EP0368299B1 - Apparatus for checking the relative position of two optical axes - Google Patents

Description

The invention relates to a device according to the preamble of claim 1. Such a device is known from the unpublished EP-A-0 315 892.

To measure the axis parallelism of two optical axes, it is known from DE-C-216 854 to provide two optical deflection systems connected in a scissor-like manner via a central joint, which deflect an incident light beam in each scissor position (for example, from a light source adapted axially parallel in a weapon barrel of a weapon system is sent) in parallel. As a result, the emerging light beam (which, for example, falls into a telescopic sight of the weapon system) runs exactly parallel to the axis of the weapon barrel, regardless of the scissor angle at which the two deflection systems are positioned. The desired parallel offset can thus be achieved by adjusting the scissor angle. Each of the two deflection systems consists of a support tube for holding a positionally stable optical deflection element, a light entry or exit window being provided in the jacket of each support tube. The deflecting element of the front support tube - as seen in the direction of light incidence - consists of a rhomboid element with two reflecting surfaces running parallel to one another, whereas the deflecting element of the rear supporting tube consists of a triple element with three reflecting surfaces running at right angles to each other. Because of Given the limited length of the carrier tubes, the known measuring device is only suitable for checking small arms, but not for guns, for example anti-aircraft armored vehicles, which have offset distances of up to 1.5 meters. In order to keep the weight of the optical deflecting elements and thus the mechanical deflection as low as possible in the case of longer support tubes for the latter purpose, it is known from DE-A-3 205 610 that one behind the entry window of the deflection system of the front support tube is 45 with respect to the tube axis ° to mount the inclined plane mirror, which is opposite a 45 ° roof prism at the light exit window of the same tube. In the rear support tube, the 45 ° roof prism is replaced by a plane mirror inclined by 45 °. The light paths between the two plane mirrors or between the plane mirror and the roof prism run through the hollow tube interior. To adjust the deflection systems, e.g. B. as a result of bending of the support tubes with unequal temperature load or changed weight distributions in different scissor positions, a self-test position is provided in the latter device. In this self-test position, the two deflection systems are rotated to one another in such a way that the exit window of the rear support tube comes to lie over a test window attached to the entry window of the front support tube, as a result of which the emerging light beam is superimposed on the incoming light beam. In the case of correct adjustment, interference lines appear on an axial view of the front support tube. If such interference lines are missing, there is a misalignment of unknown magnitude; in this case the device must be completely re-calibrated at the factory. In addition, in the self-test position mentioned only the axis parallelism in this special scissor position of both carrier tubes is checked; In all other scissor positions, due to changed weight distributions and the resulting bending of the support tubes, misalignments are possible that remain undetected.

In contrast, the object of the invention is to be able to detect and correct measurement errors in all scissor positions and under all temperature conditions in a device of the type mentioned at the outset.

This object is achieved by the characterizing features of claim 1.

Advantageous refinements and developments of the device according to the invention result from the subclaims.

Fig. 1

eine schematische Schnittdarstellung eines Ausführungsbeispiels einer erfindungsgemäßen Vorrichtung in Meßstellung;

Fig. 2

eine schematische Darstellung der Vorrichtung nach Fig. 1 in Selbstprüfstellung;

Fig. 3

eine schematische Darstellung des Grundprinzips der Lichtablenkung mittels hintereinander angeordneter Rhomboid- bzw. Z-Elemente und eines abschließenden Tripelelementes;

Fig. 4

eines schematische Darstellung eines Tripelelementes bzw. tripelprismas in Blickrichtung "A" gemäß Fig. 5;

Fig. 5

eine schematische Darstellung eines Tripelprismas in Blickrichtung "B" gemäß Fig. 6;

Fig. 6

eine schematische Darstellung eines Tripelprismas in Blickrichtung "C" gemäß Fig. 7;

Fig. 7

eine schematische Darstellung eines Tripelprismas in Blickrichtung "A" gemäß Fig. 5;

