EP0446413A1 - Projectile doté d'un autodirecteur infrarouge installé dans la proue - Google Patents

Projectile doté d'un autodirecteur infrarouge installé dans la proue Download PDF

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Publication number
EP0446413A1
EP0446413A1 EP90119791A EP90119791A EP0446413A1 EP 0446413 A1 EP0446413 A1 EP 0446413A1 EP 90119791 A EP90119791 A EP 90119791A EP 90119791 A EP90119791 A EP 90119791A EP 0446413 A1 EP0446413 A1 EP 0446413A1
Authority
EP
European Patent Office
Prior art keywords
projectile
scanning
target
laser
deflection device
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.)
Withdrawn
Application number
EP90119791A
Other languages
German (de)
English (en)
Inventor
Helmut Dr. Neff
Jürgen Heinrich
Gerhard Dr. Glotz
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.)
Tzn Forschungs- und Entwicklungszentrum Unterluess GmbH
Original Assignee
Tzn Forschungs- und Entwicklungszentrum Unterluess GmbH
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 Tzn Forschungs- und Entwicklungszentrum Unterluess GmbH filed Critical Tzn Forschungs- und Entwicklungszentrum Unterluess GmbH
Publication of EP0446413A1 publication Critical patent/EP0446413A1/fr
Withdrawn legal-status Critical Current

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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
    • F41G7/2246—Active homing systems, i.e. comprising both a transmitter and a receiver
    • 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
    • F41G7/222—Homing guidance systems for spin-stabilized missiles
    • 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
    • F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves

