DE3919573A1 - Method and device for acquisition of a target point - Google Patents

Method and device for acquisition of a target point

Info

Publication number
DE3919573A1
DE3919573A1 DE19893919573 DE3919573A DE3919573A1 DE 3919573 A1 DE3919573 A1 DE 3919573A1 DE 19893919573 DE19893919573 DE 19893919573 DE 3919573 A DE3919573 A DE 3919573A DE 3919573 A1 DE3919573 A1 DE 3919573A1
Authority
DE
Germany
Prior art keywords
target
distance
roof
projectile
ground
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.)
Withdrawn
Application number
DE19893919573
Other languages
German (de)
Inventor
Des Erfinders Auf Nennung Verzicht
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.)
Diehl Stiftung and Co KG
Original Assignee
Diehl Stiftung and Co KG
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 Diehl Stiftung and Co KG filed Critical Diehl Stiftung and Co KG
Priority to DE19893919573 priority Critical patent/DE3919573A1/en
Publication of DE3919573A1 publication Critical patent/DE3919573A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01SRADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S13/06Systems determining position data of a target
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2226Homing guidance systems comparing the observed data with stored target data, e.g. target configuration data
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2246Active homing systems, i.e. comprising both a transmitter and a receiver
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2273Homing guidance systems characterised by the type of waves
    • F41G7/2286Homing guidance systems characterised by the type of waves using radio waves
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41WEAPONS
    • F41GWEAPON SIGHTS; AIMING
    • F41G7/00Direction control systems for self-propelled missiles
    • F41G7/20Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/22Homing guidance systems
    • F41G7/2273Homing guidance systems characterised by the type of waves
    • F41G7/2293Homing guidance systems characterised by the type of waves using electromagnetic waves other than radio waves
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01SRADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S13/06Systems determining position data of a target
    • G01S13/08Systems for measuring distance only
    • G01S13/10Systems for measuring distance only using transmission of interrupted pulse modulated waves
    • G01S13/18Systems for measuring distance only using transmission of interrupted pulse modulated waves wherein range gates are used

Description

The invention relates to a method according to the preamble of the An saying 1 or a device according to the preamble of claim ches 5th

It is widely known, for example from GB-A-21 33 514, by means of an active locating device in the course of approaching a Target object and / or when flying over it against each other set distance measurements across the target's heights contour to capture, then with a predetermined pattern to compare and derive from that in the projection geometry of the target object's optimal target point at which the target object should be taken. Such a recording of a height profile of the target to be fought is only then representable Rem apparatus work feasible if the target object is down richly different from its surroundings, if significant Differences not only in the target geographic survey country, but also with regard to the reflective properties sufficient information in the received retroreflection locator lead.

This is the case, for example, with a hard-armored vehicle on a flat, overgrown surface. Such conditions are however For example, not if the target object is stationary Protective structures that do not abruptly emerge from the surrounding area  and possibly in the same way as the target environment tet, for example overgrown. If such targets with Milli meter wave or laser energy can be sampled in the received signal reflected to the transmitter no significant sub distinguished between reflections, for example, from the roof of the target object building of interest and from the inclined side walls adjoining grounds.

This has a particularly serious impact when an airfield protective structure in a steep dive with explosive or penetration ammunition to be gripped. In this case, the effect is sufficient Target object (especially inside the shelter against something parked there Aircraft) can only be expected if the hit-target point is approximately in Zen strum of the roof, while a hit point, for example an inclined side wall does not promise a sufficient result.

The invention is based on the knowledge of these circumstances is based on a method and a device of the generic type to be designed in such a way that without unacceptable sensory Additional effort a central target point location even with such a target objects can be achieved, which can be found in the applied search head tech technology does not significantly differ from its target area environment the.

According to the invention, this object is essentially achieved by that the method or the device of the generic type according the characterizing part of claim 1 and claim 5 out are designed.

The solution is based on the surprising finding that despite well camouflaged in the environment of target objects that are rise sufficiently from the surrounding area, but meaningful Information results if not the retroreflective distance information mations of the target object and its surroundings as such  are evaluated, but only an overlay of distance information from wengists two defined, mutually ver set distance ranges; the kind of as flat Hori zonal sections are placed in such a way that one covers the basic area of the Target object and thus its closer surroundings captured, while the other detects an upper area of the target object. Thereby results for each distance range above the scanning swivel angle of the seeker head a significant course of the retroreflective reception power. For predetermined performance levels, the two can then be used respectively assigned seeker head pivot angles of the power curve averaging a distance range; and the resulting mean value, which results from the aforementioned Averages (especially if they are from different distances ranges are obtained) is a good approximation Measure of the position of the currently targeted target point on the target object or for the storage of its center, can therefore be as Control correction information for the final phase steering of the Pro jectiles can be used.

