DE3902129C2 - - Google Patents

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Publication number
DE3902129C2
DE3902129C2 DE19893902129 DE3902129A DE3902129C2 DE 3902129 C2 DE3902129 C2 DE 3902129C2 DE 19893902129 DE19893902129 DE 19893902129 DE 3902129 A DE3902129 A DE 3902129A DE 3902129 C2 DE3902129 C2 DE 3902129C2
Authority
DE
Germany
Prior art keywords
target
sensor
doppler
tank
evaluation
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
Application number
DE19893902129
Other languages
German (de)
Other versions
DE3902129A1 (en
Inventor
Gunther Dr. 8012 Ottobrunn De Sepp
George Prof. Dr. 8000 Muenchen De Stroke
Horst Dipl.-Ing. 8012 Ottobrunn De Prem
Robert Dr. 8028 Taufkirchen De Knopp
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Priority to DE19893902129 priority Critical patent/DE3902129C2/de
Publication of DE3902129A1 publication Critical patent/DE3902129A1/en
Application granted granted Critical
Publication of DE3902129C2 publication Critical patent/DE3902129C2/de
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G3/00Aiming or laying means
    • F41G3/22Aiming or laying means for vehicle-borne armament, e.g. on aircraft
    • F41G3/24Bombsights
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G9/00Systems for controlling missiles or projectiles, not provided for elsewhere
    • F41G9/02Systems for controlling missiles or projectiles, not provided for elsewhere for bombing control

Description

The invention relates to an anti-tank system for low fly ger according to the preamble of claim 1.

Such anti-tank systems for vertical ballistic weapons are in themselves known. In one embodiment, there is a so-called syndrome sensors with an infrared detector (IR-line scanner), a mm wel len radiometer and a laser rangefinder and with associated Scan setup the presence, the target shape, target direction and target distance of the tank determined. Then one or more missiles by (FK), which slants in with slightly different directions Ab directed towards the direction of flight of the carrier aircraft shot tubes of a weapon case are stored, shot down sen. The gun barrel (s) to be fired and the time of firing are chosen such that a FK due to the superimposition of the flight tool forward speed and the backward component of the FK and the Aircraft position flies almost vertically down and therefore the target regardless depending on the respective flight altitude. With these known Systems the combat value is limited by the fact that two to three VBW projectiles (vertical ballistic weapon projectiles) at the same time have to be shot since the syndrome sensor system admittedly the direction of the Longitudinal axis of the tank, but not the direction and speed of the Panzers can determine. These systems have other disadvantages on, for example when a tank is close to a bush or one Hut drives. Here, the syndrome sensors recognize through their mm wel len-Radiometer the metal of the target and through their IR-line scanner so-called "hot spot" of the target, which recognizes the laser range finder but not clearly the shape of the tank. As with the previous versions then a "tank syndrome" is clearly not present in the present case, a shot at the projectiles was not initiated and thus the tank did not fight either.  

Another disadvantage of the prior art is that the syndrome sensor system for measuring the vector of the aircraft speed uses a radar Doppler sensor, the measured values mostly not ge are sufficiently precise so that even a standing target can only be reached with one against FK can be taken safely.

The present invention has for its object a tank heir to create fighting system of the type mentioned that the pre written disadvantages and with which the combat value of weapons systems can be increased significantly by targeting in the Re gel only a single floor has to be fired, as well even if the shape of the tank is unclear, a moving tank is recognized as a target and fought and thus expanded the mission of a mission flight and you Combat value up to more than tripled.

This object is achieved by the measures outlined in claim 1 solves. Refinements and developments are in the subclaims specified, and exemplary embodiments are explained in the description. The figures in the drawing complete these explanations. Show it:

Fig. 1 shows a scene image with arrangement of the weapon system, ie Syn drom- and Doppler sensors and weapons container on the carrier aircraft in a schematic representation;

Fig. 2 is a scene image in plan view of the carrier aircraft with zugeord NetEm scanning area of the syndrome and Doppler sensor in a schematic representation;

Fig. 3 is a block diagram of the system in a simplified view of the weapon,

Fig. 4 is a block diagram of an embodiment of the measuring arrangement for a Doppler sensor based on a diode pumped solid state laser,

Fig. 5 is a schematic diagram relating the various vectors and angle of carrier aircraft and target,

Fig. 6 is a schematic image of the Doppler laser sensor, scan device and additional scan mirror.

