EP1493986A1 - Tragbares Boden-zu-Luft-Flugkörpersystem - Google Patents

Tragbares Boden-zu-Luft-Flugkörpersystem Download PDF

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Publication number
EP1493986A1
EP1493986A1 EP04253948A EP04253948A EP1493986A1 EP 1493986 A1 EP1493986 A1 EP 1493986A1 EP 04253948 A EP04253948 A EP 04253948A EP 04253948 A EP04253948 A EP 04253948A EP 1493986 A1 EP1493986 A1 EP 1493986A1
Authority
EP
European Patent Office
Prior art keywords
output
electrically connected
input
logic unit
switch
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Withdrawn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
EP04253948A
Other languages
English (en)
French (fr)
Inventor
Sergeyi Alexandrovich Shumov
Viktor Ivanovich Buzanov
Anatolyy Vladimirovich Molodyk
Ivan Ivanovich Zabolotnyy
Lev Vasylyevich Kuzmin
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.)
Immersion Hi TECH Ltd
Shumov Serhiy Oleksandrovych
Original Assignee
Immersion Hi TECH Ltd
Shumov Serhiy Oleksandrovych
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 Immersion Hi TECH Ltd, Shumov Serhiy Oleksandrovych filed Critical Immersion Hi TECH Ltd
Publication of EP1493986A1 publication Critical patent/EP1493986A1/de
Withdrawn legal-status Critical Current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
    • F41G7/224—Deceiving or protecting means

