EP1637827A1 - Ballistisch geschossenes Fernerkundungsgerät - Google Patents

Ballistisch geschossenes Fernerkundungsgerät Download PDF

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Publication number
EP1637827A1
EP1637827A1 EP05108690A EP05108690A EP1637827A1 EP 1637827 A1 EP1637827 A1 EP 1637827A1 EP 05108690 A EP05108690 A EP 05108690A EP 05108690 A EP05108690 A EP 05108690A EP 1637827 A1 EP1637827 A1 EP 1637827A1
Authority
EP
European Patent Office
Prior art keywords
bullet
reconnaissance device
reconnaissance
vision system
launching
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.)
Withdrawn
Application number
EP05108690A
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English (en)
French (fr)
Inventor
Mauro Zona
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.)
Zona Deltaspace Srl
Original Assignee
Zona Deltaspace Srl
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 Zona Deltaspace Srl filed Critical Zona Deltaspace Srl
Publication of EP1637827A1 publication Critical patent/EP1637827A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G3/00—Aiming or laying means
    • F41G3/02—Aiming or laying means using an independent line of sight

Definitions

  • the present invention relates to devices for the remote reconnaissance of territory areas, of the type including a bullet to be launched with launching means of any type, a camera vision system installed in the bullet, and a transmission system installed in the bullet, for remotely transmitting data emitted by said vision system.
  • UAV aircrafts of large dimensions such as, for example, the Global Hawk ex Northrop Grumman
  • UAV aircrafts of large dimensions such as, for example, the Global Hawk ex Northrop Grumman
  • the level of the request of using a means capable of preventive reconnaissance which in the past was an exclusive of the strategic command of the operations, is, for some time decreasing, by also interesting, sometimes, the command for instance of a single battalion.
  • RPV aircrafts constituted by model aircrafts made of polyurethane foam with engine and radio control typical of the amusement model aircrafts have been proposed.
  • the performances and the duty time of such aircrafts are obviously limited, but however sufficient for the local use.
  • such solutions have the advantage of being extremely inexpensive, an advantage which is not completely negligible as reconnaissance aircrafts of this type hardly return to the base.
  • the Achilles'heel of these systems is, however, the possibility of being shot down also by a simple carabine shot because of the poor altitude and velocity performances.
  • the object of the present invention is to propose a new remote reconnaissance device which is able to obviate to the drawbacks above-mentioned and which results, in particular, of a relatively reduced cost, so as to make conceivable a use thereof of the "fire and forget" type (that is of the "disposable” type) and which shows however high characteristics from the point of view of the width of the area which can be subjected to reconnaissance, the low interceptability and the low visibility.
  • remote reconnaissance devices which instead of being constituted of aircrafts having an own engine and remotely piloted, are, on the contrary, only in the form of bullets which are shot by a gun and which have an on-board system of vision which can remotely transmit the data emitted from it.
  • the territory area which can be subjected to reconnaissance substantially corresponds to the base of a theoretical lighting cone with which the vision system sees the territory once it has been parachuted, for example after having left the transport bullet (US-A-5 467 681), or after the ballistic trajectory of the bullet has interrupted itself with the exit of the parachute and the system vision placed on the tip of the bullet is directed downwards (US-A-3 962 537).
  • the ballistic trajectory of the bullet is not used for a reconnaissance purpose, and the bullet has the only task of bringing the vision system in place, after which the reconnaissance is carried out during a step of parachuted fall. Therefore, such known solutions involve some limits from the point of view of the width of the area which can be subjected to reconnaissance and also from the point of view of the invulnerability.
  • the object of the present invention is a remote reconnaissance device of a territory area, of the type including:
  • the main advantage of the present invention is that the reconnaissance is carried out while the bullet covers its normal parabolic ballistic trajectory.
  • the vision system In each moment of the bullet flight along said ballistic trajectory, the vision system is able to observe the territory area subtended by the vision cone leaving the side window of the bullet, which leads, at the completion of the trajectory, to the observation of a whole strip of territory, extending from the launching point to the point of final impact of the bullet and having a progressively decreasing width from the center towards the ends of the strip (since the area subtended by the vision cone increases with the increase of the bullet altitude).
  • the device according to the invention differs itself from RPV aircrafts in that it is not an aircraft equipped with an own engine, nor is remotely piloted. This allows to reduce of a great extent the cost of the device with respect to such RPV aircrafts, so as to render conceivable a use of the ""disposable" type. From the other side, the device according to the invention differs itself from the known solutions already using ballistically launched bullets in that therein the ballistic trajectory of the bullet is exploited for executing the reconnaissance.
  • a first simple solution of the problem is that the system of data processing exiting from the vision system is programmed in order to use the data emitted in the steps wherein the window is substantially pointed towards the ground, rejecting the data emitted in the remaining time intervals.
  • a second, more sophisticaded solution which always relates to the use of a rifled barrel launching gun, foresees the arrangement of the vision window on a part of the body of the bullet which is rotatably mounted around the longitudinal axis of the bullet with respect to a second part of said body.
