CA2334373C - Method of remote controlled combat of near-surface and/or surface-bound targets - Google Patents
Method of remote controlled combat of near-surface and/or surface-bound targets Download PDFInfo
- Publication number
- CA2334373C CA2334373C CA002334373A CA2334373A CA2334373C CA 2334373 C CA2334373 C CA 2334373C CA 002334373 A CA002334373 A CA 002334373A CA 2334373 A CA2334373 A CA 2334373A CA 2334373 C CA2334373 C CA 2334373C
- Authority
- CA
- Canada
- Prior art keywords
- target
- missile
- homing
- reconnaissance system
- phase
- 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 - Fee Related
Links
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
- F41G7/2206—Homing guidance systems using a remote control station
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G3/00—Aiming or laying means
- F41G3/14—Indirect aiming means
- F41G3/16—Sighting devices adapted for indirect laying of fire
- F41G3/165—Sighting devices adapted for indirect laying of fire using a TV-monitor
Abstract
The invention relates to a method for combating near-surface and/or surface targets such as tanks or the like by using a missile comprising a seeker head, an effective charge and at least one thruster. According to the invention, the missile is redirected into an essentially horizontal cruising and seeking phase after completing an essentially vertical start phase. During said cruising and seeking phase, the missile scans the terrain ahead of it using the seeking head, whereupon an approaching phase which is directed in an essentially downward direction follows after the finally ensues head locks onto an identified target. An external reconnaissance system in an appropriate aircraft and/or spacecraft such as in a helicopter, a drone or in a satellite receives information for guiding the missile which is transmitted to the same.
Description
A METHOD OF REMOTE CONTROLLED COMBAT
OF NEAR-SURFACE AND/OR SURFACE-BOUND TARGETS
FIELD OF INVENTION
The invention relates to a method of combating near-surface and/or surface-bound targets, such as tanks and the like by means of a missile comprising a homing head, an effective charge, and at least one propulsive unit, the missile, after having passed an essentially vertical launching phase, being deflected into an essentially horizontal cruising and homing phase during which the missile scans the terrain ahead by means of the homing head, whereupon finally an essentially vertically dawnwardly directed approaching phase follows, once the homing head has locked on to a recognized target, an external reconnaissance system in an appropriate aircraft and/or space vehicle, such as a helicopter, a drone, or a satellite picking up information for guidance of the missile.
BACKGROUND ART
DE 196 26 975 C1 describes a missile which hardly can be improved further, at reasonable expenditure, as regards its structure to increase the probability of hitting. However, new tank protection systems in particular, such as so-called active protection systems require further improvement.
It was suggested in DE 42 17 185 C1, for example, that a missile be divisible so that, instead of a body member containing the warhead, sensors of a tank will detect and combat a decoy body which is detachable from the body member that includes the warhead.
Furthermore, an autonomous missile is disclosed in DE 42 23 531 C2, namely a missile comprising an inertia reference system to reduce initializing errors.
Likewise known are missiles which are guided towards a target entirely by an external means, instead of autonomous missiles, especially with homing heads and/or inertia reference systems. DE 44 16 885 A1, for instance, discloses a method of guiding a missile by at least one radiation source which can be located by two sensors disposed offset from each other in a launch pad. Guide commands are derived from the locating signals and transmitted to a guide means of the missile so as to keep the missile in the line of sight of at least one sensor detecting a target.
This kind of missile control is complicated with LOS operations, i.e. in case of a direct shot method, if a disturbance occurs between the launch pad and the target.
The known method, however, fails completely if the target is not in any line of sight connection with the launch pad, such as is the case with NLOS operations.
A method of the generic kind defined is known from GB-A-2 148 465 according to which the missile trajectory is adjustable by adjustment of a launch means in response to target information received from the reconnaissance system, and photographs taken by the reconnaissance system are input into the missile memory before the missile is launched.