Definitions

  • This invention relates to the missile technology and, more especially, this invention relates to portable surface-to-air missile systems.
  • the closest device to the present invention is an Igla-1 - 9K310 portable surface-to-air missile system.
  • This system includes a missile with a frequency modulated autonomous guidance infrared head with a selector and a launcher connected to it, which includes a transport and launch container, a launcher, and a power supply unit (Igla-1 portable surface-to-air missile system (9K310) - see Technical Description and Operations Manual for 9K310 TO, Moscow, Voyennoye Izdatelstvo Publishing House, 1983).
  • thermal deception targets In order to fight surface-to-air missiles using infrared guidance systems, up-to-the-date combat aircraft utilize thermal deception targets as infrared deception flares.
  • the thermal deception targets are ejected by the carrier aircraft.
  • the energy parameters of an infrared deception flare are in excess of the energy parameters of its carrier aircraft.
  • the infrared guidance system of the missile that was tracking the radiation from the combat aircraft, switches over to track the more powerful radiation source, i.e. the infrared deception flare.
  • the infrared deception flare moves in space with retard to the combat aircraft.
  • the target that has been aimed at and the infrared deception flare do not fit into the sight of the missile guidance system. Since the missile guidance system is tracking a more powerful infrared deception flare, the target that has been aimed at goes out of the missile guidance system, with the result that the target is missed.
  • the present invention is aimed at minimising the vulnerability of portable surface-to-air missiles to flares. This is effected by equipping the infrared autonomous guidance head of the portable surface-to-air missile with a system distinguishing the target from an infrared deception flare.
  • a portable surface-to-air missile system which comprises a missile with a frequency-modulated infrared autonomous guidance head and a selector, which is electrically and pneumatically connected to a launcher, which includes a transport and launch container, a launch mechanism and a power supply unit, characterised by implementation of the selector of the infrared autonomous guidance head with the opportunity to use kinematic differences between a real target and a deceptive flare, while the launcher has an indicator changing the operating program of the selector, with the selector made of interconnected analyser, logic unit, and function circuit, an input of the analyser electrically connected to an output of a light signal amplifier, with an output of the analyser electrically connected to a first input of the logic unit, with a second input of the logic unit electrically connected to the launcher, and with a first output of the logic unit electrically connected to a first input of the function circuit, with a second input of the function circuit electrically connected to an output of
  • the analyser may be implemented as an electrically interconnected amplifier, two comparators and timer, with an input of the amplifier electrically connected to the output of the light signal amplifier, with the output of the amplifier electrically connected to inputs of the comparators, and with outputs of the comparators electrically connected to the first input of the logic unit.
  • the logic unit may be a switch.
  • the function circuit is implemented as electrically interconnected first and second switches, first and second function formers, a generator, and an analog random-access memory, with a first input of the analog random-access memory electrically connected to the output of the correction amplifier, with a second input of the analog random-access memory electrically connected to an output of the generator, with an output of the analog random-access memory electrically connected to the input of the first function former, with the output of the first function former electrically connected to the first input of the first switch, with the second input of the first switch electrically connected to the first output of the logic unit, with the output of the first switch electrically connected to one of the inputs of the correction amplifier, with the input of the second function former electrically connected to the output of the cage winding, with the output of the second function former electrically connected to the first input of the second switch, with the second input of the second switch electrically connected to the first output of the logic unit, and with the output of the second switch electrically connected to one of the inputs of the correction amplifier.
  • the use of a programmed selector in the missile guidance system enables utilisation of kinematic differences between the real target and deceptive flares, while the launcher has an indicator changing selector operation.
  • missile 1 an IRAGH 2
  • optics and mechanics unit 3 an electronic compartment 4
  • programmed selectors 5 a launcher 6, a transport and launch container 7, a launch mechanism 8, and a ground power supply 9.
  • FIG. 3 there is shown an amplifier 13, a first comparator 14, a second comparator 15, and a timer 16.
  • FIG 4 there is shown an analog random-access memory 17, a generator 18, a first function former 19, a first switch 20, a second function former 21, and a second switch 22.
  • the portable surface-to-air missile system operates as follows.
  • the first input of missile 1 is electrically connected to the first output of the IRAGH 2.
  • the output of missile 1 is kinematically connected to the body of IRAGH 2.
  • the output of the optics and mechanics unit 3 is electrically connected to the input of the electronic compartment 4, with the programmed selector 5 comprising a constituent part of it.
  • the output of the electronic compartment 4 is electrically connected to the input of the optics and mechanics unit 3.
  • the launcher 6 comprises of the transport and launch container 7, the launch mechanism 8 and the ground power supply 9.
  • the first output of the transport and launch container 7 is electrically connected to the second input of missile 1.
  • the second output of the transport and launch container is electrically and pneumatically connected to the input of the IRAGH 2.
  • the second output of the IRAGH 2 is electrically connected to the first input of the transport and launch container 7.
  • the third output of the transport and launch container 7 is electrically connected to the input of the LM 8.
  • the output of the LM 8 is electrically connected to the second input of the transport and launch container 7.
  • the fourth output of the transport and launch container 7 is kinematically connected to the input of the ground power supply 9.
  • the output of the ground power supply 9 is electrically and pneumatically connected to the third input of the transport and launch container 7.
  • the electric signal is supplied from the light signal amplifier to the input of the analyser which contains data on sources of input light signals, on the target and infrared deception flares.
  • the output of the analyser is electrically connected to the first input of the logic unit (switch) 11.
  • the electric signal from the transport and launch container 7 goes into the second input of the logic unit 11.
  • the electric signal from the first output of the logic unit 11 goes to the first input of the function circuit 12.
  • the electric signal from the output of the cage winding (which is part of the optics and mechanics unit) goes into the second input of the function circuit 12.
  • An electric signal from the output of the function circuit 12 goes to one of the inputs of the correction amplifier (which is part of the electronic compartment 4).
  • the electric signal from the output of the light signal amplifier goes to the input of the amplifier 13.
  • the electric signal from the first output of the amplifier 13 goes to the input of the first comparator 14.
  • the electronic signal from the second output of the amplifier 13 goes to the input of the second comparator 15.
  • the outputs of the comparators 14 and 15 are electrically connected to the first and second inputs of the timer 16, respectively.
  • the output of the timer 16 is electrically connected to the first input of the logic unit 11.
  • the electric signal from the output of the correction amplifier goes into the first input of the analog random-access memory 17.
  • the electric signal from the generator 18 goes to the second input of the analog random-access memory 17.
  • the electric signal from the output of the analog random-access memory 17 goes into the input of the first function former 19.
  • the electric signal from the first function former 19 goes into the first input of the first switch 20.
  • the electric signal from the output of the logic unit 11 goes into the second input of the first switch 20.
  • the electric signal from the output of the first switch 20 goes into the input of the correction amplifier (which is part of the electronic compartment 4).
  • the electric signal from the output of the cage winding goes into the input of the second function former 21.
  • the electric signal from the output of the function former 21 goes into the first input of the second switch 22.
  • the electric signal from the output of the logic unit 11 goes into the second input of the switch 22.
  • the electrical signal from the output of the switch 22 goes into the input of the correction amplifier (which is part of the electronic compartment 4).
  • the trajectory and kinematic difference between the target being attacked and the infrared deception flare is based on the difference between the masses of the infrared deception flare and high-speed targets. Because of a substantial speed of the target and a swift spatial deceleration of the infrared deception flare, regardless of the direction of its dropping, at the end of the day, the infrared deception flare will always be behind the target in space and the IRAGH coordinate system.
  • the optical system of the missile IRAGH receives an infrared signal about the targets in its sight and delivers an electric signal about the targets to the electronic compartment of the IRAGH.
  • the electronic compartment forms and delivers electric commands both to the executing mechanism of the IRAGH control system (correction winding), which corrects the position of the IRAGH optical system axis, and to the actuating mechanism for the missile rudders (not shown on the drawings) during the flight.
  • the programmed selector forms commands for the actuating mechanism for the IRAGH control system (correction winding), which corrects the position of the IRAGH optical system axis, with the infrared deception flare going out of the missile guidance sight and the target it has been aimed at remaining in the sight. This is the way of ensuring that the target the missile has been aimed at is hit.
  • the principle of operation of the infrared deception flare trajectory and kinematics selector is in selecting from among the sources located in the sight those which have moved in space along the vector of angular velocity ⁇ or along the bearing ⁇ (in proportion to the signal in the cage winding), which has been set during IRAGH operation following the "launch" command.
  • the signal Upon arriving of an electric signal from the light signal amplifier to the analyser, the signal is amplified and compared in the first comparator with the value set beforehand. If the given value has been exceeded, the first comparator 14 will send an electric signal about the appearance of an infrared deception flare to the logic unit 11 through the timer 16.
  • the output signal from the logic unit 11 opens the first switch 20 and closes the second switch 22.
  • the ARAM 17 Upon receipt of a correction signal and a signal from the generator 18 by the inputs of the ARAM 17, the ARAM 17 memorises with the given frequency of updating the correction signal, and delivers it to the first function former 19 and further through the open switch 20 to the correction amplifier, to which an electric signal which is a function of the angular velocity w comes. This signal corrects the gyroscope axis position.
  • the logic unit with a pre-selected delay time gives the command to close the first switch 20 and open the second switch 22.
  • a signal from the second function former 21 which depends upon the bearing ⁇ , will come to the input of the correction amplifier (in the electronic compartment 4).
  • the second comparator 15 will work and switch off the timer 16 (or the timer will be off following the operation time set).
  • the logic unit 11 will block the signal from the outputs of the switches 20 and 22.