Definitions

  • the invention relates to a projectile as specified in more detail by the features of the preamble of claim 1.
  • the successful combat of tactical and ballistic missiles with barrel weapons requires the use of sensor-supported ammunition with a comparatively high target range and accuracy.
  • the sensors for target determination can be based on active and passive systems. Active systems offer the possibility of autonomously determining the target distance, thus allowing modified proportional navigation with the result of improved hit accuracy.
  • Most of the systems for guided missiles that have been implemented so far require gyro-stabilized systems with high mechanical complexity. These systems can often not be exposed to the stresses that occur during launch.
  • a target search device for missiles which contains a passive sensor.
  • This essentially consists of a gyroscopic rotor which is mounted in a housing, a detector being arranged fixed to the housing in the central swivel arm.
  • There is an optical on the gyro rotor System that maps an infinite viewfinder field of view as a field of view image in the plane of the detector.
  • a torque generator which acts on the gyro rotor and receives corresponding scanning signals from a scanning signal generator, is provided as means for generating the relative movement between the visual field image and the detector. With a suitable choice of the scanning signals, it is possible to achieve a rosette-shaped scanning of the target area.
  • U.S. Patent No. 3,035,818 discloses a missile that includes both an optical homing device and an optical proximity detonator.
  • the receiving device of the passive targeting device serves at the same time as the receiver of the active proximity detonator.
  • An active method for the target search device is not disclosed in this document.
  • the invention has for its object to develop a projectile with an IR target search system of the type mentioned in such a way that mechanical components are dispensed with on the one hand and rosette-shaped scanning of the target area is possible on the other hand.
  • the invention is therefore based on an active laser-assisted sensor system for target recognition and steering.
  • the target area is scanned by means of an acousto-optical sensor system mounted in the search head of the rotating projectile.
  • the storey position relative to the target or the line of sight angle can then be determined from the scanning parameters of the acousto-optical device by receiving and evaluating the laser light scattered back from the target.
  • At least two control nozzles are used for projectile guidance, which are attached in a fixed predetermined plane relative to the scanning plane of the laser.
  • 10 designates a spin-stabilized projectile which rotates about its longitudinal axis 10 '.
  • the floor 10 has a dome 11 which is transparent to the IR rays.
  • the laser beam emanating from the laser transmission and scanning module 12 is designated 18 and the corresponding scan plane 19 .
  • the structure of the laser transmitter and scan module 12 is shown in FIG. 2. It essentially consists of a laser (e.g. DC solid-state laser) 120, a lens arrangement 121 connected downstream of the laser and indicated only schematically for beam conditioning, and a preferably electro-optical modulator 122 for amplitude modulation of the laser beam. Amplitude modulation is necessary because the signal bandwidth can be increased due to the reduced signal bandwidth. Furthermore, amplitude modulation of the laser beam is necessary to determine the distance between the projectile and the target (see below).
  • the laser beam is deflected with the aid of an acousto-optical deflection device 123.
  • the solid-state laser 120 is supplied with power with the aid of a power supply source 124, which is controlled by a control device 125.
  • control devices 127 and 128 of the electro-optical modulator 122 or the are also connected via a synchronization device 126 acousto-optical deflector 123 connected.
  • the control devices 127 and 128 are also connected via lines 129 and 129 'to the evaluation electronics 14 described below.
  • the receiving module 13 consists essentially of a fast photodiode 130. This is preceded by a schematically illustrated focusing optics 131, with which the incident laser light 132 reflected from the target is focused on the photodiode.
  • the output signals of the photodiode 130 are amplified in a signal preprocessing device and, if necessary, filtered and then fed to the evaluation electronics 14 via a line 134.
  • the evaluation electronics 14 essentially consist of a microcomputer (/ u C) 140.
  • the devices / devices 141, 142, 143 and 144 for measuring the distance, the line-of-sight angle, the floor swing and the roll rate are connected upstream of the / u C.
  • the path correction of the projectile is calculated from the determined distance of the target, the line-of-sight angle and the line-of-sight rotation speed derived therefrom, as well as the roll rate and, if applicable, the projectile swing (pitch and yaw movement).
  • the corresponding correction signals are then fed to the thrusters 16 and 17 so that the projectile can change its trajectory accordingly.
  • the distance data can also be used to trigger the ignition.
  • the distance measurement is preferably carried out using the method described in the publication by RS Rogowsky et al "Proceedings of the International Society for Optical Engineering", vol. 663, page 86. This is done using a method used, which is used in an anologic way to determine the distance with FMCW-RADAR (frequency modulated continous wave).
  • FMCW-RADAR frequency modulated continous wave
  • the emitted laser radiation is modulated so that the amplitude increases linearly in the modulation frequency within a predetermined period.
  • the output signal and the laser light reflected from the target are superimposed using a mixer. The difference in transit time between the two signals produces a low-frequency beat frequency at the mixer output, which is proportional to the distance.
  • the line of sight angle is the angle between the line of sight and the longitudinal axis of the projectile.
  • the line-of-sight angle is derived from the electrical operating parameters of the acousto-optical deflection unit in such a way that the operating voltage required for deflecting the laser beam is proportional (linear or square) to the deflection angle.
  • the line-of-sight rotation speed follows from the change in the line-of-sight angle over time and is obtained by differentiation, for example by evaluating two successive projectile rotations.
  • an acceleration pickup 15 can be used, for example, with which the rotational rate ⁇ of the projectile can be determined from the radial acceleration is determined, where b r means the radial acceleration and r the distance of the acceleration sensor 15 from the axis of rotation of the projectile (cf. also FIG. 5).
  • the corresponding correction signals are fed to the thrusters 16 and 17 shown schematically in FIG. 5.
  • 5 also shows the position of the scanning plane 19 relative to the thrusters and the position of the roll rate sensor 15.
  • the thrusters 16 and 17 are preferably attached in a line running through the center of gravity of the projectile.
  • Known hot gas or pulse engines are preferably used.
  • Scanning plane 19 and thrusters 16 and 17 are rotated by the angle ⁇ . This results in a lead time ⁇ in which the path correction can be carried out from the input parameters.
  • the time T for triggering the thrust nozzles is determined at a fixed angle ⁇ from - as described in more detail above - the rotation rate ⁇ of the projectile obtained by means of the roll rate sensor 15.
  • the roll rate sensor 15 is attached at a distance r from the axis of rotation of the projectile.
  • the scanning process can be seen in FIGS. 6 and 7.
  • the rotating projectile is designated by 10, the laser beam by 18 and a target by 20.
  • the rotation of the projectile at the angular velocity ⁇ in the range from 50 to 200 Hz results in a rosette-shaped scanning figure in the target area with periodic linear deflection of the laser beam (cf. (Fig. 2) and the distance - as described in more detail above - can be determined.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
EP90119791A 1990-03-10 1990-10-16 Projectile doté d'un autodirecteur infrarouge installé dans la proue Withdrawn EP0446413A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4007712A DE4007712A1 (de) 1990-03-10 1990-03-10 Geschoss mit einem bugseitig angeordneten ir-suchsystem
DE4007712 1990-03-10

