DE2309344A1 - TARGET SIMULATOR FOR A SIGHTING DEVICE - Google Patents

Description

HEINZ H. PUSCW-ANN PATENT ADVOCATE

S024 DEISENHOTENb. , Munich 2309344

Am 5rci3 8 ■ Telephone OSll / 6133297

I'Iatheiaa Corporation r.T. <) eisenhofon, the

P 135/72 Vfiduz / Lichtonstein Pu / mo

'il · iL-J · ?? - ¥:}] 2; -? ⁴ '~ Ρ? ^Λ ^ fil ¹ 'a V i_sie Tv; i: -. I ^ J ^ htung

The invention relates to a target simulator for a sighting device with a movable member for visual representation of the apparent movements of a to be combated. Goal on a Kautsched.be and with a device for generating a Hichtfohler that may arise from the sighting device indicating temporarily effective light mark.

»Such target singers are used for the training of Anti-aircraft guns required manual gunner.

In a known target simulator this work is ever a projector is attached to a stub shaft, which are coaxially arranged and their facing each other Ends are each connected to a straight Leitkurventräger in the manner of one-armed lever, which under the action of guide pins on one moved in a straight line by a motor at constant speed Carriages are pivotable. Here give by the

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Projectors emitted light beams on the target plate connected to the simulator, both the target movement and the movement of the initial point in the form of points of light again; see DT-AS 1 198 ?

With such a training of the Zi oil simulators must when changing the target speed the targets and when changing the flight altitude of the target to be simulated the saddle carrying the guide pins replaced become, which is not only cumbersome and expensive but also disadvantageous for the training of the shooters ic.t. Further can essentially only simulate floods. The simulation of an inclined target approach is basically possible, but due to the constructive The training of the guide apparatus and the targets are only possible within very good limits and within these limits still distorted. The one for the training of a shooter important lead variable is not automatically reduced but must be calculated on a case-by-case basis .. Lor instructor can therefore only check the accuracy, but not the accuracy,

But the combat effectiveness of an ^{anti-aircraft weapon from Hard 4} "depends in a very strong hatred on the speed and accuracy with which the gunner can pick up and pursue the target to be fought. A training program must therefore Include goal-setting and goal-tracking exercises.

However, these exercises must be as realistic as possible, This means that the target to be simulated should, if possible, carry out all the movements that would occur in real combat come as close as possible to anticipated movements. The target paths to be displayed should be as close as possible an unlimited number can be simulated in order to get the trainee +

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Gunner no opportunity to rrebon themselves the Note the displayed Ziolbahnen. Hereby v: ird falsifies the training obligation.

Such a zioloiaiulatoi 'should also simply be in its structure and directly on the anti-defense weapons in question, or on so-called directional sinulators be used to thereby in particular the basic training of the gunner on such defensive weapons and to simplify the sights assigned to these weapons, without the associated high costs real aerial targets must be used.

The invention is based on the object of an essentially consisting of mechanical components to create a simple and reliable target simulator, with the help of which, in addition to targeting the target, also the foreshark t values can be simulated, which requires their calculation and representation according to size and direction, Furthermore, for the purpose of an intensive training, which also includes the important target acquisition, also interrupted ones Target flights, single and group flights, the direction of entry of the air target in the gun range and finally also the shape and size of the air target depending on the programmed target flight and the resulting distances, can be simulated.

Based on the considerations known from DT-PS 956 025 on the representation of the flight plane, which passes through the straight flight path FW of the target and the horizontal, referred to as map plane KE, intersects in a straight line that passes through the location of the gun G, whereby the any

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Inclination angle assuming flights with one apparently bullet wrapped around the location of the gun in one Largest crois. Cuts, on which the hess points of the Flugvoges lying, and realizing that .oielanfliice and their properties only depend on the location of the Guns can be judged from, based on that when aiming! and not when aiming resulting kichting movements, is this The object is achieved in that the movable organ is about three mutually perpendicular axes, of which sv; ei coincide with the azimuth and elevation axes of a gun to be aimed, mounted movably and around each of these axes to the extent of one programmable point distance, of a Ncigungov; incels the flight plane within which the target to be simulated is located, a flight inclination angle and a Target speed for generating the apparent target movement it can be motorized that the azimuth and elevation angle assigned manual control means are provided, through which one of the apparent target movement opposite movement of the movable Organes is enforceable, and that for generation the light mark indicating the directional error is used to simulate the lead as a function of a predefinable one Weapon ballistics serving device is provided, the light mark when the straightening process is successful lies in the crosshairs of the sighting device.