The basic concept for solving the task - namely the fight increase in value of vertical ballistics weapons (VBW) - provides that the VBW system is equipped with a Doppler laser sensor (DLS). From the target shape measured by the syndrome sensor technology, which is the target longitudinal axis determines the Doppler frequencies of the measured by the Doppler laser sensor Target and its surroundings, the difference of which is the radial component of the Target speed results, as well as the deflection angle of the scanner the speed vector of the target relative to the aircraft is derived and preferably a single corresponding flight from the weapon system Body selected to fight the target and shot down.

For this purpose, a Doppler laser sensor 13 working in homodyne mode and a Doppler evaluation unit 14 is assigned to the syndrome sensor system 12 of the carrier aircraft 9 in an exemplary embodiment, the Doppler laser sensor 13 itself being connected to a scanning device 15 . This scanning device 15 deflects the measuring field of view 13 a of the Doppler laser sensor 13 transversely to the longitudinal axis 9 a of the aircraft and looking obliquely downwards and forwards, in the same way as for the individual sensors of the syndrome sensor system 12 , ie laser rangefinder, infrared detector and mm-wave radiometer ( Fig. 1 to Fig. 3).

The DLS 13 with the scan transverse to the longitudinal axis 9 a of the aircraft supplies, through the evaluation and control unit 16, the radial speed component of the target Z, which will preferably be a tank. The radial component of the target movement is thus determined by the determination of a target Z moving relative to the ground by the Doppler evaluation in the Doppler evaluation unit 14 and the direction to the target is determined by the scanning device 15 . The syndrome sensor system 12 measures the shape of the target Z and the direction of the longitudinal axis ZL of this target shape. The evaluation of Doppler frequency and target shape in the evaluation and control unit 16 results in the fact that the tank can only travel in the direction of its longitudinal axis ZL, the actual target speed vector v Z of the target (tank) relative to the ground, and as a result selects the launch tube -Selection unit 17 a single one of the gun barrels 11 a to 11 n and activates this at the optimal time.

The evaluation and control unit 16 thus calculated from the sample at the cross originating from the bottom of Doppler frequencies continuously the size and the direction of the true airspeed vector "groundspeed" concentration relative to the aircraft longitudinal axis 9 a, and ρ the roll and yaw angle and γ the carrier aircraft 9 . By adding the ground distance measured by the syn drom sensor system 12 in the scanning direction and the flight altitude measured with a separate altimeter 17 , the pitch angle ν of the carrier aircraft 9 is determined and thus its ( 9 ) orientation is given relative to the target Z. With known deflection of the measuring face of 13 a by the scanning device 15 , the roll angle ρ and the yaw angle γ of the carrier aircraft 9 ( FIG. 5) result from the course of the Doppler frequency with the scan angle α and the forward viewing angle β.

With negligible angles γ and ν and symmetrical deflection, for example, the roll angle ρ is equal to the angle between the vertical axis of the aircraft 9 and the direction of view with maximum Doppler frequency. At negligible angles ρ and ν, the same angle is equal to the yaw angle γ.

If the angles ρ, γ, ν are all different from zero at the same time, the course of the Doppler frequency with the viewing angle depends on all three angles and on the airspeed vector v F. In this, too, the general case, all 4 sizes can be determined mathematically. because there are enough measuring points, ie measured Doppler frequencies at different scanning angles α available.

The determined information about a movement actually detected the appropriate goal is to be seen as additional goal verification, which is not yet the case, as already stated at the beginning.  

The proposed use of the DLS 13 creates a certain unambiguity in that when an appropriate object that is not clearly identified as a tank moves with the syndrome sensor system 12 , it is recognized as a tank and thus as a target to be combated and the projectile on it is fired. In this case, the actual target speed vector from the Doppler signal and the "combined" form of target and masking (bush, hut, etc.) cannot be clearly derived, because the measurement results do not clearly indicate what the length or the width of the detected objects - for example hut and tank. As a rule, the shape evaluation then yields two or more possible longitudinal directions. Now can be used for several options available, that is, for several values of the putative longitudinal direction and from the Doppler measurement the possible velocity vectors calculated who a- and the respective ejection barrels 11 11 n selected and scored abge. The syndrome sensor system 12 therefore derives two or more possible longitudinal longitudinal axes ZL from the measured shape of the presumed target and forwards them to the evaluation and control unit 16 . This calculates the corresponding possible target speed vectors from the measured Doppler frequency and transmits them to the launch tube selection unit 17 . The latter then selects corresponding weapon barrels 11 a- 11 n and fires the individual missiles.

