EP0173001A2 - Reconnaissance system - Google Patents

Reconnaissance system Download PDF

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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
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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
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German (de)
French (fr)
Other versions
EP0173001A3 (en
EP0173001B1 (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
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Dynamit Nobel AG
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Publication date
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Priority to AT85106476T priority Critical patent/ATE81201T1/en
Publication of EP0173001A2 publication Critical patent/EP0173001A2/en
Publication of EP0173001A3 publication Critical patent/EP0173001A3/en
Application granted granted Critical
Publication of EP0173001B1 publication Critical patent/EP0173001B1/en
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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.

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  • 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)
  • Cyclones (AREA)
  • Glass Compositions (AREA)
  • Centrifugal Separators (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

Sounding devices (12) are ejected from a missile (10), land on the ground and are brought into a position suitable for starting by a righting device (15). Each sounding device (12) has at least one sensor (16) for detecting objects (26). When it detects an object, the sounding device (12) or a transmitter of this sounding device is fired in the air. While in flight, the sounding device (12) transmits via an antenna (17) detecting signals, which are received by a distant receiver. A great range with low transmitted power is achieved for the transmitter. <IMAGE>

Description

Die Erfindung betrifft ein Aufklärungssystem mit mindestens einem Sondengerät, das eine Sonde zur Detektierung von in der Nähe befindlichen Objekten und einen Sender zur Übermittlung der Detektierung an einen entfernten Empfänger aufweist.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.

Eine wirksame Bekämpfung gegnerischer militärischer Ziele ist nur dann möglich, wenn diese Ziele nach Art, Ort und Zahl möglichst in Echtzeit aufgeklärt worden sind. Es ist bekannt, zu diesem Zweck Fotografien oder Videobilder von Flugzeugen, Raketen oder Satelliten aus, aufzunehmen. Ferner ist es bekannt, Sonden oder Sensoren im Gelände auszulegen oder zu verschießen. Derartige Sonden bzw. Sensoren sind mit Sendern ausgestattet, die auf das Vorhandensein bestimmter Objekte in der Nähe ansprechen und an einen entfernt angeordneten Sender ein Detektierungssignal funken. Wegen der geringen Sendeleistung ist die Reichweite solcher Sender begrenzt. Hinzu kommt, daß die Sender meist am Boden liegen und wegen der topografischen Gegebenheiten ein weitreichender Empfang in der Regel nicht möglich ist. Man verwendet daher Relaisstationen, die in der Nähe der verteilt angeordneten Sondengeräte positioniert werden und die Sendesignale verstärken und an den entfernt angeordneten Empfänger weiterleiten. Ein derartiges System mit Relaisstationen ist jedoch aufwendig und störempfindlich.An effective fight against enemy military targets is only possible if these targets have been cleared in real time, if possible, in terms of type, location and number. For this purpose, it is known to take photographs or video images from aircraft, rockets or satellites. It is also known to design or fire probes or sensors in the field. Such probes or sensors are equipped with transmitters which respond to the presence of certain objects in the vicinity and which transmit a detection signal to a remote transmitter. The range of such transmitters is limited due to the low transmission power. In addition, the transmitters are mostly on the ground and because of the topographical conditions, far-reaching reception is usually not possible. Relay stations are therefore used, which are positioned in the vicinity of the distributed probe devices and amplify the transmit signals and forward them to the remotely located receiver. However, such a system with relay stations is complex and sensitive to interference.

Der Erfindung liegt die Aufgabe zugrunde, ein Aufklärungssystem der eingangs genannten Art zu schaffen, das auch bei geringer Sendeleistung eine Information über die Erregung eines Sondengerätes schnell und zuverlässig an den entfernt angeordneten Sender überträgt, unabhängig von der Geländestruktur und dem Standort des Sondengerätes.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.

Zur Lösung dieser Aufgabe ist erfindungsgemäß vorgesehen, daß der Sender in einem von einer Startvorrichtung aus abschießbaren oder mit einem Triebwerk ausgestatteten Flugkörper enthalten ist, der bei Detektierung eines Objektes gestartet wird und daß der Sender derart gesteuert ist, daß er bei oder nach dem Start zum Aussenden eines Detektierungssignals in Funktion gesetzt wird.To achieve this object, it is provided according to the invention that 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.