Methods of guiding missiles which are started from airplanes are known from EP 0 797 068 A2, US 5,458,041, and DE 37 15 909 C1.
DE 3145 374 A1 and DE 33 03 763 A1 describe methods of combating surface targets by means of missiles. These missiles, however, cannot be guided on the basis of information which may be obtained through an external reconnaissance system.
SUMMARY OF THE INVENTION
It is, therefore, the object of the invention to improve the method of the generic kind in question such that the short-comings of the prior art are overcome, i.e. in particular that more accurate target lock-on and a higher hit rate are achieved.
According to the invention, there is provided a method of combating a target located at least near a surface, by means of a missile comprising a homing head, an effective charge, and at least one propulsive unit, wherein the missile, after having passed an essentially vertical launching phase, is deflected into an essentially horizontal cruising and homing phase during which the missile scans the terrain ahead by means of its homing head, whereupon an essentially vertically downwardly directed approaching phase follows once the target has been selected and the homing head has locked on to a recognized target, wherein an external reconnaissance system scans the target area and communicates with the missile, wherein during the homing phase following the target selection, target data pertaining to the selected target is transmitted from the reconnaissance system to the missile so that the homing angle of the missile homing head is optimized continuously in response to such target data with a view to recognizing the target.
Thus, in accordance with the invention, the missile guidance information picked up by the reconnaissance system is transmitted to the missile and, during the homing phase, the homing angle of the missile homing head is optimized continuously in response to target data transmitted to the missile by the reconnaissance system with a view to recognizing the target.
It may be provided, according to the invention, that the reconnaissance system scans the possible target area either statically or in flight during a mission with an external reconnaissance system picking up and transmitting information for guidance ofi the missile.
It is likewise proposed, according to the invention, that, once a combat target has been recognized by the reconnaissance system, in particular as regards the type of target, location of target, and/or target movement, the missile is launched, under control of signals transmitted by the reconnaissance system to a missile launcher, such that the quasi-ballistic course of the missile will lead essentially to the target caught by the reconnaissance system.
According to the invention it is further preferred that, during the target approaching phase, once the target has been recognized and the missile homing head has locked on to it, the homing angle of the missile homing head is reduced and minimized largely together with a corresponding increase in resolution to recognize details of the combat target transmitted to the missile by the reconnaissance system, such as the engine area of a tank and the like.
Moreover, it may be provided according to the invention that the reconnaissance system passes on information picked up to a transmitter station and that the missile is guided to the target via the transmitter station.
Finally, it is also proposed, according to the invention that the missile supplies information to the transmitter station and this information is processed in the transmitter station, together with the data transmitted by the reconnaissance system for guidance of the missile.
The invention thus is based on the surprising finding that missiles conventionally operating autonomously by means of a homing head can be remote controlled, in addition, by a reconnaissance system and data can be transmitted permanently to the missile by the external reconnaissance system in order to continuously optimize the aiming direction of the missile during the homing phase so that, in principle, the result is a combination of two conventional homing methods, whereby the elimination of errors is greatly enhanced and the resulting hit rate far superior over the state of the art. The data link according to the invention between the missile and the reconnaissance system thus makes it possible to transmit timely target data 'to the missile, while in flight already, either directly or indirectly through a transmitter station, so as to increase the combat effectiveness.
BRIEF DESCRIPTION OF THE DRAWING
Further features and advantages of the invention may be gathered from the following description which specifies an embodiment of the invention in greater detail, with reference to a diagrammatic drawing. The drawing which consists of a single figure is a perspective view of a combat scenario.
DETAILED DESCRIPTION OF THE INVENTION
The figure illustrates a combat scenario where a tank 1 is to be attacked by a missile 2. To this end, a helicopter 3 flies over the possible target area, scanning the same within a cone of sight I. As soon as the helicopter 3 has recognized the tank 1 as the target, in respect of the type of target, location of target, and target movement, the helicopter 3 transmits signals to a launch means (not shown) of the missile 2 at starting point A. These signals may be transmitted by the helicopter 3 to a transmitter station 4 and then to the launch means and they contain information which permits the missile 2 to be brought from the starting point A into a quasi-ballistic course a which leads essentially to the tank 1 detected by the helicopter 3..