An advantageous solution to the problems in the presence of the above-described "insufficient shape criteria" is given by the fact that by assigning an additional scan mirror 15 a to the scan device 15 ( FIG. 6), the forward viewing angle β of the Doppler sensor system 12 a is reduced in such a way that a new scanning of the preceding scanning lines 15 b in the transverse direction ( FIG. 2) is carried out in the detection of the moving target. The scan mirror 15 a is thus reset by a few scanning lines in the transverse scanning (in relation to the direction of flight). After a certain time .DELTA.t, the scanning beam of the DLS 13 again hits the same location of the possibly moving target Z of the previous scanning. Since within the time difference Δt also v Z = const. applies, the desired speed v Z (“range rate method”) results directly from Δt and the two associated viewing directions. So only one of the gun barrels 11 a- 11 n is needed to fight the target.

Usually used as a Doppler laser sensor for speed measurement the more expensive heterodyne reception used because this in Contrary to the homodyne reception between the movement towards the sensor and can distinguish away from him. In the present case, this is sub However, a distinction is also possible due to the sensor's own movement, so that the simpler homodyne operation is proposed.

The laser sensor with Doppler homodyne evaluation 13 can now be a CO 2 laser, a solid-state laser or an arrangement of frequency-stable semiconductor laser diodes. It could be demonstrated that a diode-pumped Nd: YAG laser is sufficiently frequency stable at a distance of 200 m, ie a homodyne laser sensor with a diode-pumped Nd: YAG laser can be used well as a target speed laser for VBW systems. Because of the eye-safe laser wavelength, however, either a CO 2 laser or, for example, a solid-state laser doped with erbium is preferred, which should also be pumped through semiconductor laser diodes in order to have a high efficiency with the required high frequency stability. When using a CO 2 laser, it is possible in view of its power reserves to move the Doppler target search strip further forward (in the direction of flight) and thus have more time for the target evaluation. The use of solid-state lasers has the advantage that no cryogenically cooled detectors have to be used. A simple exemplary embodiment of such a Doppler laser sensor 13 is outlined in FIG. 4, only known components having been used for this embodiment.

The device for distance measurement 18 , consisting of the acousto-optic modulator 18 a with associated driver, the phase detector 18 b and an oscillator that controls these components are also specified. This device 18 operates in accordance with the known method on / cw-Ver (amplitude modulation with phase detection).

Claims (8)