Additional alternatives and further training as well as further features and advantages of the invention result from the further claims and, also taking into account the explanations in the summary solution, from the description below one in the drawing below Restriction to the essentials in a highly abstracted manner preferred implementation example for the solution according to the invention. It shows:

Fig. 1 shows the typical scenario in the present side view representation for use the invention,

Fig. 2 in the strongly simplified block diagram of the locating technical features of the projectile according to Fig. 1,

Fig. 3 (3a to 3c) in an idealized sketch of the qualitative dependent on the instantaneous pivoting angles of the seeker head reception powers in as shown in FIG. 2 from each evaluated separately distance ranges, and

Fig. 4, the target point determined by averaging from the above the pivot angle dependent reception energy storage in the distance ranges according to Fig. 3b and Fig. 3c.

From a target area 11 ( FIG. 1), a target object 12 trapezoidal cross-section rises, such as, in particular, a concrete sub-stand for aircraft and / or operational or warfare agents on a flight area. This target object 12 is to be acquired (detected and hit) in the steepest possible descent by means of a projectile 13 that is maneuverable (continuously steerable or discontinuously correctable in its flight orientation) at least in its final approach phase, for which purpose at least in the interest of high effectiveness of the attack on the target object 12 in a cross-sectional plane, the aiming point 14 which is as central as possible is aimed for, that is to say an impact approximately in the middle of the shelter roof 15 considered here. For this purpose (in Fig. 1 outlined unrealistically large) steering projectile 13 with a in the direction of the projectile longitudinal axis 16 oriented ahead and in at least one plane pivotable ren search head 17 , which is essentially the transmit-receive Transducer (antenna) of a retroreflective distance measuring device 18 (radar, lidar). The current distance E of the measuring device 18 and thus of the projectile 13 in the current flight orientation 19 over the ground G (target area 11 ) can thus be determined in a known manner from the transit time of the echo of transmitted pulses or from the reception frequency in the case of a frequency-modulated continuous wave transmitter.

In a target object 12 , the roof T longitudinally inclined and often covered with soil or vegetation covered side walls 20 in the surrounding area 11 , differ when painting the ground G, the side walls 20 and the roof T, the receiving lines in the distance measuring device 18 On board the projectile 13 is not sufficiently significant to be able to obtain a projection geometry (in the sectional plane of the search head pivoting direction) for the geometric extrapolation of the roof center point to be controlled as the target point 14 . This basic difficulty is avoided, however, according to the invention by the simple additional measures of a distance window staggering (over the known the typical height of the target object 12 between base G and roof T), so that in the individual, delimited distance ranges when pivoting the seeker, reception services fluctuate significantly can be evaluated. Geometrically, the distance windows F can be represented as radially narrow ring sections which are staggered concentrically to the pivot point 21 of the seeker head 17 ( FIG. 1). Technically, it is the distance device 18 downstream gate circuits (distance gates 22 ) that only receive information (retroreflective power A) from a predetermined range with the neighboring substantially non-overlapping range (window F). A distance window FO ( Fig. 1), which is so short from the projectile 13 that it does not affect the base G or even the target roof T, provides practically no retroreflective power AO ( Fig. 3a), regardless of which Angular position w relative to the missile longitudinal axis 16 of the seeker head 17 is just pivoted.

A window FG, the mean value of which corresponds to the momentary missile distance E above the target site 11 or is somewhat larger, delivers retroreflective power AG only then and in the angular positions w in which a circular arc around the pivot point 21 of the seeker head 17 with this (distance) Radius intersects the base G - which (see FIG. 1) is only the case on both sides next to the transition of the target side walls 20 into the target site 11 . This corresponds to an angular position-dependent course of the retroreflective power AG ( FIG. 3c) with two pronounced maxima, which move further apart the smaller the missile distance E above the ground G. From this geometry it is therefore possible to obtain a criterion for how large the current basic distance E is when scanning a mutually offset distance window F, namely represented by the distance measure of the distance window F at which this pronounced double maximum ( FIG. 3c) occurs. Of course, the distance above ground G can also be derived in a conventional manner from the retroreflection information not filtered via distance window F or obtained via a separate range finder 23 . If necessary, the latter can also provide information about the height H of the target object 12 over ground G; or the typical height H of the target object 12 to be combated is stored in an input device 27 .

Typical target objects 12 have typical heights H of their roof T above ground G, in the case of aircraft shelters, for example, on the order of 10 m. If the current missile height E has been determined using the background G, a further range window FT can be set with the range mean value "EH". In this narrow range, there is only a retroreflective power AT if the antenna characteristic of the seeker head 17 just sweeps over the surface of the roof T. This results in a bell-shaped, only maximum receiving information AT over the seeker head pivot angle w ( Fig. 3b).