During the homing phase the missile 2 flies essentially horizontally and at supersonic speed. At this time, during the homing phase, the homing angle of the homing head, i.e. the cone of sight b of the guided missile 2 is optimized continuously in response to the target data transmitted by the helicopter 3 to the missile 2 with a view to recognizing the tank 1. The course c of the center of the cone of sight b of the missile 2 is shown in exemplary fashion in the figure, such as it results from the remote guidance by means of the data sensed, processed and transmitted by the helicopter 3.
After the homing head of the missile 2 has recognized the tank 1 and the missile 2 has locked on to the tank 1, i.e. during the target approach phase, the angle of the cone of sight b of the guided missile 2 is reduced continuously in response to details of the tank 1 to be attacked which were sensed by the helicopter 3. This serves to increase the resolution within the cone of sight b of the missile 2 whereby the aiming accuracy is increased as well. In this manner it is possible, for instance, to aim directly at the engine area of the tank 1 so that the effective charge of the missile 1 will have its effect in the engine range, as symbolized in the figure.
The features of the invention disclosed in the above specification, in the drawing, as well as in the claims may be essential to the implementation of the invention in its various embodiments, both individually and in any desired combination.
OF NEAR-SURFACE AND/OR SURFACE-BOUND TARGETS
FIELD OF INVENTION
The invention relates to a method of combating near-surface and/or surface-bound targets, such as tanks and the like by means of a missile comprising a homing head, an effective charge, and at least one propulsive unit, the missile, after having passed an essentially vertical launching phase, being deflected into an essentially horizontal cruising and homing phase during which the missile scans the terrain ahead by means of the homing head, whereupon finally an essentially vertically dawnwardly directed approaching phase follows, once the homing head has locked on to a recognized target, an external reconnaissance system in an appropriate aircraft and/or space vehicle, such as a helicopter, a drone, or a satellite picking up information for guidance of the missile.
BACKGROUND ART
DE 196 26 975 C1 describes a missile which hardly can be improved further, at reasonable expenditure, as regards its structure to increase the probability of hitting. However, new tank protection systems in particular, such as so-called active protection systems require further improvement.
It was suggested in DE 42 17 185 C1, for example, that a missile be divisible so that, instead of a body member containing the warhead, sensors of a tank will detect and combat a decoy body which is detachable from the body member that includes the warhead.
Furthermore, an autonomous missile is disclosed in DE 42 23 531 C2, namely a missile comprising an inertia reference system to reduce initializing errors.
Likewise known are missiles which are guided towards a target entirely by an external means, instead of autonomous missiles, especially with homing heads and/or inertia reference systems. DE 44 16 885 A1, for instance, discloses a method of guiding a missile by at least one radiation source which can be located by two sensors disposed offset from each other in a launch pad. Guide commands are derived from the locating signals and transmitted to a guide means of the missile so as to keep the missile in the line of sight of at least one sensor detecting a target.
This kind of missile control is complicated with LOS operations, i.e. in case of a direct shot method, if a disturbance occurs between the launch pad and the target.
The known method, however, fails completely if the target is not in any line of sight connection with the launch pad, such as is the case with NLOS operations.
A method of the generic kind defined is known from GB-A-2 148 465 according to which the missile trajectory is adjustable by adjustment of a launch means in response to target information received from the reconnaissance system, and photographs taken by the reconnaissance system are input into the missile memory before the missile is launched.
Methods of guiding missiles which are started from airplanes are known from EP 0 797 068 A2, US 5,458,041, and DE 37 15 909 C1.
DE 3145 374 A1 and DE 33 03 763 A1 describe methods of combating surface targets by means of missiles. These missiles, however, cannot be guided on the basis of information which may be obtained through an external reconnaissance system.