Fig. 8

eine schematische Darstellung eines aus drei hintereinander angeordneten Tripelprismen bestehenden Ablenksystems, wobei die Tripelprismen aufgrund Verbiegungen des Trägerrohrs aus ihrer gegenseitigen Normallage verschoben sind;

Fig. 9

eine schematische Darstellung eines weiteren Ausführungsbeispiels einer Prüfvorrichtung in Selbstprüfstellung;

Fig. 10

eine schematische Darstellung eines vergrößerten Details der Prüfvorrichtung nach Fig. 9 in dessen Betriebsstellung "Funktionstest";

Fig. 11

eine schematische Darstellung ähnlich wie in Fig. 10 für die Betriebsstellung "Kalibriertest";

Fig. 12

eine perspektivische Darstellung für die Verwendung der Prüfvorrichtung für die Gleichlaufprüfung der rechten Waffe eines Flugabwehr-Panzerfahrzeugs;

Fig. 13

eine perspektivische Darstellung für die Verwendung der Prüfvorrichtung zur Justierung der rechten Waffe eines Flugabwehr-Panzerfahrzeugs, und

Fig. 14

eine schematische Darstellung eines Koordinatenantriebs für die Prüfvorrichtung bei der Justierung der Waffe(n) eines Waffensystems.

The invention is explained below with reference to exemplary embodiments in the drawings. It shows:

Fig. 1

is a schematic sectional view of an embodiment of a device according to the invention in the measuring position;

Fig. 2

a schematic representation of the device of Figure 1 in self-test position.

Fig. 3

a schematic representation of the basic principle of light deflection by means of rhomboid or Z elements arranged one behind the other and a final triple element;

Fig. 4

a schematic representation of a triple element or triple prism in viewing direction "A" according to FIG. 5;

Fig. 5

a schematic representation of a triple prism in viewing direction "B" according to FIG. 6;

Fig. 6

a schematic representation of a triple prism in the viewing direction "C" according to FIG. 7;

Fig. 7

a schematic representation of a triple prism in viewing direction "A" according to FIG. 5;

Fig. 8

is a schematic representation of a deflection system consisting of three triple prisms arranged one behind the other, the triple prisms being displaced from their mutual normal position due to bending of the support tube;

Fig. 9

a schematic representation of another embodiment of a test device in self-test position;

Fig. 10

a schematic representation of an enlarged detail of the test device of Figure 9 in its operating position "function test";

Fig. 11

a schematic representation similar to that in Fig. 10 for the operating position "calibration test";

Fig. 12

a perspective view of the use of the test device for the synchronism test the right weapon of an anti-aircraft armored vehicle;

Fig. 13

a perspective view of the use of the test device for adjusting the right weapon of an anti-aircraft armored vehicle, and

Fig. 14

a schematic representation of a coordinate drive for the test device when adjusting the weapon (s) of a weapon system.

The embodiment of a test device 1 according to the invention shown in FIG. 1 is composed of two longitudinal arms in the form of support tubes 2, 3, which are connected to one another in a scissor-like manner via a joint 4. The total length of the test device 1 can be infinitely adjusted as required via the connecting joint 4, the total length being understood to mean the offset between the incoming and outgoing light beam. An angle scale (not shown) is attached to the joint 4 in order to be able to set the scissor angle between the two support tubes 2, 3 in a defined manner.

The deflection optics held in each carrier tube 2, 3 comprises a number of triple elements 5, each of which has three reflection surfaces 6, 7 and 8 which are at right angles to one another. The deflection elements 5 can be made of full glass (triple prisms), surface mirrors (triple mirrors), for example in shape consist of glass tubes (Fig. 9), in which the front end is chamfered and the rear end is chamfered twice (apex 90 °), these inclined surfaces are provided with surface plane mirrors (triple mirror). Instead of a triple element 5, a rhomboid or Z element 28 can also be provided, as shown in the embodiment according to FIG. 9, which in the case of FIG. 9 consists of a glass tube with two pointed ends, which in turn are provided with surface plane mirrors are. As the comparison of FIGS. 1 and 9 shows, the rhomboid element 28 replaces two triple elements 5 in the carrier tube 2.

