DE4112016C1 - Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre - Google Patents

Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre

Info

Publication number
DE4112016C1
DE4112016C1 DE4112016A DE4112016A DE4112016C1 DE 4112016 C1 DE4112016 C1 DE 4112016C1 DE 4112016 A DE4112016 A DE 4112016A DE 4112016 A DE4112016 A DE 4112016A DE 4112016 C1 DE4112016 C1 DE 4112016C1
Authority
DE
Germany
Prior art keywords
missile
optical fibre
speed
flight path
unwinding
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 - Fee Related
Application number
DE4112016A
Other languages
German (de)
Inventor
Wolfgang Von 8012 Riemerling De Hoessle
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.)
LFK Lenkflugkoerpersysteme GmbH
Original Assignee
Messerschmitt Bolkow Blohm 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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Priority to DE4112016A priority Critical patent/DE4112016C1/en
Priority to FR9204154A priority patent/FR2675250B1/en
Priority to ITMI920879A priority patent/IT1258311B/en
Application granted granted Critical
Publication of DE4112016C1 publication Critical patent/DE4112016C1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/055—Umbilical connecting means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65H—HANDLING THIN OR FILAMENTARY MATERIAL, e.g. SHEETS, WEBS, CABLES
    • B65H61/00—Applications of devices for metering predetermined lengths of running material
    • B65H61/005—Applications of devices for metering predetermined lengths of running material for measuring speed of running yarns
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/01—Arrangements thereon for guidance or control
    • F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
    • G01P3/42—Devices characterised by the use of electric or magnetic means
    • G01P3/50—Devices characterised by the use of electric or magnetic means for measuring linear speed
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
    • G01P3/42—Devices characterised by the use of electric or magnetic means
    • G01P3/50—Devices characterised by the use of electric or magnetic means for measuring linear speed
    • G01P3/54—Devices characterised by the use of electric or magnetic means for measuring linear speed by measuring frequency of generated current or voltage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65H—HANDLING THIN OR FILAMENTARY MATERIAL, e.g. SHEETS, WEBS, CABLES
    • B65H2513/00—Dynamic entities; Timing aspects
    • B65H2513/10—Speed
    • B65H2513/11—Speed angular
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B65—CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65H—HANDLING THIN OR FILAMENTARY MATERIAL, e.g. SHEETS, WEBS, CABLES
    • B65H2557/00—Means for control not provided for in groups B65H2551/00 - B65H2555/00
    • B65H2557/30—Control systems architecture or components, e.g. electronic or pneumatic modules; Details thereof
    • B65H2557/33—Control systems architecture or components, e.g. electronic or pneumatic modules; Details thereof for digital control, e.g. for generating, counting or comparing pulses

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

An arrangement for determining the flight distance and/or the true flight speed of missiles steered via optical fibres contains a coil of optical fibre in the missile which is unwound from it as it flies. The optical fibre is passed through an annular gap (7) at the rear end of the missile (1) between two parts (4, 2, 6) fixed to the missile and unwinds with a helical motion circulating in the gap. A sensor (8, 9) in the gap contactlessly detects the rotary fibre motion. It feeds evaluation electronics (11) which determine the number of and/or time intervals between rotations. USE/ADVANTAGE - Simple yet precise measurement of flight distance and/or speed of optical fibre guided missiles without additionally mechanically loading optical fibre.

Description

Die Erfindung betrifft eine Vorrichtung zur Bestimmung des Flugweges und/oder der realen Fluggeschwindigkeit eines über eine optische Faser­ leitung gelenkten Flugkörpers, in welchem ein Spulenkörper fest angeord­ net und am Ende des Flugkörpers koaxial zur Flugkörperlängsachse mit einem Ende der Spulenachse befestigt ist, wobei die optische Faser­ leitung von dem Spulenkörper während des Fluges abgewickelt wird.The invention relates to a device for determining the flight path and / or the real flight speed of an optical fiber line-guided missile, in which a coil body is arranged net and at the end of the missile coaxial with the longitudinal axis of the missile one end of the coil axis is attached, the optical fiber line is unwound from the coil form during the flight.