In order to obtain angle information w1, wr from the traverser A (w) ( FIG. 4), comparator queries are expediently carried out regarding the exceeding or falling below thresholds ST, SG in the memory and evaluation circuit 24 of the projectile 13 . The location of the thresholds S are primarily dependent on the device-typical transmission / reception characteristic of the seeker head 17 and its swiveling speed, but it changes as a function of the instantaneous distance E (height) above the ground G and of the extreme values (minima , Maxima) of the current power curve A (w). The mean angular positions wm are advantageous for the base G when the power curve AG (w) falls below such an adaptive base threshold SG ( FIG. 4) and for the roof T when rising above an adaptive roof threshold ST from an averaging determined, as indicated symbolically in Fig. 4.

The flight orientation (sample-and-tilt angle w = o = wm) already approximated with the axis of symmetry coincides If according to FIG. 1 by the target object 12, thus the missile longitudinal axis 16 already approximately vertically passes through the desired central target point 14 in the roof T, resulting the curves A (w) approximately symmetrical to the seeker center position wm. If the curve profiles according to FIG. 3 are superimposed (see FIG. 4), the central angular positions wm for certain amplitude values (corresponding to certain identical deflections wl, wr to the left or to the right) lie on a line that is more precise with the ordinate the superimposed amplitude curves coincide, the more precisely the projectile longitudinal axis 16 coincides with the normma len N through the ideal target point 14 . In practice, however, the resulting mean value WM (the angular mean position wmT-wmG from the superimposition of the curve profiles; FIG. 4) is offset by an amount K from the desired target point 14 .

In terms of circuitry, the superimposition of the power curves A (w) filtered out by the distance gates 22 takes place in a storage and evaluation circuit 24 for the determination, as described above, of the mean value WM currently resulting in each case and for outputting course correction information K to a projectile control unit 25 , it is therefore a question of the storage of the current resulting mean value WM from the center position or zero position angle wm of the scanning seeker head 17 . The control device 25 is now guided in such a way that the course correction information K becomes as small as possible by means of corresponding rudder deflections or transverse pulse triggers, and thus the desired target point 14 is aimed as precisely as possible in advance in the longitudinal axis 16 of the missile.

The projectile 13 thus enters the target object 12 in a good approximation in the middle of the roof T, in order to (depending on the design as a balancing projectile and / or as an explosive projectile) when hitting the roof T or entering the interior of the target object 12, if necessary to bring a fire or explosive charge to its full effect.

Claims (9)

1. A method for acquisition of a central possible target point (14) on an airport in the surrounding ground (G) target object (12) by scanning the object on the terrain (11) is collected target (12) by means of a reflection light distance measuring (18) characterized in that a distance is determined from at least one position approximately above the target object ( 12 ) to the base (G) and / or to the roof (T) of the target object ( 12 ), whereupon at least two distance windows (F) narrow in the distance direction - one of them in the vicinity of the base (G) and another which detects the target object ( 12 ) in the vicinity of its roof (T) - are defined in order to reflect reflected retroreflective energy ( 26 ) as a function of the current scanning swivel angle (w) of the distance measuring device ( 18 ) only from these distance ranges and for given amounts of the retroreflective power (A) the mean value (wm) of the two assigned angular positions ngen (wl, wr) for obtaining course correction information (K) in the direction of a centrally located target-target point ( 14 ).
2. The method according to claim 1, characterized, that a resultant for the course correction information (K) telwert (WM) from the angular position mean values (wm) for the  Reflective powers (A) in different distance windows (F) is obtained.
3. The method according to claim 1 or 2, characterized in that a roof distance window (FT) is obtained from a distance measurement determined by a distance measurement basic distance window (FG) in which the measured on board the projectile ( 12 ) basic Distance (E) the specified typical height (H) of a target object ( 12 ) is subtracted from the ground (G).
4. The method according to claim 1 or 2, characterized in that on board the projectile ( 13 ) for setting the distance window (F) distance measurements to the target roof (T) and the surrounding target area ( 11 ).
5. A device for the acquisition of an approximately central target target point ( 14 ) on the roof (T) of a target object ( 12 ) rising from the surrounding target area ( 11 ) by means of a return beam distance measuring device ( 18 ) on board a maneuverable projectile ( 13 ), characterized in that the distance measuring (18) head with a pivotable search is equipped (17) for scanning the target object (12) and the surrounding terrain (11) and that the return beam Entfer nungsmeßgerät (18) at least one range (22 ) for a narrow distance range in the plane of the target roof (T) or the surrounding ground (G) is connected, which selectively receives the retroreflective power (A) from this distance range depending on the current seeker head angle position (w) a memory and evaluation circuit ( 24 ) passes on, in which course correction information (K) for the pro jectile control unit ( 25 ) from the communication of the two angular positions (wl, wr) for the same retroreflective powers (A (w)).
6. Device according to claim 5, characterized in that in the storage and evaluation circuit ( 24 ) a result of the mean (WM) from the angular position mean values (wm) different distance windows (F) for delivering a course correction information (K) is obtained .
7. Device according to claim 5 or 6, characterized in that it is equipped with an additional range finder ( 23 ) for the current projectile distance (E) over the ground (G).
8. Device according to one of claims 5 to 7, characterized in that it with an input device ( 27 ) for specifying the typical height (H) of the target roof (T) over ground (G) to define the shortest distance window (FT) Is provided.
9. Device according to one of claims 6 to 8, characterized in that in the storage and evaluation circuit ( 24 ) distance-dependent thresholds (S) for the angular evaluation of the power curves (A (w)) are formed.
DE19893919573 1989-06-15 1989-06-15 Method and device for acquisition of a target point Withdrawn DE3919573A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19893919573 DE3919573A1 (en) 1989-06-15 1989-06-15 Method and device for acquisition of a target point