In this way, a first light mark is generated that represents the air target and appears to the gunner on the ground glass set up in front of the sight, which, with the exception of simulated direct approaches, its position depending on the programmed alternating points, distance, the angle of inclination of the flight plane, the flight

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the angle of inclination and the speed of the turtle and the resulting angular speed constantly changes. The gunner must use the gun or a directional simulator depending on the depicted Align target movements in such a way that it matches the proranmierten target flight that appears on the screen corresponding first light mark with a ViGier mark then brings in cover if the reserve size and hold direction of both facilities match. The directional movements resulting from the target tracking therefore require a corresponding one in the target simulator Return of the first light mark.

For the purpose of checking the alignment accuracy, when an actuator is operated, the screen appears on the screen of the target simulator a second light mark depending on the point of impact calculated by the target simulator. V / enn the gunner has aimed correctly and the sight has correctly determined and steered the lead values, the second light mark appears in the middle of the crosshair of the sighting device, which is identical to the point of contact or the screen. The margin is to be understood as the value by which the gun barrel, compared to the air target, has to emigrate so that the projectile and air target meet on the flight path. the The lead direction in turn determines the course of this flight path around which the pipe must migrate.

According to a further feature of the invention, the movable member for generating the first light mark is on arranged at the end of a lever arm which is pivotable in a longitudinal axis perpendicular to each other reciprocally movable traverse is mounted with a second lever arm is movably connected, at the end of which another organ for generating the second light + η

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brand is arranged.

Boide lever arms are connected to one another via a gear chain connected, the translation ratio of which embodies the ballistics of the weapon Curve is determined.

The traverse is preferably arranged on a longitudinally movable slide, which is vertically movable, mounted in a ring movable about two mutually perpendicular axes, the movement of which about the vertical axis ⁺ possible bearing point uta a transverse axis intersecting the envelope position of the movable member is pivotable.

Here, the bearing points of the ring are carried by a frame which can be pivoted in a further frame is stored, its distance to the ground glass adjustable int.

The moving parts in relation to each other are driven by servomotors, which are controlled by a program unit are controllable, while the parts simulating the speed of the target to be displayed are via a Tachometer generator are controllable.

In order to make the training as intensive as possible, the invention also assumes that the simulated target flights can be interrupted so that the gunner can correct his aiming errors immediately and not just after Explain the sequence of the target flight.

According to a further feature of the invention, the drive means are for the purpose of depicting rotten flights of the movable organ after a + he

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specifiable. Time program intermittent, switchable, in the! switching pauses an automatic change of the flight altitude, the direction of flight or the parameters representing the angle of flight can be carried out is.

.I'm appearing in the representation of rotten flights not all light markings of the planes forming a group at x * the same time on the ground glass, but only one at a time, which occurs after the first burst of fire, i.e. immediately after releasing the trigger, disappears again; and invisible in one, one, programmed Time delay corresponding initial position returns. As soon as the time delay has expired, the light mark lights up again and a new one begins Target flight. By slightly adjusting the programmed flight characteristics, such as the flight altitude, the direction of flight or the angle of inclination during the time in which the light mark is returning to its original position, the light mark appears under different initial conditions than before, which gives the gunner the feeling that it is actually appearing another aerial target. The assessment of the alignment accuracy, i.e. the interruption of the simulation process is also ensured with rotten flights. In this way, the gunner can change target quickly practice. This offers the possibility for the light and medium air defense very much to practice important target acquisition under real conditions. Finally, precautions have been taken to ensure that The size and shape of the air target depending on the distances and the programmed target flight change; so the trainee gunner has that

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Feeling that the target is approaching the gun emplacement In fact.

The invention is illustrated below with reference to a 3 in FIG Drawing of a schoraatically illustrated example of execution described in more detail. Show in detail:

Fipures
1 to 5

Figure 6

Figure 7

Figure 0

geometric representations of the target approaches to be simulated and of these Pre-flight values assigned to target approaches;

a geometric representation of the return dor the first light mark at the Simulation of the target flights j

a perspective view of a target simulator according to the invention;

a side view of individual parts of the target simulator and

FIG. 9 shows a plan view of the target simulator} FIG. 10 shows a circuit diagram;

FIG. 11 shows a plan view of the individual parts according to FIG. 8.

