• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:

    公开号:NL9400170A
    申请号:NL9400170
    申请日:1994-02-04
    公开日:1998-11-02
    发明作者:Luitjen Ennenga
    申请人:Atlas Elektronik Gmbh；
    IPC主号:
    专利说明:

    Fire control system for especially mobile anti-aircraft systems.
    The invention relates to a fire control device for, in particular, mobile air defense systems of the type defined in the preamble of claim 1.
    In a known anti-aircraft gun armor vehicle (CH 665 493 A5), the target tracking sensor includes a tracking radar, which automatically tracks the target and provides continuously measured target data such as target position, speed and acceleration, as well as a laser rangefinder, which provides a redundant, interference-free target distance measurement. . The target data from the tracking radar and the laser rangefinder are transferred to the aiming angle computer, which determines the aiming angle according to the angle of attack and design for the tower and weapon, taking into account the day influences, such as projectile start speed, air pressure, temperature, wind strength and wind direction. Tracking radar, laser rangefinder and weapon are autonomous systems, which are linked by means of secondary computers.
    In a known fire control device of the type mentioned in the preamble for air defense systems equipped with guide projectiles such as Stinger, Mistral or the like, optical sensors such as TV camera and / or infrared camera coupled with a laser range meter are used as target follow-up sensors. Since guided missiles have their own target search heads, which generally operate on the basis of infrared, the target follow-up sensor is rigidly coupled to the elevation-pivotable firing device for the guided missiles for constructional simplification, and both are mounted together on a in azimuth rotatable platform. In this way, the line of sight of the target prosecution sensor and the longitudinal axis of the firing device for the guided missiles are always approximately parallel to each other, so that when tracking the target prosecution sensor, the control unit only matches the platform in azimuth and the firing device in elevation. with the tracking signals generated by the tracking computer.
    During the target tracking, the line of sight of the target search head of the guided missile is aligned with the axis of the firing device and thus, like the line of sight of the target tracking sensor, is aimed at the target. Before firing the shot, a target upshift takes place through the stabilized target search head of the guided missile, after which the platform is pivoted over the retention angle in azimuth and the firing device over the mount in elevation. As a result, now that the target search head of the guided missile follows the target, however, the line of sight of the target follow-up sensor and the guided missile itself are pivoted over the aiming angle, indicating the calculated point of impact, the so-called "kill point", therefore no longer aim at the goal. This resulting target loss of the target follow-up sensor when firing the guided missile has the drawback that for performing a second shot at the same target by a second firing device, which is rigidly coupled to the first firing device and always takes part in its adjustment movement, the target must first be searched again and then passed to the target tracking sensor. In many cases, the necessary, not insignificant, time required to release the second shot affects the combat strength of the anti-aircraft system. The same problem arises when, after firing the first shot, a second target has to be fought, which flies not far from the pursued target and thus is always in the field of view of the target follow-up sensor. Due to the target loss from the target follow-up sensor when firing the guided missile, the second target is also lost and must be received again.
    The object of the invention is to improve a fire control device of the type mentioned in the preamble, such that when aiming up for the release of a shot and the associated adjustment of the firing device over the required aiming angle in azimuth and elevation, target contact of the target follow-up sensor is maintained.
    This object is achieved in a fire control device of the type according to the invention indicated in the preamble of claim 1 by the features of the characterizing part of claim 1.
    In the fire control device according to the invention, the adjustments of the target sequencing sensor for the firing release of the guided missile over the retention angle and design associated with the target upshift are compensated for by an equally large, but oppositely directed pivoting of the line of sight of the target succession sensor. This is accomplished by a corresponding adjustment of the two-axis pivoting pivoting mirror mounted in the line of sight. The target follow-up sensor therefore remains switched on the target even after the shot has been released. A second shot at the target or a further shot at a second target present in the field of view of the target follow-up sensor is possible within the shortest time after the angle of formation has been formed and set up by the aiming angle computer and a new setting of the firing device. The time-consuming search and the transfer of the target to the target follow-up sensor is completely eliminated, so that the time required until the second shot is released is considerably reduced. This greatly increases the combat power of the fire control system.
    Advantageous embodiments of the fire control device according to the invention with effective further embodiments and forms of the invention are found in the further claims.