The geometric shape of the triple elements 5 can be seen in more detail with reference to FIGS. 4 to 7 described. Each triple element 5 contains a radiation entry region 9 and a radiation exit region 10, the triple elements 5 in the carrier tubes 2, 3 according to FIG. 1 or the triple elements 5 and the rhomboid element 28 in the carrier tube 2 and the triple elements 5 in the carrier tube 3 according to FIG. 9 in each case are arranged so that the beam exit area 10 of an element 5 or 28 is opposite the beam entry area 9 of the downstream (adjacent) element 5, that is to say the areas 9, 10 overlap one another. This overlap requires a corresponding one shown in FIGS. 1 and 9 clearly shown offset of successive elements 5, 28.

The connecting joint 4 has a free beam passage, in which, in the case of FIG. 1, a correction element 11 is arranged which has optical wedge disks which can be rotated relative to one another.

The front support tube 2 has for attaching the test device 1 e.g. on a weapon (cf. FIG. 12) a clamping joint 31 (FIG. 9) which, like the connecting joint 4, carries an angle scale, not shown.

In the jacket of the support tubes 2, 3, window openings 12a, 12b (support tube 2) and 13 (support tube 3) are provided in the region of the end faces in order to allow the radiation to enter and exit from the support tubes 2, 3. The window openings 12a and 12b lie radially opposite one another, only the window opening 12a being used for the normal operation of the test device 1 (test position according to FIG. 1). The window opening 12b is only in the self-test position of the device 1 according to FIGS. 2 and 9 used, as will be explained in more detail.

In the self-test position of the device 1 (FIGS. 2 and 9), the parallelism of the incoming and the outgoing beam is checked. This is done in that the carrier tube 2 is folded parallel to the carrier tube 3, so that the beam entering the device 1 (target line 14 'in FIG. 2) and the exit beam superimposed on the incoming beam (target line 14' in Fig. 2 ) can be observed by an observation device arranged in the emitting radiation source 15. In the case of the embodiment according to FIGS. 1 and 2, the radiation source 15 is used for the function test, which is also provided for the normal test function of the device 1 (FIG. 1), as shown in FIGS. 12 and 13 will be explained in more detail. In the case of the embodiment according to FIG. 9, an autocollimator 150 is used as the radiation source for the self-test, which is arranged in front of a third window opening 12c in the end face of the carrier tube 2. The implementation of the self-test in the device 1 according to FIG. 9 is based on FIGS. 10 and 11 explained in detail. In the case of FIG. 2, the self-test is carried out as follows:

The first reflection surface 6 at the window opening 12 of the support tube 2 is a semi-transparent mirror, e.g. partially mirrored mirrors in the visible wavelength range. As a result, the beam emerging from the radiation source 15 (target line 14 ') can be returned to the radiation source 15 as a reflected beam (target line 14˝) and the parallelism of both beams can be checked. This is done by means of a beam splitter 26 arranged in the radiation source 15 or in the mirror collimator, through which in the eyepiece 27 on the one hand the line mark 19 generated by a line mark carrier 18 of the target line 14 'and on the other hand the line mark 19' of the reflected target line 14 'can be reproduced. Any storage of the reflected line mark 19 'from the line mark 19 indicates the inaccuracy of the test device 1, which can be eliminated via the correction element 11.

For the self-test of the embodiment according to FIGS. 9, as shown in FIGS. 10 and 11 can be seen, a small auxiliary prism 62 and 81 are arranged on the first mirror surface 6 and on the last mirror surface 8 of the deflection system located in the support tube 2, the auxiliary prism 62 in the beam path of a first measuring beam 152 and the auxiliary prism 81 in the beam path of a second measuring beam 153 of the autocollimator 150. The auxiliary prism 62 sits on one semi-permeable plate 61. The plate 61 covers two circular openings 63, 64 in the reflection surface 6. In front of the autocollimator 150, an adjustable diaphragm 151 is arranged, which covers the measuring beams 152, 153 in the position according to FIG. 10 and in the position according to FIG 11 transmits the measuring beam 152 to the auxiliary prism 62 and the measuring beam 153 via the circular opening 64 to the auxiliary prism 81. In the first position of the aperture 151 according to FIG. 10, an auxiliary beam path 154 is released, which passes the auxiliary prism 62 through the circular opening 64, strikes the reflecting surface 8 next to the auxiliary prism 81 and from there into the deflection system of the rear carrier tube 3 ( which is only indicated by the beam path in Fig. 10) occurs. From there, the auxiliary beam 154 falls through the window openings 13, 12b (FIG. 9) onto the reflection surface 6 and from there into the autocollimator 150.