In order to facilitate the understanding of the invention, the target approaches to be simulated are based on FIGS. 1 to 5 explained in more detail.

The target flights to be simulated can be divided into three main groups, namely direct approaches, in

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overflights and in flyby. Here, if from

so-called undertakings, but with

Exception of the target approach according to FIG. 3 only rarely and

then at most can occur in the mountains, it is about Trade horizontal or inclined flights.

For horizontal lies the flight inclination v / lukel V is equal to Hall degree, for incline flights it can theoretically reach ^{QO 0.} Tilt flights can also be recognized from horizontal flights by initially larger flight altitude, ie from the higher Hohem.luke 1 J * "when targeting. During underflights, the Höhonwinkol -J ^ decreases iminor during target tracking.

1 shows a direct approach to the gun located in G in the center of the map plane KE. The aerial target located at the measuring point M of an angle T - 90 ° with the plane of the map including the probes Flugeben FE moves on the flight path FW, which is characterized by the flight inclination angle V , in lease G. Since this is approached directly, there are no directional movements of the gun still derived angular velocities according to the side and elevation. The lead distance S drawn on the flight path F ¹ J results from the formula Vt, where V represents the target speed and t the projectile flight path from G to the point of contact T. The lead distance S thus corresponds to the lead variable mentioned above. It must therefore be aimed directly with the crosshair.

Fig. 2 shows an inclined overflight, i.e. the air target located at the measuring point M is moving on the Flight path FW, which is determined by the flight inclination angle V and the

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Change point distance el / marked i. without t, in the direction of central point W and object Ob. Since the FV / has a central point distance eW and since the angle of inclination "T" is 90 °, the gun can only be aligned according to the height; A corresponding elevation angular velocity results from the elevation movement. Here, the triangle formed by the straight lines GT, GM and MT between GT and GH includes the lead angle, the value of which is determined by the change point distance eW and the lead distance S. The lead direction is given by the angle of inclination V , ie it always remains 0 ° at a T of 90 °.

Comes for sighting during the riclit process therefore the point of intersection between the lower vertical pole ray Po (see Figure 6) and the lead curve associated with an inclined overflight VK in question. At the end of the vertical directional movement must always be aligned with the lower area of the sight image.

Pig, 3 shows an inclined undergate flight, i.e. the flight path FV /, which is characterized by the inclination angle V and the turning point distance eW, runs under the gun G, i.e. the exchange 1-point distance eW, compared to the changing point distance eW shown in FIG., has a decreasing height directional movement result.

The lead ratios are here in spite of a certain similarity with those of FIG Leading direction completely different, because due to the decreasing height directional movements you have to fly under

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v / earth directed with the upper toilet of the visor image. Since X - 90 ° is also in this flight, the vertical but upper pole beam of the sight image must be directed towards the ground.

In the flight v / eg F. · / shown in FIG Change point distance cV is marked and on which the air target located in M flies in direction V /, it is a horizontal overflight, i.e. the Fv / runs parallel to track 0-0. With horizontal Overflights and underflights correspond to the V / echse Ip point distance eW of the flight altitude h.

As with all of the Flugwegon described so far, the Angle of inclination T * also here 90 °. Accordingly, it retains also with this flxig the angle of the apparent Direction of flight, i.e. the direction of the headland, always has the zero value at, with the gunner also on this flight must align with the vertical lower pole beam of the sight image »

Since the initial lead angle is always a bit greater in horizontal flights than in inclined flights, must the gunner select a correspondingly large lead when aiming the gun.

5 is a horizontal flyby, at an angle T 90 °, at which the flight path PW, which is characterized by the changing point distance eV /, runs from M to V / and that on the map plane KE, as a result of the inclined Flight plane FE, which forms the flight path FW running parallel to track 0-0. The change point Distance eW does not meet the more

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Flight altitude h, as with overflights and underflights. At the ICE map level, there is also a map change point distance ekW.

In addition to the elevation angle /) f ″, the inclined flight plane FE also results in a side angle when tracking the target <cT. From both angles X "and G * arises on the Flight plane FE the directional angle <3 \ These three angles form a spherical triangle in which the angle C indicating the apparent direction of flight, i.e. the lead direction, is contained, which now does not remain constant, but an ever increasing value assumes and always reaches 90 ° at the changeover point V / compared to the vertical.