    The invention is described in more detail below with reference to an illustrative embodiment shown in the drawing. In each case, in schematic representation: Fig. 1 shows a block diagram of a fire control device for a mobile defense system with guided projectiles, Figs. 2 and 3 each show a perspective view of the construction of the fire control device in Fig. 1 at target continuation (Fig. 2) and after target upshifting (Fig. 3), Fig. 4 is a longitudinal section of a sensor housing of the fire control device of Figs. 2 and 3, and Fig. 5 is a section along line vv in Fig. 4.
    The fire control device for a mobile anti-aircraft system, which is only shown in block diagram in Fig. 1, has a platform 10 which is rotatably mounted on a vertical axis 11 and two firing devices 12, 13, so-called launcher, mounted on the platform 10, which are used for firing Guided missiles not shown here are equipped with an infrared target search head. Both firing devices 12, 13 are rigidly coupled and rotatable about a horizontal axis 14, for which purpose they are received with stub axles 15, 16 in two pivot bearings 17, 18 attached to the platform. The pivot bearings 17, 18 are integrated in two bearing blocks 19 , 20, which are spaced apart and are rectangularly spaced from the platform 10 (see also Figures 2 and 3). A sensor housing 21 is arranged between the bearing blocks 17, 18, which is connected rotationally to the two stub axles 15, 16 and is thus rigidly coupled to the two firing devices 12, 13. The two firing devices 12, 13 and the sensor housing 21 are actuated by an actuator 22 pivoted in azimuth over the horizontal axis 14. An adjustment drive 23 is provided for rotating the platform 10 over its vertical axis 11, which drive, for example, drives the platform via a drive gear 24 combed with an external toothing on the platform 10.
    The fire control device has at least one target tracking sensor 25, which here includes a day vision TV camera 26, an infrared night vision camera 27, and a laser range finder 28 for measuring the target distance. The line of sight of the target follow-up sensor 25 installed in the sensor housing 21 is led out via a swivel mirror 29 and via a viewing window 30 in the sensor housing 21 (Fig. 5). In the Figures 4 and 5, the line of sight of the IR camera 27 is indicated by 31 and the line of sight of the laser rangefinder 28 is indicated by 32. The line of sight of TV camera 26 (shown only as a block in Fig. 1) is not drawn, but, since IR camera 27 and TV camera 26 can only be operated alternately, with line of sight 31 of the IR camera 27 coincide. The pivoting mirror 29 is, as symbolically indicated in Fig. 1, biaxial, pivoted vertically and horizontally. The pivoting of the mirror 29 about its two axes is effected by means of a mirror drive 33, which, as schematically indicated in Fig. 1, is realized by two adjusting motors 331 and 332, which pivot the pivoting mirror 29 about its horizontal and vertical pivoting axis 34 and 35, respectively. to turn.
    In Figs. 4 and 5, the sensor housing 21 is shown in longitudinal section in two different cross-section embodiments. The sensor housing 21 is made up of two parts and takes in the left cap-shaped housing part 211 the target follow-up sensor 25 with TV camera 26, IR camera 27 and laser range finder 28, and in the right housing part 212 adjacent to it, the swivel mirror 29 with the mirror drive 33 on. As can be seen from Fig. 4, the right housing portion 212 is covered with a cap 36 so that after the cap 36 is removed, the pivoting mirror 29 and the mirror drive 33 are accessible. On the left and right of the sensor housing 21, therefore on the one hand on the housing part 211 and on the other hand on the housing part 212, two centering stubs 37, 38 are formed as one piece with the sensor housing 21, which grip over the stub axles 15, 16 of the firing devices 12, 13 and are connected to it rotationally. The sensor housing 21 is thereby oriented relative to the firing devices 12, 13 in such a way that the sight lines 31, 32 of the target follow-up sensor 25 when the swivel mirror 29 is in the basic position run exactly parallel to the longitudinal axes 39, 40 of the two firing devices 12, 13, as schematically indicated in FIG. 2.
