EP2524189A1 - Procédé pour corriger la trajectoire d'un projectile guidé en particulier en phase finale et projectile pour la mise en uvre du procédé - Google Patents

Procédé pour corriger la trajectoire d'un projectile guidé en particulier en phase finale et projectile pour la mise en uvre du procédé

Info

Publication number
EP2524189A1
EP2524189A1 EP10795931A EP10795931A EP2524189A1 EP 2524189 A1 EP2524189 A1 EP 2524189A1 EP 10795931 A EP10795931 A EP 10795931A EP 10795931 A EP10795931 A EP 10795931A EP 2524189 A1 EP2524189 A1 EP 2524189A1
Authority
EP
European Patent Office
Prior art keywords
projectile
laser beam
correction
target course
time
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
EP10795931A
Other languages
German (de)
English (en)
Other versions
EP2524189B1 (fr
Inventor
Jens Seidensticker
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rheinmetall Air Defence AG
Original Assignee
Rheinmetall Air Defence AG
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 Rheinmetall Air Defence AG filed Critical Rheinmetall Air Defence AG
Publication of EP2524189A1 publication Critical patent/EP2524189A1/fr
Application granted granted Critical
Publication of EP2524189B1 publication Critical patent/EP2524189B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems
    • F41G7/263—Means for producing guidance beams
    • 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
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems
    • 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
    • F41G7/24—Beam riding guidance systems
    • F41G7/26—Optical guidance systems
    • F41G7/266—Optical guidance systems for spin-stabilized missiles

