US3046892A - Proximity fuse - Google Patents

Proximity fuse Download PDF

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Publication number
US3046892A
US3046892A US821259A US82125959A US3046892A US 3046892 A US3046892 A US 3046892A US 821259 A US821259 A US 821259A US 82125959 A US82125959 A US 82125959A US 3046892 A US3046892 A US 3046892A
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US
United States
Prior art keywords
target
optical
radio
detector
projectile
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 - Lifetime
Application number
US821259A
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English (en)
Inventor
Cosse Claude
Loy Fernand
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.)
Telecommunications Radioelectriques et Telephoniques SA TRT
Original Assignee
Telecommunications Radioelectriques et Telephoniques SA TRT
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Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/02—Proximity fuzes; Fuzes for remote detonation operated by intensity of light or similar radiation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C13/00—Proximity fuzes; Fuzes for remote detonation
    • F42C13/04—Proximity fuzes; Fuzes for remote detonation operated by radio waves

Definitions

  • This invention relates to proximity fuses for detonating the load of a projectile as soon as it has approached a target up to a predetermined distance.
  • the present invention relates to a device of the kind mentioned in the preamble, in which by means of radio waves a signal is obtained if a target is at a distance which is less than a predetermined distance.
  • An object of the invention is to provide such a device which permits of adjusting the position of the target with respect to the axis of the fuse at the moment of detonation with high accuracy.
  • the invention consists in that, in combination with the said radio-electric means, use is made of optical means producing a signal at a given angular position, but only if a target is present in a portionof the space determined by an angle, provision being made of a coincidence device so that detonation can occur only if both signals are present at the same time.
  • FIG. 1a shows a longitudinal section of the optical part of a device according to the invention
  • FIG. 1b is a cross-sectional view of this device
  • FIG. 2 shows the diagram of a device according to the invention
  • FIG. 3 shows a projectile provided with a device according to the invention
  • FIG. 4 is a cross-sectional view of the peak of a projectile having a device according to the invention, in which the relative positioning of the various elements is shown.
  • the target in order to be struck with reasonable security, the target must be present in a zone determined by the optical device and, in order to ensure safe operation there is also provided a radio-electric device which permits detonation onlywhen a target is present within a predetermined distance.
  • An exact active Zone independent of the surface of the target is defined by means of the optical device,'the field of which may have a very fiat shape;
  • the disadvantages of optical systems are largely eliminated due to their range of activity being limited by means of the radio-electric device.
  • Detonation occurs if the conditions are fulfilled that a target is present within an active zone and that the distance is less than a predetermined critical distance.
  • the optical device is of the passive type, that is to say, a source of radiation is not available.
  • the device In the day-time the device is sensitive to the contrast between the sky and the aircraft passing through the detection cone determined by the optical device. At night and by day it is sensitive to the infrared radiation of an aircraft passing through the said cone.
  • FIGS. 1a and lb the optical part of a device according to the invention is shown in two sections.
  • Reference numeral 1 indicates the outer wall of the proximity fuse
  • 2 indicates a photo-electric detector
  • 3 indicates an annular lens.
  • channels 8, 9, 10, 11 and lens 3 the beams of a conical space the axis of which coincides with the axis of the proximity fuse, are projected onto detector 2.
  • Each channel has two plane mirrors positioned so that, for each window, the incident beam corresponds to a quadrant of the space.
  • channel It has two plane mirrors 10a and 1017 on two opposing lateral faces.
  • FIGS. 1a and lb show the paths of the light rays which pass through the channel 10 and are convergent on detector 2.
  • the detection cone has an apical angle of about 40, the beam having an angle of aperture of 4.
  • the axis of the channels are inclined at an angle of 40 with respect to the axis of the fuse, their cross-section being 4X4 sq. cms.
  • One embodiment of the device is such that the inclination of the beam with respect to the axis of the fuse may be varied within comparatively wide limits by displacing the detector 2 on the said axis along line AB.
  • the inclination of the beam it is alternatively possible for the inclination of the beam to be adapted to the manner in which the projectile approaches its target.
  • the photo-electric detector is contituted by a lead-sulphide cell, the sensitive layer of which is maintained at a temperature below 20 C. One thus obtains, after filtration, a detection in the band between 1 p and 2.7 IL.
  • the windows 4, 5, 6 and 7 are in this case of quartz.
  • An aircraft the smallest lateral dimension of which is of the order of 2 metres, at its most unfavorable position occupies 6 of field at a distance of 20 metres and hence, the sixtieth part of the total field of the detector. It may be assumed that, in the day-time, the brightness of the aircraft differs not more than 10% from the brightness ofthe sky so that, when the aircraft passes through the detection cone, thereoccurs avariation of about j of the total amount of light received. This variation can readily be observed if it is more than 10- watts. In fact, use is made of a cell which in the dark can detect 10- watts.
  • FIG. 2 shows a diagram of a device according to the invention.
  • a rectangle represents the optical portion and a rectangle represents the radio-electric portion.
  • the former comprises an optical system 21 and the detector 2 previously described, together with an amplifier 23.