SUMMARY OF THE INVENTION
It is, therefore, the object of the invention to improve the method of the generic kind in question such that the short-comings of the prior art are overcome, i.e. in particular that more accurate target lock-on and a higher hit rate are achieved.
According to the invention, there is provided a method of combating a target located at least near a surface, by means of a missile comprising a homing head, an effective charge, and at least one propulsive unit, wherein the missile, after having passed an essentially vertical launching phase, is deflected into an essentially horizontal cruising and homing phase during which the missile scans the terrain ahead by means of its homing head, whereupon an essentially vertically downwardly directed approaching phase follows once the target has been selected and the homing head has locked on to a recognized target, wherein an external reconnaissance system scans the target area and communicates with the missile, wherein during the homing phase following the target selection, target data pertaining to the selected target is transmitted from the reconnaissance system to the missile so that the homing angle of the missile homing head is optimized continuously in response to such target data with a view to recognizing the target.
Thus, in accordance with the invention, the missile guidance information picked up by the reconnaissance system is transmitted to the missile and, during the homing phase, the homing angle of the missile homing head is optimized continuously in response to target data transmitted to the missile by the reconnaissance system with a view to recognizing the target.
It may be provided, according to the invention, that the reconnaissance system scans the possible target area either statically or in flight during a mission with an external reconnaissance system picking up and transmitting information for guidance ofi the missile.
It is likewise proposed, according to the invention, that, once a combat target has been recognized by the reconnaissance system, in particular as regards the type of target, location of target, and/or target movement, the missile is launched, under control of signals transmitted by the reconnaissance system to a missile launcher, such that the quasi-ballistic course of the missile will lead essentially to the target caught by the reconnaissance system.
According to the invention it is further preferred that, during the target approaching phase, once the target has been recognized and the missile homing head has locked on to it, the homing angle of the missile homing head is reduced and minimized largely together with a corresponding increase in resolution to recognize details of the combat target transmitted to the missile by the reconnaissance system, such as the engine area of a tank and the like.
Moreover, it may be provided according to the invention that the reconnaissance system passes on information picked up to a transmitter station and that the missile is guided to the target via the transmitter station.
Finally, it is also proposed, according to the invention that the missile supplies information to the transmitter station and this information is processed in the transmitter station, together with the data transmitted by the reconnaissance system for guidance of the missile.
The invention thus is based on the surprising finding that missiles conventionally operating autonomously by means of a homing head can be remote controlled, in addition, by a reconnaissance system and data can be transmitted permanently to the missile by the external reconnaissance system in order to continuously optimize the aiming direction of the missile during the homing phase so that, in principle, the result is a combination of two conventional homing methods, whereby the elimination of errors is greatly enhanced and the resulting hit rate far superior over the state of the art. The data link according to the invention between the missile and the reconnaissance system thus makes it possible to transmit timely target data 'to the missile, while in flight already, either directly or indirectly through a transmitter station, so as to increase the combat effectiveness.
BRIEF DESCRIPTION OF THE DRAWING
Further features and advantages of the invention may be gathered from the following description which specifies an embodiment of the invention in greater detail, with reference to a diagrammatic drawing. The drawing which consists of a single figure is a perspective view of a combat scenario.
DETAILED DESCRIPTION OF THE INVENTION
The figure illustrates a combat scenario where a tank 1 is to be attacked by a missile 2. To this end, a helicopter 3 flies over the possible target area, scanning the same within a cone of sight I. As soon as the helicopter 3 has recognized the tank 1 as the target, in respect of the type of target, location of target, and target movement, the helicopter 3 transmits signals to a launch means (not shown) of the missile 2 at starting point A. These signals may be transmitted by the helicopter 3 to a transmitter station 4 and then to the launch means and they contain information which permits the missile 2 to be brought from the starting point A into a quasi-ballistic course a which leads essentially to the tank 1 detected by the helicopter 3..
