NL8005915A - METHOD AND SYSTEM FOR REPRODUCTION OF AN AIR-LAYING BULK. - Google Patents

Description

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Method and system for simulating airborne bombardment.

The invention relates to a method and a system for simulating airborne bombardment.

Pilot training for airborne firing, ie firing at a movable target in the air, which is generally considered to be an 'TO hit' enemy aircraft, is known by actually firing a propelled goal carried out.

This method has several drawbacks. As the target is advanced, it allows only limited maneuvers to be carried out to avoid shooting by the pursuers, these maneuvers not corresponding to the actual conditions of an independently controlled target. In addition, the cost of the grenades and the different projectiles used must be taken into account, the latter factor being able to influence the duration and number of training lessons.

The invention has for its object to propose a means against these disadvantages, by providing a method and a system for simulated shooting, because it uses not a real projectile but a beam of light, which makes it possible to aim at an independent target. to shoot.

The advantages resulting from this method and system are due to the features that the pilots to be trained are placed in shooting conditions that are close to the actual conditions, where 3Q is free in the target to perform all kinds of maneuvers , in order to have the possibility to extend the duration and the number of training lessons at comparable costs.

According to a first feature of the invention, it is believed that the fictitious grenades are fired in synchronism with the regular emitting of a light pulse, while 8 0 0 3 a. - ..............

• 9 ΐ * their directions and positions are determined by a periodic calculation, taking into account the maneuvers of the target and the aircraft to reflect the result of a shelling, j According to another feature of the invention the airborne mimicking system a pulse laser light source, and a scatter meter (diaspora-mètre) for aligning the axis of the radiated beam, an optical receiver in an area 1q coaxial with the radiated light beam to capture the reflected light and to focus this received radiation on a four-quadrant photodetector, applying the signals so detected to a metering circuit to measure the distances between the aircraft and the target, and to an anomaly circuit to measure the angular deviation with the aim, a calculator that periodically takes off The position of the target, as well as the flight data and the location of the aircraft, the direction of sight of the axis along which the dangerous fictional grenades 20 are located are almost the same distance from the aircraft as the target, in order to be able to measure the obtain the result of the shelling.

The invention will now be explained in more detail with reference to the figures.

Figure 1 shows a general scheme of a mimic system according to the invention; Figures 2 and 3 show basic sketches which relate to the method for simulating a fictitious shelling and to the determination of danger-causing grafts; figure k shows a basic sketch of the fields or areas which relate to the emitted, received and other light; Figure 5 shows a chronological diagram for the periodically performed procedure, which is used by the mimicking system; and Figures 6 and 7 show a basic sketch and a diagram for the implementation of the mimic system.

The simulation system shown in Figure 1 of an airborne bombardment includes means for emitting a beam of divergence so large as to cover a predetermined illuminable field or area, thereby emitting the beam. light takes place with the help of periodically emitted light pulses. These means 10 are preferably made with the aid of a pulse laser source 1 and a diverging optical element 2, which may consist of a simple lens. The beam thus obtained has a divergence angle Θ with respect to its optical axis Z. At the location of the exit, a deflector is arranged to change the direction of the axis Z according to a deflection field, which is determined by the half top angle S. In the illustrated example, the deflector consists of a spreader (diasporamètre), which contains 2 prisms 3Λ, which are arranged one against the other and which can be rotated by means of servo members 5 and 6. A reflecting mirror 7 placed obliquely on the axis Z offers the possibility of applying the radiation received again via an optical focusing member 8 to a detector 9 of the four-quadrant type. The mirror is placed between the lens 2 and the dispersion meter 3 and is provided with a hole in the middle for the laser radiation to pass. By the optical receiver 7-8, a detector is determined with the detector 9, which extends coaxially with the transmission field and is located within it, i.e. the half apex angle thereof is at most equal to 30 °. The required coaxial relationship is obtained by the oblique the position of the plane of the mirror 7 relative to the axis Z so that the reflection direction in question corresponds to that of the axis Z 'of the receiving system 8-9. Behind the detector, the receiving system contains an angle deviation circuit 10 and a 35 8 0 0 5 9 j mT] «, * metering circuit 11. The angular deviation circuit TO derives the coordinates ΞΧ, EY of the image of the covered target from 2 Cartesian reference axes X and Y in a known manner, the angular deviation of 5 from the target from the ashes are interpreted. These deviations are calculated from the four detection output signals by means of the circuit 10 is calculated. In contrast, these outlets for feeding to the remote meter 11 are combined into a single output, measuring the distance D from the target to the aircraft performing the bombardment by this timer by chronometric means. measure the time lag between the transmission time of an impulse and the detection time of the echo.