Definitions

  • the invention is primarily concerned with the coding of a distance-dependent release, in particular end-phase steered projectiles in the medium caliber range and preferably relates to a Leitstrahl compiler as a method for detecting the shelf size of the projectile.
  • Straight end-steered projectiles usually have to be changed in their trajectory or they can change themselves. This is done either by aerodynamic or pulse generating actuators.
  • the steering information is determined autonomously in the projectile or by means of a seeker head, or alternatively forwarded from the ground (guide-beam method).
  • DE 44 16 210 A1 relates to a method and a device for determining the roll angle position on the basis of laser light.
  • a phase-coded laser light beam is generated by means of a holographic optical element. This is decoded by means of another holographic element on the missile. The generated signal is then used for correction.
  • DE 44 16 211 A1 discloses a method and a device for trajectory correction of projectiles.
  • a guide beam laser In order to correct both individual projectiles and a plurality of temporally closely spaced projectiles with different shelves, it is proposed to divide a guide beam laser into at least five sub-beams or segments which are arranged around a central guide beam segment aligned with the collision point.
  • Each Leitstrahlsegment is modulated differently. With the help of the receiving device in the projectile this then determines from the modulation of the Leitstrahlsegmentes the angular position required for the correction with respect to the collision point.
  • CONFIRMATION COPY EP 2 083 243 A2 includes a method for determining the roll angle position of a missile.
  • the method comprises generating a moving laser beam pattern over a solid angle of a laser beam, within which the missile is located. This step is followed by the detection of the laser light on the missile by a detection point located laterally to its axis of rotation and the tap of the laser beam pattern at the respective position of the detection point and determination of the instantaneous roll angle position based on the Doppler shift.
  • the laser beam pattern is hereby generated by stripes which move at a predetermined frequency over the solid angle of the laser beam.
  • EP 2 128 555 describes a method for determining the roll angle position of a rotating projectile or missile.
  • a light beam receiving from the missile is emitted by a fixed station, which focuses the light beam onto a sensor in the tail of the missile with the aid of an optical element.
  • the focusing is dependent on the angular position of the missile in space.
  • WO 2009/085064 A2 a method is known in which the programming is carried out by retransmitting light beams.
  • the projectile has peripheral optical sensors.
  • This embossing is transmitted to the projectile, for example, based on the AHED method with an induction coil at the muzzle (CH 691 143 A5).
  • Alternative transmission possibilities for example by means of microwave transmitters, can be deduced to the person skilled in the art, for example, from EP 1 726 91 1 A1.
  • the invention has as its object to provide a simple trajectory correction method that acts effectively.
  • the object is achieved by the features of claim 1.
  • Advantageous embodiments are reflected in the dependent claims.
  • the invention is based on the basic idea of the Leitstrahlvons for each floor, based on the idea to run a laser beam around the center of the current target course of the projectile or rotate so that the projectile itself recognizes its filing and then makes a self-correction.
  • a method known from seeker heads is combined with that of the beacon method without seeker head.
  • other electro-magnetic waveforms such as light, radar, microwave radiation in sufficiently focused and directed form can be used; also in combination with each other.
  • a laser is used by way of example for directional information transmission.
  • the projectile is tracked after leaving the tube on its path by sensors, such as radar or optronic type, and continuously compared the actual trajectory with the desired trajectory. Correction may also be required by the target changing its predicted trajectory; in this case, the desired trajectory of the projectile of the changed target trajectory is tracked. If the bullet is in the central circle, it is on target. If the target course is found to be outside the range, the trajectory must be corrected. For the correction, an optionally modulated laser beam bundle is forwarded around the center of the projectile to the projectile in the Leitstrahlsupervised.
  • the pulse engine (s) could be variably dimensioned in terms of their (their) effectiveness or else one or more pulse engines (e) with fixed pulse power could be ignited at different times with respect to the expected impact point on the target. A combination of these options is possible. If a smaller offset correction is desired, the pulse engine (s) ignites shortly before the calculated impact point on the target, with a larger correction, the engine is ignited correspondingly earlier with a shorter or longer residual flight time.
  • a first laser flash over a certain range is triggered, which preferably simultaneously triggers the beginning of a time count.
  • a two- The laser then rotates around a central circle at a preferably fixed rotational frequency.
  • the projectile recognizes the second laser after a certain time. This time corresponds to a bearing or angle around the central circle.
  • a sensor After recognizing its geostationary position in space, a sensor then initiates at least one pulse engine (if several are involved, including these) in such a way that it is again at target speed at the target and thus hits the target.
  • the projectile To calculate the correct ignition timing in relation to the time of impact, the projectile not only detects the size of its deposit, but also the corresponding earlier or later ignition of the pulse engine (s).
  • the laser beam is coded dependent on the storage in continuation of the invention.
  • this can be done by dividing the laser beam in the form of a grid in light and dark zones.
  • the projectile with its sensor preferably tail sensor
  • senses for example, fewer dark lines than in the outer area.
  • This is then interpreted as a larger filing.
  • the size of the tray is then determined and, in the case of a large tray, the correction is initiated immediately, with a smaller one correspondingly later.
  • the projectile has a Geuntere own processor in which the respective delays are preprogrammed or stored.
  • This process is used in addition to a cutting ammunition also in shaped charge projectiles or the like. It is due to the high penetration and high temperature and the fight mortars possible.
  • a laser beam is projected over a certain range around the target course of the projectile. sent, which can simultaneously trigger the start of a time counting. For example, at the same time, another rotating laser beam with a fixed rotational frequency is placed around the area. Based on this second laser beam, the projectile then recognizes its deposit relative to the target course and initiates the correction on the basis of the determined deposit. The size of the determined storage is then used to make the timing of the correction. For this purpose, delays of the triggering are implemented in the projectile.
  • Fig. 1 shows a projectile or missile 1 with a rear side receiving window and a rear sensor 2, a sensor 3, explosive 4 and a discharge element 5 as a correction pulse motor 6.
  • an on-board processor is characterized, which is functionally connected to the other modules in combination ,
  • a coding corresponding time delays for the initiation of the pulse motor 6 are deposited.
  • a magnetic field sensor is preferably used as the sensor 3.
  • a sensor 100 integrated on the weapon side is identified by 11 and 12 two laser beams which are generated, for example, by two laser devices 13, 14 (FIG. 2).
  • the magnetic field sensor 3 recognizes, on the one hand, the rotational speed (rolling rate) of the projectile 1 and, on the other hand, the direction of the fundamentally known terrestrial magnetic field relative to the projectile 1.
  • the projectile 1 itself, after leaving a non-illustrated Tube of a weapon tracked on its path by at least one sensor 10 and continuously compared the actual flight path with a desired trajectory. If a deviation is detected, the emission of an optionally spatially modulated laser beam bundle 12 takes place around the center of the current target course, so that the projectile 1 detects its deposit itself and makes the correction by initiating the pulse motor 6.
  • the bundle 12 is sensed by the rear sensor 2.
  • Fig. 3 shows the projectile 1 in relation to different areas 15, which are formed by the laser beam 11 in a plane perpendicular to the trajectory of the projectile. If the projectile is in the central circular path 13, which is hatched vertically in the FIGURE, it is on the target course. If, however, it is outside of this range 13, the trajectory must be corrected.
  • a first laser flash 1 is triggered over a certain area 15, which can simultaneously trigger the start of a time counting.
  • the projectile 1, which is located in the right lower region 17 in the exemplary embodiment, recognizes the second laser steel 12 after a time ⁇ ⁇ . This time corresponds to a position around the central circle (13) in space by the angle o ⁇ .
  • the projectile 1 can then initiate detection of its geostationary position in space via the magnetic field sensor 3, the pulse motor 6 so that it is in the target (not shown) again on the target course and hits the target.
  • the pulse engine 6 is ignited just before the calculated impact point in a smaller storage.
  • a larger deposit causes an earlier ignition with a shorter or longer residual flight time.
  • the laser beam 12 is additionally coded.
  • the coding can be done by dashes (FIG. 4), dots (FIG. 3) as well as combinations of both, etc. in the laser beam 12. 4 shows a further position-dependent position determination.
  • the rotating laser beam 12 is asymmetrically (in the tray) (ie shaped in the radial direction around the desired trajectory around, for example tapering towards the outer edge or as shown - tapering towards the center) and is by a grid 18 in Hell - and dark zones 19, 20 divided. If the projectile 1 is located outside the central core area 13 but in the vicinity, the projectile 1 with its rear sensor 2 senses, for example, two to three dark lines.
  • the bullet 1 therefore has to initiate the correction earlier or even immediately in the case of a large deposit, whereas in the case of a smaller deposit the bullet 1 can take place later in time.
  • This information is stored, for example, from the comparison of earlier identical situations in the processor 7, ie, in the processor 7, the respective delays are preprogrammed accordingly.
  • the use of the method is not limited to bullets or ammunition in the medium caliber range, but the use is caliber independent.