  • the latter comprises transistors of the type CC '70; the amplification is 10,000 with a band width of from 500 to 1000 c./s.
  • the radio-electric portion includes a distance meter in which use is made of the Doppler effect and the microphony of oscillators is partly eliminated.
  • aerial 31 serves both for transmission and reception. It is directed forwards and the amplification is 3 db.
  • Reference numeral 32 indicates an oscillator. Any variation in the impedance of the aerial or, which amounts to the same, any energy absorbed by the aerial, results in a variation in the output current of the oscillator. This variation constitutes the useful signal.
  • a conductor 33 connecting oscillator 32 and aerial 31 there are arranged two detectors 34 and 35 at a mutual distance of a quarter of a wave-length as measured along theconnection 33.
  • the detectors are arranged at points which, in the absence of a target in the field of the distance meter, correspond to a maximum and a minimum of the voltage of the standing waves which occur as a result of the interference of the waves propagating from the oscillator towards the aerial with the waves which are reflected at the lower end of the aerial and travel from the aerial towards the oscillator.
  • a transformer 36 By means of a transformer 36, the primary winding of whichis powered via the oppositely-connected detectors Hand 35 it is possible to setup a voltage at a secondary winding of the transformer, which voltage is proportional to the variable part of the useful signal.
  • the ratio of transmission of the transformer is such that the voltage of the said signal and the input voltage of amplifier 37 are matched with each other. In the embodiments under consideration, thetransformation ratio was 30, the oscillator frequency was 240 mc./s., and the symmetrical mixing system including the two detectors yielded an uncoupling of 30 db;
  • the signals which, due to their presence, indicate a target at a distance less than 20 metres, are given off by the amplifier 37 in the form of rectangular voltages, whereasthe amplifier 23 indicates the signals which, in the presence of a target occur, in the optical detection :one in the form of a direct voltage located above a given .evel.
  • These various signals are led to a coincidence ievice 40, the output voltage of which controls the detonaion of the projectile by means of a device 41.
  • the coin- :idencedevice '40 may contain a plurality of diodes.
  • the levice 41 contains a thyratron, the anode current of vhich brings about the ignition.
  • FIG. 3 shows a device E, wherein H represents the 'adiation diagram of the aerial and-F indicates the detecion' cone for the optical device.
  • H represents the 'adiation diagram of the aerial
  • -F indicates the detecion' cone for the optical device.
  • the 'adiation diagram of the aerial may be wider than in :nown devices i'n-whichthe directional effect of the aerial mly is used for obtaining an accurate detection ofv angle.
  • the coincidence device controls the detonation if the utput voltage of the optical device indicates the presence 4 of a target in the detection cone-and the output voltage of the radio-electric device indicates the presence thereof at a distance less than 20 metres.
  • the targets brought to light need, strictly speaking, not be the same, it is highly improbable that several targets are indicated by the two detectors at the same time. This applies more particularly if the device is not adjusted until it has left the earth or at least its nose is directed upwards.
  • the electrical portion of the device use may be advantageously made of transistors.
  • the devices, except of course, the aerial may then readily be arranged in a space having a volume of a cubic decimetre.
  • the optical portion may readily be housed in a space which is smaller than 4 cubic decimetres.
  • FIG. 4 shows in what manner the optical portion and the electrical portion may be positioned with respect to each other. and 10 of the optical detection device and also the photo sensitive detector 2 and the aerials 31 of the radio-electric detector. Two aerials are present so that the desired directional eifect in the forward direction is obtained.
  • the circuits associated with the radio-electric device are housed in a space 30 Whereas the amplifier 23 associated with the optical detector and the coincidence device 40 are arranged in a space 40'.
  • the optical device may be of the active type, that is to say, may contain a source of radiation, together with'a detector which is sensitive to the radiation reflected by a target.
  • a proximity fuse for detonating the charge of a projectile comprising a source of radio signals, means for transmitting said radio signals, means for receiving said radio signals to provide a first output signal 'dependent upon the proximity of a target, optical means for providing a second output signal dependent upon the occurrence of a target at'a predetermined angular position with respect to the longitudinal axis of said projectile, a coincidence device, means applying said first'and second output signals to said'coincidence device whereby a detonating signal is produced only when said first and second signals both indicate the presence of a target.
  • optical means comprises photo-electric detector means, and means'fop directing light rays upon said detector means which originate from light sources located between two concentric cones of revolution whose axes coincidewith the longi tudinal axis of said projectile.
  • a proximity fuse for detonating the charge of a projectile comprising a source of radio signals, means for transmitting said radio signals, means for receiving said radio signals to provide a first output signal depend ent upon the proximity of a target, photosensitive means, means for directing light from a predetermined angular direction with respect to the longitudinal axis 'of'said projectile on said photosensitive means to provide a second output signal dependent upon the occurrence/of a target in the path of said light, a coincidencedevice' means applying said first and second output signals to said coincidence device whereby a detonating signal ,is produced only when said'first and second signals' both indicate the presence of a target.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US821259A 1958-06-20 1959-06-18 Proximity fuse Expired - Lifetime US3046892A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1095168X 1958-06-20

