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EP0173001B1 - Système de reconnaissance - Google Patents

Système de reconnaissance Download PDF

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Publication number
EP0173001B1
EP0173001B1 EP85106476A EP85106476A EP0173001B1 EP 0173001 B1 EP0173001 B1 EP 0173001B1 EP 85106476 A EP85106476 A EP 85106476A EP 85106476 A EP85106476 A EP 85106476A EP 0173001 B1 EP0173001 B1 EP 0173001B1
Authority
EP
European Patent Office
Prior art keywords
transmitter
missile
probe
probe device
flight
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
EP85106476A
Other languages
German (de)
English (en)
Other versions
EP0173001A2 (fr
EP0173001A3 (en
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 is set up on the ground in the terrain and has a probe for the detection of objects located nearby and a transmitter for transmitting the detection to a remote receiver.
  • DE-C2-29 10 956 describes a reconnaissance system which consists of a low-flying object and an additional missile.
  • a reconnaissance aircraft e.g. Individual information from the area flown over and entered in the form of data into a memory which is stored in the additional missile, e.g. a rocket that is housed.
  • the missile is then fired from the flying object with the storage at least partially filled in the direction of a ground station and traverses a high, essentially ballistic trajectory. After reaching the reception area of the ground station, the stored data are sent out for reception by the ground station by means of a radio transmitter housed in the missile.
  • This system is very complex and only enables clarification at the point in time when the respective area is scanned.
  • 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 receiver, 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 set-up device which, after hitting the ground, into a for the Start appropriate position.
  • a missile in particular a rocket and can be launched by the missile in flight
  • the probe device has a set-up device which, after hitting the ground, into a for the Start appropriate position.
  • the missile with the probe device can have a parachute that unfolds during the flight, which preferably is controlled so that it is unfolded at the apex of the trajectory.
  • 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. 1a shows a rocket 10 in flight.
  • the probe device 12 with the launch base 13 fastened underneath 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. 1c 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 is then ignited in the probe device 12 (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 primarily used to identify the probe device in question, which 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.
  • Mounted on the cylindrical projectile body is the mounting device 19, which consists of a plurality of 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 touched the ground, the feet 21 spring open around the joints 20 so that the missile 18 is brought into a vertical position suitable 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 by 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)
  • Measurement Of Velocity Or Position Using Acoustic Or Ultrasonic Waves (AREA)
  • Arrangements For Transmission Of Measured Signals (AREA)
  • Radar Systems Or Details Thereof (AREA)
  • Glass Compositions (AREA)
  • Centrifugal Separators (AREA)
  • Cyclones (AREA)

Claims (5)

  1. Système de reconnaissance comportant au moins un appareil d'exploration qui est posé sur le sol du terrain d'action, une sonde pour la détection d'objets situés dans le voisinage et un émetteur pour la transmission des informations à un récepteur éloigné, caractérisé par le fait que l'émetteur (24) est contenu dans un projectile (18) pouvant être tiré à partir d'un dispositif de lancement (13) ou muni d'un dispositif de propulsion (22), projectile qui est lancé lors de la détection d'un objet (26) et par le fait que l'émetteur (24) est commandé de manière telle que celui-ci soit mis en service lors du ou après le lancement aux fins d'émission d'un signal de détection.
  2. Système de reconnaissance selon la revendication 1, caractérisé par le fait que l'appareil d'exploration (12) est lui aussi logé dans un projectile, notamment dans une fusée (10) et peut être largué à partir dudit projectile et que l'appareil d'exploration (12) comporte un dispositif de positionnement (15; 19) qui, après que ledit appareil d'exploration ait touché le sol, place celui-ci dans une position adéquate pour son lancement.
  3. Système de reconnaissance selon la revendication 1 ou 2, caractérisé par le fait que le projectile (18) et l'appareil d'exploration (12) sont munis d'un parachute qui se déploie pendant le vol.
  4. Système de reconnaissance selon la revendication 3, caractérisé par le fait que le parachute est commandé de manière telle que celui-ci s'ouvre à l'apogée de la trajectoire.
  5. Système de reconnaissance selon l'une des revendications 1 à 4, caractérisé par le fait que l'appareil d'exploration (12) est logé à l'intérieur du projectile (18).
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 EP0173001A2 (fr) 1986-03-05
EP0173001A3 EP0173001A3 (en) 1990-05-02
EP0173001B1 true 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)

Families Citing this family (6)

* 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
GB9015445D0 (en) * 1990-07-13 1991-02-20 Royal Ordnance Plc Projectile surveillance apparatus
RU2227892C1 (ru) * 2002-10-14 2004-04-27 Ванин Виктор Николаевич Комплекс противовоздушной ракетно-космической обороны
DE10349838A1 (de) * 2003-10-25 2005-05-25 Rheinmetall Waffe Munition Gmbh Aufklärungssystem zur Ermittlung von Zielen und Zielbewegungen
RU2247312C1 (ru) * 2004-05-24 2005-02-27 Табачук Игорь Сергеевич Способ контроля результатов поражения цели
CN115282533B (zh) * 2022-06-30 2023-06-27 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

Family Cites Families (6)

* 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
DE1800121C3 (de) * 1968-10-01 1981-06-11 Dynamit Nobel Ag, 5210 Troisdorf Vorrichtung zur definierten Positionierung von Abwurfkörpern, insbesondere Sprengladungen
FR2551198B1 (fr) * 1975-04-24 1986-11-21 France Etat Armement Dispositif de neutralisation des allumeurs de mine
DE2907249A1 (de) * 1979-02-26 1980-08-28 Siemens Ag Einrichtung zur entdeckung und abwehr maskierter hubschrauber
DE2910956C2 (de) * 1979-03-21 1981-06-11 Siemens AG, 1000 Berlin und 8000 München Verfahren zur Übermittlung von Daten
DE3304070A1 (de) * 1983-02-07 1984-08-09 Rheinmetall GmbH, 4000 Düsseldorf Sensortraeger

Also Published As

Publication number Publication date
ATE81201T1 (de) 1992-10-15
EP0173001A2 (fr) 1986-03-05
EP0173001A3 (en) 1990-05-02
DE3586703D1 (de) 1992-11-05
DE3421607A1 (de) 1985-12-12

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