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)
  • Optical Radar Systems And Details Thereof (AREA)
  • Lasers (AREA)
  • Laser Surgery Devices (AREA)

Abstract

L'invention a pour objectif de guider et de tourner un faisceau de rayons laser (12) autour du centre (13) du cap théorique momentané d'un projectile (1), de telle sorte que le projectile (1) reconnaisse lui-même sa déviation et effectue alors une autocorrection. A cet effet, un premier rayon laser (11) est envoyé sur une zone définie (15) autour du cap théorique du projectile (1), qui peut déclencher en même temps le début d'un chronométrage. Dans le même temps, un autre rayon laser (12) rotatif est placé par exemple à une fréquence de rotation (Ω) fixe autour de la zone (15). A l'aide de ce second rayon laser (12), celui-ci détecte sa déviation par rapport au cap théorique et amorce la correction sur la base de la déviation déterminée. La grandeur de la déviation déterminée est utilisée ensuite pour effectuer l'amorçage dans le temps de la correction. A cet effet, des temporisations du déclenchement sont mises en place dans le projectile (1).
EP10795931.4A 2010-01-15 2010-12-07 Procédé pour corriger la trajectoire d'un projectile guidé en particulier en phase finale et projectile pour la mise en oeuvre du procédé Active EP2524189B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010004820A DE102010004820A1 (de) 2010-01-15 2010-01-15 Verfahren zur Flugbahnkorrektur eines insbesondere endphasengelenkten Geschosses sowie Geschoss zur Durchführung des Verfahrens
PCT/EP2010/007428 WO2011085758A1 (fr) 2010-01-15 2010-12-07 Procédé pour corriger la trajectoire d'un projectile guidé en particulier en phase finale et projectile pour la mise en œuvre du procédé