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19893919573 DE3919573A1 (en) 1989-06-15 1989-06-15 Method and device for acquisition of a target point
GB9012932A GB2238441B (en) 1989-06-15 1990-06-11 A method and apparatus for the acquisition of a target point
FR9007323A FR2649514B1 (en) 1989-06-15 1990-06-13 Method and device for acquiring a target

Publications (1)

Publication Number Publication Date
DE3919573A1 true DE3919573A1 (en) 1990-12-20

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Family Applications (1)

Application Number Title Priority Date Filing Date
DE19893919573 Withdrawn DE3919573A1 (en) 1989-06-15 1989-06-15 Method and device for acquisition of a target point

Country Status (3)

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DE (1) DE3919573A1 (en)
FR (1) FR2649514B1 (en)
GB (1) GB2238441B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0568426A1 (en) * 1992-04-30 1993-11-03 Thomson-Csf Method and device for detection and localisation of objects on a relatively level surface
WO2000047943A1 (en) * 1999-02-13 2000-08-17 Dynamit Nobel Gmbh Explosivstoff- Und Systemtechnik Target detection method and device

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018109440A1 (en) * 2016-12-13 2018-06-21 Bae Systems Plc Antenna arrangement

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2739441A1 (en) * 1976-09-01 1978-03-02 Raytheon Co Signal processing device, in particular for flugkoerper-radar steering systems
US4332468A (en) * 1976-02-28 1982-06-01 Firma Diehl Optoelectronic proximity sensor
DE3427020A1 (en) * 1984-07-21 1986-01-23 Messerschmitt Boelkow Blohm Navigation and flight guidance
EP0057235B1 (en) * 1980-08-11 1986-12-30 Martin Marietta Corporation Optical target tracking and designating system

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2537263B2 (en) * 1981-06-04 1990-04-27 Diehl Gmbh & Co Device for generating a priming signal for flying missile
DE3527522C2 (en) * 1985-08-01 1988-11-24 Diehl Gmbh & Co, 8500 Nuernberg, De

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4332468A (en) * 1976-02-28 1982-06-01 Firma Diehl Optoelectronic proximity sensor
DE2739441A1 (en) * 1976-09-01 1978-03-02 Raytheon Co Signal processing device, in particular for flugkoerper-radar steering systems
EP0057235B1 (en) * 1980-08-11 1986-12-30 Martin Marietta Corporation Optical target tracking and designating system
DE3427020A1 (en) * 1984-07-21 1986-01-23 Messerschmitt Boelkow Blohm Navigation and flight guidance

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0568426A1 (en) * 1992-04-30 1993-11-03 Thomson-Csf Method and device for detection and localisation of objects on a relatively level surface
FR2690754A1 (en) * 1992-04-30 1993-11-05 Thomson Csf Method for detecting and locating objects on relatively flat ground and device for implementing it.
WO2000047943A1 (en) * 1999-02-13 2000-08-17 Dynamit Nobel Gmbh Explosivstoff- Und Systemtechnik Target detection method and device

Also Published As

Publication number Publication date
GB2238441B (en) 1993-10-20
GB9012932D0 (en) 1990-08-01
FR2649514A1 (en) 1991-01-11
GB2238441A (en) 1991-05-29
FR2649514B1 (en) 1993-10-15

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