During the homing phase the missile 2 flies essentially horizontally and at supersonic speed. At this time, during the homing phase, the homing angle of the homing head, i.e. the cone of sight b of the guided missile 2 is optimized continuously in response to the target data transmitted by the helicopter 3 to the missile 2 with a view to recognizing the tank 1. The course c of the center of the cone of sight b of the missile 2 is shown in exemplary fashion in the figure, such as it results from the remote guidance by means of the data sensed, processed and transmitted by the helicopter 3.
After the homing head of the missile 2 has recognized the tank 1 and the missile 2 has locked on to the tank 1, i.e. during the target approach phase, the angle of the cone of sight b of the guided missile 2 is reduced continuously in response to details of the tank 1 to be attacked which were sensed by the helicopter 3. This serves to increase the resolution within the cone of sight b of the missile 2 whereby the aiming accuracy is increased as well. In this manner it is possible, for instance, to aim directly at the engine area of the tank 1 so that the effective charge of the missile 1 will have its effect in the engine range, as symbolized in the figure.
The features of the invention disclosed in the above specification, in the drawing, as well as in the claims may be essential to the implementation of the invention in its various embodiments, both individually and in any desired combination.
Claims (11)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A method of combating a target located at least near a surface, by means of a missile comprising a homing head, an effective charge, and at least one propulsive unit, wherein the missile, after having passed an essentially vertical launching phase, is deflected into an essentially horizontal cruising and homing phase during which the missile scans the terrain ahead by means of its homing head, whereupon an essentially vertically downwardly directed approaching phase follows once the target has been selected and the homing head has locked on to a recognized target, wherein an external reconnaissance system scans the target area and communicates with the missile, wherein during the homing phase following the target selection, target data pertaining to the selected target is transmitted from the reconnaissance system to the missile so that the homing angle of the missile homing head is optimized continuously in response to such target data with a view to recognizing the target.
2. The method according to claim 1, wherein the reconnaissance system is in an aircraft, a space vehicle, a drone or an orbiting satellite.
3. The method according to claim 1 or 2, wherein the reconnaissance system is in flight while scanning the target area.
4. The method according to any one of claims 1 to 3, wherein the reconnaissance system is static while scanning the target area.
5. The method according to any one of claims 1 to 4, wherein the launching phase is performed after the target had been selected.
6. The method according to claim 5, wherein the target is selected based on one or more of the following parameters: type of target; location of target;
and target movement.
and target movement.
7. The method according to any one of claims 1 to 6, wherein during the approaching phase the homing angle of the missile homing head is reduced and minimized largely together with a corresponding increase in resolution, to recognize details of the target transmitted to the missile by the reconnaissance system.
8. The method according to claim 7, wherein the detail of the target is an engine area of a tank.
9. The method according to any one of claims 1 to 8, wherein the target data transmitted from the reconnaissance system to the missile travels through a transmitter station.
