GB2136097A - Target-tracking Interception Control Systems - Google Patents
Target-tracking Interception Control Systems Download PDFInfo
- Publication number
- GB2136097A GB2136097A GB07943942A GB7943942A GB2136097A GB 2136097 A GB2136097 A GB 2136097A GB 07943942 A GB07943942 A GB 07943942A GB 7943942 A GB7943942 A GB 7943942A GB 2136097 A GB2136097 A GB 2136097A
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- United Kingdom
- Prior art keywords
- computer
- target
- lead
- tracking
- follow
- 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
Links
- 238000001514 detection method Methods 0.000 claims abstract description 9
- 238000004364 calculation method Methods 0.000 claims description 12
- 238000000034 method Methods 0.000 claims description 6
- 230000035484 reaction time Effects 0.000 claims description 3
- 238000003745 diagnosis Methods 0.000 claims description 2
- 101100323274 Arabidopsis thaliana ANR1 gene Proteins 0.000 abstract description 5
- 238000012544 monitoring process Methods 0.000 abstract 1
- 230000001133 acceleration Effects 0.000 description 6
- 238000012937 correction Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000006978 adaptation Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000009466 transformation Effects 0.000 description 3
- 101100323290 Saccharomyces cerevisiae (strain ATCC 204508 / S288c) ANR2 gene Proteins 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000013213 extrapolation Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
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- 101000803389 Viola hederacea Root cyclotide 1 Proteins 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000004069 differentiation Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
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- 238000000926 separation method Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G5/00—Elevating or traversing control systems for guns
- F41G5/14—Elevating or traversing control systems for guns for vehicle-borne guns
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
In a target-tracking interception control system, in particular for mobile anti-aircraft defence systems, fire or launch control is effected from information derived from a plurality of target sensors, 1, 3, 4, 6, which effect detection target tracking, and follow-up for controlling one or more weapon systems. The weapon follow-up is carried out taking into account a lead-angle value that is calculated by one or more lead-angle computer units 7 using the target tracking data provided by respective computer units, ANR1 to ANRn, allotted to the respective sensors. In order to decentralise the system, the computer units are designed as individual system components linked by highways, which are all controlled by an operating mode computer, 5. The follow-up computer units and the lead-angle computer units can be coordinated in respect of various functions by means of the operating mode computer, and extra computer units may be included to improve reliability and facilitate servicing and system monitoring. <IMAGE>
Description
SPECIFICATION
Target-Tracking Interception Control Systems
The invention relates to target-tracking interception systems for weapon fire or launch control, for example in mobile anti-aircraft defence systems, sensors being provided for target detection and for target tracking, together with follow-up devices for movement control of the sensors and weapon system or systems. The weapon follow-up control is carried out taking into account a lead-angle value, the target tracking, follow-up control of the sensors and of the weapons, together with the calculation of the lead-angle each being effected by computer means.
For the fire or launch control of an anti-aircraft defence system, it is known to combine a search radar, an optical sensor device, and a tracking radar with a computer for target detection, target tracking and weapon control, as is described, for example, in Flugwehr und technik, 1957, parts 10 and 11.
The necessary processing of the signals from the sensors, for vectoring, target tracking and weapon system alignment, is carried out in a computer device which must simultaneously carry out a plurality of functions, e.g. the transformation of the measured target coordinates and the calculation of the requisite lead-angle taking into account the projectile ballistics. In order to be able to carry out all the functions of a fire control device, the computer must be assigned special significance.In addition to a main computer, for example an analogue computer which analyses the target data, calculates the target speed and projectile flight time, and determines the leadangle of the weapon and adjustment values for the directional drive of the target tracking radar, in the event that this main computer breaks down an emergency computer is normally provided to carry out an approximate lead-angle calculation.
A main computer of this kind, which is designed as a central computer, must not only undertake the pure calculating functions, but also serve for the follow-up control of the sensors and the weapon system. Such a complex intermeshing of the computer with virtually all the systems operational components disadvantageously influences the facilities for operational mode modification, servicing, and the overall reliability of the system. In addition, the accuracy of analogue computers, even of most modern design, is limited by the technology employed.
The rapid development of aircraft and helicopter design means that the design of antiaircraft defence systems must be matched in development to meet the increasing threat that is presented. For the reasons given above circuitry adaptation of the fire control devices to these increased requirements involves extensive and costly modifications.