The gunner no longer has to aim with the vertical but with a pole beam PS lying between the vertical and the horizontal, whereby the angle of the apparent flight direction ο, ^{viewed from the} vertical pole beam, becomes larger and larger during a horizontal overflight.

The above-mentioned straight lines G-T, G-M and M-T, where G-T is the striking distance, G-M is the measuring distance and M-T correspond to the lead distance S, represent the starting position for the now in connection with the figures 7 to 10 to be described straightening simulator In Fig. 6, the straight line G-M is denoted by the M-arm and carries the air target at the measuring point simulating light mark ML, which disappears when the trigger is operated, while the straight line G-T with T-arm is referred to, which carries the light mark TL simulating the air target at the point of impact, which when actuated of the trigger lights up. By rotating the

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Gun around the values Γ (vertical angle) and C (lateral angle) the light mark ML is adjusted according to size and direction depending on the original values so that it appears on the lead curve. If the gunner has correctly taken the lead values into account, then the Target light mark TL when pulling the trigger in the crosshairs FK of the sight image VB appear.

In Fig. 7, a bracket 2 is rotatably mounted by means of bearings 3 about the axis b-b in a housing frame 1. Above a parallelogram (not shown here) and a lever arm 4- are used by a gunner to be trained executed directional movements for the purpose of returning the light mark MIj to be described as a function Transfer the elevation angle Jf to bracket 2.

With the help of a synchro gear 5 »which is attached to a carrier 6 connected to the lever arm 4, a setting corresponding to the inclination angle V can be made, whereby the bracket 2 is adjusted to the lever arm 4 · and thereby to the elevation angle J ^ by the value / .

On the bracket 2, a disc 7 and a bearing piece are rotatably mounted about an axis 9 and are via a Synchro gear 10 and a toothing 11 as a function of the lateral angle C of the movements of the gun G adjusted, which also results in a return of the light mark ML, which is still to be described Has. With the help of the synchro gear 10 and the toothing 11, a programmed direction of flight can also be set of the air target on the disc 7 and the bearing piece 8 be transmitted.

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In the bearing piece 8, a toothed segment 12, which is designed as a main carrier, is mounted so that it has a Synchro gear 13 (see also FIG. 9) as a function of the angle of inclination T of the flight plane FE rotated around the imaginary point G of the map plane KE, and around the track 0-0, which forms an axis.

A slide 21 guided by Eolzen 19 and 20 is (see. Also FIG. 9) by a threaded spindle 15, which is of a motor tachometer generator 16 via an angular gear as a function of a programmed target speedV on the horizontal a-a, which corresponds to the track 0-0 in Figures 1 to 5, in the direction of those on the axis b-b Points G shifted. The bolts 19 and 20 and the threaded spindle 15 are in a U-shaped carrier 14 stored, which in a manner to be described also is movable.

As a result of the displacement of the carriage 21, a cross member 22 connected to it and a meeting point T (see Fig. 1-5) marking bolt 23 also on the Horizontal a-a shifted.

The carrier 14 is guided by bolts 24 and 25, the are also fixed in the toothed segment 12 and can with the help of a threaded spindle 26, a synchro gear 27, a displacement encoder 28 and a toothing 29 (Fig. 9) in the Vertical plane c-c, starting from the horizontal a-a, can be adjusted, whereby the traverse 22 is supported Bolt 23 as a function of a programmed turning point distance eW, raised or lowered.

The bolt 23 engages in a T-arm 30, which is in the toothed segment 12, with the help of the bearing bolt 51 in the axis b-b, on which also the imaginary point G (gun)

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is pivoted.

A lever arm 31 on the one hand and a toothed segment 32 on the other hand are attached to the bolt 23 (cf. of the bolt 23 on the horizontal aa in the direction of the axis bb and because it is guided in a groove 35 of the T-arm 30, when the slide 21 is displaced, the lever arm 31 »the bolt 23 and the toothed segment 32 rotate, By means of a toothed rack 36 engaging in the toothed segment 32 and an ^{M-beam 37 connected to it and slidably mounted in the crossbeam 22 ″ h} , an additional movement likewise running on the horizontal aa can be carried out.