10. The method according to claim 9, wherein the missile is guided to the target via the transmitter station.
11. The method according to claim 9 or 10, wherein the transmitter station receives information from the missile and processes such received information, together with target data received from the reconnaissance system and produces therefrom a guidance signal that is transmitted to the missile.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19828644A DE19828644C2 (en) | 1998-06-26 | 1998-06-26 | Process for remote control of ground-based and / or ground-based targets |
| DE19828644.9 | 1998-06-26 | ||
| PCT/DE1999/001862 WO2000000779A1 (en) | 1998-06-26 | 1999-06-25 | Method for remote controlled combat of near-surface and/or surface targets |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2334373A1 CA2334373A1 (en) | 2000-01-06 |
| CA2334373C true CA2334373C (en) | 2006-03-14 |
Family
ID=7872185
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002334373A Expired - Fee Related CA2334373C (en) | 1998-06-26 | 1999-06-25 | Method of remote controlled combat of near-surface and/or surface-bound targets |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US6455828B1 (en) |
| EP (1) | EP1090263B1 (en) |
| JP (1) | JP4262889B2 (en) |
| CA (1) | CA2334373C (en) |
| DE (2) | DE19828644C2 (en) |
| WO (1) | WO2000000779A1 (en) |
Families Citing this family (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002522421A (en) | 1998-08-04 | 2002-07-23 | アストラゼネカ アクチボラグ | Amide derivatives useful as inhibitors of cytokine production |
| IL138831A (en) * | 2000-10-03 | 2007-07-24 | Rafael Advanced Defense Sys | Gaze-actuated information system |
| DE10060090A1 (en) * | 2000-12-02 | 2002-06-13 | Lfk Gmbh | Procedure for handing over a target to a missile |
| JP4087104B2 (en) * | 2001-11-20 | 2008-05-21 | シャープ株式会社 | Group robot system |
| IL163450A (en) * | 2004-08-10 | 2009-12-24 | Rafael Advanced Defense Sys | Guided missile with distributed guidance mechanism |
| US7328644B2 (en) * | 2005-07-12 | 2008-02-12 | Scv Quality Solutions, Llc | System and method for intercepting a projectile |
| ES2619597T3 (en) * | 2005-09-23 | 2017-06-26 | Saab Ab | Missile Guidance System |
| DE102005054776A1 (en) * | 2005-11-15 | 2007-05-24 | Lfk-Lenkflugkörpersysteme Gmbh | Steering method for missiles |
| DE102007021112B3 (en) * | 2007-05-05 | 2008-07-31 | Lfk-Lenkflugkörpersysteme Gmbh | Reconnaissance radius enlarging method for combat helicopter, involves carrying unmanned reconnaissance drones in combat helicopters, and launching reconnaissance drones into operational area from flying combat helicopters |
| DE102010022728A1 (en) * | 2010-06-04 | 2011-12-08 | Diehl Bgt Defence Gmbh & Co. Kg | Method for instructing a missile on a target |
| US11313650B2 (en) * | 2012-03-02 | 2022-04-26 | Northrop Grumman Systems Corporation | Methods and apparatuses for aerial interception of aerial threats |
| US11947349B2 (en) | 2012-03-02 | 2024-04-02 | Northrop Grumman Systems Corporation | Methods and apparatuses for engagement management of aerial threats |
| DE102012218746A1 (en) * | 2012-10-15 | 2014-04-17 | Cassidian Airborne Solutions Gmbh | Weapon composite system and method of controlling the same |
| FR3010180B1 (en) * | 2013-09-04 | 2016-10-21 | Dcns | METHOD FOR USING A MISSILE AND ASSOCIATED MISSILE EMPLOYMENT SYSTEM |
| DE102014007456B3 (en) * | 2014-05-21 | 2015-01-22 | Mbda Deutschland Gmbh | Modular guided missile system |
| US11112787B2 (en) | 2015-03-25 | 2021-09-07 | Aerovironment, Inc. | Machine to machine targeting maintaining positive identification |
| KR101745853B1 (en) * | 2017-03-03 | 2017-06-09 | 국방과학연구소 | Automatic target designation device using space virtual image and method thereof |