Publications (1)

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US3046892A true US3046892A (en) 1962-07-31

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US821259A Expired - Lifetime US3046892A (en) 1958-06-20 1959-06-18 Proximity fuse

Country Status (4)

Country Link
US (1) US3046892A (fr)
DE (1) DE1095168B (fr)
FR (1) FR1207476A (fr)
GB (1) GB865842A (fr)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3161375A (en) * 1962-09-11 1964-12-15 Justin M Ruhge Solar cell look-angle detecting system
US3181814A (en) * 1961-11-07 1965-05-04 Charles W Pittman Missile target intercept angle measuring system
US3793958A (en) * 1972-06-22 1974-02-26 Raytheon Co Optical fusing arrangement
US3902172A (en) * 1962-03-29 1975-08-26 Us Navy Infrared gated radio fuzing system
US3905298A (en) * 1961-10-21 1975-09-16 Telefunken Patent Electronic proximity fuse incorporating means for preventing premature detonation by electronic counter measures
US3933097A (en) * 1968-01-04 1976-01-20 The United States Of America As Represented By The Secretary Of The Navy Device to determine effective target size for fixed angle fuzes
FR2276557A1 (fr) * 1974-06-25 1976-01-23 Bofors Ab Fusee de proximite de type infrarouge passif
US3942446A (en) * 1974-09-06 1976-03-09 The United States Of America As Represented By The Secretary Of The Army Optical fuze and/or miss distance indicator
US3945008A (en) * 1961-11-29 1976-03-16 Telefunken Patentverwertungs-G.M.B.H. Electronic proximity fuse having multiple Doppler frequency channels
DE2527368A1 (de) * 1975-06-19 1976-12-30 Messerschmitt Boelkow Blohm Sensor fuer einen annaeherungszuender
US4193072A (en) * 1962-03-13 1980-03-11 The United States Of America As Represented By The Secretary Of The Navy Combination infrared radio fuze
US4356488A (en) * 1960-05-20 1982-10-26 Electric & Musical Industries Limited Device for indicating the proximity of a target
FR2537263A2 (fr) * 1981-06-04 1984-06-08 Diehl Gmbh & Co Dispositif destine a engendrer un signal d'amorcage pour missile de survol
FR2548347A1 (fr) * 1983-06-30 1985-01-04 Diehl Gmbh & Co Procede de production d'un signal d'allumage et dispositif de detection et d'allumage a plusieurs detecteurs
US4627351A (en) * 1983-09-08 1986-12-09 U.S. Philips Corporation Fuse for projectiles
US4765244A (en) * 1983-04-15 1988-08-23 Spectronix Ltd. Apparatus for the detection and destruction of incoming objects
US4848239A (en) * 1984-09-28 1989-07-18 The Boeing Company Antiballistic missile fuze
ES2049621A2 (es) * 1991-11-15 1994-04-16 Alaveses Explosivos Espoleta de proximidad.
US6279478B1 (en) 1998-03-27 2001-08-28 Hayden N. Ringer Imaging-infrared skewed-cone fuze
DE10207923A1 (de) * 2002-02-23 2003-09-18 Diehl Munitionssysteme Gmbh Annäherungssensor, insbesondere für die Zündauslösung des Gefechtskopfes einer Abwehrgranate gegen ein anfliegendes Projektil
DE102004040218A1 (de) * 2004-08-19 2006-03-09 Diehl Bgt Defence Gmbh & Co. Kg Annäherungssensoranordnung
CN102840799A (zh) * 2012-08-30 2012-12-26 中国科学院长春光学精密机械与物理研究所 具有双重安保设计的激光点火系统
US10935357B2 (en) 2018-04-25 2021-03-02 Bae Systems Information And Electronic Systems Integration Inc. Proximity fuse having an E-field sensor

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2816892A1 (de) * 1978-04-19 1986-10-09 Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt Annaeherungszuender

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2137598A (en) * 1935-04-02 1938-11-22 Ericsson Telefon Ab L M Artillery projectile
US2856852A (en) * 1944-05-30 1958-10-21 Jr Wilbur S Hinman Proximity fuze
US2892093A (en) * 1944-12-30 1959-06-23 Joseph E Henderson Fuze