1. anti-tank system for low-flying aircraft, which is provided with a Syn drom sensor system for determining the presence, direction, distance and shape of the tank to be combated and a weapon container with several controllable weapons tubes by this sensor system for almost perpendicular to the target firable missile (FK), characterized in that
  • a) the weapon system ( 10 ) with the syndrome sensor system ( 12 ), a double sensor system ( 12 a) with a double laser sensor ( 13 ) working in homodyne mode, a Doppler evaluation unit ( 14 ), a scanning device ( 15 ) and an evaluation and control unit ( 16 ) is assigned,
  • b) the scanning device ( 15 ) deflects the measuring field of view ( 13 a) of the Doppler laser sensor ( 13 ) transversely to the direction of flight and looking obliquely downwards in the same manner as for the individual sensors of the syn dome sensor system ( 12 ).
  • c) The evaluation and control unit ( 16 ) from the Doppler frequencies originating from the ground during the transverse scanning, measured by the Doppler evaluation unit ( 14 ) and the associated viewing directions of the measuring field of view ( 13 a) continuously determine the size and direction of the true (" Above-ground ") airspeed vector (v F ) relative to the aircraft longitudinal axis ( 9 a) as well as the roll angle (ρ) and the yaw angle (γ) of the carrier aircraft ( 9 ) are calculated and measured using the syndrome sensor system ( 12 ) Ground distance in the direction of view and the flight height measured by means of an altitude ( 17 ) determines the pitch angle (ν) of the carrier aircraft ( 9 ) and thus indicates its orientation relative to the target (Z).
  • d) the evaluation and control unit ( 16 ), which continuously checks the Doppler frequencies corresponding to the respective lines of sight of the measuring field of view ( 13 a), to determine whether they correspond to the calculated flight speed (v F ) and thus originate from a stationary surface element of the ground,
  • e) upon detection of a target (Z) by the syndrome sensor system ( 12 ), the evaluation and control unit ( 16 ) determines the shape of the target (Z) and the direction of view of the target (Z), and also upon detection of a shape corresponding to a tank also the orientation of the tanks longitudinal axis (PL) transmitted,
  • f) upon detection of a target (Z) by the syndrome sensor system ( 12 ), the evaluation and control unit ( 16 ) the Doppler frequency corresponding to the radial component of a possible target movement as the difference between the surface element of the ground measured in the target direction and that of a non-moving surface element corresponding Doppler frequency calculated so that and with the line of sight to the target (Z) and its longitudinal axis orientation (longitudinal axis PL) determines the actual Geschwin speed vector (v Z ) of the target relative to the ground and the sen a launch tube selection unit ( 17 ) transmitted
  • g) and the launch tube selection unit ( 17 ) from the direction of view transmitted to it by the syn dome sensor system ( 12 ) to the target (Z), the speed vector (v F ) and the orientation of the carrier aircraft ( 9 ) relative to the target (Z) and the distance and the target (Z), the speed vector (v Z ) preferably selects a single shot tube ( 11 a- 11 n) from the weapon container ( 11 ) according to the highest probability of success and fires at the optimized time.
2. Anti-tank system according to claim 1, characterized in that a target (Z) suspected of being a tank, which is not identified by the syndrome sensor system ( 12 ) only because of the non-applicable form criterion (ie approximate dimensions for length and width) and is intended for combat, is then treated as a real target when the evaluation and control unit ( 16 ) of the Doppler sensor system ( 12 a) detects a target movement relative to the ground.
3. anti-tank system according to claim 1 or 2, characterized in that the syndrome sensor system ( 12 ) derives several (ie 2-4) possible longitudinal axes of the tank (PL) from the measured shape of the target (Z) and the evaluation with an unclear shape criterion and control unit ( 16 ), and that this ( 16 ) calculates the corresponding possible target speed vectors (v Z ) from the measured Doppler frequency and transmits it to the launch tube selection unit ( 17 ), which corresponds to the corresponding weapon tubes ( 11 a- 11 n) of the weapon container ( 11 ) selects and fires.
4. anti-tank system according to claims 1 to 3, characterized in that when determining "insufficient shape criteria" (approximate dimensions for length and width of the presumed target) by an additional mirror ( 15 a) of the scanning device ( 15 ) the forward view angle β of the Doppler sensor system ( 12 a) is reduced in such a way that the scanning starts again in the transverse direction at the preceding scanning lines ( 15 b) in the discovery of the moving target ( 15 b), the evaluation and control unit ( 16 ) from the Retrieved moving target (Z), the "reset angle" of the Doppler sensor system ( 12 a), the target distance and the time difference between the first and second location of the moving target (Z) calculates its speed vector (v Z ) relative to the ground and select the appropriate weapon barrel ( 11 a - 11 n).
5. anti-tank system according to claims 1 to 4, characterized in that the Doppler laser sensor ( 13 ) works with a CO 2 laser.
6. anti-tank system according to claims 1 to 4, that the Doppler laser sensor ( 13 ) works with an eye-safe, diode-damped solid body laser.
7. anti-tank system according to one or more of claims 1 to 6, characterized in that the Doppler sensor system ( 12 a) is equipped with an additional device for distance measurement ( 18 ) and the for measuring the distance and shape of the target (Z) seen sensor of the syndrome sensor system ( 12 ) replaced.
8. anti-tank system according to claim 7, characterized in that the device for distance measurement ( 18 ) has an acousto-optical modulator ( 18 a) and a phase detector ( 18 b) and works on the / cw method.
DE19893902129 1989-01-25 1989-01-25 Expired - Fee Related DE3902129C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19893902129 DE3902129C2 (en) 1989-01-25 1989-01-25

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19893902129 DE3902129C2 (en) 1989-01-25 1989-01-25

Publications (2)

Publication Number Publication Date
DE3902129A1 DE3902129A1 (en) 1990-08-09
DE3902129C2 true DE3902129C2 (en) 1991-07-18

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6750807B1 (en) * 2003-06-11 2004-06-15 Honeywell International Inc. Radar altimeter with forward obstacle avoidance capabilities

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2650804C1 (en) * 1976-11-06 1986-07-17 Messerschmitt Boelkow Blohm Installation on low-lying weapon carriers to combat ground targets
DE3430888C2 (en) * 1984-08-22 1988-10-06 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De

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Legal Events

Date Code Title Description
OP8 Request for examination as to paragraph 44 patent law
D2 Grant after examination
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: DEUTSCHE AEROSPACE AG, 8000 MUENCHEN, DE

8339 Ceased/non-payment of the annual fee