    The target tracking sensor 25 is continuously tracked to the flying target after picking up the target, continuously mixing the target data, such as target position, target speed and target distance. A tracking computer 41 connected to the target tracking sensor 25, namely to the TV camera 26 or IR camera 27, generates from the storage of the target position the line of sight of the target tracking sensor 25 (line of sight 31 of the TV camera 26 or IR camera 27 ) guidance signals in azimuth and elevation, which are supplied to a control unit 46. The control unit 46 pivots in dependence on these guidance signals via the actuators 22, 23, the firing devices 12, 13 with sensor housing 21 and platform 10. Continuously through the target follow-up sensor 25, namely, target data issued by the TV camera 26 or IR camera 27 and the laser range finder 28 are fed to a aiming angle computer 42, which is guided therefrom from the predicted target point (kill point) on the basis of the casting data of the guided missiles. calculate projectile and target as well as the required target angles "retention" and "set-up" of the guided missile when fired. These aiming angles are supplied by the aiming angle computer 42 to the control unit 46, which immediately switches up the holding angle on the platform 10 and fires the setup on the firing device 12, 13 and the associated sensor housing 21, i.e. the platform 10 via the actuator 23 pivoted through an azimuth angle α corresponding to the holding angle and the firing devices 12, 13 with the sensor housing 21 via the actuator 22 pivoted through an elevation angle corresponding to the design (fig. 3).
    At the time of the hold-up and set-up mounting on platform 10 and firing devices 12, 13, the control unit 46 controls the mirror drive 33 of the swivel mirror 29 with the aiming angle data in such a way that the swivel mirror 29 corresponds to an azimuth and elevation angle α, ε is adjusted against the direction of adjustment of platform 10 and firing devices 12, 13. As a result, as shown in Fig. 3, the longitudinal axes 39, 40 of the firing devices 12, 13 point away from the flight target to the so-called "kill point", while the adjustment in the opposite direction of the swivel mirror 29 causes the sight lines 31, 32 of the target tracking sensor 25 remain aimed at the flight target, so that despite the pivoting of the sensor housing 21 with the firing devices 12, 13 in the direction "kill point" the target contact of the target tracking sensor 25 is maintained.
    For the sake of completeness, Figures 2 and 3 show the line of sight of the infrared-based target search head of a projectile guided in the firing device 12 ready for firing. This line of sight is indicated by 43. During the target tracking (Fig. 2), the line of sight of the IR search head is coupled to the longitudinal axis 39 of the firing device 12. Line of sight 43 of the IR search head and the longitudinal axis of the firing device 12 are mutually connected located in line. When upward angle of retention and setup on firing device 12 is switched up, the target data is switched up on the IR search head of the guided missile and its sightline 43 is simultaneously decoupled from the longitudinal axis of firing device 12. The line of sight 43 of the IR search head thus focuses on the target. This is shown in Figure 3 by the dotted line of sight 43 of the IR search head. Opposite this target line of sight of the IR search head, the longitudinal axis 39 of the firing device is pivoted in azimuth over the retention angle α and in elevation over the angle ε, as shown in Figure 3, the longitudinal axis 39 of the firing device 12 points to the pre-calculated "kill point". The same description also applies to the firing device 13 and to the guide projectile deployed therein ready for firing.
    Since the second firing device 13 is always exactly flush with the first firing device 12 and the target follow-up sensor 25 does not lose the target contact through the pivot adjustment in the opposite sense of the pivot mirror 29 when the retention angle and set-up on the firing devices 12, 13 is switched up. firing from the firing device 12, after new target measurement with calculation of design and retention, by the aiming angle computer 42 and after setting the new design and retention at the firing device 13, a second guided projectile from the firing device 13 is fired relatively quickly at the flight target . In the same way, a second target can also be fought alternatively, which flies relatively close to the pursued flight target and is therefore constantly present in the field of view of the target follow-up sensor. After firing the firing device 12 at the continued target, the line of sight 31, 32 of the target tracking sensor 25 can be quickly set to the second target and measured and controlled in the same manner. The time lapse required for the renewed combat of the target by the second firing device 13 after firing the first firing device 12 is very small, thereby considerably increasing the combat power of the anti-aircraft system.
    A stabilization of the sight lines 27, 28 thereof is essential for a trouble-free functioning of the target follow-up sensor 25. This can be achieved relatively easily by the swivel mirror 29 switched on in sight lines 27, 28, for which purpose a stabilizing electronics 44 generates corresponding control signals, which are converted by the control unit 46 into a corresponding control of the adjustment drive 33 for the swivel mirror 29. Follow-up computer 41, aiming angle computer 42, control unit 46 as well as stabilizing electronics 44 are combined in an electronics box 45, which is preferably flanged to the sensor housing 21, as outlined in FIGS. 2 and 3. The transmission of the control signals from the control unit 46 to the actuator 23 for the platform 10 takes place via slip rings 47.
