an autopilot under acceleration or transverse angular velocity. The following presentation is made by assuming a missile stabilized in roll and equipped with an autopilot in acceleration.
  • the accelerated missile orders are first calculated in the reference frame x c , y c , z c . They have two components.
  • the function f is chosen, in conjunction with the amplitude ⁇ max of the command and the dynamics of the missile, to adjust the amplitude and the frequency of the limit cycle as appropriate.
  • the passage distance is of the order of the amplitude of this cycle.
  • the acceleration orders are then calculated in the missile coordinate system x m y m , z m (measured by the inertial unit), on the condition that their projections on y c and z c are respectively equal to ⁇ yc and ⁇ zc ,
  • FIG. 3 constitutes a simplified functional diagram of the method according to the invention showing the functions exercised by the sensor (s) (function A), the inertial unit (function B), the estimator (functions C) and the controller (functions D).
  • FIG. 4 shows the relative trajectory 8 ′ of the missile around the cone generator 8 contained in the plane defined by this generator 8 and the normal 11.
  • the missile is launched from a firing station.
  • the invention applies to a land, naval or air fire station.
  • the launching direction can be arbitrary under the conditions that the missile rallies the shock wave of the target and has sufficient kinematic capacities to enslave itself there and catch up with the target.
  • the missile is slaved to a precalculated rallying trajectory under the criterion that the speed of the missile relative to the goal at the first crossing of the the shock wave has a direction as close as possible to that of the generatrix of the conical sheet, that is to say that the kinematic condition of interception indicated in FIG. 5 is fulfilled.
  • FIG. 6 shows a complete relative trajectory of interception for a shooting station located inside the conical sheet, which could be the case of an air-air shooting. We see the target 5, its shock wave 7, the relative rallying trajectory 16 and the relative interception trajectory 17.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (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)
EP19910401006 1990-04-23 1991-04-16 Verfahren zur Selbstlenkung eines Flugkörpers gegen ein Überschallziel Expired - Lifetime EP0455531B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9005305 1990-04-23
FR9005305A FR2661245B1 (fr) 1990-04-23 1990-04-23 Procede d'autoguidage d'un missile supersonique sur une cible supersonique comportant les dispositions de mise en óoeuvre et les modalites d'utilisation du procede.

Publications (2)

Publication Number Publication Date
EP0455531A1 true EP0455531A1 (de) 1991-11-06
EP0455531B1 EP0455531B1 (de) 1995-02-22

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP19910401006 Expired - Lifetime EP0455531B1 (de) 1990-04-23 1991-04-16 Verfahren zur Selbstlenkung eines Flugkörpers gegen ein Überschallziel

Country Status (3)

Country Link
EP (1) EP0455531B1 (de)
DE (1) DE69107508T2 (de)
FR (1) FR2661245B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6563763B2 (en) * 2001-04-03 2003-05-13 Aai Corporation Method and system for correcting for curvature in determining the trajectory of a projectile
CN109596019A (zh) * 2018-12-19 2019-04-09 中国空气动力研究与发展中心超高速空气动力研究所 一种弹丸飞行速度和轨迹的测量装置及测量方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE915790C (de) * 1943-12-03 1954-07-29 Otto Nitzschke Verfahren und Vorrichtung zum Zuenden von Geschossen
US3678453A (en) * 1970-10-23 1972-07-18 Us Army Flush mounted acoustic sensor
DE3334758A1 (de) * 1983-09-26 1985-04-18 Bundesrepublik Deutschland, vertreten durch den Bundesminister der Verteidigung, dieser vertreten durch den Präsidenten des Bundesamtes für Wehrtechnik und Beschaffung, 5400 Koblenz Hubschrauberbekaempfungsverfahren mit lenkflugkoerper
EP0157397A2 (de) * 1984-04-03 1985-10-09 DRELLO, Ing. Paul Drewell GmbH & Co. KG Anordnung zur Ermittlung der Trefferlage und/oder der Geschwindigkeit und/oder des Auftreffwinkels von mit Überschallgeschwindigkeit auf ein Ziel treffenden Geschossen
DE3528075A1 (de) * 1985-08-05 1987-02-12 Ingbuero Fuer Elektro Mechanis Verfahren und einrichtung zur stereoakustischen trefferablagemessung von geschossen
DE3535575C1 (en) * 1985-10-05 1989-11-23 Licentia Gmbh Fuze sensor for a projectile mine, and a method for use of the detonating sensor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE915790C (de) * 1943-12-03 1954-07-29 Otto Nitzschke Verfahren und Vorrichtung zum Zuenden von Geschossen
US3678453A (en) * 1970-10-23 1972-07-18 Us Army Flush mounted acoustic sensor
DE3334758A1 (de) * 1983-09-26 1985-04-18 Bundesrepublik Deutschland, vertreten durch den Bundesminister der Verteidigung, dieser vertreten durch den Präsidenten des Bundesamtes für Wehrtechnik und Beschaffung, 5400 Koblenz Hubschrauberbekaempfungsverfahren mit lenkflugkoerper
EP0157397A2 (de) * 1984-04-03 1985-10-09 DRELLO, Ing. Paul Drewell GmbH & Co. KG Anordnung zur Ermittlung der Trefferlage und/oder der Geschwindigkeit und/oder des Auftreffwinkels von mit Überschallgeschwindigkeit auf ein Ziel treffenden Geschossen
DE3528075A1 (de) * 1985-08-05 1987-02-12 Ingbuero Fuer Elektro Mechanis Verfahren und einrichtung zur stereoakustischen trefferablagemessung von geschossen
DE3535575C1 (en) * 1985-10-05 1989-11-23 Licentia Gmbh Fuze sensor for a projectile mine, and a method for use of the detonating sensor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6563763B2 (en) * 2001-04-03 2003-05-13 Aai Corporation Method and system for correcting for curvature in determining the trajectory of a projectile
CN109596019A (zh) * 2018-12-19 2019-04-09 中国空气动力研究与发展中心超高速空气动力研究所 一种弹丸飞行速度和轨迹的测量装置及测量方法

Also Published As

Publication number Publication date
EP0455531B1 (de) 1995-02-22
DE69107508D1 (de) 1995-03-30
DE69107508T2 (de) 1995-06-14
FR2661245B1 (fr) 1994-07-29
FR2661245A1 (fr) 1991-10-25

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