One object of the invention is to provide improved reliability and servicing facilities in respect of fire control in a target-tracking interception control system of the type described in the introduction, and to increase its accuracy, particularly when high-speed targets are involved, and to achieve a high degree of flexibility as regards adaptation to new requirements, such as the use of new types of weapon or missile, the introduction of new operating modes, and adaptation to defeat electronic countermeasure developments.
The invention consists in a target-tracking interception control system for weapon or missile launch fire control, in which detection and target tracking and with follow-up devices for sensors and weapons, wherein the weapon follow-up is carried out taking into account a lead value, and wherein the target tracking and lead calculation are assisted by a computer, characterised in a plurality of individual digital follow-up computer units are each assigned a respective sensor or group of sensors for target and weapons detection and tracking, and further individual computer units are provided for follow-up control and weapon setting, at least one lead-angle computer unit being provided to facilitate the necessary calculations, all said computer units being governed by means of an operating mode computer so that they may be coordinated in respect of the logic-linking of input signals to form the requisite control signals in accordance with the desired mode of operation, the aliocation of the individual functions being determined by the operating mode, which also determines the required interconnection of the system components. Thus, individual digital follow-up computer units, each assigned to a sensor or group of sensors, or to tracking the weapon control setting drive means for follow-up purposes, are connected together with at least one lead-angle computer unit, and possibly to an enemy air position computer unit, which cooperate by means of the operating mode computer to provide a selected operating mode.
As a result of the consequent separation of functions, a system designed in this way can be
clearly laid out, with simple intermeshing, and thus can be programmed with a low outlay in
control switching, and easily reprogrammed in the
event of modification requests. Thus for example,
it is easily possible to modify the ballistic function
in order to match the ballistic behaviour of new
types of projectiles. Likewise, if new sensors
become available for passive target tracking, the
operating mode control can be modified in a
simple manner. A standardised interface or bus
providing a common highway system facilitates a
simple exchange of sensors and follow-up
computer units for different operating modes.
Another advantage consists in that the
autonomous control of a plurality of sensors
facilitates multiple target tracking, which is a
prerequisite of the shortening of the reaction time
in a combat involving a plurality of targets
attacking simultaneously, or in close succession.
Advantageously, a control bus enables the
operating mode computer to logic-link all the system components in dependence upon the selected operating mode.
In addition, the use of servicing programmes is facilitated, which serves to assist the diagnosis and detection of any faults during servicing, which may be performed during off-line operation if extra computer units are provided.
The invention will now be described with reference to the drawings, in which: Figure 1 is a block schematic circuit diagram of one exemplary embodiment of a system constructed in accordance with the invention, for use in anti-aircraft system mounted in a tank or armoured vehicle;
Figure 2 is a block schematic circuit diagram of a fire control computer unit for the system shown in Figure 1;
Figure 3 is a block schematic circuit diagram illustrating details of a follow-up computer unit of the system shown in Figure 1; and
Figure 4 is a block schematic circuit diagram of a further exemplary embodiment illustrating a special fire control computer arrangement for use in combats involving more than one target.
The following references have been used in the description for defining items of information.
target azimuthal angle: a;
target elevational angle: A; target range: r;
for the Cartesian coordinates: x, y, z;
speed: V;
acceleration: V;
change in acceleration: V; and any error
correction signals are prefixed by E.
The system shown in Figure 1 comprises a search radar device 1, which serves for the discovery of flying targets, provides a representation of the air position of any target on a PPI search radar screen, and provides a reduntant measurement of the target range, this target range information being fed via a search radar computer unit ANR1 to the tracking radar computer unit ANR2 and to the computer units
ANR4 and ANR5 of a periscope 6.
An IFF device 2 is provided for differentiation between friend and foe in the representation on the PPI screen of the search radar 1, and act to inhibit any fire control or launch signal in the case of friendly target being identified in the tracking position.
A tracking radar 3 serves as a sensor for tracking the target, and supplies target position data via a tracking radar computer unit ANR3 to a lead-anglecomputer 7, this provides the data x, y, z, v and v.
