• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an actuating element (1) for adjusting the position of a target of a telescopic sight with a head module and a trunk module, wherein the head module and the trunk module are interconnected by a coupling mechanism and the coupling mechanism for separating the head module of the trunk module is manually operable.
    公开号:AT516059A4
    申请号:T50907/2014
    申请日:2014-12-15
    公开日:2016-02-15
    发明作者:Peter Dipl Ing Öttl；Helmut Wiedermann
    申请人:Swarovski Optik Kg；
    IPC主号:
    专利说明:

    The invention relates to an actuating element for adjusting the position of a target of a telescopic sight according to the preamble of claim 1.
    When shooting a weapon together with a target device or a riflescope usually first occurring deviations of the actual impact point of a projectile from the desired impact point or the position of the target are eliminated by the orientation of the target carrying the inner tube is changed using generic actuators. Such a shooting is known to occur at a fixed firing distance (for example, 100 m) with a horizontally aligned line of sight at a target and using a munition typical of the weapon. Generic, also known as towers, actuators also allow the consideration of occurring in practice deviations from the original Einschießbedingungen beyond. These influencing factors, which must be taken into account, include, above all, a target distance deviating from the original shotgun distance as well as ballistic characteristics of the ammunition used or the bullet used. In the prior art, it is therefore also known to provide generic actuators with one or more, push-on index elements. With the aid of markings affixed to the index elements, it is possible to make adjustments to the setting towers as quickly as possible by taking into account deviating firing ranges and / or types of ammunition used. In the prior art, actuators used as so-called side towers are known with which crosswind can be considered. A disadvantage of known from the prior art actuators that changes in the setting of the index elements are often cumbersome and costly only possible using tools. Also, making such changes to the settings proves to be very error prone.
    It is the object of the invention to provide an actuator with which the adjustment of the position of a target of a riflescope can be made easier and with greater flexibility.
    The object of the invention is achieved by an actuating element for adjusting the position of a target of a telescopic sight with a head module and with a trunk module, wherein the head module and the trunk module are interconnected by a coupling mechanism and wherein the coupling mechanism for separating the head module of the trunk module manually operable is. This has the advantage that the head module can be easily separated from a user by the fuselage module remaining on the riflescope without the need for additional tools. However, a particular advantage of the actuating element is also that head modules which are designed with specific or different functionalities can be combined with the same trunk module almost as desired.
    According to an advantageous development of the actuating element, it is provided that for marking a predeterminable position of the target, the head module comprises a scale and the trunk module a zero index. The head module preferably comprises a carrier sleeve, the scale being attached to this carrier sleeve. According to a further advantageous embodiment, it is provided that at least one index element for identifying a predeterminable position of the target mark is fixed in a rotationally fixed manner to the rotary sleeve. It is further provided that the fuselage module comprises a latching housing, a spindle rotatably mounted in the latching housing about a rotation axis and a latching hub rotatable about the rotation axis for moving the spindle. It is also envisaged that the carrier sleeve is rotationally coupled to the locking hub.
    Another advantage is the development according to which the coupling mechanism forms part of a locking mechanism, wherein the locking mechanism a
    Clamping plant with preloaded springs covers. The locking mechanism also has an operating element, which is in operative connection with the tensioning device, wherein the connection between the head module and the trunk module can be released by actuating the operating element. Preferably, the operating element of the closing mechanism is formed by a push button.
    If, in connection with the separation or assembly of the head module and the trunk module of the actuating element according to the invention, it is said that this can be done by manual actuation, it is expressly understood that this can be done without the aid of special separate tools. That is, to release or restore the connection between the head module and the trunk module, the bare hands of a user are sufficient.