A bolt 38 mounted in the M-beam 37 (Fig. 7) engages into a groove 39 of an M-arm 4-0, the segment ring in the tooth 12 is also rotatably movably mounted in the axis b-b-lying-. Since the carrier 37 with the rack 36 is firmly connected, the bolt 38 is also shifted on the horizontal a-a, with the one separating it from the bolt 23, the lead distance S corresponding Distance AB is reduced as a function of the ballistic curve 34- (see Fig. 1).

The ballistic curve 34 and the radius R ^ (see Fig. 8) of the lever arm 31> meet a plurality of target speeds V, provided that a different radius R2 of the tooth segment for each target speed 32 is calculated and this is exchanged depending on the desired target speed V and that the lead distance S is correctly set depending on the max.

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In order to avoid replacing the tooth segment 32 and _{to be able to program UT 1} the lead distance S and the target speed Y steplessly, the distance A between the ground glass 47 and the axis bb is adjustable, v; od by the lead distance S that appears perpendicular to the ground glass 47 the tangent ^{radio L -} ion dec corresponds to the lead angle δ , which is calculated using the following formula:

Tang A = S. sin G. eT + S. cos 6

In order to indicate to the gunner the air target M, which can be determined by the bolt 33, a laser beam tube 41 fastened in the tooth segment 12 throws a light beam via the mirror 44 fastened in the axis bb of the tooth segment 12 via mirrors 42 and 43 fastened to a bracket 52 The mirror 45 attached to the M-Ai ¹ in 40, rotatable about the axis b - b, which deflects it via the lenses 18 and 18a through the slot 46 made in the end face 48 onto the ground glass 47, where it appears as a KL light mark . The lenses 18 and 18a are used to enlarge the + of the laser beam and to keep the beam path parallel so that the ILL light mark on the focusing screen appears to be the same size at every distance A.

The aperture 49 attached in front of the slot 46 of the end face 48 of the M arm 40 is made in a known manner Way, depending on the bolt 38 moving in the direction b-b, adjusted so that the HL light mark at the maximum target distance on the ground glass 47 as a point and with decreasing distance, in connection with the Slot 46 and the lenses 18 and 18a an enlarging Assumes line shape, making dom gunner + diameter

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the longitudinal axis of the aircraft and thus also the apparent plug direction is made recognizable.

Using the light mark MIj just described, the Instructors the straightening course, but not the straightening accuracy check. To also this! 'Solubility to create, a light mark TL is marked on the ground glass 47 as follows:

When a trigger 60 (Fig. 7,9 and 10) is operated a mirror 50 is moved by the switching magnet 'TH into the beam path of the laser tubes. This will on the one hand the light beam ζ v / i see the mirror 42 and interrupted, whereby the MIi light mark disappears and elsewhere the light beam is deflected onto a mirror 53 lying in the axis b-b, from where it is directed over a mirror 54 connected to the T-arm 30, over here Optical lenses 18 ′ and 18a (not shown in greater detail) are guided onto a mirror 55. This leads him on Half mirrors 56 and 57 and finally on the ground glass 47. The half mirrors 56 and 57 are arranged so that the Liciijstrahl falling through the slot 46 is not interrupted. One between the.i.opie gel 55 on the one hand and the half mirrors 56 and 57 on the other hand The lying iris diaphragm 58, which is controlled like that of the M-arm, will appear on the ground glass screen 47 TL light markers enlarged so that the trainer can adjust the pointing accuracy depending on the distance to the target can judge.

The assignments shown in FIGS. 1 to 6 Points and the switching elements in Figs. 7 to 9 is the following: In the zero position of the target simulator, the gun is at the intersection of axes a-a

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also in the axis bb, the horizontal aa corresponds to the track 0-0, the T arm of the straight line GT, the II arm of the straight line GII, the bolt 23 to the meeting point 'T, the bolt 38 to the measuring point M, the distance between deu bolts 23 and 38 of the lead distance S, the distance between the horizontal aa and the. straight line formed by the bolts 23 and 38 of the changing point distance el · /, the displacement of the bolt 38 of the target movement on the flight path FvJ and the turning of the tooth segment 12 the setting of the angle of inclination 'C of the plane of flight FE.

If, for example, no turning point distance eW is set, the bolts 23 and 38 move on the horizontal aa, which corresponds to a direct approach without angular velocities, ie the end of the M-arm 40 facing the ground glass 47 does not move and remains in the horizontal aa.- If a flight inclination angle V is set under the same conditions, the entire mechanism mounted on the bracket 2 is rotated by the value V , which corresponds to a programming of the direct approach depicted in FIG. 1.