| CN112461059B (en) * | 2020-10-30 | 2022-12-13 | 彩虹无人机科技有限公司 | Image homing guided missile ground launching method |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3131089C2 (en) * | 1981-08-06 | 1985-06-13 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Reconnaissance and fire control system |
| DE3145374C2 (en) * | 1981-11-14 | 1984-12-20 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Method and device for combating ground targets by means of missiles |
| DE3303763A1 (en) * | 1983-02-04 | 1984-08-09 | Diehl GmbH & Co, 8500 Nürnberg | METHOD FOR TARGETING A PROJECTILE AND DETERMINING ITS BALLISTIC FLIGHT TRACK AND DEVICES FOR EXECUTING THE METHOD |
| GB2148465B (en) * | 1983-10-20 | 1987-05-28 | Nader Dadabhoy Daroga | Missile control systems |
| US5379966A (en) * | 1986-02-03 | 1995-01-10 | Loral Vought Systems Corporation | Weapon guidance system (AER-716B) |
| DE3715909C1 (en) * | 1987-05-13 | 1998-05-14 | Daimler Benz Aerospace Ag | Target seeking method for missile |
| US5131602A (en) * | 1990-06-13 | 1992-07-21 | Linick James M | Apparatus and method for remote guidance of cannon-launched projectiles |
| DE4132233C2 (en) * | 1990-11-22 | 2003-03-06 | Rheinmetall W & M Gmbh | Antitank missile system |
| US5260709A (en) * | 1991-12-19 | 1993-11-09 | Hughes Aircraft Company | Autonomous precision weapon delivery using synthetic array radar |
| US5186414A (en) * | 1992-04-20 | 1993-02-16 | The United States Of America As Represented By The Secretary Of The Navy | Hybrid data link |
| DE4217185C1 (en) | 1992-05-23 | 1993-10-21 | Deutsche Aerospace | Anti-tank projectile - has detaching head to accelerate ahead and trigger defence systems, to give clear zone for projectile to strike |
| DE4223531C2 (en) | 1992-07-17 | 1994-10-20 | Bodenseewerk Geraetetech | Device for guiding a powered missile shot from a launcher |
| DE4416885C2 (en) | 1994-05-13 | 1998-04-09 | Daimler Benz Aerospace Ag | Missile guidance device |
| US5458041A (en) * | 1994-08-02 | 1995-10-17 | Northrop Grumman Corporation | Air defense destruction missile weapon system |
| DE19546017C1 (en) * | 1995-12-09 | 1997-04-24 | Daimler Benz Aerospace Ag | Missile weapon system |
| IL117589A (en) * | 1996-03-21 | 2001-10-31 | Israel Aircraft Ind Ltd | Guidance system for air-to-air missiles |
| DE19626075C1 (en) | 1996-06-28 | 1998-01-15 | Buck Chem Tech Werke | Missiles to combat moving targets |
| US5917442A (en) * | 1998-01-22 | 1999-06-29 | Raytheon Company | Missile guidance system |
| US6318667B1 (en) * | 1999-03-31 | 2001-11-20 | Raymond C. Morton | Stealth weapon systems |
-
1998
- 1998-06-26 DE DE19828644A patent/DE19828644C2/en not_active Expired - Fee Related
-
1999
- 1999-06-25 EP EP99927726A patent/EP1090263B1/en not_active Expired - Lifetime
- 1999-06-25 JP JP2000557108A patent/JP4262889B2/en not_active Expired - Fee Related
- 1999-06-25 CA CA002334373A patent/CA2334373C/en not_active Expired - Fee Related
- 1999-06-25 DE DE59901512T patent/DE59901512D1/en not_active Expired - Lifetime
- 1999-06-25 US US09/720,426 patent/US6455828B1/en not_active Expired - Lifetime
- 1999-06-25 WO PCT/DE1999/001862 patent/WO2000000779A1/en active IP Right Grant
Also Published As
| Publication number | Publication date |
|---|---|
| JP2002519619A (en) | 2002-07-02 |
| WO2000000779B1 (en) | 2000-04-27 |
| WO2000000779A1 (en) | 2000-01-06 |
| EP1090263A1 (en) | 2001-04-11 |
| CA2334373A1 (en) | 2000-01-06 |
| DE19828644C2 (en) | 2001-12-06 |
| US6455828B1 (en) | 2002-09-24 |
| DE19828644A1 (en) | 2000-01-20 |
| JP4262889B2 (en) | 2009-05-13 |
| EP1090263B1 (en) | 2002-05-22 |
| DE59901512D1 (en) | 2002-06-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20140625 |