CA2437374C - Apparatus for combating targets - Google Patents
Apparatus for combating targets Download PDFInfo
- Publication number
- CA2437374C CA2437374C CA2437374A CA2437374A CA2437374C CA 2437374 C CA2437374 C CA 2437374C CA 2437374 A CA2437374 A CA 2437374A CA 2437374 A CA2437374 A CA 2437374A CA 2437374 C CA2437374 C CA 2437374C
- Authority
- CA
- Canada
- Prior art keywords
- target
- missile
- sensor
- homing head
- 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.)
- Expired - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G5/00—Elevating or traversing control systems for guns
- F41G5/12—Elevating or traversing control systems for guns acoustically influenced
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G5/00—Elevating or traversing control systems for guns
- F41G5/08—Ground-based tracking-systems for aerial targets
-
- 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
- F41G7/2253—Passive homing systems, i.e. comprising a receiver and do not requiring an active illumination of the target
-
- 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
- F41G7/2293—Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Electromagnetism (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Radar Systems Or Details Thereof (AREA)
- Measurement Of Velocity Or Position Using Acoustic Or Ultrasonic Waves (AREA)
- Catching Or Destruction (AREA)
- Soil Working Implements (AREA)
- Plasma Technology (AREA)
Abstract
The invention relates to an apparatus for combating targets (2) within an area to be monitored, comprising a ground-installed aimable launching device (7), a target acquisition device (5) connected to the launching device (7) and at least one missile (14) launchable from the launching device (7). In order to ensure a short reaction time of the apparatus (1) between reception of acoustic target-characteristic signals and launching of the missile (14), and to render the position of the launching and target acquisition devices (7, 5) of such an apparatus (1) incapable of being located, the invention proposes a target acquisition device (5) which determines the target direction of the target (2) to be combated solely by means of passive sensors (10). The missile (14) has a target-seeking homing head (15), so that after the launch in the target direction said homing head (15) autonomously seeks and destroys -the target (2), e.g. by means of an infrared sensor.
Description
DESCRIPTION
Apparatus for combating targets The invention relates to an apparatus for combating targets within an area to be monitored, comprising a ground-installed aimable launching device, a target acquisition device connected to the launching device and at least one missile launchable from the launching device.
It is known, for example, from DE 31 40 728 C2 to carry out a precise fixing of the location of the target by means of a combination of passive and active sensors in order to combat tanks. The passive sensors (e.g. acoustic sensors) are used for determining the target direction and the active sensors are used for determining the target velocity. The trajectory of the target and therefore the launching time of the missile can be determined from the change in the target direction and target velocity.
A disadvantage, among others, of these known devices is that a relatively large amount of time is required for determining the trajectory of the target and the subsequent aiming of the launching device of the missile, so that the reaction time of the apparatus from receiving the acoustic, target-characteristic signals to launching the missile for combating very fast-moving targets, such as helicopters, is too long. Moreover, the use of the active sensors of the target acquisition device gives rise to the danger that the enemy can locate and destroy the ground-installed launching device.
It is the object of the invention to specify an apparatus of the above-mentioned type which is constructed in a simple and low-cost manner, has a short reaction time and the launching and target acquisition devices of which cannot be located by the use of corresponding sensors.
The invention is based substantially on the idea that the apparatus includes a target acquisition device which utilises only passive sensors and which determines only the target direction but not the trajectory of the target to be combated before the launching of the associated missile, and that the missile of the apparatus has a homing head which, after launching of the missile in the direction of the target, autonomously seeks and then destroys the target (e.g. by means of an infrared sensor). A locatable connection between the missile and the launching device or the target acquisition device does not exist during the flight phase of the missile.
The apparatus according to the invention has the advantage that, being a relatively small, autonomous unit, it can be installed, e.g. manually, within an area to be monitored, and monitors the-corresponding spatial area for a relatively long time. For this purpose the apparatus is provided with e.g. an acoustic alerting sensor. The target acquisition device then carries out a continuous frequency analysis of the acoustic signals received. As soon as the acoustic frequency spectrum indicates a target to be combated, the directional sensor is activated and the bearing angle of the target is determined. The launching device is aligned in the direction of bearing and the missile (e.g. a "Stinger" rocket) is launched. The infrared sensor of the rocket then seeks a heat source (target) in the area segment determined by the acoustic direction-finding, and the rocket is guided to the target by means of a suitable steering device.