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
LU31517A1 (fr) * 1952-06-06

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2137598A (en) * 1935-04-02 1938-11-22 Ericsson Telefon Ab L M Artillery projectile
US2856852A (en) * 1944-05-30 1958-10-21 Jr Wilbur S Hinman Proximity fuze
US2892093A (en) * 1944-12-30 1959-06-23 Joseph E Henderson Fuze

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4356488A (en) * 1960-05-20 1982-10-26 Electric & Musical Industries Limited Device for indicating the proximity of a target
US3905298A (en) * 1961-10-21 1975-09-16 Telefunken Patent Electronic proximity fuse incorporating means for preventing premature detonation by electronic counter measures
US3181814A (en) * 1961-11-07 1965-05-04 Charles W Pittman Missile target intercept angle measuring system
US3945008A (en) * 1961-11-29 1976-03-16 Telefunken Patentverwertungs-G.M.B.H. Electronic proximity fuse having multiple Doppler frequency channels
US4193072A (en) * 1962-03-13 1980-03-11 The United States Of America As Represented By The Secretary Of The Navy Combination infrared radio fuze
US3902172A (en) * 1962-03-29 1975-08-26 Us Navy Infrared gated radio fuzing system
US3161375A (en) * 1962-09-11 1964-12-15 Justin M Ruhge Solar cell look-angle detecting system
US3933097A (en) * 1968-01-04 1976-01-20 The United States Of America As Represented By The Secretary Of The Navy Device to determine effective target size for fixed angle fuzes
US3793958A (en) * 1972-06-22 1974-02-26 Raytheon Co Optical fusing arrangement
FR2276557A1 (fr) * 1974-06-25 1976-01-23 Bofors Ab Fusee de proximite de type infrarouge passif
US3942446A (en) * 1974-09-06 1976-03-09 The United States Of America As Represented By The Secretary Of The Army Optical fuze and/or miss distance indicator
DE2527368A1 (de) * 1975-06-19 1976-12-30 Messerschmitt Boelkow Blohm Sensor fuer einen annaeherungszuender
FR2537263A2 (fr) * 1981-06-04 1984-06-08 Diehl Gmbh & Co Dispositif destine a engendrer un signal d'amorcage pour missile de survol
US4765244A (en) * 1983-04-15 1988-08-23 Spectronix Ltd. Apparatus for the detection and destruction of incoming objects
FR2548347A1 (fr) * 1983-06-30 1985-01-04 Diehl Gmbh & Co Procede de production d'un signal d'allumage et dispositif de detection et d'allumage a plusieurs detecteurs
US4627351A (en) * 1983-09-08 1986-12-09 U.S. Philips Corporation Fuse for projectiles
US4848239A (en) * 1984-09-28 1989-07-18 The Boeing Company Antiballistic missile fuze
ES2049621A2 (es) * 1991-11-15 1994-04-16 Alaveses Explosivos Espoleta de proximidad.
US6279478B1 (en) 1998-03-27 2001-08-28 Hayden N. Ringer Imaging-infrared skewed-cone fuze
US20020020321A1 (en) * 1998-03-27 2002-02-21 Ringer Hayden N. Imaging-infrared skewed cone fuze
US6817296B2 (en) * 1998-03-27 2004-11-16 Northrop Grumman Corporation Imaging-infrared skewed cone fuze
DE10207923A1 (de) * 2002-02-23 2003-09-18 Diehl Munitionssysteme Gmbh Annäherungssensor, insbesondere für die Zündauslösung des Gefechtskopfes einer Abwehrgranate gegen ein anfliegendes Projektil
US20040261646A1 (en) * 2002-02-23 2004-12-30 Raimar Steuer Proximity sensor, especially for ignition of the warhead of a shell directed against an aprroaching missile
DE10207923B4 (de) * 2002-02-23 2005-09-22 Diehl Bgt Defence Gmbh & Co. Kg Annäherungssensor, insbesondere für die Zündauslösung des Gefechtskopfes einer Abwehrgranate gegen ein anfliegendes Projektil
DE102004040218A1 (de) * 2004-08-19 2006-03-09 Diehl Bgt Defence Gmbh & Co. Kg Annäherungssensoranordnung
DE102004040218B4 (de) * 2004-08-19 2008-04-17 Diehl Bgt Defence Gmbh & Co. Kg Annäherungssensoranordnung
CN102840799A (zh) * 2012-08-30 2012-12-26 中国科学院长春光学精密机械与物理研究所 具有双重安保设计的激光点火系统
US10935357B2 (en) 2018-04-25 2021-03-02 Bae Systems Information And Electronic Systems Integration Inc. Proximity fuse having an E-field sensor

Also Published As

Publication number Publication date
GB865842A (en) 1961-04-19
DE1095168B (de) 1960-12-15
FR1207476A (fr) 1960-02-17

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