In the position according to FIG. 10, just as in accordance with FIG. 2, a function test of both deflection systems takes place in the support tubes 2, 3. Just as in connection with the function test description of FIG. 2, non-parallelism can also occur in the case of FIG. 10 can be recognized by a corresponding filing between a transmitted and a received line mark. A detected inaccuracy of the test device 1 - unlike in the case of FIG. 2 - is eliminated in the embodiment according to FIG. 9 by first calibrating the front deflection system (carrier tube 2) by means of the adjusting device 30a (FIG. 9). For this purpose, the calibration test illustrated in FIG. 11 is carried out, in which the congruence of the measurement marks of the autocollimator 150 reflected by the auxiliary prisms 62, 81 is checked. To check the parallelism of the reflection surfaces 6 and 8, it is not enough, only the reflections on the partially mirrored hypotenuse surfaces of the auxiliary prisms 62, 81, but also the reflections on the roof edges of the auxiliary prisms 62, 81 must be checked in order to detect a possible tilting of the reflection surfaces 6, 8 against each other. The adjusting device 30a may be adjusted until the calibration test no longer shows any deviations. This means that only the front deflection system (support tube 2) is calibrated. Subsequently, the rear deflection system (support tube 3) is also calibrated to the front deflection system by adjusting the rear deflection system in the "function test" position according to FIG. 10 by means of the adjusting device 30b until the measurement marks are no longer deposited in accordance with the auxiliary beam path 154.

As explained with reference to FIGS. 12 and 13, the test device 1 can be used for the adjustment test (FIG. 13) and for the synchronization test (FIG. 12) of the weapon barrels 101, 102 of a weapon system, in the example shown an anti-aircraft armored vehicle. In the case of the synchronism test according to FIG. 12, the test device 1 is fastened to the weapon barrel 101 to be tested by means of the clamping joint 31, while the radiation source 15 (collimator) is fastened in the rear region of the weapon barrel 101 or to its rotary bearing 104. The beam emitted by the collimator 15 strikes the light entry window 12a of the carrier tube 2 and is deflected via the device 1 to the target line 14 of the gunner's periscope 22, which is moved synchronously with the weapon 101. The attachment of the collimator 15 in the rear region of the weapon barrel 101 or of the rotary bearing 104 ensures that the collimator 15 remains unaffected by bending of the weapon barrel 101, as can occur due to the weight of the test device which is necessarily positioned further forward. As a result, that the light beam emitted by collimator 15 accurately reflects the angular position of the weapon. This exact angular position is passed on to the periscope 22 by the test device 1, regardless of its possible change in position due to the bending of the weapon barrel.
In the case of the adjusting device according to FIG. 13, the device 1 is attached with its clamping joint 31 to a stand 107 and adjusted so far that the light entry window 12a in the beam path of a collimator 15 (FIG. 1) attached in the weapon barrel 101 and the light exit window 13 in the beam path of the periscope 22. As shown in FIG. 1, the radiation source or the collimator 15 is adapted in a precise fixation in the mouth of the weapon barrel 101 in such a way that the core axis 17 of the weapon barrel 101 coincides with the target line 14 generated by the radiation source 15. Arranged in the radiation source 15 is a line mark carrier 18 (FIG. 2), by means of which a line mark 19 representing the adjustment position of the weapon 16 around the eyepiece 20 of the commandant periscope 17 can be represented via the target line 14 entering the beam path of the commander periscope 17. A possible deposit of the line mark 19 from the sighting mark 21 of the commander's periscope 17 thus indicates the adjustment deviation to be corrected between the target line of the cannon and the sighting line of the commander's periscope.