Bei dem erfindungsgemäßen Aufklärungssystem werden Sondengeräte entweder durch Verschießen oder durch Verlegung in einem Gelände aufgestellt. Sobald ein Sensor eines der Sondengeräte ein Objekt erkennt und anspricht, wird entweder das gesamte Sondengerät oder nur der Sender dieses Gerätes durch Verschießen oder durch einen Raketenantrieb zum Aufsteigen gebracht. Während des Fluges strahlt der Sender mindestens ein Detektierungssignal ab, das wegen der großen Höhe auch bei geringer Sendeleistung weitreichend empfangen werden kann. Dabei ist ein direkter Empfang ohne Zwischenstationen möglich. Wenn mehrere Sondengeräte verlegt werden, ist es zweckmäßig, daß jedes Sondengerät seine eigene Kennung erhält, d.h. sein eigenes Detektierungssignal, das sich von den Detektierungssignalen der anderen Sondengeräte durch eine Kodierung unterscheidet. Auf diese Weise ist ein Identifizierung des aktivierten Sondengerätes und des Ortes, an dem das Objekt erkannt worden ist, möglich.In the reconnaissance system according to the invention, 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.

Der Sender oder das Sondengerät kann entweder von einer Abschußvorrichtung in die Höhe katapultiert werden, oder mit einem eigenen Raketenantrieb ausgestattet sein.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.

Gemäß einer bevorzugten Ausführungsform der Erfindung ist vorgesehen, daß auch das Sondengerät in einem Flugkörper, insbesondere einer Rakete, untergebracht und von dem Flugkörper im Flug abwerfbar ist und daß das Sondengerät eine Aufstellvorrichtung aufweist, die es nach dem Auftreffen auf dem Boden in eine für den Start geeignete Position stellt. Dies ermöglicht eine besonders einfache und schnelle Art der Verlegung von Sondengeräten, wobei ein einziger Flugkörper mehrere Sondengeräte gleichzeitig oder nacheinander abwerfen kann. Nachdem die Sondengeräte auf dem Boden auftreffen, werden sie durch die Aufstellvorrichtung aufgerichtet, um anschließend abgeschossen zu werden. Der Abschuß erfolgt vorzugsweise senkrecht nach oben. Eine für die Positionierung des Sondenkörpers geeignete Aufstellvorrichtung ist z.B. durch die DE-PS 18 00 121 bekannt.According to a preferred embodiment of the invention it is provided that 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. This enables a particularly simple and quick way of laying probe devices, with a single missile being able to launch several probe devices simultaneously or in succession. After the probe devices hit the ground, they are erected by the erection device to be subsequently fired. The shot is preferably carried out vertically upwards. A suitable device for positioning the probe body is e.g. known from DE-PS 18 00 121.

Der Flugkörper mit Sondengerät kann einen sich während des Fluges entfaltenden Fallschirm aufweisen, der vorzugsweise derart gesteuert ist, daß er im Gipfelpunkt der Flugbahn entfaltet wird. An diesem Fallschirm schwebt der Flugkörper langsam herab, so daß einerseits sichergestellt ist, daß seine Detektierungssignale erkannt werden und daß er andererseits auch leicht zu orten ist. Im Prinzip reicht es grundsätzlich aus, wenn ein einziges Detektierungssignal ausgesandt wird, es kann aber auch zweckmäßig sein, über eine bestimmte Zeitspanne hinweg Detektierungssignale nacheinander auszusenden, um sicherzustellen, daß mindestens eines dieser Signale empfangen und im Empfänger erkannt wird.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. In principle, 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.

Das Sondengerät kann in seiner Gesamtheit in dem Flugkörper untergebracht sein, so daß es nach dem Detektieren hochgeschossen wird. Es ist aber auch möglich, daß das Sondengerät auf dem Boden bleibt, während nur der Sender im Flugkörper angeordnet ist und hochgeschossen wird.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.

Im folgenden wird ein Ausführungsbeispiel der Erfindung unter Bezugnahme auf die Zeichnungen näher erläutert.An exemplary embodiment of the invention is explained in more detail below with reference to the drawings.

Es zeigen:

  • Fig. 1 eine schematische Darstellung der Funktion des Aufklärungssystems anhand der zeitlichen Folge der einzelnen Vorgänge, und
  • Fig. 2 eine schematische Ansicht eines Sondengerätes.
Show it:
  • Fig. 1 is a schematic representation of the function of the reconnaissance system based on the chronological sequence of the individual processes, and
  • Fig. 2 is a schematic view of a probe device.

Fig. la zeigt eine Rakete 10 im Fluge. In Fig. Ib wird aus der Rakete 10 nach dem Ablösen des Kopfstücks 11 das Sondengerät 12 mit der darunter befestigten Abschußbasis 13 abgeworfen. Das Sondengerät 12 hängt an einem Fallschirm, so daß es zusammen mit der Abschußbasis 13 langsam auf den Boden herabsinkt. Nach dem Aufsetzen auf dem Boden wird der Fallschirm 14 von dem Sondengerät abgetrennt. Der Fallschirm 14 ist nicht unbedingt erforderlich. Ggf. kann das Sondengerät ohne Fallschirm abgeworfen werden.Fig. La shows a rocket 10 in flight. In FIG. 1b, after the headpiece 11 has been detached, 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. After touching down on the ground, 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.

