EP0173001A2 - Système de reconnaissance - Google Patents

Système de reconnaissance Download PDF

Info

Publication number
EP0173001A2
EP0173001A2 EP85106476A EP85106476A EP0173001A2 EP 0173001 A2 EP0173001 A2 EP 0173001A2 EP 85106476 A EP85106476 A EP 85106476A EP 85106476 A EP85106476 A EP 85106476A EP 0173001 A2 EP0173001 A2 EP 0173001A2
Authority
EP
European Patent Office
Prior art keywords
missile
probe device
transmitter
probe
reconnaissance system
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
EP85106476A
Other languages
German (de)
English (en)
Other versions
EP0173001A3 (en
EP0173001B1 (fr
Inventor
Willi J. Dr. Petters
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.)
Dynamit Nobel AG
Original Assignee
Dynamit Nobel 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 Dynamit Nobel AG filed Critical Dynamit Nobel AG
Priority to AT85106476T priority Critical patent/ATE81201T1/de
Publication of EP0173001A2 publication Critical patent/EP0173001A2/fr
Publication of EP0173001A3 publication Critical patent/EP0173001A3/de
Application granted granted Critical
Publication of EP0173001B1 publication Critical patent/EP0173001B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F41G7/226—Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/14—Indirect aiming means
    • 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
    • F41G7/2286—Homing guidance systems characterised by the type of waves using radio waves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/365—Projectiles transmitting information to a remote location using optical or electronic means

Definitions

  • the invention relates to a reconnaissance system with at least one probe device, which has a probe for the detection of nearby objects and a transmitter for transmitting the detection to a remote receiver.
  • the invention has for its object to provide a reconnaissance system of the type mentioned, which quickly and reliably transmits information about the excitation of a probe device to the remotely located transmitter, even with low transmission power, regardless of the terrain structure and the location of the probe device.
  • the transmitter is contained in a missile which can be fired from a starting device or is equipped with an engine and which is started upon detection of an object, and that the transmitter is controlled in such a way that it starts at or after launch Sending a detection signal is set in function.
  • probe devices are set up either by firing or by laying them on a site. As soon as a sensor of one of the probe devices detects and responds to an object, either the entire probe device or only the transmitter of this device is raised by firing or by a rocket drive. During the flight, the transmitter emits at least one detection signal Transmission power can be received widely. Direct reception is possible without intermediate stations. If several probe devices are installed, it is expedient for each probe device to be given its own identifier, ie its own detection signal, which differs from the detection signals of the other probe devices by means of an encoding. In this way it is possible to identify the activated probe device and the location at which the object has been recognized.
  • the transmitter or the probe device can either be catapulted into the air by a launcher or can be equipped with its own rocket propulsion.
  • the probe device is housed in a missile, in particular a rocket, and can be launched by the missile in flight, and that the probe device has a positioning device which, after hitting the ground, into a for the Start appropriate position.
  • a positioning device which, after hitting the ground, into a for the Start appropriate position.
  • the missile with probe device can have a parachute that unfolds during the flight is preferably controlled such that it is deployed at the apex of the flight path.
  • the missile floats down slowly on this parachute, so that it is ensured on the one hand that its detection signals are recognized and that it is also easy to locate.
  • it is generally sufficient if a single detection signal is transmitted, but it may also be expedient to transmit detection signals in succession over a certain period of time in order to ensure that at least one of these signals is received and recognized in the receiver.
  • the probe device as a whole can be accommodated in the missile, so that it is shot up after detection. However, it is also possible for the probe device to remain on the ground while only the transmitter is arranged in the missile and is shot up.
  • Fig. La shows a rocket 10 in flight.
  • the probe device 12 with the launch base 13 fastened beneath it is ejected from the rocket 10.
  • the probe device 12 is attached to one Parachute so that it slowly descends to the ground together with the launch base 13.
  • the parachute 14 is separated from the probe device.
  • the parachute 14 is not absolutely necessary. Possibly. the probe device can be dropped without a parachute.
  • Fig. Lc the state is shown that the probe device 12 is on the launch base 13 on the ground, with a set-up device 15, which opens automatically, ensures correct orientation.
  • a sensor 16 of the probe device 12 detects an object 26 located nearby.
  • a rocket engine in the probe device 12 is then ignited (FIG. 1e) and the probe device 12 rises vertically from the launch base 13.
  • An antenna 17 is extended from the probe device 12 and a transmitter (not shown) in the probe device 12 emits one or more detection signals via the antenna 17. This transmission of signals takes place when the probe device has reached a certain height and preferably after the rocket engine has already gone out (FIG. 1f).
  • the detection signal is used primarily to identify the probe device in question that emits this signal, but it can also provide information about the detected target and the like. contain.
  • the entire probe device 12 rises with the aid of its own rocket drive.
  • a mortar-like launching device can be provided with which the missile is shot up.
  • FIG. 1 Another variant of the missile is shown in FIG.
  • This missile 18 has the shape of a projectile.
  • the mounting device 19 On the cylindrical projectile body the mounting device 19 is attached, which consists of several feet 21 which can be pivoted about joints 20.
  • the feet 21 are first folded into the longitudinal grooves 22 of the missile 18. After the missile has landed on the ground, the feet 21 spring open around the joints 20 so that the missile 18 is brought into a suitable vertical position for launching.
  • the missile 18 contains an engine 23 with a nozzle 22, the probe device 12, the transmitter 24 with antenna 17 and in the missile tip 25 a parachute (not shown).
  • the probe device 12 is equipped with a plurality of sensors 16 for the detection of objects. If one of the sensors 16 responds, the rocket engine is started and the missile 18 rises. At the apex of the trajectory, the missile tip 25 opens and the parachute is deployed. At the same time, the transmitter 24 is activated so that detection signals are emitted from the antenna 17 during the slow descent of the missile.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Centrifugal Separators (AREA)
  • Cyclones (AREA)
  • Glass Compositions (AREA)
  • Measurement Of Velocity Or Position Using Acoustic Or Ultrasonic Waves (AREA)
  • Arrangements For Transmission Of Measured Signals (AREA)
EP85106476A 1984-06-09 1985-05-25 Système de reconnaissance Expired - Lifetime EP0173001B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT85106476T ATE81201T1 (de) 1984-06-09 1985-05-25 Aufklaerungssystem.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3421607 1984-06-09
DE19843421607 DE3421607A1 (de) 1984-06-09 1984-06-09 Aufklaerungssystem