Bei Flugkörpern, die über eine optische Faserleitung gelenkt werden (z. B. DE 31 32 547 C1) und die einen Suchkopf mit einer bilderzeugenden Kamera aufweisen, ist es vorteilhaft, wenn eine Möglichkeit zur Bestimmung der realen Fluggeschwindigkeit existiert. Die in Flugzeugen hierfür üblicherweise verwendeten Pitotrohre sind für Flugkörper wenig geeignet, da solche Pitotrohre in einer Position mit möglichst unge­ störter Strömung angeordnet sein sollen. Diese Lösung ist für Flugkörper schwer zu realisieren; außderdem ist der apparative Aufwand für eine derartige Fluggeschwindigkeitsmessung relativ hoch.For missiles that are guided via an optical fiber line (e.g. DE 31 32 547 C1) and the one search head with an image-generating Have camera, it is advantageous if a way to Determination of the real airspeed exists. The one on airplanes Pitot tubes commonly used for this are little for missiles Suitable because such pitot tubes are in a position with as little as possible disrupted flow should be arranged. This solution is for missiles difficult to realize; in addition, the equipment required for one such airspeed measurement is relatively high.

Bei Flugkörpern, die im Zieldeckungsverfahren gelenkt werden, ist es vorteilhaft, den zurückgelegten Flugweg zu kennen, um aus der Größe der Winkelabweichung die reale Größe der Abweichung von der Sichtlinie zu erhalten.It is for missiles that are guided in the target detection process advantageous to know the flight path covered in order to get out of size the angular deviation is the real size of the deviation from the line of sight to obtain.

Es ist daher Aufgabe der vorliegenden Erfindung, eine Möglichkeit zur Bestimmung des Flugweges und/oder der realen Fluggeschwindigkeit eines fasergelenkten Flugkörpers zu schaffen, die relativ einfach und dennoch präzise ist und die Faserleitung nicht noch zusätzlich mechanisch belastet.It is therefore an object of the present invention to provide a way Determination of the flight path and / or the real flight speed of a fiber guided missile to create the relatively simple yet is precise and the fiber line is not additionally mechanical charged.

Die Lösung dieser Aufgabe gelingt durch eine nach den Merkmalen des Patentanspruchs ausgebildete Vorrichtung.This problem is solved by a according to the characteristics of Claim trained device.

Aus der DE-AS 11 48 158 ist ein drahtgelenkter Flugkörper bekannt, bei dem einzelne Windungen der Lenkdrahtspule kraft- oder formschlüssig mit Auslösegliedern verbunden sind, die einen oder mehrere Vorgänge am Flug­ körper nach dem Start in Abhängigkeit von einer zurückgelegten Weg­ strecke beim Abziehen je einer vorbestimmten Windung der Lenkradspule auslösen können. Da optische Faserleitungen eine deutlich geringere Festigkeit als vergleichbar dicke metallische Leiter aufweisen und bereits die Abzugskraft beim Abspulen während des Fluges 30% der maxi­ malen Festigkeit des Leiters erreichen kann, sind weitere mechanische Belastungen durch Auslöseglieder und dergleichen nicht mehr tolerierbar, zumal optische Faserleitungen zusätzlich noch eine geringere Knickbe­ lastung als metallische Leiter vertragen. Insofern läßt sich die aus der DE-AS 11 48 158 bekannte Einrichtung auch nicht auf eine Vorrichtung zur Bestimmung des Flugweges und/oder der realen Fluggeschwindigkeit eines über eine optische Faserleitung gelenkten Flugkörpers übertragen.A wire-guided missile is known from DE-AS 11 48 158, at the individual turns of the steering wire coil with a positive or positive fit  Trip members are linked to one or more operations on the flight body after the start depending on a distance traveled stretch when pulling a predetermined turn of the steering wheel coil can trigger. Because optical fiber lines are significantly less Have strength as a comparable thick metallic conductor and the pulling force when unwinding during the flight is 30% of the maxi paint strength of the conductor can be further mechanical Loads caused by trip elements and the like can no longer be tolerated, especially since optical fiber lines also have a lower kink tolerate load as a metallic conductor. In this respect, the DE-AS 11 48 158 known device also not on a device for Determination of the flight path and / or the real flight speed of a transmitted via an optical fiber guided missile.