Regarding the usual measurements, it is noted that the optical receiving path has been completed by an optical filter located within the range of the laser beam band, and that the target is designed to cooperate with the respective laser light. by equipping this target with a reflecting means (a reflector or something else) adapted to the illumination frequency used. These usual means are not shown.

The remainder of the system is mainly constituted by an interposed transition circuit 12 and a calculator 13. The interposed transition circuit 12 connects the calculator 13 to the correction circuit 11 as well as the offset circuit 10 and the servo circuits 5-6 to adjust the position of the spreading meter 3-1.

In fact, the calculator 13 can be considered as part of the material already on board the aircraft, as well as the elements identified by reference numerals 1U and 15, showing different sensors and the trigger of the gun, respectively, on ae. handle is available to the operator. The system can thus be derived from the combination of elements 1 to 12 8 0 0 5 9 1 5 r ^ —______ (i s · ΜΜι

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which are installed on board the aircraft and connected to the computer. The connections comprise a command chain ST which is connected to the laser source 1., and 2 single direction busbars B1, B2 which are connected to the intermediate transition circuit 12.

After the construction of the system has been established by means of figure 1, its operation will now be described, which will show the principle which is applied for the implementation of the method.

IQ This principle consists of determining the properties of a fired fictional grenade instead of an actual grenade with given ballistic characteristics, of knowing the position of this fictional grenade and the distance traveled by it at any time, and of deriving the bombardment result therefrom.

The times of the firing are determined by the times of the emission of the laser pulses by taking into account the fact that a fictitious grenade 20 is fired in synchronization with this pulse for each transmitted pulse. The starting firing direction is the same as that of the axis of the cannon, the position of which is known with respect to the aircraft serving as reference object. The auxiliary sensors offer the possibility to know the flight parameters and the location of the bombarding aircraft at any time, this information becoming in the form of numerical data. which are passed on to the computing device 13. With the aid of this data, the computing device 13 can calculate the respective directions corresponding to the paths covered by the successive fictional grenades and likewise the respective positions 3q of this grenade. In order not to load the computer with useless data, the number of data processed by it is limited to a number n, for example n - 10, thereby including the last n shots fired. These calculations are periodically renewed, for example in the rhythm of the shooting, ie in the transmission rhythm of the light source.

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The fictional grenades, which are capable of intercepting the target, form the hazardous grenades which must be identified so as to be able to interpret a bombardment result. For this it is necessary to know the 5 maneuver performed by the target; this maneuver being known from the data for the distance D and the deviation coordinates EX, EY, which are passed on to the computer. Preferably, the bombardment result is calculated by calculating the angle y between the direction of the target toward the target aircraft and the direction between the target and the hazard grenade as depicted in Figure 2. The fictional grenades or projectiles indicated by Pj -1, Pj, Pj +1 have been fired beforehand at times tj - T, tj, tj + T, where T represents the transmission period.

15 A grenade Pj which is dangerous, is considered to be the grenade which, at the time of calculation, is most likely to hit target C.

In the example considered, a hazardous grenade is defined somewhat differently as shown in sketches in Figures 20-3. It consists of a fictitious grenade P'j, which can be considered as a grenade at the time of calculation, which is at the same distance D from the target aircraft A as the target C, its position being interpolated from the target. positions of two fictitious grenades Pj and Pj -1 are derived, which are located in the vicinity of the target C. The direction of P'j can be interpreted as a line, which is at the preceding firing time tj (the firing time of the closest projectile Pj). .

passes through the position Aj of the aircraft at P'j. In fact, the fictional grenades are close enough to each other at the firing distance D when a fast-firing rate can be accounted for so that it is possible to apply this range approach without compromising the accuracy of the system.

35 The visor axis SE of the system from the output of the 5. -i deflector is adjusted by the servo members in the direction calculated for the hazard grenade. This optical axis is the same for the transmit field as for the receive field; and corresponds to the center of the four-quadrant output detector 9, whereby by measuring the deviation of the laser light emitted to the target, the characteristic deviation y for the type of bombardment is directly given.