Publications (1)

Publication Number Publication Date
EP0446413A1 true EP0446413A1 (fr) 1991-09-18

Family

ID=6401936

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90119791A Withdrawn EP0446413A1 (fr) 1990-03-10 1990-10-16 Projectile doté d'un autodirecteur infrarouge installé dans la proue

Country Status (4)

Country Link
US (1) US5088659A (fr)
EP (1) EP0446413A1 (fr)
DE (1) DE4007712A1 (fr)
IL (1) IL97230A0 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6322709B1 (en) 1992-07-13 2001-11-27 Pall Corporation Automated method for processing biological fluid

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DE4309295A1 (de) * 1992-06-29 1995-10-05 Daimler Benz Aerospace Ag Verfahren zur eigenständigen Steuerung eines lenkbaren und mit einem Gefechtskopf versehenen Flugkörpers und Anordnung zur Durchführung des Verfahrens
US5275354A (en) * 1992-07-13 1994-01-04 Loral Vought Systems Corporation Guidance and targeting system
US5424823A (en) * 1993-08-17 1995-06-13 Loral Vought Systems Corporation System for identifying flat orthogonal objects using reflected energy signals
US5669581A (en) * 1994-04-11 1997-09-23 Aerojet-General Corporation Spin-stabilized guided projectile
DE19706958C2 (de) * 1997-02-21 2001-11-08 Lfk Gmbh Schwenkbarer Sucher
RU2131576C1 (ru) * 1998-03-25 1999-06-10 Конструкторское бюро приборостроения Способ формирования команды управления снарядом, регулярно вращающимся по углу крена с помощью аэродинамических сил и устройство для его осуществления
DE60023007T2 (de) * 1999-07-21 2006-07-13 General Dynamics Ordnance and Tactical Systems, Inc., St. Petersburg Geschosslenkung mittels einer ringanordnung und optisch ausgelösten ablenkvorrichtungen
US6817569B1 (en) 1999-07-21 2004-11-16 General Dynamics Ordnance And Tactical Systems, Inc. Guidance seeker system with optically triggered diverter elements
FR2797042B1 (fr) * 1999-07-30 2002-09-06 Aerospatiale Matra Missiles Procede et dispositif de guidage a balayage laser d'un missile vers une cible
KR100374323B1 (ko) * 2000-08-10 2003-03-03 최종수 로젯 주사 영상을 위한 클러스터링 방법
DE10153094A1 (de) * 2001-10-30 2003-05-15 Bodenseewerk Geraetetech Optischer Sensor mit einem Sensorstrahlengang und einem parallel zu der optischen Achse des Sensorstrahlenganges emittierenden Laserstrahler
UA63801A (en) * 2003-07-01 2004-01-15 Serhii Oleksandrovych Shumov Portable anti-aircraft rocket complex
WO2007089243A2 (fr) * 2005-02-07 2007-08-09 Bae Systems Information And Electronic Systems Integration Inc. Procédé et système de commande de munition à guidage optique
US7947937B1 (en) * 2007-10-19 2011-05-24 Langner F Richard Laser guided projectile device and method therefor
US8497457B2 (en) * 2010-12-07 2013-07-30 Raytheon Company Flight vehicles with improved pointing devices for optical systems
FR2974625B1 (fr) * 2011-04-28 2013-05-17 Mbda France Procede de gestion automatique d'un autodirecteur monte sur un engin volant, en particulier sur un missile
DE102013003660A1 (de) * 2013-03-02 2014-09-04 Mbda Deutschland Gmbh Optische Vorrichtung
US9568280B1 (en) * 2013-11-25 2017-02-14 Lockheed Martin Corporation Solid nose cone and related components
US9222755B2 (en) * 2014-02-03 2015-12-29 The Aerospace Corporation Intercepting vehicle and method
US9534868B1 (en) 2014-06-03 2017-01-03 Lockheed Martin Corporation Aerodynamic conformal nose cone and scanning mechanism
AU2016432331B2 (en) * 2016-12-15 2023-12-14 Bae Systems Information And Electronic Systems Integration Inc. Guided munition systems for detecting off-axis targets
GB2589006B (en) * 2019-10-09 2022-06-15 Mbda Uk Ltd Acousto-optic device and method