Publications (2)

Publication Number Publication Date
EP2524189A1 true EP2524189A1 (fr) 2012-11-21
EP2524189B1 EP2524189B1 (fr) 2016-03-02

Family

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Application Number Title Priority Date Filing Date
EP10795931.4A Active EP2524189B1 (fr) 2010-01-15 2010-12-07 Procédé pour corriger la trajectoire d'un projectile guidé en particulier en phase finale et projectile pour la mise en oeuvre du procédé

Country Status (11)

Country Link
US (1) US8558151B2 (fr)
EP (1) EP2524189B1 (fr)
JP (1) JP2013517443A (fr)
KR (1) KR20120115280A (fr)
CN (1) CN102656417A (fr)
BR (1) BR112012017296A2 (fr)
CA (1) CA2785693C (fr)
DE (1) DE102010004820A1 (fr)
RU (1) RU2509975C1 (fr)
SG (1) SG182381A1 (fr)
WO (1) WO2011085758A1 (fr)

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CN103604316B (zh) * 2013-11-22 2015-06-10 北京机械设备研究所 一种用于多弹发射的弹道校正方法
US9279651B1 (en) 2014-09-09 2016-03-08 Marshall Phillip Goldberg Laser-guided projectile system
CN105043171B (zh) * 2015-06-30 2017-08-29 北京航天长征飞行器研究所 一种带倾角约束的火箭弹纵向导引方法
RU2616963C1 (ru) * 2015-10-13 2017-04-18 Юрий Дмитриевич Рысков Лазерный патрон
RU2612054C1 (ru) * 2015-11-20 2017-03-02 Открытое акционерное общество "Конструкторское бюро приборостроения им. академика А.Г. Шипунова" Способ наведения управляемого снаряда, телеориентируемого в луче лазера (варианты)
US11555679B1 (en) 2017-07-07 2023-01-17 Northrop Grumman Systems Corporation Active spin control
US10345087B2 (en) * 2017-08-01 2019-07-09 BAE Systems Informaticn and Electronic Systems Integration Inc. Mid body seeker payload
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RU189193U1 (ru) * 2018-04-05 2019-05-15 Федеральное Государственное Бюджетное Образовательное Учреждение Высшего Образования "Новосибирский Государственный Технический Университет" Патрон для стрелкового оружия
RU189190U1 (ru) * 2018-04-05 2019-05-15 Федеральное Государственное Бюджетное Образовательное Учреждение Высшего Образования "Новосибирский Государственный Технический Университет" Патрон для стрелкового оружия
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Also Published As

Publication number Publication date
KR20120115280A (ko) 2012-10-17
CA2785693A1 (fr) 2011-07-21
CN102656417A (zh) 2012-09-05
EP2524189B1 (fr) 2016-03-02
SG182381A1 (en) 2012-08-30
CA2785693C (fr) 2015-02-10
JP2013517443A (ja) 2013-05-16
US20120292432A1 (en) 2012-11-22
RU2012134788A (ru) 2014-02-20
US8558151B2 (en) 2013-10-15
BR112012017296A2 (pt) 2016-04-19
WO2011085758A1 (fr) 2011-07-21
RU2509975C1 (ru) 2014-03-20
DE102010004820A1 (de) 2011-07-21

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