    According to a preferred embodiment, an actuating element for adjusting the position of a target of a telescopic sight is provided, which is formed with a locking housing, a rotatably mounted in the locking housing about a spindle axis spindle, a rotatable about the rotation axis locking hub for moving the spindle and a support sleeve. In this case, the support sleeve is rotationally coupled to the locking hub and is rotatably fixed to the support sleeve at least one index element for identifying a predeterminable position of the target. The carrier sleeve and the at least one index element form components of a head module. The locking housing, the spindle and the locking hub form part of a fuselage module. The head module and the trunk module of the actuating element are connected to one another by a closing mechanism, wherein the closing mechanism comprises a tensioning mechanism with pretensioned springs. This has the advantage that differently set but equally modular head modules in the thus formed actuator can be easily replaced. This will also make a larger number of pre-set positions of the target available. However, this embodiment of the actuating element is also advantageous in the case of damage to the head module, where it can easily be exchanged for a reserve head module, but on the other hand, the trunk module can also be used on its own.
    Advantageously, the locking mechanism comprises a push button, which is in operative connection with the tensioning device, wherein the connection between the head module and the trunk module can be released by pressing the push button. So it is sufficient a simple manual operation of the locking mechanism on the push button, without the need for a special, additional tool would be required.
    Due to the design of the actuating element, according to which the clamping mechanism of the closing mechanism has at least two stable layers, on the one hand an open and on the other hand a closed state of the clamping mechanism can be maintained respectively, whereby the removal of the head module as well as the placement of the head module on the trunk module are facilitated.
    According to a development of the actuating element, the clamping mechanism of the closing mechanism comprises sleeves which are arranged coaxially with respect to the axis of rotation and are movable into one another. This has the advantage of a compact internal structuring, since even with a thin-walled design of the sleeves still a relatively high mechanical stability can be achieved.
    Furthermore, it is provided that the closing mechanism comprises a frame sleeve and a locking sleeve displaceable in the frame sleeve, wherein in a lower end portion of the locking sleeve at least one radially extending tunnel is formed and in the tunnel at least one locking ball is arranged, wherein the at least one locking ball in the radial direction is movable back and forth. Depending on the position of the locking ball at one end or at the other end of the tunnel, the blocking ball can fulfill in two ways the function of a blocking device or latch relative to the relative displacement of the locking sleeve in the axial direction.
    An advantageous embodiment of the actuating element is also that the locking sleeve has at least one axially extending slot and the frame sleeve at least one standing with the slot engaged pin. As a result, a clearly limited adjustment away the locking sleeve is defined. In the actuating element is also provided that the locking hub comprises an upper tube portion having an encircling groove on an inner side, and further that in a connected state of the head module and trunk module, the lower end portion of the locking sleeve is received in the upper tube portion of the locking hub, wherein the at least one locking ball is engaged in the groove of the locking hub. This has the advantage that in each angular position of the head module relative to the fuselage module a positive connection can be made.
    The locking mechanism of the actuating element further comprises an outer clamping sleeve and a first, outer compression spring which is arranged between the frame sleeve and the outer clamping sleeve and held clamped. This has the advantage that when the connection is released by pressing the push button, the entire head module is lifted automatically under the action of this compression spring.
    It is also advantageous that the closing mechanism comprises an inner clamping sleeve and a second, inner compression spring, which is arranged and clamped between the locking sleeve and the inner clamping sleeve. And further, that in the connected state of the head module and the trunk module, a lower end region of the inner clamping sleeve bears against the at least one blocking ball and keeps it locked in the circumferential groove of the locking hub. This will maintain a closed state by itself.
    Also advantageous are developments of the actuating element, according to which the inner clamping sleeve has an encircling groove on an outer side, wherein in an intermediate position when separating the head module and the fuselage module, the at least one locking ball is at least partially received in the circumferential groove of the inner clamping sleeve and in a separate state of Head module and fuselage module, the at least one blocking ball is held in its radial position in the tunnel (49) by a constriction formed in the outer end region of the tunnel (49). Thus, the locking ball can be kept in a defined position.
    In the actuating element is also provided that the frame sleeve has at an upper end portion an outwardly projecting upper disc portion which is connected to the carrier sleeve, wherein the Scheibenab section is screwed with a thread in the carrier sleeve. In the upper end portion of the frame sleeve also a screw ring is fixed, by which the inner clamping sleeve is held clamped with the second, inner compression spring. The locking mechanism of the actuator can therefore be easily assembled or disassembled.