The adjustment position is checked in the same way with respect to the gunner's periscope 22, the target line 14 being able to be aligned with the beam path of the gunner's periscope by simply pivoting the longitudinal arms 2 and 3 about the axis 4 of the joint 4.

Due to the use of a mirror collimator as the radiation source 15, in addition to the visible wavelength range, also in the infrared wavelength range, e.g. 10μ range are emitted, whereby the line mark 19 can also be imaged in the thermal imaging device 23.

To check the laser transmitter 24, the window opening 13 is in the transmission beam 25 of the laser transmitter 24 and the window opening 12a in the Beam path of the radiation source 15 is pivoted, with a radiation-sensitive plate being pivoted in instead of the line mark carrier 18, with which the radiation from the laser transmitter 24 can be made visible. Panels coated with phosphorescent material are particularly suitable for this, since they are reusable. The line mark carrier 18 and the radiation-sensitive plate are arranged so that they can be pivoted into the beam path of the radiation source 15 as required. The light energy of the laser 24 is directed to the radiation source 15 via the test device and there generates an afterglow point on the radiation-sensitive plate. The angular position of this point with respect to a periscope, for example the commandant's periscope 17, can then be made visible by pivoting the window opening 13 out of the transmission beam 25 of the laser transmitter 24 into the beam path of the commandant's periscope 17. A possible deposit of the afterglow point from the sighting mark 21 of the commandant's periscope 17 indicates the adjustment deviation of the laser transmitter 24 to be corrected from the commandant's periscope 17 which has already been adjusted.

In the synchronism test (Fig. 12), the collimator 15 is first adjusted to the crosshairs of the periscope 22, e.g. by means of a side and height-adjustable bracket, not shown in FIG. After swiveling the test device 1 into the line of sight of the periscope 22, the line mark of the collimator 15 appears in the periscope eyepiece.

After the collimator 15 has been adjusted to the crosshairs of the periscope 22, the actual synchronization test can be carried out:
Setting the desired elevation angle, if necessary tracking the test device and reading the deviation in side and height using the line mark.

The synchronism check of non-optical target devices requires, as with the adjustment check, a separate telescope which is attached to the elevatable device to be tested.

3 shows the basic structure of a test device containing optical rhomboid elements 28. This also achieves a parallel offset of a target line 14 generated by a radiation source 15, for example a mirror collimator fixed in the muzzle of a cannon, with which, in the same way as with the embodiment according to FIGS. 1 and 2, the adjustment position and the synchronism of the commander's periscope 17, of the directional protection periscope 22 and other elements can be checked.

The rhomboid elements 28 each contain two mutually parallel rhomboid reflection surfaces 29 with which a Z-shaped parallel offset of the target line 14 can be achieved. In contrast to the triple element 5, a rhomboid element 28 is cheaper. The embodiment shown in FIG. 3 consists of only one longitudinal arm, but a two-armed, articulated test device corresponding to the embodiment according to FIG. 1 can also be created when using rhomboid elements.

4 to 7 show in solid lines a triple element 5 with the reflection surfaces 6, 7 and 8 and the radiation input region 9 and the radiation output region 10.

In order to enable simple assembly of the elements 5, 28 in the carrier tubes 2, 3, as shown in FIG. 9, the carrier tubes 2, 3 are each formed from two half-shells, with all elements 5, 28 of the carrier tube 2 and 3 respectively which are attached to a half shell by means of shock-absorbing clamps. These load-bearing half-shells are connected to one another via the joint 4.

For the exact setting of the test device 1, a coordinate drive 200 can also be used, as shown in FIG. 14, which has horizontally displaceable guides 201, 203 on which vertically movable carriages 202 and 204 are mounted. The ends of the test device 1 are rotatably mounted on the slides 202, 204. Any points in the coordinate plane of the drive 200 can thus be approached with the light entry and exit windows 12a and 13 of the device 1. The drive 200 is preferably designed to be program-controlled, so that the axis positions of the viewing devices or weapons of a wide variety of vehicles can be approached with the test device 1 by appropriate preprogramming.