    权利要求:
    Claims (3)
    [1]
    Fire guidance device for, in particular mobile, anti-aircraft systems with a platform (10) rotatable about a vertical axis (11), with at least one firing device (12 mounted on the platform (10) pivotable about a horizontal axis (14), 13) for guided missile equipped projectiles, having at least one target optical tracking sensor (25) rigidly coupled to the firing device (12, 13), which continuously determines target data, such as target position, target speed, target distance, with a target tracking sensor (25) Connected aiming angle computer (42), which calculates from the target data the predictable point of impact of guided missile and air target, as well as the target angles "retention" and "set-up" of the guided missile required for firing, with a target tracking sensor ( 25) connected tracking computer (41), which stores tracking signals in azimuth and elevat from the target position of the line of sight (31) of the target tracking sensor (25) ie, and with a control unit (46) connected to the tracking and aiming angle computer (41, 42) with actuator (23, 22) for platform (10) and firing device (12, 13), which, depending on the tracking signals, (10) in azimuth and the firing device pivots in elevation, and before firing a shot, switches up the angle of retention on the platform (10) and the mounting angle on the firing device (12,13), characterized in that the line of sight (31,32 ) of the target tracking sensor (25) is guided via a vertically and horizontally pivotable pivot mirror (29), and that a mirror drive (33) driving the pivot mirror (29) is controlled by the control unit (46) such that the pivot mirror (29) an azimuth and elevation angle (a, c) corresponding to the angle of retention and positioning angle each time is adjusted against the adjustment device of the platform (10) and firing device (12,13).
    [2]
    2. Device according to claim 1, characterized in that the swiveling mirror (29) is electronically stabilized in two axes.
    [3]
    Device according to claim 1 or 2, characterized in that the target follow-up sensor (25) and the mirror-driven swivel mirror (29) are housed in the interior of a sensor housing (21) displaying a viewing window (30), and that the sensor housing (21) is rigidly attached to a pivot shaft (15,16) of the firing device (12,13) incorporated in pivot bearings (17,18) fixed to the platform.
    类似技术:
    公开号 | 公开日 | 专利标题
    NL9400170A|1998-11-02|Fire control system for especially mobile anti-aircraft systems.
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    GB1564597A|1980-04-10|Sighting and aiming system
    同族专利:
    公开号 | 公开日
    DE4306913B4|2008-07-03|
    TR27095A|1994-10-26|
    FR2761463A1|1998-10-02|
    FR2761463B1|1999-11-19|
    US5992292A|1999-11-30|
    GB2322692B|1998-12-09|
    DE4306913A1|1998-08-27|
    GB9403411D0|1998-06-10|
    GB2322692A|1998-09-02|
    引用文献:
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    US8355536B2|2009-02-25|2013-01-15|Light Prescriptions Innovators Llc|Passive electro-optical tracker|
    DE202009017995U1|2009-06-10|2011-01-05|Lkf-Lenkflugkörpersysteme Gmbh|Device for measuring the distance to an approaching target|
    US8646374B2|2010-07-27|2014-02-11|Raytheon Company|Weapon station and associated method|
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    RU2460029C1|2011-02-17|2012-08-27|Ольга Вячеславовна Трифонова|Device to launch missile from mobile carrier|
    RU2465532C1|2011-07-12|2012-10-27|Анна Вячеславовна Трифонова|Device to launch missile from mobile carrier|
    RU2467277C1|2011-07-12|2012-11-20|Ольга Вячеславовна Трифонова|Device to launch rocket from mobile carrier|
    RU2465533C1|2011-07-12|2012-10-27|Анна Вячеславовна Трифонова|Device to launch missile from mobile carrier|
    RU2514324C1|2012-09-18|2014-04-27|Николай Евгеньевич Староверов|Portable surface-to-air missile system /versions/|
    CN103389007B|2013-07-03|2016-08-10|北京航天发射技术研究所|A kind of car launcher unit control system|
    FR3019279B1|2014-03-28|2018-06-22|Safran Electronics & Defense|OPTRONIC ARMY TURTLE|
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    法律状态:
    1998-11-02| A1A| A request for search or an international-type search has been filed|
    1999-05-03| BB| A search report has been drawn up|
    1999-11-01| BV| The patent application has lapsed|
    优先权:
    申请号 | 申请日 | 专利标题
    DE4306913|1993-03-05|
    DE19934306913|DE4306913B4|1993-03-05|1993-03-05|Fire control device for, in particular mobile, air defense systems|
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