For the principle formulated above, it is necessary to know the distance from the bombarding aircraft to the target and to measure the flight parameters of this bombarding aircraft.

The distance to the target is measured using a laser braking method. Using a laser transmitting power obtained by a YAV crystal, it is possible to cover the currently desired field, so that it is unnecessary to apply a complicated mechanical scanning system to locate the target. The laser beam, which by its very nature does not diverge, passes through the diverging optical element 2 and covers the entire detection field by the angle 20.

for the purpose. With the aid of a reflecting refractor, which is installed on the target aircraft, it is possible to obtain a point echo of sufficient receiving energy, taking into account the diverging course of the transmission beam 25. is being held. The echo is received by the photo-electric cell 9 with four quadrants, after which this is used on the one hand for carrying out the distant measurement and on the other hand for carrying out the deviation measurement. The time which elapsed between the emission of the laser pulse and the reception of the echo is measured by the ehrono-metric electronic circuit 11. This time is proportional to the distance between the target and the aircraft, with the chronometric circuit providing a measurement of the distance to the target at each receiving time of a laser echo.

The measurement signal for the flight parameters of the aircraft, which has been derived by the auxiliary sensors 1U, is applied to the audit device 13 for the cock of a grenade compared to the reference point at the time of firing this grenade. to calculate the aircraft considered, cj and to calculate the displacement (the translation of the center of gravity and the rotation around this center of gravity) of the aircraft relative to the aircraft considered as the reference point at the time of firing the grenade. By combining these two calculations, it is possible at any time to calculate the direction IQ and distance of a previously fired grenade from the target aircraft, and from this, taking into account the position of the danger grenade, the position of the derive aforementioned n grenades.

The parameters used differ depending on whether the aircraft is equipped with an inertial central unit or with a gyroscopic central unit. In both cases, the following parameters are used to calculate the trajectory of the grenade, relative to the aircraft serving as the reference point at the firing time, viz .: the own speed of the aircraft, the density of the air (o f the height read on the barometer), the pendulum angle, the studbook, the angle of incidence and (possibly) the exit angle.

In the absence of a laser echo from the target, the distance to the target is not known to the system, and so this system cannot calculate the direction of a hazardous grenade. During this prior target search period, the system is operated to produce successive light pulses and while the pilot is aiming his device approximately at the target, the optical output 2q gangas ZO is set in a direction which is is deemed effective for the importance of carrying out the following actions. A direction of interest can be defined as a direction, in which the fictitious grenades are surrounded by the associated receiving field, or the largest number of these, which are in a certain distance range from the

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10ÊÊÊÊÊÊÊtteiÊÊtm shelling aircraft, for example, at a distance between 300 and 1500 meters. This direction is always in the rhythm of. renewed the emitted laser pulses, which during this previous phase, for example, 1 Hz. amounts. As long as the target 5 has not yet been detected, i.e. does not fall within the receiving field, the calculator is programmed not to execute the firing command when the operator operates the trigger 15 of the gun. As soon as a laser echo is received, the distance to the target is measured, and renewed in the transmitter's transmit rhythm, the center of the receiving field then directed toward a distant and hazardous grenade, after which the investigation phase is ended.

Fighter aircraft used today are generally equipped with a sighting device (16, figure 1), whereby the pilot observes a certain field. The control of the aircraft is carried out in such a way that the target is hereby brought into a good shooting position in the field of the sighting device. By way of example, in figure U the boundary 20 of the sight field CV is indicated, as well as for comparison the boundary CD of the deflection field (- δ), the boundary CE of the emitted radiation field (- θ) and the boundary CR of the receiving field. The fields CV and CD are arranged to coax each other and make a certain angle to the longitudinal axis of the aircraft, which may be symbolically indicated by projecting a reticle RA. The horizon is indicated by a second wire line RH. The receiving field CR is slightly smaller than the transmitting field CE, a common center being denoted by 0, it being understood that it can be moved within the field CD using the deflector provided for this purpose. The shooting direction is made visible by means of a firing wire figure RT between the crosshair RA and the center point 0, the last wire figure having to be aimed at the target with the aid of the sight 35 in order to achieve a good performance under the given distance conditions —— m - j Ί „| M _J I. '^ 10 0 5 9 15 # «*

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shot to be conceived. In the absence of the sighting device, it can be observed that a shot is fired by the pilot only at the guess.