In an advantageous embodiment of the invention the acoustic directional sensor includes at least four microphones arranged in each case at the corner-points of a tetrahedron.
The alerting sensor is preferably one of the microphones of the directional sensor.
3a In accordance with this invention there is provided an apparatus for combating targets within an area to be monitored, comprising a ground-installed aimable launching device, a target acquisition device connected to the launching device and at least one missile launchable from the launching device, with the features:
a) the missile has a target-seeking homing head; b) the target acquisition device includes an electronic evaluation device, a passive, acoustic alerting sensor connected to the evaluation device and a passive acoustic directional sensor for determining the target direction connected to the evaluation device; c) the individual assemblies of the apparatus are in eff ective connection with one another such that, after reception of target-characteristic signals by means of the alerting sensor, the electronic evaluation device activates the directional sensor, determines signal values for aligning the launching device in the target direction and activates the corresponding positioning drives of the aiming arrangement of the launching device, and that the missile is then launched in the target direction and autonomously takes over the target-finding function with its homing head.
3b Further details and advantages of the invention will be apparent from the following embodiments which are elucidated with reference to Figures, in which:
Fig. 1 is a schematic side few of an apparatus according to the invention for combating airborne targets;
Fig. 2 is a plan view of the apparatus illustrated in Fig. 1, and Fig. 3 is a block diagram of a target acquisition device.
In Figs. 1 and 2 an apparatus according to the invention for combating helicopters 2 within a predefined area to be monitored is denoted by reference numeral 1. The apparatus 1 consists of a housing 3 in which an energy supply unit and an electronic evaluation device 4 of a target acquisition device 5 are housed (cf. also Fig. 3).
Adjoining the top of the housing 3 is an aiming arrangement 6 by means of which a launching device 7 can be aimed in azimuth and in elevation.
Arranged at the sides of the housing 3 are three legs 8 supported on the ground 9, to which three microphones 10 of an acoustic directional sensor 11 are attached. A fourth microphone 10 of the acoustic directional sensor 11 is arranged on the aiming arrangement 6, so that the four microphones 10 of the directional sensor 11 form the corner-points of a tetrahedron. All the microphones 10 of the directional sensor 11 are connected to the electronic evaluation device 4 via electrical lines 12. The evaluation device 4 contains a microprocessor 13.
At least one missile 14 which is provided with a target-seeking IR homing head 15 and a steering device (not illustrated) is arranged in the launching device 7.
The operation of the apparatus according to the invention is explained in more detail below.
After the apparatus 1 has been installed it is switched on.
The device 1 is then initially in a so-called listening mode, i.e. only an acoustic alerting circuit connected to only one of the microphones 10 is activated. The electronic evaluation device 4 continuously performs a Fast Fourier Transform (FFT) of the acoustic signal being measured by the microphone 10. As soon as the frequency spectrum resembles the acoustic signature of a helicopter the target acquisition device is switched to the so-called direction-finding mode.
In the direction-finding mode all four microphones 10 are 5 activated and the electronic evaluation device 4 determines the spatial direction to the target 2. For this purpose the acoustic signals coming from the target 2 are measured in a time-offset manner by the microphones 10. The spatial direction of the target 2 is then determined from this 1-0 phase displacement by means of the microprocessor 13.
As soon as the direction-finding operation is stable and the frequency spectrum has been identified as the acoustic signature of a helicopter, the launching device 7 is aligned in azimuth and in elevation by means of the aiming arrangement 6 in such a way that the missile 14 is aligned in the direction of the acoustic direction-finding. At the same time the IR sensor of the homing head 15 of the missile 14 is cooled to operating temperature, a friend-foe identification inquiry is carried out and, in the case of an enemy, the missile 14 is launched.
The missile 14 is accelerated to supersonic velocity and the IR homing head 15 seeks a target (heat source) in the area segment which has been determined by means of the acoustic direction-finding. After acquiring the target 2 the missile 14 is guided to the target by means of the IR
homing head 15 and the steering device.
Self-evidently, the invention is not restricted to the above-described embodiment. For example, the homing head of the missile can also be a radar homing head.
Moreover, if a passive IR homing head is used it can be provided that the missile is launched only if the homing head has already detected the target in the area segment defined by the acoustic direction-finding before the 5 launching of the missile.