Die Erfindung wird im folgenden anhand eines teilweise schematisch dar­ gestellten Ausführungsbeispieles näher beschrieben.The invention is illustrated below in part schematically presented embodiment described in more detail.

Bei dem in der Figur dargestellten Ausführungsbeispiel ist am Ende eines Flugkörpers 1, der sich in der mit dem Pfeil 2 bezeichneten Richtung bewegt, eine Spule einer optischen Faserleitung (im folgenden nur mit Leitung bezeichnet) angeordnet, über welche Lenk- und ggf. Bildsignale zwischen dem Flugkörper und einem Lenkstand geführt werden. Die Spule 3 ist dabei mit einem Ende 4.1 der Spulenachse 4 an dem Flugkörper 1 befestigt und koaxial zu dessen Längsachse 1.1 angeordnet. Die Leitung 5, die mit ihrem rückwärtigen Ende mit dem nicht dargestellten Lenkstand fest verbunden ist, wird während des Fluges von der Spule 3 abgewickelt und führt dabei eine schraubenförmige, um den Spulenkörper 3 und die Achse 4 umlaufende Bewegung aus. Die Spule 3 ist von einer zylindrischen Spulenhaube 6 umgeben, die an ihrem vorderen Ende direkt mit dem Flugkörper 1 verbunden ist und an ihrem rückwärtigen Ende mit dem Ende 4.2 der Spulenachse 4 einen ringförmigen Spalt 7 bildet, durch welchen die Leitung 5 während des Fluges abgezogen und dabei innerhalb des Spaltes 7 umläuft. In the exemplary embodiment shown in the figure, at the end of a missile 1 which moves in the direction indicated by the arrow 2 , a coil of an optical fiber line (hereinafter referred to only as a line) is arranged, via which steering and possibly image signals between the missile and a steering position. The coil 3 is attached to the missile 1 at one end 4.1 of the coil axis 4 and is arranged coaxially with its longitudinal axis 1.1 . The line 5 , which is firmly connected at its rear end to the steering position, not shown, is unwound from the coil 3 during flight and thereby performs a helical movement around the coil body 3 and the axis 4 . The coil 3 is surrounded by a cylindrical coil hood 6 , which is connected at its front end directly to the missile 1 and at its rear end with the end 4.2 of the coil axis 4 forms an annular gap 7 through which the line 5 is withdrawn during flight and revolves within the gap 7 .

An einer Stelle des Ringspaltes 7 ist mittels einer Laser- oder Leucht­ diode 8 und einer Empfangsdiode 9 eine Lichtschranke 10 angeordnet, die den Durchgang der Leitung 5 beim Abwickeln je einer Windung registriert und an eine Auswerteelektronik 11 weitergibt. Die Zahl der Lichtschrankenunterbrechungen pro Zeiteinheit wird hier ermittelt und mit einem Korrekturfaktor versehen, der berücksichtigt, daß die Windungen der äußeren Lage der Spule 3 einen größeren Umfang haben als weiter innen liegende Windungen. Bei bekannter Leitungslänge in den einzelnen Windungen kann daraus unmittelbar der Flugweg sowie die aktuelle Flugkörpergeschwindigkeit bestimmt werden.At one point of the annular gap 7 , a light barrier 10 is arranged by means of a laser or light-emitting diode 8 and a receiving diode 9 , which registers the passage of the line 5 during the winding of one turn and forwards it to an electronic evaluation unit 11 . The number of light barrier interruptions per unit of time is determined here and provided with a correction factor which takes into account that the turns of the outer layer of the coil 3 have a larger circumference than turns lying further inside. If the line length in the individual turns is known, the flight path and the current missile speed can be determined directly therefrom.