A laser device 4a provides a supplementary, redundant, interference-free measurement of the target range, which is supplied from its control unit 4 via the computer unit ANR2 to the tracking radar computer unit ANR3 and the computer units
ANR4 and ANR5 of the periscope 6.
Operating mode computer 5, (BR in Figure 4) provides the required logic-linking of the fire control assemblies in accordance with the selected operating mode, governing any necessary logic-linking of the input signals to form control signals, and also providing control of time flows.
The periscope 6 provides two sensors for manual or automatic optical vectoring and target tracking, supply of the target data thus obtained being fed via the computer units ANR4 or ANR5 to the lead-angle computer 7, (x, y, z, v andv) using the range information from the search radar or the tracking radar or the laser device.
The lead-angle computer unit 7 serves for the calculation of the lead-angle, and thus determines the direction for the turret and gun or weapon launcher mounting 8 for the operation by the weapon computer unit ANR6.
The functional data flow in the radar operating mode is as follows: the omni-directional search radar 1 scans the air space periodically, for example, once per second. Any detected targets are represented on the associated PPI screen to indicate azimuthal angle and range. The height is not shown. From the display on the screen the operator then decides which target, if any, is to be combated, and places a target designation mark against this target. As a result of a vectoring command, the designated target position is fed to the tracking radar device 3. By means of the autonomous follow up computer unit ANR3 of the tracking radar device, the azimuthal angle of the selected target is fed to the directional control device 4 of the tracking radar 3, which in this case represents the carrier of the antenna, and the range of the selected target is fed to the tracking radar.The height angle, which is yet to be determined, is established by the tracking radar which performs a height searching movement of its antenna, which stops as soon as the supplied target is discovered by the tracking radar. The tracking radar then automatically follows the target in respect of three coordinates of azimuthal angle, elevation angle and range, and continuously transmits the measured target position, the speed V, and the acceleration v, to the lead-angle computer unit 7. This computer unit determines the lead-angle, and thus the directions at which the turret and the weapon mounting 8 must be set, whilst taking into account influences indicated as additional information from the unit 9, which may include the starting speed of the projectile, the ambient atmospheric pressure and temperature, the wind speed and the wind direction. The periscope 6 has two eye-pieces K and R (not shown) to form a binocular type range-finder, and may be automatically controlled via its computer units
ANR4 and ANR5, or manually corrected via control sticks StkK and StkR if visual observation indicates that the automatic control data is
incorrect, in which case the necessary correction is fed back to the search and tracking radars by operation of a switch.
Figure 2 illustrates further details of the digital computer units of the system, with the lead-angle computer unit 7, the autonomous follow-up computer units ANR1 to 6, the operating mode computer 5, and an enemy air position computer unit FLR. This illustration shows that the followup computer units ANR are functionally assigned to the individual sensors formed by the search radar (range), and laser (range) tracking radar, the two periscope viewers K and R, (not shown) and the weapon mounting 8, and decentrally and autonomously cause the latter to follow-up by means of direction drive means RA (not shown) governing the tracking radar, periscope and weapon mounting. All the follow-up computer units ANR1 to 6 are connected to the lead-angle computer unit 7 via the operating mode computer 5, although some data may be fed directly from one unit to another.The operating mode computer 5, which can be freely programmed, controls the correct and prompt logic-linking of all the system components.
The principle of a follow-up computer unit wiil be explained with reference to a target tracking radar device, as shown in Figure 3. From the target position information supplied by a radar device 11 and the position of a direction finding device 12, (e.g. a search radar and a tracking radar or periscope), the target position is determined in polar co-ordinates az (target azimuthal angle), Az (target elevation angle), and rz (target range). This information is firstly transformed and fed to via respective analogue/digital converters 13 and 14 to addition stages 20 and 21. The output of the adder 20 is converted into Cartesian coordinates in a coordinate transformation stage 15, in order to avoid pseudo-accelerations which would result if performing calculation in the polar coordinate system.From the resultant target coordinates x, y and z, the target speed v,acceleration V and any change in acceleration V can be derived and any interference removed in filter stages 1 6 to 1 9.
The smoothed quantities are forwarded in
Cartesian form to the lead angle computer 7, and are also transformed back into polar values in a transformation stage 23 to form correction values in a further computer unit 24 which feeds the adder 21 so that the original polar target data and the correction values are logic-linked and, following digital/analogue conversion, are used as a control value in a target tracking radar control unit 22. Information from a further sensor can be fed in at an input E of the adder 21.