In Fig. lc ist der Zustand dargestellt, daß das Sondengerät 12 auf der Abschußbasis 13 auf dem Erdboden steht, wobei eine Aufstellvorrichtung 15, die selbsttätig aufklappt, für eine lagerichtige Orientierung sorgt.In 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.

In Fig. ld erkennt ein Sensor 16 des Sondengerätes 12 ein in der Nähe befindliches Objekt 26. Daraufhin wird ein Raketentriebwerk im Sondengerät 12 gezündet (Fig. le) und das Sondengerät 12 steigt von der Abschußbasis 13 aus senkrecht auf. Dabei wird eine Antenne 17 aus dem Sondengerät 12 ausgefahren und ein (nicht dargestellter) Sender im Sondengerät 12 strahlt über die Antenne 17 eines oder mehrere Detektionssignale ab. Dieses Aussenden von Signalen erfolgt, wenn das Sondengerät eine gewisse Höhe erreicht hat und vorzugsweise, nachdem das Raketentriebwerk bereits erloschen ist (Fig. lf).In FIG. 1d, 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).

Das Detektionssignal dient in erster Linie zur Identifizierung des betreffenden Sondengerätes, das dieses Signal aussendet, es kann jedoch auch Informationen über das erkannte Ziel u.dgl. enthalten.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.

Bei dem beschriebenen Ausführungsbeispiel steigt das gesamte Sondengerät 12 mit Hilfe eines eigenen Raketenantriebs auf. Alternativ besteht die Möglichkeit, in dem aufsteigenden Flugkörper nur den Sender unterzubringen und das Sondengerät selbst am Boden zu belassen. Ferner kann anstelle des Raketenantriebs eine mörserähnliche Abschußvorrichtung vorgesehen sein, mit der der Flugkörper hochgeschossen wird.In the exemplary embodiment described, the entire probe device 12 rises with the aid of its own rocket drive. Alternatively, there is the option of accommodating only the transmitter in the ascending missile and leaving the probe device itself on the ground. Furthermore, instead of the rocket drive, a mortar-like launching device can be provided with which the missile is shot up.

In Fig. 2 ist eine andere Variante des Flugkörpers dargestellt. Dieser Flugkörper 18 hat die Form eines Geschosses. An dem zylindrischen Geschoßkörper ist die Aufstellvorrichtung 19 angebracht, die aus mehreren um Gelenke 20 herum schwenkbaren Füßen 21 besteht. Die Füße 21 sind zunächst in Längsnuten 22 des Flugkörpers 18 eingeklappt. Nach dem der Flugkörper auf dem Boden aufgesetzt hat, klappen die Füße 21 unter Federwirkung um die Gelenke 20 herum auf, so daß der Flugkörper 18 in eine zum Starten geeignete senkrechte Position gebracht wird. Der Flugkörper 18 enthält ein Triebwerk 23 mit einer Düse 22, das Sondengerät 12, den Sender 24 mit Antenne 17 und in der Flugkörperspitze 25 einen (nicht dargestellten) Fallschirm. Das Sondengerät 12 ist mit mehreren Sensoren 16 zur Erkennung von Objekten ausgestattet. Wenn einer der Sensoren 16 anspricht, wird das Raketentriebwerk gestartet und der Flugkörper 18 steigt auf. Im Scheitelpunkt der Flugbahn öffnet sich die Flugkörperspitze 25 und der Fallschirm wird entfaltet. Gleichzeitig wird der Sender 24 aktiviert, so daß während des langsamen Absinkens des Flugkörpers Detektierungssignale von der Antenne 17 abgestrahlt werden.Another variant of the missile is shown in FIG. This missile 18 has the shape of a projectile. 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.