List of reference numerals 1 Apparatus 2 Target, helicopter 3 Housing 4 (Electronic) evaluation device 5 Target acquisition device 6 Aiming arrangement 7 Launching device 8 Leg 9 Ground 10 Sensor, microphone, alerting sensor 11 Directional sensor 12 Electrical line 13 Microprocessor 14 Missile 15 Homing head
Apparatus for combating targets The invention relates to an apparatus for combating targets within an area to be monitored, comprising a ground-installed aimable launching device, a target acquisition device connected to the launching device and at least one missile launchable from the launching device.
It is known, for example, from DE 31 40 728 C2 to carry out a precise fixing of the location of the target by means of a combination of passive and active sensors in order to combat tanks. The passive sensors (e.g. acoustic sensors) are used for determining the target direction and the active sensors are used for determining the target velocity. The trajectory of the target and therefore the launching time of the missile can be determined from the change in the target direction and target velocity.
A disadvantage, among others, of these known devices is that a relatively large amount of time is required for determining the trajectory of the target and the subsequent aiming of the launching device of the missile, so that the reaction time of the apparatus from receiving the acoustic, target-characteristic signals to launching the missile for combating very fast-moving targets, such as helicopters, is too long. Moreover, the use of the active sensors of the target acquisition device gives rise to the danger that the enemy can locate and destroy the ground-installed launching device.
It is the object of the invention to specify an apparatus of the above-mentioned type which is constructed in a simple and low-cost manner, has a short reaction time and the launching and target acquisition devices of which cannot be located by the use of corresponding sensors.
The invention is based substantially on the idea that the apparatus includes a target acquisition device which utilises only passive sensors and which determines only the target direction but not the trajectory of the target to be combated before the launching of the associated missile, and that the missile of the apparatus has a homing head which, after launching of the missile in the direction of the target, autonomously seeks and then destroys the target (e.g. by means of an infrared sensor). A locatable connection between the missile and the launching device or the target acquisition device does not exist during the flight phase of the missile.
The apparatus according to the invention has the advantage that, being a relatively small, autonomous unit, it can be installed, e.g. manually, within an area to be monitored, and monitors the-corresponding spatial area for a relatively long time. For this purpose the apparatus is provided with e.g. an acoustic alerting sensor. The target acquisition device then carries out a continuous frequency analysis of the acoustic signals received. As soon as the acoustic frequency spectrum indicates a target to be combated, the directional sensor is activated and the bearing angle of the target is determined. The launching device is aligned in the direction of bearing and the missile (e.g. a "Stinger" rocket) is launched. The infrared sensor of the rocket then seeks a heat source (target) in the area segment determined by the acoustic direction-finding, and the rocket is guided to the target by means of a suitable steering device.
In an advantageous embodiment of the invention the acoustic directional sensor includes at least four microphones arranged in each case at the corner-points of a tetrahedron.
The alerting sensor is preferably one of the microphones of the directional sensor.
3a In accordance with this invention there is provided an apparatus for combating targets within an area to be monitored, comprising a ground-installed aimable launching device, a target acquisition device connected to the launching device and at least one missile launchable from the launching device, with the features:
a) the missile has a target-seeking homing head; b) the target acquisition device includes an electronic evaluation device, a passive, acoustic alerting sensor connected to the evaluation device and a passive acoustic directional sensor for determining the target direction connected to the evaluation device; c) the individual assemblies of the apparatus are in eff ective connection with one another such that, after reception of target-characteristic signals by means of the alerting sensor, the electronic evaluation device activates the directional sensor, determines signal values for aligning the launching device in the target direction and activates the corresponding positioning drives of the aiming arrangement of the launching device, and that the missile is then launched in the target direction and autonomously takes over the target-finding function with its homing head.
3b Further details and advantages of the invention will be apparent from the following embodiments which are elucidated with reference to Figures, in which:
Fig. 1 is a schematic side few of an apparatus according to the invention for combating airborne targets;
Fig. 2 is a plan view of the apparatus illustrated in Fig. 1, and Fig. 3 is a block diagram of a target acquisition device.
In Figs. 1 and 2 an apparatus according to the invention for combating helicopters 2 within a predefined area to be monitored is denoted by reference numeral 1. The apparatus 1 consists of a housing 3 in which an energy supply unit and an electronic evaluation device 4 of a target acquisition device 5 are housed (cf. also Fig. 3).