Apart from the follow-up computer units and the operating mode computer 5 (BR in Figure 4),
the most important component of the digital computer system is the lead-angle computer unit.
From the items of target information supplied by the follow-up computer unit the lead-angle
computer unit calculates the point of impact and thus the direction setting for the weapons
mounting. Together with the follow-up computer
units and the operating mode computer, the lead
angle computer unit facilitates great flexibility.
Thus, for example, by reprogramming it is
possible to exchange ballistic functions in order to facilitate the use of more modern missiles or
improved ammunition in a simple manner.
Furthermore, when passive target tracking methods are used, new operating modes can be introduced by the use of infra-red-sensitive sensors.
Various methods can be used for calculating the most probable point of impact. In addition to conventional known and used methods, such as linear and quadratic extrapolation, other conceivable methods of calculating the probability are, for example, the use of Kalman filtering and the consideration of special antiaircraft box-barrage profiles. Out-manoeuvring of the anti-aircraft defence system by adopting special flight paths by any attacking flying targets is made considerably more difficult. The use of more than one lead-angle computer unit in conjunction with the autonomous follow-up computer unit and the use of more than one leadangle calculation provides the possibility of determining the lead-angle values of more than one target, and thus provides a reduction in reaction time.In large systems comprising more than one independent weapon system, (e.g. both cannon and rocket launcher) this enhances the possibility of successful multiple target combat.
Figure 4 schematically illustrate a system specially designed for multiple target combat, and possibly indicate means for selecting the optimum lead-angle method to be adopted. In the assigned automonous follow-up computer units
ANR1 to ANRn, control signals are obtained for following-up a target by use of information provided by the input signals of respective sensors or groups of sensors S1 to Sn, and target data is supplied via an input highway E-BUS to respective lead-angle computer units VHR1 to
VHRn. The lead-angle computer units determine the most likely impact point possibly in accordance with various strategies, and transmit the associated control data via an output highway
A-BUS back to the follow-up computer units
ANRn+1 and ANRn+2 which control respective weapon systems WS 1 and WS2.The strategy used can consist, for example, of quadratic extrapolation to give anti-aircraft flight prediction.
The lead-angle computer units also continuously determine the impact probability, which depends, inter alia, upon the algorithm used, and upon the
target range, the target speed and acceleration,
and also upon the selected salvo length. This
information is indicated in suitable form to an
operator so that he is able to select the optimum
time of combat. In addition, it is possible to find
an optimum as regards impact probability, and
projectile consumption, and this data may be
used to control the salvo length. Via a control
highway S-BUS, the operating mode computer BR
logic-links all the components of the system in
accordance with one of the above described
operating modes.
By the provision of more individual computer
units than are essential to perform the allotted tasks, the operating mode computer can effectively maintain operational statas by substitution if any unit is rendered unserviceable, and computer units that are off-line at any instant can be serviced or used to monitor the overall system operation in order to provide information to the operating mode computer of any malfunction in the system. The individual units can be freely dispensed about the vehicle in the case of a mobile system, to safeguard the most important functional components.
Claims (1)
1. A target-tracking interception control system for weapon or missile launch fire control, in which detection and target tracking and with follow-up devices for sensors and weapons, wherein the weapon follow-up is carried out taking into account a lead value, and wherein the target tracking and lead calculation are assisted by a computer, characterised in a plurality of individual digital follow-up computer units are each assigned a respective sensor or group of sensors for target and weapons detection and tracking, and further individual computer units are provided for follow-up control and weapon setting, at least one lead-angle computer unit being provided to facilitate the necessary calculations, all said computer units being governed by means of an operating mode computer so that they may be coordinated in respect to the logic-linking of input signals to form the requisite control signals in accordance with the desired mode of operation, the allocation of the individual functions being determined by the operating mode, which also determines the required interconnections of the system components.
2. A system as claimed in Claim 1, in which a control highway is provided for the operating mode computer to logic-link the required circuit components of the system in dependence upon the selected operating mode, and the follow-up computer units assigned to any sensor of weapon control are themselves connected via an input highway and an output highway to at least one lead-angle computer unit.