  • motor means for controlling the rotation of the part having the vision window if necessary with the help of a gyroscopic system are further foreseen, for the purpose of constantly maintaining the vision window substantially pointed towards the ground, despite the remaining part of the body of the bullet is rotating.
  • the launching of the bullet with a smooth-barrel gun can be, on the contrary, foreseen for the purpose of launching the bullet without imparting it a rotation around its axis.
  • the bullet is arranged with wings which spread themselves in an operating position immediately after the launching.
  • the bullet can be however arranged with spreadable and rotary wings, for the purpose of imparting a glided trajectory to the bullet which differs itself from the theoretical parabolic trajectory in the end step preceding the ground impact.
  • the device according to the invention includes a bullet 1 which is launched through a launching means of any type, for example through a gun 2, so as to cover a ballistic parabolic trajectory from the launching point A to the point of ground impact B.
  • the bullet 1 includes a body made of a plastic material having a longitudinal axis 3, an ogive 4 and a back base equipped with a heat shield 5 which protects the body of the bullet 1 from a ballistic charge 6 (shown with a dashed line in figure 2) which is used for the launching from the gun 2.
  • Numeral 7 shows an array of optical sensors, for example of the CCD type, constituting a camera forming part of the vision system of the device.
  • the camera 7 observes the scene exterior to the bullet through a lens 8 placed in a side window 9 of the ogive 4, and further thanks to a reflecting mirror 10.
  • Numeral 11 shows the electron control system of the camera 7, and numeral 12 shows the electron system for the processing and the remote transmission of the data exiting from the camera 7.
  • Such data are remotely transmitted, on an appropriate frequency, to a receiving antenna which can be, for example, carried by an air balloon 13 anchored to the ground close to the launching point A (figure 1).
  • the embodiment shown in the figure 2 relates to the case in which the launching is carried out with a rifled barrel gun 2, which imparts a rotation to the body of the bullet 1 around its longitudinal axis 3.
  • the ogive 4 constitutes a body separated from the remaining part of the bullet (shown by 13) which is rotatably mounted on the part 13 around the longitudinal axis 3 through bearings 14.
  • An engine (not shown) is installed in the part 13 of the bullet body and drives the rotation of a pinion which engages a crown wheel carried by the ogive 4, so as to drive a rotation of such ogive.
  • Numeral 15 shows the electron control system of the rotation of the ogive 4.
  • the system 15 can be programmed for imparting to the ogive 4 a rotation relative to the part 13 of the bullet which undergoes the rotation imparted by the gun, so as to annul or at least reduce the rotation speed of the ogive 4 relative to a fixed observer. This can also be obtained, in case, with the help of a gyroscopic system.
  • the vision window will result permanently pointed towards the ground, so as to allow a continuous observation of the strip of territory covered by the window.
  • Such strip is shown by 5 in figure 1 and corresponds to the envelope of the areas "illuminated” by the vision cone exiting from the window during the ballistic trajectory of the bullet. This can also be observed with reference to the figure 3, wherein the theoretical vision cones of the window of the bullet 1 are diagrammatically shown in the course of the trajectory.
  • the processing system of the data emitted from the camera will be able, however, to use the data emitted in the time intervals in which the window is substantially pointed downwards, by rejecting the data emitted in the remaining time intervals.
  • Figure 4 shows a bullet intended for being launched with a smooth-barrel gun 2.
  • the bullet will not undergo a rotation around its axis because of the launching.
  • the body of the bullet 1 is, in this case, monolithic but for the rest the components arranged therein are completely similar to those described in figure 2 and therefore they have been shown by the same reference number.
  • the bullet is equipped with stabilizing wings (for example three or four wings angularly spaced) which automatically spread themselves after the launching.
  • Figure 4 shows two wings 16 which are swingingly mounted on the body of the bullet 1 around two axis 17.
  • the wings 16 can automatically be returned towards the operating spreaded position, which is shown in figure 4, starting from a retracted position shown with a dashed line in figure 4 by resilient means (not shown).
  • the wings 16 can be hold in the retracted position by a hooking system which is automatically disconnected by a timer after the launching.
  • the structure and the arrangement of the hooking device of the timer are not described nor shown herein, as such components are per se known and can be carried out according any additional configuration. Therefore, such details have been eliminated from the drawings both as they do not lie, per se, in the ambit of the present invention and as their elimination makes the drawings of a simpler and easier comprehension.
  • the spreadable wings 16 have a body 16a which can be orientated around its longitudinal axis 16b in the direction of the arrows R, relative to the base part 16c.
  • Such oscillation can be controlled in order to confer to the bullet a glided trajectory, which differs from the parabolic theoretical trajectory in the final part preceding the ground impact.
  • the final part of the glided trajectory P that in this way the bullet follows in the final part of its path, is shown therein. In this way, the ground impact will not occur in position B, but in correspondence with a point B' more distant from A.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
EP05108690A 2004-09-21 2005-09-21 Ballistisch geschossenes Fernerkundungsgerät Withdrawn EP1637827A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ITTO20040632 ITTO20040632A1 (it) 2004-09-21 2004-09-21 Dispositivo per la ricognizione a distanza, a lancia balistico