Adjoining the top of the housing 3 is an aiming arrangement 6 by means of which a launching device 7 can be aimed in azimuth and in elevation.
Arranged at the sides of the housing 3 are three legs 8 supported on the ground 9, to which three microphones 10 of an acoustic directional sensor 11 are attached. A fourth microphone 10 of the acoustic directional sensor 11 is arranged on the aiming arrangement 6, so that the four microphones 10 of the directional sensor 11 form the corner-points of a tetrahedron. All the microphones 10 of the directional sensor 11 are connected to the electronic evaluation device 4 via electrical lines 12. The evaluation device 4 contains a microprocessor 13.
At least one missile 14 which is provided with a target-seeking IR homing head 15 and a steering device (not illustrated) is arranged in the launching device 7.
The operation of the apparatus according to the invention is explained in more detail below.
After the apparatus 1 has been installed it is switched on.
The device 1 is then initially in a so-called listening mode, i.e. only an acoustic alerting circuit connected to only one of the microphones 10 is activated. The electronic evaluation device 4 continuously performs a Fast Fourier Transform (FFT) of the acoustic signal being measured by the microphone 10. As soon as the frequency spectrum resembles the acoustic signature of a helicopter the target acquisition device is switched to the so-called direction-finding mode.
In the direction-finding mode all four microphones 10 are 5 activated and the electronic evaluation device 4 determines the spatial direction to the target 2. For this purpose the acoustic signals coming from the target 2 are measured in a time-offset manner by the microphones 10. The spatial direction of the target 2 is then determined from this 1-0 phase displacement by means of the microprocessor 13.
As soon as the direction-finding operation is stable and the frequency spectrum has been identified as the acoustic signature of a helicopter, the launching device 7 is aligned in azimuth and in elevation by means of the aiming arrangement 6 in such a way that the missile 14 is aligned in the direction of the acoustic direction-finding. At the same time the IR sensor of the homing head 15 of the missile 14 is cooled to operating temperature, a friend-foe identification inquiry is carried out and, in the case of an enemy, the missile 14 is launched.
The missile 14 is accelerated to supersonic velocity and the IR homing head 15 seeks a target (heat source) in the area segment which has been determined by means of the acoustic direction-finding. After acquiring the target 2 the missile 14 is guided to the target by means of the IR
homing head 15 and the steering device.
Self-evidently, the invention is not restricted to the above-described embodiment. For example, the homing head of the missile can also be a radar homing head.
Moreover, if a passive IR homing head is used it can be provided that the missile is launched only if the homing head has already detected the target in the area segment defined by the acoustic direction-finding before the 5 launching of the missile.
List of reference numerals 1 Apparatus 2 Target, helicopter 3 Housing 4 (Electronic) evaluation device 5 Target acquisition device 6 Aiming arrangement 7 Launching device 8 Leg 9 Ground 10 Sensor, microphone, alerting sensor 11 Directional sensor 12 Electrical line 13 Microprocessor 14 Missile 15 Homing head
Claims (6)
1. An apparatus for combating targets (2) within an area to be monitored, comprising a ground-installed aimable launching device (7), a target acquisition device (5) connected to the launching device (7) and at least one missile (14) launchable from the launching device (7), with the features:
a) the missile (14) has a target-seeking homing head (15);
b) the target acquisition device (5) includes an electronic evaluation device (4), a passive, acoustic alerting sensor (10) connected to the evaluation device (4) and a passive acoustic directional sensor (11) for determining the target direction connected to the evaluation device (4);
c) the individual assemblies of the apparatus (1) are in effective connection with one another such that, after reception of target-characteristic signals by means of the alerting sensor (10), the electronic evaluation device (4) activates the directional sensor (11), determines signal values for aligning the launching device in the target direction and activates the corresponding positioning drives of the aiming arrangement (6) of the launching device (7), and that the missile (14) is then launched in the target direction and autonomously takes over the target-finding function with its homing head (15).
a) the missile (14) has a target-seeking homing head (15);
b) the target acquisition device (5) includes an electronic evaluation device (4), a passive, acoustic alerting sensor (10) connected to the evaluation device (4) and a passive acoustic directional sensor (11) for determining the target direction connected to the evaluation device (4);
c) the individual assemblies of the apparatus (1) are in effective connection with one another such that, after reception of target-characteristic signals by means of the alerting sensor (10), the electronic evaluation device (4) activates the directional sensor (11), determines signal values for aligning the launching device in the target direction and activates the corresponding positioning drives of the aiming arrangement (6) of the launching device (7), and that the missile (14) is then launched in the target direction and autonomously takes over the target-finding function with its homing head (15).