3. A system as claimed in Claim 2, in which means are provided for a plurality of targets to be tracked simultaneously and independently, and for a lead-angle calculation to be carried out for each target, whereby the reaction time is reduced.
4. A system as claimed in any preceding claim, in which a plurality of independent weapon systems are carried, and said operating mode computer makes it possible to combat a plurality of targets simultaneously.
5. A system as claimed in any preceding claim, in which means operate throughout the whole of any target tracking process to continuously determine the impact probability and displayed this in a suitable form.
6. A system as claimed in Claim 5, in which means are provided by which the salvo length is controlled in such manner that an optimum in respect of projectile consumption and impact probability is achieved.
7. A system as claimed in any preceding claim, in which spare computer units are provided, and during off-line operation the computer units assist in servicing and fault diagnosis.
8. A system as claimed in any preceding claim,
in which additional function units of the lead-angle computer are used to reduce the possibility of any target out-manoeuvring the anti-aircraft defence.
9. A target-tracking interception control system substantially as described with reference to Figure 1 or any one or more of Figures 2 to 4 in conjunction with Figure 1.
New Claims or Amendments to Claims Filed on 3 December 1981.
Superseded Claim 1.
New Claim
1. A target-tracking interception control system for weapon or missile launch fire control, in which a plurality of individual digital follow-up computer units are each assigned a respective sensor or group of sensors for target detection and tracking, and further individual computer units are provided for follow-up control and weapon setting, at least one lead-angle computer unit being provided to facilitate the necessary calculations, all said computer units being governed by means of an operating mode computer which regulates logic-linking of input signals so that they are coordinated to form the requisite control signals in accordance with the desired mode of operation, allocates individual computer unit functions, and determines the required interconnections of the system components to provide said desired mode of operation.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE2912587A DE2912587C1 (en) | 1979-03-30 | 1979-03-30 | Fire control device, in particular for a mobile anti-aircraft system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2136097A true GB2136097A (en) | 1984-09-12 |
| GB2136097B GB2136097B (en) | 1985-06-05 |
Family
ID=6066855
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB07943942A Expired GB2136097B (en) | 1979-03-30 | 1979-12-31 | Target-tracking interception control systems |
Country Status (6)
| Country | Link |
|---|---|
| CH (1) | CH665493A5 (en) |
| DE (1) | DE2912587C1 (en) |
| FR (1) | FR2545597B1 (en) |
| GB (1) | GB2136097B (en) |
| IT (1) | IT1130705B (en) |
| NL (1) | NL184381C (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0327029A2 (en) * | 1988-02-01 | 1989-08-09 | ESG Elektronik-System- Gesellschaft mbH | Fire control device |
| EP0475043A2 (en) * | 1990-08-16 | 1992-03-18 | Hughes Aircraft Company | Missile interface unit |
| TR27095A (en) * | 1993-03-05 | 1994-10-26 | Atlas Elektronik Gmbh | Hidden. |
| EP0852326A1 (en) * | 1996-12-09 | 1998-07-08 | Oerlikon-Contraves AG | Weapon battery, specially for anti-aircraft fire units |
| GB2380244A (en) * | 2001-08-13 | 2003-04-02 | Michael Joseph Zabrana | Automated defence system |
| WO2006021813A1 (en) * | 2004-07-09 | 2006-03-02 | Bae Systems Plc | Collision avoidance system |
| US7548184B2 (en) * | 2005-06-13 | 2009-06-16 | Raytheon Company | Methods and apparatus for processing data from multiple sources |
| US7910867B1 (en) | 2006-03-03 | 2011-03-22 | Lockheed Martin Corporation | Architecture for a launch controller |