Publications (3)

Publication Number Publication Date
EP0173001A2 true EP0173001A2 (fr) 1986-03-05
EP0173001A3 EP0173001A3 (en) 1990-05-02
EP0173001B1 EP0173001B1 (fr) 1992-09-30

Family

ID=6238062

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85106476A Expired - Lifetime EP0173001B1 (fr) 1984-06-09 1985-05-25 Système de reconnaissance

Country Status (3)

Country Link
EP (1) EP0173001B1 (fr)
AT (1) ATE81201T1 (fr)
DE (2) DE3421607A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2246420A (en) * 1990-07-13 1992-01-29 Royal Ordnance Plc Surveillance apparatus.
EP1526353A1 (fr) * 2003-10-25 2005-04-27 Rheinmetall Waffe Munition GmbH Système de reconnaissance pour la détection de cibles et de mouvements des cibles
CN115282533A (zh) * 2022-06-30 2022-11-04 温州温工工程机械有限公司 一种高楼灭火用电磁弹射灭火弹

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2644575B1 (fr) * 1989-03-14 1991-05-31 Thomson Csf Marqueur d'objectif pour attirer des projectiles munis d'un autodirecteur

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2910956C2 (de) * 1979-03-21 1981-06-11 Siemens AG, 1000 Berlin und 8000 München Verfahren zur Übermittlung von Daten
DE1800121C3 (de) * 1968-10-01 1981-06-11 Dynamit Nobel Ag, 5210 Troisdorf Vorrichtung zur definierten Positionierung von Abwurfkörpern, insbesondere Sprengladungen
FR2551198A1 (fr) * 1975-04-24 1985-03-01 France Etat Armement Dispositif de neutralisation des allumeurs de mine
US4589340A (en) * 1983-02-07 1986-05-20 Rheinmetall Gmbh Sensor carrier

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3092770A (en) * 1956-06-26 1963-06-04 Leslie E Shoemaker Emergency long range communication system
DE2907249A1 (de) * 1979-02-26 1980-08-28 Siemens Ag Einrichtung zur entdeckung und abwehr maskierter hubschrauber

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1800121C3 (de) * 1968-10-01 1981-06-11 Dynamit Nobel Ag, 5210 Troisdorf Vorrichtung zur definierten Positionierung von Abwurfkörpern, insbesondere Sprengladungen
FR2551198A1 (fr) * 1975-04-24 1985-03-01 France Etat Armement Dispositif de neutralisation des allumeurs de mine
DE2910956C2 (de) * 1979-03-21 1981-06-11 Siemens AG, 1000 Berlin und 8000 München Verfahren zur Übermittlung von Daten
US4589340A (en) * 1983-02-07 1986-05-20 Rheinmetall Gmbh Sensor carrier

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2246420A (en) * 1990-07-13 1992-01-29 Royal Ordnance Plc Surveillance apparatus.
EP1526353A1 (fr) * 2003-10-25 2005-04-27 Rheinmetall Waffe Munition GmbH Système de reconnaissance pour la détection de cibles et de mouvements des cibles
CN115282533A (zh) * 2022-06-30 2022-11-04 温州温工工程机械有限公司 一种高楼灭火用电磁弹射灭火弹

Also Published As

Publication number Publication date
EP0173001A3 (en) 1990-05-02
EP0173001B1 (fr) 1992-09-30
ATE81201T1 (de) 1992-10-15
DE3421607A1 (de) 1985-12-12
DE3586703D1 (de) 1992-11-05

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