After detecting the target, a shot when the trigger of the gun is actuated by the pilot is indeed fired by the pilot and the results achieved by this shot will be delivered by the system. The receiving field has in the center, in a field with an angle of about 1 degree, a linear deviation measuring zone with two axes, so that the deviation of the laser echo (the target) from the center of the field (ie one of a danger grenade-derived echo) is given. As a result of this deviation, a direct measure of the result achieved by the shot is formed, which can be made known to the pilot and / or registered on the sighting device. In order to obtain good dynamic accuracy during the firing of a burst of valid shots, the firing rate of the laser impulse may be different and higher than the rate applied during the tracking, for example ... 5 Hz instead of 1 Hz. This also makes it possible to use the laser source operating at full power only during very limited periods of time. The firing command ST (Figure 1) is issued by the calculator 13 to the transmitter 1 so that the latter operates in a certain rhythm, the signal ST being able to consist of a series of regularly occurring pulses, of which, in the absence of the validity signal SV only 1 in 5 is transmitted, this validity signal being produced by operating the gun trigger 15.

Figure 5 summarizes a possible chronological process for controlling the mimic system. The firing period or the laser period is formed by the duration, so that two successive firing times t0 and t1 are separated from one another. Each period of these periods is divided chronologically into different parts in order to be able to perform different calculations successively. In the illustrated example, the period is divided into 6 cycles with a duration t.

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The calculation of the aircraft related parameters _ of. the grenades includes: calculating the initial velocity of the grenades, the magnitude of the distance traveled by each grenade, the ballistic corrections for the grenades, the determination of the aircraft missile vector using ground-related axles, and then using aircraft-related axles, taking into account the maneuvers performed by the aircraft and the more accurately approximated distance between the aircraft and the missile with only the data from the last ten shots (n = 10) are retained, with the parameters of the last grenade fired at time tO serving as replacement data for the grenade fired at the most remote time, etc. This calculation of the the aircraft-related parameters of the aircraft is performed only in 1 or 2 cycles, with the other cycle based on priority for controlling h The actual mimicking of the shooting is reserved. During the initial phase, the deflector is not in such a position that 10 first 20 shots could have been fired. To take the response time of the deflector into account, several firing cycles begin to position this deflector in the correct direction and predict hazard grenades at a firing time tl by.

25 revise a deviation measurement method, which will be corrected at a later time tl + τ.

The implementation of the system can be implemented in the form, which is carried out by means of a schematic in Figure 7 is illustrated, and is summarized in two cabinets 20 and 21.

The cabinet 20 is shown in more detail in Figure 6. It contains the deflector 22, as well as an optical and detection compartment 23, and the laser transmitting circuit 1 and the measuring circuit 11.

The deflector 22 consists of two prism% 3- ^ of the spreader meter, which are rotated by means of the servomechanis-. 8905915 __ ✓ -u '__ï I ^ ÊÊÊÊEÊÊÊÊÊÊL men 5 and 6. The respective rotation commands * 1 Θ 2 for the prisms respectively are calculated by the calculator of the calculator and transmitted via the electrical cabinet 21, which contains the servo amplifiers , the output of which supplies the excitation signals for the motors of the servo mechanisms 5 and 6. The two prisms are set separately because the spreader works with parallel beams. The deflection effected by this assembly consists of a so-called (ρ, θ) deflection, where p indicates the state in which the IQ prisms rotate against each other and θ the state in which the prisms rotate together. The elevation and azimuth angles are converted into p, 9 by the calculator and subsequently in position instructions en1 and Each prism is cylindrical, mounted in a gear ring and can be mounted by means of rotate a member fitted with bearings.

The drive is effected by a DC motor and a reduction stage. A position indicator 01 and 0g are output by a position indicator, which may be in the form of a potentiometer, which is driven by the gear ring 20. Angle stops are also provided to limit the angle traversed by the prisms as a function of the selected scanning field.

The middle compartment 23 contains an optical assembly for the emitted laser pulses and for the pulses received again via the detector 9. The detection outputs SE (as well as possibly the sum output eventueel in order to be able to realize a weighted measurement) are connected to the deviation measuring circuits 10, which are located in the electronic box 21. The electronic circuit for pre-amplifying the laser echoes is arranged behind the output of the detector 9 in the middle compartment, however this is not shown in the figure for the sake of simplification.