Publications (1)

Publication Number Publication Date
EP1637827A1 true EP1637827A1 (de) 2006-03-22

Family

ID=35517350

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05108690A Withdrawn EP1637827A1 (de) 2004-09-21 2005-09-21 Ballistisch geschossenes Fernerkundungsgerät

Country Status (2)

Country Link
EP (1) EP1637827A1 (de)
IT (1) ITTO20040632A1 (de)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3962537A (en) * 1975-02-27 1976-06-08 The United States Of America As Represented By The Secretary Of The Navy Gun launched reconnaissance system
GB1495166A (en) * 1975-05-21 1977-12-14 Elliott Bros Missile guidance systems
US5425514A (en) * 1993-12-29 1995-06-20 Raytheon Company Modular aerodynamic gyrodynamic intelligent controlled projectile and method of operating same
US5467681A (en) * 1994-07-21 1995-11-21 The United States Of America As Represented By The Secretary Of The Army Cannon launched reconnaissance vehicle
DE19505527A1 (de) * 1995-02-18 1996-08-22 Diehl Gmbh & Co Verfahren und Einrichtung zur Ziel- oder Lageaufklärung
DE19714539A1 (de) * 1997-04-09 1998-10-15 Diehl Stiftung & Co Aufklärungs-Drohne
EP1391681A1 (de) * 2002-08-20 2004-02-25 Diehl Munitionssysteme GmbH & Co. KG Verfahren und Vorrichtung zur Echtzeit-Geländeaufklärung

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3962537A (en) * 1975-02-27 1976-06-08 The United States Of America As Represented By The Secretary Of The Navy Gun launched reconnaissance system
GB1495166A (en) * 1975-05-21 1977-12-14 Elliott Bros Missile guidance systems
US5425514A (en) * 1993-12-29 1995-06-20 Raytheon Company Modular aerodynamic gyrodynamic intelligent controlled projectile and method of operating same
US5467681A (en) * 1994-07-21 1995-11-21 The United States Of America As Represented By The Secretary Of The Army Cannon launched reconnaissance vehicle
DE19505527A1 (de) * 1995-02-18 1996-08-22 Diehl Gmbh & Co Verfahren und Einrichtung zur Ziel- oder Lageaufklärung
DE19714539A1 (de) * 1997-04-09 1998-10-15 Diehl Stiftung & Co Aufklärungs-Drohne
EP1391681A1 (de) * 2002-08-20 2004-02-25 Diehl Munitionssysteme GmbH & Co. KG Verfahren und Vorrichtung zur Echtzeit-Geländeaufklärung

Also Published As

Publication number Publication date
ITTO20040632A1 (it) 2004-12-21

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