When setting a change point distance eW, the bolts 23 and 38 move away from the horizontal a-a. By moving the bolt 38 in the groove 39 of the M arm 40 rotates in the direction of the axis b-b the M arm 40 about the axis b-b and forms an angle with the horizontal a-a. The smaller the distance between the axis b-b and the bolt 38, the larger this angle becomes. To the same extent the speed of the angular increase also increases, thereby increasing the angular speed of the

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Air target is simulated. Since, due to the lead distance S, the bolt 23 is closer to the axis bb than the bolt 38, the lead angle Δ is formed between the T and K arms.

A simulation process now takes place in the following way: After the instructor works on the one assigned to him Programming device PG, see FIG. 10 with the aid of the potentiometer P 5>, which has switches (not shown) P 10, P 13, P 16 and P 27 have set the values necessary for simulating a target approach, the target simulator is connected to the power supply by pressing the main switch HS and switched on by pressing the trigger switch S ^. A DC / DC converter, not shown, provides the necessary DC voltage. The respectively Engaged motors now move the switching elements assigned to them in the manner described above from the rest position, so that the generated via the laser beam tube 41 and deflected via the mirrors 42 and 4-3 and through the aperture 46 of the M-arm 40 exiting light beam generates a light mark ML, which moves across the screen 47 in accordance with the simulated target approach. The gunner occupying seat 64 has now by actuating the leveling wheel 65, which is via an electrical or mechanical transmission is connected to the lever 4 to move the bracket 2 depending on the height angle) (*. Depending on the preset When approaching the target, the synchro motor 10 can also be controlled by moving the footplate 66, over which the lateral straightening angle G is initiated. Both manual control devices are to be operated in such a way that

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that the emigrating light mark ML in the crosshairs FK or on the lead curve VK along one of the pole rays PS of the visor image shown on the ground glass 47 arrives. If this is the case, the Gunner by actuating the trigger 60, through which the contact t ^ is actuated, the straightening process interrupt. Closing the contact ti becomes namely the switching magnet TM made to respond, whereby the contact tmi opened and thus the power supply circuits of said electric motors are interrupted. At the same time, the deflection mirror is thereby created 5Ck into the beam path of the laser beam tube 41 brought (see. Fig. 9)> so that the light beam now over the T-arm 30 and over the of He wore mirrors 55, 56 and 57 on the screen 47 is steered. If the gunner has aimed correctly, the point of light generated is there TL at the meeting point T, i.e. in the center of the crosshairs FK. The Magnet TM.

With the response of the switching magnet TM, the switching magnet UM is also made to respond with a time delay via a delay element VG, which closes the holding contact and moves the contacts urn up to ^ o into the working position. This reverses the polarity of all motors and moves the extended switching elements back into the rest position. As soon as they are there, they open the contacts tmj and um ^, so that the magnets TM and UM are de-energized and the electrical starting position is reached again .

With / releasing of the trigger 60 will be referred to

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Switching solenoids de-energized. A new simulation process can take place by actuating the trigger switch S2.

In order to be able to simulate rotten flights, a timer ZW is provided in the programmer, which can be switched on via a switch S ^. This changes the effect of the trigger 60 in such a way that when it is actuated immediately after the light mark TM lights up, the switching means is reversed via a briefly effective switching magnet MR which actuates the contacts tmz and around. A target represented by the light marker ML therefore appears to the shooter again, coming from the same approach direction, so that he has to repeat his straightening process. If fly-bys are to be simulated, the main carrier 12 is to be rotated with the aid of the motor 13 in relation to FIG. 7. With increasing adjustment of the main support 12, the plane of flight * V becomes smaller and reaches the smallest value, ie 0 °, at 90 ° adjustment.