The laser transmission source 1 contains a laser cavity with a YAG rod. As a result, the shooting command ST from 25 the computer is recorded via the case 21 and the shooting synchronizing signal 8 0 0 5 9 1 5

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«F !! ·! ST1 is sent back to this computer corresponding to the time of the emission of a light pulse. The signal ST1 is also sent to the chronometric remote measuring circuit 11 to calculate the duration, thereby interpreting the distance of the laser echo.

The electronic box 21 contains the transition circuit (12 of Figure 1) between the calculator and the deflector to convert the numerical deflection instructions (, 9 ^) into an analog form and the angular position signals (0 ^, 0g) again in inverse sense T0. put. This cabinet further contains the deviation measuring circuit (10 of Fig. 1) to process the four detection signals SE and to calculate the Cartesian information EX, EY of the deviation measurement and the information from the chronometric distance measuring circuit 11 with respect to the distance D in a numerical form 15.

Block 130 symbolically indicates a numerical input / output intermediate circuit of the computing device 13.

The foregoing description has clearly shown the examples of a simulation system for an airborne bombardment according to the invention, which advantages have already been stated in the introduction to the description, and which mainly consist of the absence of the need to to fire real grenades and from the possibility of reproducing real maneuver conditions due to the availability of an independent target.

The reception circuits 10 and 11 have not been discussed in great detail. The chronometric operation of the circuit T1 can be easily realized, for example, by counting the pulses of a clock signal, the frequency of which is a multiple of the transmission frequency 1 / T, namely between the moment of the transmission of an impulse and the time when the ultrasound returns; wherein this clock signal can be output by the computing device 13 according to the connections already considered, and can be synchronized by the latter. For the deviation measuring circuit 10, also known techniques of §0 0 5 9 1 5 "imiimmim— 7% can be used, for which, inter alia, according to the known from the French patent application 7 ^ +. ++ 0035 of 6 December 197 ^ which is published under number 2.293.71 ^ +.

The basic equations corresponding to the equations used for continuously calculating an expanded path for bombardment can be used to calculate the aircraft-related parameters of a grenade. These equations can be processed by the numerical processors already mentioned by taking as the running time the time given by the expression jt, where τ equals the interval between the two position calculations.

The calculation of the aircraft grenade vectors can be reduced to simple operational operations of a number of parameters, which are periodically calculated using subprograms. The programming can be compiled in various ways and according to appropriate conventional information processing techniques and, as a result, it has not been described because it is outside the scope of the present invention.

The mimic system just described can be implemented in numerous variants, which nevertheless correspond to the features set out and thus fall within the scope of the invention.

The transmitting means may consist of a YAG laser, or of a glass laser or of a diode laser, etc. The deflecting members may consist of a deflecting construction, which is made with a mirror instead of the construction described with a spreading meter, which is nevertheless very is compact.

The detection means can be performed for the same function by using a detection mosaic containing a greater number of direction-determining photoconductive elements (Photodirectors) than the basic matrix of the four-quadrant type described in the description, and which first can serve as a sensing means for measuring the angular position or the deviation coordinates of the target 8 0 0 5 9 1 5? With a detection mosaic, such as a matrix scanner switched from a CCD circuit (from the English Charge Coupled Device), it is possible to detect a video image, so that it can be used for the latter function, whereby the distant measuring circuit and the deviation measuring circuit can then serve to process the measurement data D, EX and EY in such a way that, for example, one line-by-line scanning is taken into account by means of the detector.

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Claims (9)