Claims (1)

Vorrichtung zur Bestimmung des Flugweges und/oder der realen Flugge­ schwindigkeit eines über eine optische Faserleitung gelenkten Flug­ körpers, in welchem ein Spulenkörper fest angeordnet und am Ende des Flugkörpers koaxial zur Flugkörperlängsachse mit einem Ende der Spulenachse befestigt ist, wobei die optische Faserleitung von dem Spulenkörper während des Fluges abgewickelt wird, dadurch gekennzeichnet,
daß am rückwärtigen Ende des Flugkörpers (1) zwischen zwei flugkörper­ festen Teilen (4.2, 6) ein Ringspalt (7) gebildet wird, durch welchen die optische Faserleitung (5) herausgeführt und in schraubenförmigen, im Ringspalt (7) umlaufenden Bewegungen abwickelbar ist,
daß an mindestens einer Stelle des Ringspaltes (7) ein Sensor (8, 9) angeordnet ist, der die Umläufe der sich abwickelnden optischen Faser­ leitung (5) berührungslos erfaßt und,
daß der Sensor (8, 9) mit einer Auswerteelektronik (11) zur Bestimmung der Zahl und/oder der zeitlichen Abstände der Umläufe verbunden ist.Apparatus for determining the flight path and / or the real Flugge speed of a guided over an optical fiber line body, in which a coil body is fixed and fixed at the end of the missile coaxially to the missile longitudinal axis with one end of the coil axis, the optical fiber line from the coil body is handled during the flight, characterized in that
that an annular gap ( 7 ) is formed at the rear end of the missile ( 1 ) between two missile-fixed parts ( 4.2 , 6 ), through which the optical fiber line ( 5 ) is led out and can be developed in helical movements rotating in the annular gap ( 7 ),
that at least one point of the annular gap ( 7 ) a sensor ( 8 , 9 ) is arranged, which detects the revolutions of the unwinding optical fiber line ( 5 ) without contact and,
that the sensor ( 8 , 9 ) is connected to evaluation electronics ( 11 ) for determining the number and / or the time intervals of the revolutions.
DE4112016A 1991-04-12 1991-04-12 Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre Expired - Fee Related DE4112016C1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE4112016A DE4112016C1 (en) 1991-04-12 1991-04-12 Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre
FR9204154A FR2675250B1 (en) 1991-04-12 1992-04-06 METHOD AND DEVICE FOR DETERMINING THE EFFECTIVE FLIGHT SPEED OF MISSILES.
ITMI920879A IT1258311B (en) 1991-04-12 1992-04-10 DETERMINATION OF THE REAL FLIGHT SPEED OF MISSILES

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE4112016A DE4112016C1 (en) 1991-04-12 1991-04-12 Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre

Publications (1)

Publication Number Publication Date
DE4112016C1 true DE4112016C1 (en) 1992-08-06

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Family Applications (1)

Application Number Title Priority Date Filing Date
DE4112016A Expired - Fee Related DE4112016C1 (en) 1991-04-12 1991-04-12 Flight path and/or actual speed detector - uses sensor at circular gap between fixed parts of missile to register speed of unwinding of guiding optical fibre

Country Status (3)

Country Link
DE (1) DE4112016C1 (en)
FR (1) FR2675250B1 (en)
IT (1) IT1258311B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2719111A1 (en) * 1994-04-25 1995-10-27 Aerospatiale Installation of fired ammunition firing from a mobile launcher.
FR2722284A1 (en) * 1994-07-08 1996-01-12 Aerospatiale FIBER LENGTH TRACKING DEVICE ON AN OPTICAL FIBER COIL AND METHOD FOR MANUFACTURING SUCH A DEVICE
WO1997007406A1 (en) * 1995-08-14 1997-02-27 State Of Israel, Ministry Of Defence Armaments Development Authority, Rafael Filamentary structure speed measuring method and device