| RU2519289C1 (en) * | 2012-11-13 | 2014-06-10 | Открытое акционерное общество "Конструкторское бюро приборостроения" | Method of direct guidance of weapon to target |
| EP2645047A4 (en) * | 2010-11-22 | 2015-11-18 | Beijing Mechanical Equipment Inst | Low-altitude low-speed small target intercepting method based on firing table fitting |
| EP2623921A4 (en) * | 2010-09-29 | 2015-11-25 | Beijing Mechanical Equipment Inst | Low-altitude low-speed small target intercepting method |
| US11221195B2 (en) * | 2018-04-27 | 2022-01-11 | Rheinmetall Waffe Munition Gmbh | Method and device for protecting a vehicle against a threat |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3575085A (en) * | 1968-08-21 | 1971-04-13 | Hughes Aircraft Co | Advanced fire control system |
| US4004729A (en) * | 1975-11-07 | 1977-01-25 | Lockheed Electronics Co., Inc. | Automated fire control apparatus |
-
1979
- 1979-03-30 DE DE2912587A patent/DE2912587C1/en not_active Expired
- 1979-12-31 GB GB07943942A patent/GB2136097B/en not_active Expired
-
1980
- 1980-03-18 IT IT20720/80A patent/IT1130705B/en active
- 1980-03-27 NL NLAANVRAGE8001799,A patent/NL184381C/en not_active IP Right Cessation
- 1980-03-28 FR FR8007009A patent/FR2545597B1/en not_active Expired
-
1984
- 1984-03-26 CH CH1500/84A patent/CH665493A5/en not_active IP Right Cessation
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0327029A2 (en) * | 1988-02-01 | 1989-08-09 | ESG Elektronik-System- Gesellschaft mbH | Fire control device |
| EP0327029A3 (en) * | 1988-02-01 | 1990-12-27 | ESG Elektronik-System- Gesellschaft mbH | Fire control device |
| EP0475043A2 (en) * | 1990-08-16 | 1992-03-18 | Hughes Aircraft Company | Missile interface unit |
| EP0475043A3 (en) * | 1990-08-16 | 1992-09-23 | Hughes Aircraft Company | Missile interface unit |
| TR27095A (en) * | 1993-03-05 | 1994-10-26 | Atlas Elektronik Gmbh | Hidden. |
| FR2761463A1 (en) * | 1993-03-05 | 1998-10-02 | Atlas Elektronik Gmbh | SHOOTING DEVICE FOR ANTI-AIR DEFENSE SYSTEM, ESPECIALLY MOBILE |
| EP0852326A1 (en) * | 1996-12-09 | 1998-07-08 | Oerlikon-Contraves AG | Weapon battery, specially for anti-aircraft fire units |
| GB2380244B (en) * | 2001-08-13 | 2006-02-15 | Joseph Zabrana Michael | Automated Sound Missile and Associated Defence System |
| GB2380244A (en) * | 2001-08-13 | 2003-04-02 | Michael Joseph Zabrana | Automated defence system |
| WO2006021813A1 (en) * | 2004-07-09 | 2006-03-02 | Bae Systems Plc | Collision avoidance system |
| AU2005276241B2 (en) * | 2004-07-09 | 2010-06-10 | Bae Systems Plc | Collision avoidance system |
| US7548184B2 (en) * | 2005-06-13 | 2009-06-16 | Raytheon Company | Methods and apparatus for processing data from multiple sources |
| US7910867B1 (en) | 2006-03-03 | 2011-03-22 | Lockheed Martin Corporation | Architecture for a launch controller |
| EP2623921A4 (en) * | 2010-09-29 | 2015-11-25 | Beijing Mechanical Equipment Inst | Low-altitude low-speed small target intercepting method |
| EP2645047A4 (en) * | 2010-11-22 | 2015-11-18 | Beijing Mechanical Equipment Inst | Low-altitude low-speed small target intercepting method based on firing table fitting |
| RU2519289C1 (en) * | 2012-11-13 | 2014-06-10 | Открытое акционерное общество "Конструкторское бюро приборостроения" | Method of direct guidance of weapon to target |
| US11221195B2 (en) * | 2018-04-27 | 2022-01-11 | Rheinmetall Waffe Munition Gmbh | Method and device for protecting a vehicle against a threat |
Also Published As
| Publication number | Publication date |
|---|---|
| NL8001799A (en) | 1984-09-03 |
| NL184381C (en) | 1989-07-03 |
| GB2136097B (en) | 1985-06-05 |
| FR2545597B1 (en) | 1987-11-20 |
| DE2912587C1 (en) | 1986-05-07 |
| NL184381B (en) | 1989-02-01 |
| IT8020720A0 (en) | 1980-03-18 |
| FR2545597A1 (en) | 1984-11-09 |
| IT1130705B (en) | 1986-06-18 |
| CH665493A5 (en) | 1988-05-13 |
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