1. A method of simulating an airborne firing to simulate the firing of a shelled aircraft from grenades to an airborne target, using an on-board calculator, thereby limiting flight parameters and the location of the aircraft. the aircraft, characterized in that it comprises the editing steps in which synchronous with the periodic emission of a light pulse to illuminate the target, the firing of fictitious grenades is recorded, and in which the position of these 10 fictitious grenades and of the target is periodically recorded is determined in order to be able to derive the result of the shelling from this. Method for mimicking an airborne bombardment according to claim 1, characterized in that it comprises the processing steps in which a beam of light with a certain divergence angle is emitted in order to cover an illuminated field (CE, - θ), wherein the emitted light consists of a periodically emitted light pulse and the axis (Z) of the light beam can be varied within a certain deflection field (CD-3); and in which the light echo returned by the beam-illuminated target is again received in a receiving field (CR) located within the transmitting field and extending coaxially therewith; wherein the echo is detected and the position of the target relative to the target aircraft is measured by means of a distance measuring circuit 25 and an optical deviation measuring circuit; using an on-board calculator incorporating said target position data and parameters related to the flight and position of the airplane to calculate the position of n fictitious grafts during each transmission period, previous period have been fired, n being determined to limit the number of data to be processed by the calculator, and in which a fictitious grenade such as a grenade with known balls 8 0 0 5 9 15 \ '1 ► /? · 5 , T j ^ ······ »I listical properties have been defined, which are fired synchronously with a light impulse, and to calculate the direction of a fictional danger-generating grenade, which is located at a distance from the target aircraft is approximately equal to the distance from the target to this aircraft, and in addition to calculate the position to be given on the axis of the beam for each period in order to move it almost in the direction of the keep a dangerous grenade oriented, i.e. in a direction in which it can hit the target and which is defined starting from the n mentioned grenades; and wherein the firing is empowered or validated by the operator and this empowerment is processed by the calculator to output the shelling result determined by the angular misalignment (ε) between the target and the grenade at risk during each period. Method according to claim 2, characterized in that a fictitious danger grenade is defined as a grenade, which is at the same distance (D) from the target aircraft as from the target, interpolated its position from the positions, which have two fictional grenades closest to this distance value. Airborne mimic system to simulate the firing of grenades from a bombarding aircraft to an airborne target, this system cooperating with an overhead calculator providing flight and location data. aircraft are recorded from sensors, characterized in that this system comprises transmitting means (1 - 2) for periodically emitting light pulses to illuminate a target located within a transmitting field (CE, - ö), said transmitting means from said computing device (13) which determines the transmission rhythm for this purpose, as well as optical receiving means and focusing means (J ~ S) for the radiation emitted and returned by an illuminated target, said target being situated within a receiving field (CR) 0 05 9 1 5 üe ^ SSSr L ______ U-L -I 1., l * - ~~ ~ y _ · χ coaxially extends within the transmission field, while the contraction r received light is focused on a matrix detector, which contains at least four photodetection elements (9) and the output signals of which are applied to a chronometric remote measuring circuit (11) 5 and an angular deviation switch (10) to determine the position of the target (D, EX-EY) and provide corresponding data to the calculator, the latter serving to periodically calculate the position of n fictitious grenades scaled during n previous transmission periods, where n is recorded such that this limits the number of data to be processed by the calculator, and defines a fictitious grenade as a grenade with known ballistic properties, which is fired synchronously with a light pulse, and which outputs are applied to the said circuits in order to output from the said calculate the result of the shelling. System according to claim b, characterized in that it further comprises deflectors (22) for varying the common axis of the transmitting field and the receiving field within a given deflection field (CD - β), said deflectors being of the calculator. 6. System according to claim 5, characterized in that the computing device serves to determine the position of a danger grenade as a function of the position of the target and that of n grenades, d. w. z. a grenade likely to hit the target and calculate the corresponding stance data (Θ 1, Θ 2) intended for the deflectors to set the axis in the direction of the hazard grenade, the bombardment result being interpreted by the angular deviation signals (EX, EY). System according to one of the preceding claims 1+ to 6, characterized in that the transmitting means comprise a pulse laser light source (1), the transmission rhythm of which is transmitted by means of a command signal (ST) derived by the computing device (13) is determined, and an optical element (2) through which the emitted laser beam j | m, I, |, ||| | I% ...... a diverging gradient (- Θ) is given, which corresponds to the desired illumination field. System according to claim 5 or 6 or according to claim 7 referring to one of these claims. characterized in that the deflectors comprise a spreader gauge, which is composed of two prisms (3- ^), the position of which is adjusted separately by means of respective servo devices (5-6) commanded by the calculator, the optical receiving and focusing means comprise an optical separating member (7) for separating the transmission path and the receiving path from one another, which is arranged between the transmitting means and the prisms, and further an optical focusing element (8). System according to any one of the preceding claims 15 to 8, characterized in that it consists of two boxes, in which in a first box (20) the transmitting means, the deflecting means, the optical receiving and focusing means, the detection means and the measuring means are included, and in a second box (21) the deviation measuring circuit and the interposed transition circuits for the connection to the computing device are included, 10. Method essentially as Described in the Description and / or illustrated in the examples. 11. System Mainly as Described in the Description and / or Shown in the Figures, ^ 000 5 9 1 5 ^