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2724014A1 (en) * 1994-08-30 1996-03-01 Aerospatiale METHOD AND DEVICE FOR MONITORING THE CONDUCT OF A COIL.
CN103852037B (en) * 2012-11-30 2017-02-22 同济大学 Spring-type auxiliary measuring and control device
FR3104698B1 (en) * 2019-12-11 2022-01-07 Naval Group SYSTEM FOR DETERMINING THE DISTANCE TRAVELED BY AN UNDERWATER VEHICLE FROM AN UNDERWATER VEHICLE
FR3104697B1 (en) * 2019-12-11 2021-12-24 Naval Group SYSTEM FOR DETERMINING THE DISTANCE TRAVELED BY AN UNDERWATER VEHICLE LAUNCHED FROM AN UNDERWATER VEHICLE

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1148158B (en) * 1960-12-20 1963-05-02 Boelkow Entwicklungen Kg Triggering device on a body remotely controlled via wire, in particular a flying body
DE3132547C1 (en) * 1981-08-18 1982-12-09 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Unwinding device for a guidance glass fibre of a missile

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3156185A (en) * 1960-12-20 1964-11-10 Hermann Joachim Triggering device for a movable body
US3246860A (en) * 1961-11-03 1966-04-19 Barnes Eng Co Velocity measuring system
DE3506490A1 (en) * 1985-02-23 1986-09-04 Sobrevin Société de brevets industriels-Etablissement, Vaduz DELIVERY DEVICE FOR RUNNING THREADS

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1148158B (en) * 1960-12-20 1963-05-02 Boelkow Entwicklungen Kg Triggering device on a body remotely controlled via wire, in particular a flying body
DE3132547C1 (en) * 1981-08-18 1982-12-09 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Unwinding device for a guidance glass fibre of a missile

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2719111A1 (en) * 1994-04-25 1995-10-27 Aerospatiale Installation of fired ammunition firing from a mobile launcher.
EP0679861A1 (en) * 1994-04-25 1995-11-02 AEROSPATIALE Société Nationale Industrielle Firing installation for wire guided ammunition from a mobile launcher
FR2722284A1 (en) * 1994-07-08 1996-01-12 Aerospatiale FIBER LENGTH TRACKING DEVICE ON AN OPTICAL FIBER COIL AND METHOD FOR MANUFACTURING SUCH A DEVICE
EP0693670A1 (en) * 1994-07-08 1996-01-24 AEROSPATIALE Société Nationale Industrielle Device for indicating the length of fibre on an optical-fiber spool and procedure for its manufacture
WO1997007406A1 (en) * 1995-08-14 1997-02-27 State Of Israel, Ministry Of Defence Armaments Development Authority, Rafael Filamentary structure speed measuring method and device

Also Published As

Publication number Publication date
FR2675250A1 (en) 1992-10-16
IT1258311B (en) 1996-02-22
ITMI920879A1 (en) 1993-10-10
ITMI920879A0 (en) 1992-04-10
FR2675250B1 (en) 1997-03-28

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Legal Events

Date Code Title Description
8100 Publication of patent without earlier publication of application
D1 Grant (no unexamined application published) patent law 81
8327 Change in the person/name/address of the patent owner

Owner name: DEUTSCHE AEROSPACE AG, 8000 MUENCHEN, DE

8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: DAIMLER-BENZ AEROSPACE AKTIENGESELLSCHAFT, 80804 M

8327 Change in the person/name/address of the patent owner

Owner name: LFK LENKFLUGKOERPERSYSTEME GMBH, 81669 MUENCHEN, D

8339 Ceased/non-payment of the annual fee