Citations (8)

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US3863262A (en) * 1973-03-21 1975-01-28 Datalight Inc Laser phototypesetter
US3935818A (en) * 1974-08-26 1976-02-03 The United States Of America As Represented By The Secretary Of The Army Combined fuze and guidance system for a missile
US3954228A (en) * 1965-11-16 1976-05-04 The United States Of America As Represented By The Secretary Of The Army Missile guidance system using an injection laser active missile seeker
US4024392A (en) * 1976-03-08 1977-05-17 The United States Of America As Represented By The Secretary Of The Navy Gimballed active optical system
US4180822A (en) * 1978-04-13 1979-12-25 Rca Corporation Optical scanner and recorder
US4347996A (en) * 1980-05-22 1982-09-07 Raytheon Company Spin-stabilized projectile and guidance system therefor
EP0120775A1 (fr) * 1983-03-29 1984-10-03 Thomson-Csf Système de télémétrie laser et de mesure Doppler, à compression d'impulsions
DE3519786A1 (de) * 1985-06-03 1986-12-04 Bodenseewerk Gerätetechnik GmbH, 7770 Überlingen Optischer sucher mit rosettenabtastung

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DE2923547C2 (de) * 1979-06-09 1981-04-09 Bodenseewerk Gerätetechnik GmbH, 7770 Überlingen Zielsuchvorrichtung für Flugkörper
US4516853A (en) * 1982-03-31 1985-05-14 United Technologies Corporation Laser radar adaptive tracking system
US4533094A (en) * 1982-10-18 1985-08-06 Raytheon Company Mortar system with improved round
US4504110A (en) * 1983-05-19 1985-03-12 Rockwell International Corporation Converging beam linear optical scanner
US4560120A (en) * 1983-08-19 1985-12-24 The United States Of America As Represented By The Secretary Of The Army Spin stabilized impulsively controlled missile (SSICM)
ES2019870B3 (es) * 1986-01-30 1991-07-16 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Dispositivo para guiar una particula volatil.

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3954228A (en) * 1965-11-16 1976-05-04 The United States Of America As Represented By The Secretary Of The Army Missile guidance system using an injection laser active missile seeker
US3863262A (en) * 1973-03-21 1975-01-28 Datalight Inc Laser phototypesetter
US3935818A (en) * 1974-08-26 1976-02-03 The United States Of America As Represented By The Secretary Of The Army Combined fuze and guidance system for a missile
US4024392A (en) * 1976-03-08 1977-05-17 The United States Of America As Represented By The Secretary Of The Navy Gimballed active optical system
US4180822A (en) * 1978-04-13 1979-12-25 Rca Corporation Optical scanner and recorder
US4347996A (en) * 1980-05-22 1982-09-07 Raytheon Company Spin-stabilized projectile and guidance system therefor
EP0120775A1 (fr) * 1983-03-29 1984-10-03 Thomson-Csf Système de télémétrie laser et de mesure Doppler, à compression d'impulsions
DE3519786A1 (de) * 1985-06-03 1986-12-04 Bodenseewerk Gerätetechnik GmbH, 7770 Überlingen Optischer sucher mit rosettenabtastung

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6322709B1 (en) 1992-07-13 2001-11-27 Pall Corporation Automated method for processing biological fluid

Also Published As

Publication number Publication date
US5088659A (en) 1992-02-18
IL97230A0 (en) 1992-05-25
DE4007712A1 (de) 1991-09-12

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