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)
  • Amplifiers (AREA)
  • Alarm Systems (AREA)
  • Telescopes (AREA)
  • Optical Radar Systems And Details Thereof (AREA)
EP04253948A 2003-07-01 2004-06-30 Tragbares Boden-zu-Luft-Flugkörpersystem Withdrawn EP1493986A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
UA2003076129A UA63801A (en) 2003-07-01 2003-07-01 Portable anti-aircraft rocket complex
UA03076129 2003-07-01

Publications (1)

Publication Number Publication Date
EP1493986A1 true EP1493986A1 (de) 2005-01-05

Family

ID=34061373

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04253948A Withdrawn EP1493986A1 (de) 2003-07-01 2004-06-30 Tragbares Boden-zu-Luft-Flugkörpersystem

Country Status (6)

Country Link
US (1) US20050178875A1 (de)
EP (1) EP1493986A1 (de)
CA (1) CA2472440A1 (de)
IL (1) IL162800A0 (de)
RU (1) RU2004119375A (de)
UA (1) UA63801A (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103175445B (zh) * 2011-12-22 2015-10-28 洛阳理工学院 基于mems陀螺的位标器系统及其跟踪方法
CN106709253B (zh) * 2016-12-28 2019-05-10 中国航空工业集团公司西安飞机设计研究所 一种机载设备重要度确定方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998016794A2 (fr) * 1996-10-11 1998-04-23 Konstruktorskoe Bjuro Mashinostroenya Missile guide de defense aerienne utilisable par une personne
DE19805850C1 (de) * 1998-02-13 1999-01-28 Lfk Gmbh Lenkflugkörper
US6142412A (en) * 1999-02-22 2000-11-07 De Sa; Erwin M. Highly accurate long range optically-aided inertially guided type missile
US6565036B1 (en) * 2001-04-12 2003-05-20 The United States Of America As Represented By The Secretary Of The Army Technique for improving accuracy of high speed projectiles

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2986637A (en) * 1946-08-29 1961-05-30 Fay E Null High speed far infra-red detector and heat seeking control for guided missiles
US2997594A (en) * 1958-03-19 1961-08-22 Stephen M Macneille Target-seeking head for guided missile
US3219826A (en) * 1963-10-07 1965-11-23 Raytheon Co Target tracking guidance system with false signal detecting means
US3820742A (en) * 1965-02-08 1974-06-28 R Watkins Missile guidance and control system
FR2109488A5 (de) * 1970-10-22 1972-05-26 Telecommunications Sa
US3944167A (en) * 1973-08-24 1976-03-16 Sanders Associates, Inc. Radiation detection apparatus
USRE33287E (en) * 1980-02-04 1990-08-07 Texas Instruments Incorporated Carrier tracking system
US4666103A (en) * 1980-02-04 1987-05-19 Allen John B Carrier tracking system
US5102065A (en) * 1988-02-17 1992-04-07 Thomson - Csf System to correct the trajectory of a projectile
US5127604A (en) * 1989-08-18 1992-07-07 Raytheon Company Optical system
US5072890A (en) * 1989-08-18 1991-12-17 Raytheon Company Optical system
DE4007712A1 (de) * 1990-03-10 1991-09-12 Tzn Forschung & Entwicklung Geschoss mit einem bugseitig angeordneten ir-suchsystem

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998016794A2 (fr) * 1996-10-11 1998-04-23 Konstruktorskoe Bjuro Mashinostroenya Missile guide de defense aerienne utilisable par une personne
DE19805850C1 (de) * 1998-02-13 1999-01-28 Lfk Gmbh Lenkflugkörper
US6142412A (en) * 1999-02-22 2000-11-07 De Sa; Erwin M. Highly accurate long range optically-aided inertially guided type missile
US6565036B1 (en) * 2001-04-12 2003-05-20 The United States Of America As Represented By The Secretary Of The Army Technique for improving accuracy of high speed projectiles

Also Published As

Publication number Publication date
RU2004119375A (ru) 2006-01-10
UA63801A (en) 2004-01-15
CA2472440A1 (en) 2005-01-01
US20050178875A1 (en) 2005-08-18
IL162800A0 (en) 2005-11-20

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