Claims (5)

1. Aufklärungssystem mit mindestens einem Sondengerät, das eine Sonde zur Detektierung von in der Nähe befindlichen Objekten und einen Sender zur Übermittlung der Detektierung an einen entfernten Empfänger aufweist, dadurch gekennzeichnet , daß der Sender (24) in einem von einer Startvorrichtung (13) aus abschießbaren oder mit einem Triebwerk (22) ausgestatteten Flugkörper (18) enthalten ist, der bei Detektierung eines Objektes (26) gestartet wird und daß der Sender derart gesteuert ist, daß er bei oder nach dem Start zum Aussenden eines Detektierungssignal in Funktion gesetzt wird.1. reconnaissance system with at least one probe device having a probe for the detection of nearby objects and a transmitter for transmitting the detection to a remote receiver, characterized in that the transmitter (24) in one of a starting device (13) Shootable or with an engine (22) equipped missile (18) is included, which is started upon detection of an object (26) and that the transmitter is controlled so that it is activated at or after the start to emit a detection signal. 2. Aufklärungssystem nach Anspruch 1, dadurch gekennzeichnet, daß auch das Sondengerät (12) in einem Flugkörper, insbesondere einer Rakete (10), untergebracht ist und von dem Flugkörper im Flug abwerfbar ist und daß das Sondengerät (12) eine Aufstellvorrichtung (15;19) aufweist, die es nach dem Auftreffen auf dem Boden in eine für den Start geeignete Position stellt.2. reconnaissance system according to claim 1, characterized in that the probe device (12) in a missile, in particular a rocket (10), is housed and can be dropped by the missile in flight and that the probe device (12) has a positioning device (15; 19), which it places in a position suitable for take-off after hitting the ground. 3. Aufklärungssystem nach Anspruch 1 oder 2, dadurch gekennzeichnet, der Flugkörper (18) mit Sondengerät (12) einen sich während des Fluges entfaltenden Fallschirm aufweist.3. reconnaissance system according to claim 1 or 2, characterized in that the missile (18) with probe device (12) has a parachute deployed during the flight. 4. Aufklärungssystem nach Anspruch 3, dadurch gekennzeichnet, daß der Fallschirm derart gesteuert ist, daß er im Gipfelpunkt der Flugbahn entfaltet wird.4. reconnaissance system according to claim 3, characterized in that the parachute is controlled such that it is deployed at the apex of the trajectory. 5. Aufklärungssystem nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß das Sondengerät (12) im Flugkörper (18) untergebracht ist.5. reconnaissance system according to one of claims 1 to 4, characterized in that the probe device (12) is housed in the missile (18).
EP85106476A 1984-06-09 1985-05-25 Reconnaissance system Expired - Lifetime EP0173001B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT85106476T ATE81201T1 (en) 1984-06-09 1985-05-25 RECONNAISSANCE SYSTEM.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19843421607 DE3421607A1 (en) 1984-06-09 1984-06-09 CLEARANCE SYSTEM
DE3421607 1984-06-09

Publications (3)

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

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EP85106476A Expired - Lifetime EP0173001B1 (en) 1984-06-09 1985-05-25 Reconnaissance system

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EP (1) EP0173001B1 (en)
AT (1) ATE81201T1 (en)
DE (2) DE3421607A1 (en)

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 (en) * 2003-10-25 2005-04-27 Rheinmetall Waffe Munition GmbH Reconnaissance system for detecting targets and target movements
CN115282533A (en) * 2022-06-30 2022-11-04 温州温工工程机械有限公司 Electromagnetic ejection fire extinguishing bomb for high-rise fire extinguishment

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2644575B1 (en) * 1989-03-14 1991-05-31 Thomson Csf OBJECTIVE MARKER FOR ATTRACTING PROJECTILES WITH A SELF-DIRECTING

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2910956C2 (en) * 1979-03-21 1981-06-11 Siemens AG, 1000 Berlin und 8000 München Procedure for the transmission of data
DE1800121C3 (en) * 1968-10-01 1981-06-11 Dynamit Nobel Ag, 5210 Troisdorf Device for the defined positioning of drop bodies, in particular explosive charges
FR2551198A1 (en) * 1975-04-24 1985-03-01 France Etat Armement Device for neutralising mine igniters
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 (en) * 1979-02-26 1980-08-28 Siemens Ag DEVICE FOR DISCOVERING AND DEFENDING MASKED HELICOPTERS

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1800121C3 (en) * 1968-10-01 1981-06-11 Dynamit Nobel Ag, 5210 Troisdorf Device for the defined positioning of drop bodies, in particular explosive charges
FR2551198A1 (en) * 1975-04-24 1985-03-01 France Etat Armement Device for neutralising mine igniters
DE2910956C2 (en) * 1979-03-21 1981-06-11 Siemens AG, 1000 Berlin und 8000 München Procedure for the transmission of data
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 (en) * 2003-10-25 2005-04-27 Rheinmetall Waffe Munition GmbH Reconnaissance system for detecting targets and target movements
CN115282533A (en) * 2022-06-30 2022-11-04 温州温工工程机械有限公司 Electromagnetic ejection fire extinguishing bomb for high-rise fire extinguishment

Also Published As

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

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