The solution to the object achieved by the invention is illustrated with reference to FIG. 8. As can be seen from this, the deflection elements 5 of a support tube have been displaced from their mutual normal position as a result of a deflection of the support tube, without this having any consequences for the parallel offset of the incoming light beam to be exited. It is essential, however, that each individual deflection element 5 is inherently stable.

Another important advantage of the invention is that by using auxiliary prisms, a functional test of the test device and a possible (subsequent) calibration on the spot is possible, which avoids a time-consuming submission of the test device to the manufacturing plant.

Claims (7)

1. Apparatus for checking the axial position (parallel and point adjustment) of at least two optical axes, in particular the sight and target lines of a weapon system, with two optical deflecting systems (2, 3, 5, 28) connected to each other in the form of scissors, which make an incident light ray parallel in each position of the scissors and respectively comprise a support tube (2 or 3) for the mounting of at least two optical deflecting elements (5, 28), which have a stable position per se, in the form of triple elements (5) each with three reflection surfaces (8, 7, 8) extending at right angles to each other and possibly in the form of rhomboid elements (28) each with two reflection surfaces (29) extending parallel to each other, the support tubes (2, 3) being provided with a light inlet and light outlet window (12a, 13) and adjacent triple elements (5) or rhomboid elements (28) being staggered with respect to each other so that their ray inlet and ray outlet regions (9, 10) overlap, characterized in that at right angles to its light inlet window (12a), the front support tube (2) receiving the incident light ray comprises a further light inlet window (12c) provided for automatic checking purposes, that located on the further light inlet window (12c) is an autocollimator (150), which emits a measuring light (152) and receives it again (153), that located on the first (6) and last (8) mirror surface of the deflecting system (5, 28) of the front support tube (2) is respectively a small auxiliary prism (62 or 81) so that the auxiliary prisms (62, 81) reflect the measuring light (152, 153) of the autocollimator (150) along different axial positions.
2. Apparatus according to Claim 1, characterized in that located in front of the autocollimator (150) is an adjustable diaphragm (151), which in a first position (function test; Figure 10) deflects the measuring light (152, 153) to the auxiliary prisms (62, 81) and leaves an auxiliary ray path (154) free, which serves for a function test of both deflecting systems (2, 3, 5, 28), and which in a second position (calibrating test; Figure 11) allows the measuring light (152, 153) to reach the auxiliary prisms (62, 81) and covers the auxiliary ray path (154), that furthermore a mirror surface of the deflecting elements (5, 28) of the front support tube (2) can be adjusted in its position (adjusting device 30a; Figure 9), in case, in the autocollimator (150), the images produced by reflection by the auxiliary prisms (62, 81) are not congruent, and that a mirror surface of the deflecting elements (5, 28) of the other support tube (3) can be adjusted in its position (adjusting device 30b; Figure 9), in case a measuring mark is not congruent with its image produced by the auxiliary ray path (154) in the autocollimator (150).
3. Apparatus according to Claim 1 or 2, characterised in that at their ends the support tubes (2, 3) are located on separate carriage guides (202, 204) of a coordinate drive (200), the carriage guides (202, 204) being able to travel into pre-programmed positions (Figure 14).
4. Apparatus according to one of Claims 1 to 3, characterised in that each support tube (2, 3) consists of two half-shells (2a, 2b or 3a, 3b) and all the deflecting elements (5, 28) of the respective support tube (2 or 3) are attached to one half-shell (2a or 3a) in a shock-absorbing manner.
5. Apparatus according to one of Claims 1 to 4, characterised in that an angle scale is respectively located on a clamping joint (31) of the front support tube (2) and on a connecting joint (4) between both support tubes (2, 3).
6. Apparatus according to one of Claims 1 to 5, characterised in that the deflecting elements (5, 28) consist of surface mirrors or of solid glass.
7. Apparatus according to one of Claims 1 to 5, characterised in that the deflecting elements (5, 28) consist of glass tubes which are bevelled once or twice on the end faces, the inclined surfaces of the glass tubes being provided with plane surface mirrors.

Images