2. Apparatus according to Claim 1, characterised in teat the acoustic directional sensor (11) includes at least four microphones (10) arranged in each case at the corner-points of a tetrahedron.
3. Apparatus according to Claim 1 or 2, characterised in that the alerting sensor (10) is one of the microphones of the directional sensor (11).
4. Apparatus according to any one of claims 1 to 3, characterised in that the electronic evaluation device (4) includes a microprocessor (13) for carrying out a Fourier analysis of the measured sound signals of the alerting sensor (10), and in that these signal values are compared to signal values characteristic of the target (2) which are stored in the evaluation unit (4).
5. Apparatus according to any one of claims 1 to 4, characterised in that the homing head (15) of the missile (14) is an infrared homing head with a passive infrared sensor.
6. Apparatus according to any one of claims 1 to 4, characterised in that the homing head (15) of the missile (14) is a radar homing head.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10240314.7 | 2002-08-31 | ||
| DE10240314A DE10240314A1 (en) | 2002-08-31 | 2002-08-31 | Target combat device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2437374A1 CA2437374A1 (en) | 2004-02-29 |
| CA2437374C true CA2437374C (en) | 2010-10-19 |
Family
ID=27675207
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2437374A Expired - Fee Related CA2437374C (en) | 2002-08-31 | 2003-08-14 | Apparatus for combating targets |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP1394495B1 (en) |
| CA (1) | CA2437374C (en) |
| DE (2) | DE10240314A1 (en) |
| IL (1) | IL157599A0 (en) |
| NO (1) | NO327291B1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL228789A (en) | 2013-10-08 | 2016-03-31 | Israel Aerospace Ind Ltd | Missile system including ads-b receiver |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2678060B1 (en) * | 1976-08-03 | 1994-05-20 | Etat Francais Delegue Armement | METHOD AND APPARATUS FOR SELECTIVE FIRE OF HORIZONTAL ACTION WEAPON. |
| DE3140728C2 (en) * | 1981-10-14 | 1985-02-07 | Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn | Device for combating targets, such as tanks or the like. |
| FR2728676B1 (en) * | 1982-05-11 | 1997-03-21 | France Etat | HORIZONTAL-ACTION PYROTECHNIC CHARGE FIRE CONTROL SYSTEM |
| DE3840732A1 (en) * | 1988-12-02 | 1990-06-07 | Krupp Atlas Elektronik Gmbh | WAKE-UP DEVICE RESPECTING CHAIN VEHICLES |
| FR2641872B1 (en) * | 1989-01-18 | 1991-10-11 | Clausin Jacques | SYSTEM FOR LOCATING HIDDEN HELICOPTERS BEHIND A PLANT SCREEN |
| DE19906970C2 (en) * | 1999-02-19 | 2003-03-27 | Rheinmetall W & M Gmbh | reconnaissance probe |
-
2002
- 2002-08-31 DE DE10240314A patent/DE10240314A1/en not_active Withdrawn
-
2003
- 2003-06-25 DE DE50301073T patent/DE50301073D1/en not_active Expired - Lifetime
- 2003-06-25 EP EP03014218A patent/EP1394495B1/en not_active Expired - Lifetime
- 2003-06-27 NO NO20032967A patent/NO327291B1/en not_active IP Right Cessation
- 2003-08-14 CA CA2437374A patent/CA2437374C/en not_active Expired - Fee Related
- 2003-08-26 IL IL15759903A patent/IL157599A0/en unknown
Also Published As
| Publication number | Publication date |
|---|---|
| CA2437374A1 (en) | 2004-02-29 |
| IL157599A0 (en) | 2004-03-28 |
| DE10240314A1 (en) | 2004-03-11 |
| DE50301073D1 (en) | 2005-10-06 |
| NO20032967D0 (en) | 2003-06-27 |
| EP1394495B1 (en) | 2005-08-31 |
| EP1394495A1 (en) | 2004-03-03 |
| NO327291B1 (en) | 2009-06-02 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20160815 |