The light mark ML generated during the simulation process then moves transversely in relation to FIG. 7 to the screen

Patent claims:

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Claims (12)

-22- 23093U Mathema Corporation r.T. Deisenhofen, 02/15/73 P 135/72 Vaduz / Lichtenstein Pu / mo patent claims 1.J Aiming simulator for a sighting device with a movable organ for the visual representation of the apparent movements of a target to be attacked a ground glass and with a device for generating one when tracking the sighting device temporarily v / ineffective light mark indicating any directional errors that may arise, characterized in that that the movable organ (4-5) generating the light mark is arranged perpendicular to one another by three Axes (a ~ a, b-b, c-c), two of which with the azimuth and elevation axes of a gun to be aimed (G) match, movably mounted and about each of these axes to a programmable extent Turning point distance (eW), an angle of inclination (ΪΓ) the flight plane within which the target to be simulated is located, a flight angle (V) and a Target speed (V) for generating the apparent target movement can be driven by a motor that the azimuth and manual control means assigned to the elevation angle (6 \ # 0 (66,65) are provided, by means of which one of the apparent target movement is directed in the opposite direction Movement of the movable organ is enforceable, and that to the generation of the Hichtefehler indicative -23-409835 / 0543 Light mark (TL) a zxir simulation of the lead depending on a predefinable V / monkey ballistics device (31-37) is provided, whose light mark (TL) is in the crosshairs (I ¹ K) of the sighting device if the alignment process is successful, 2. target simulator according to claim 1, characterized in that the movable member (4-5) for generating the first light mark (ML) is arranged at the end of a lever arm (40) which is pivotable is mounted in a cross member (22) that can move back and forth along perpendicular axes, with which a second lever arm (30) is movably connected, at the end of which a further organ (5 ^) for generating the second light mark (TL) is arranged. 3 · target simulator according to claims 1 and 2 thereby characterized in that both lever arms (40,30) via a gear chain (23,31,32,33,36,37, 38) are connected to one another, the transmission ratio of which embodies the ballistics of the V / ape Curve (34) is determined. 4. target simulator according to claims 1 to 3, characterized in that the traverse (22) is arranged on a slowly moving carriage (21), which is vertically movable in one by two on top of one another vertical axes movable ring (12) is mounted, whose movement around the vertical Axis enabling bearing point (8) about a transverse axis which intersects the zero position of the movable member (45) (b-b) is pivotable. -24- 409835/0543 5. Target simulator according to claims 1 to 4, characterized in that the bearing points (7, 8) of the ring (12) are carried by a frame (2) which is pivotably mounted in a further frame ($) , the distance (A ) can be adjusted to the ground glass (47). 6. target simulator according to claims 1 to 5, characterized in that the drive of the mutually movable parts (2,6,12,14,21) via servomotors (Mc, M ^ ₀ , M-j3, Μ27, Μ7θ) takes place can be controlled via a program unit (PR), while the parts (21, 22) simulating the speed of the target to be displayed can be controlled via a servo motor with tachometer generator (M 16). 7. target simulator according to claims 1 to 6, characterized in that for the purpose of Representation of rotten flights the drive means of the movable member (45) according to a predeterminable time program (Zeitwerk ZW) can be switched on intermittently, with an automatic in the switching pauses Change of the plug height, the direction of flight or the parameters representing the plug inclination angle can be carried out. 8. target simulator according to claims 1 to 7, characterized in that the movable Organs (45, 54) are mirrors which lie in the beam path of a light source (41) with a small opening angle. 9. Target simulator according to claim 8, characterized in that apertures (49, 58) in the beam path -25-409835 / 0543 23093U whose opening depends on the simulated Flight time of the simulated target are changeable. 10. Target simulator according to claim 1 to 9, characterized in that the distance (A) between the ground glass (4-7) and the zero point (G) of the target simulator. 11. Target simulator according to claim 3, characterized in that the slide (21) driven by the motor tachometer generator (M ^ g) is a Toothed rack (36) is firmly connected, with which a carrier (22) fastened to the toothed rack can be rotated mounted toothed segment (32) which has a lever arm (31) which by means of a pin (33) into the curve embodying weapon ballistics (34-) of the T-arm (30) pivotably mounted on the ring (12) engages, while one with the rack (36) is fixed connected carrier (37) with a bolt (38) in a The groove (39) of the M-arm (40), which is also pivotably mounted on the ring (12), engages, all in such a way Arrangement that with a straight movement of the carriage (21) a cam-controlled Pivoting movement of the M and T arms takes place. 409835/0543 23093U 12. Target simulator according to one or more of the preceding claims, characterized in that that a laser tube (41) is used as the light source, the beams of which are fanned out via optics (18, 18a), guided via mirror systems (42, 4j, 53, 54, 55, 56, 57) and via variable diaphragms (49, 58) in their cross-section can be influenced in such a way that on the focusing screen (47) as a function of the decreasing target distance a proportionally enlarged target image appears. 409835/0543