    Also advantageous is the development of the actuating element, according to which the push button is connected with the interposition of a compression spring with the inner clamping sleeve. The push button is thus kept in a defined position and delays the action on the clamping mechanism of the locking mechanism to the first to be overcome spring travel. An erroneous or unintentional successful separation of the head module of the trunk module can be prevented as far as possible.
    Also advantageous is the development of the actuating element, according to which the push button comprises a pivot pin which is latched with locking lugs on an inwardly projecting projection of the inner locking sleeve. The connection between the Druckkknopf and the inner locking sleeve is thus easy to prepare but also released again.
    Furthermore, it is provided that the push button is held by the pressure spring arranged between the inner clamping sleeve and the push button in a maximum raised position.
    Further details of the present invention will be described with reference to a preferred embodiment in the following description of the figures.
    For a better understanding of the invention, this will be explained in more detail with reference to the following figures.
    In each case, in a highly simplified, schematic representation:
    Fig. 1 shows an actuating element arranged in perspective on the main tube of a telescopic sight;
    2 shows a longitudinal section of the actuating element.
    3 shows a longitudinal section of the head module of the actuating element;
    4 shows a longitudinal section of the fuselage module of the actuating element;
    Fig. 5 shows a detail of the arranged on the trunk module closing mechanism cut.
    By way of introduction, it should be noted that in the differently described embodiments, the same parts are provided with the same reference numerals or the same component names, wherein the disclosures contained in the entire description can be mutatis mutandis to the same parts with the same reference numerals or component names. Also, the location information chosen in the description, such as top, bottom, side, etc. related to the immediately described and illustrated figure and these position information in a change in position mutatis mutandis to transfer to the new location.
    Fig. 1 shows an inventive actuating element 1 for adjusting the position of a target of a riflescope in a position mounted on a tube 2 of the riflescope position shown in perspective. The upper part of the actuating element 1 comprises first a support sleeve 3 with an attached scale 4 for indicating the extent of rotation about a rotation axis 5. The scale 4 bearing annular portion of the support sleeve 3 acts simultaneously as a first index element to display the set position of Target of the riflescope. For this purpose, on the other hand, a zero index 7 is attached to a below the support sleeve 3 rotatably disposed index ring 6.
    At the top, a second index element 8, a third index element 9 and a fourth index element 10 adjoin the first index element of the carrier sleeve 3. These index elements 8, 9, 10 are attached to the carrier sleeve 3 and rotatably connected thereto. At an upper end region of the carrier sleeve 3, a cap ring 11 is finally screwed onto the carrier sleeve 3 above the fourth index element 10. The thus associated with the support sleeve 3 index elements 8, 9, 10 together with the support sleeve 3 and the screwed cap ring 11 a knob 12 of the actuator. 1
    To secure against rotation of the respective angular position of the index elements 8, 9, 10 on the support sleeve 3 can be provided that the cap ring 11 when screwed onto the support sleeve 3 with the index elements 8, 9, 10 engages in such a way that this finally by generating a Frictionally pressed against each other and fixed in such a way. In the preferred embodiment described here, however, it is provided that between the index elements 8, 9, 10 and a cylinder jacket surface of the support sleeve parallel to the direction of the axis of rotation 5 extending interlocking teeth are provided which prevent inadvertent rotation of the index elements 8, 9, 10 im prevent the carrier sleeve 3 deferred state by a positive fixation. Such a technical solution is described in detail in the document EP 1 959 221 A2 of the same Applicant in detail.
    The actuating element 1 further includes a locking ring 13 in its end region facing the tube 2 of the telescopic sight. This locking ring is designed to be rotatable or pivotable about the axis of rotation 5. The locking ring 13 makes it possible to fix the adjusting knob 12 in its angular position and thus to prevent inadvertent rotation of the adjusting knob 12.
    Finally, in the illustration according to FIG. 1, a pushbutton 14 which can be actuated by a user can still be seen in the cap ring 11. As will be explained in more detail below, with the aid of which the actuating element 1 can be disassembled into a second module part remaining on the tube 2 of the riflescope, on the one hand, and a second module part which can be removed therefrom on the other hand. The module-like construction of the actuating element achieved in this way allows a very convenient and rapid exchange of different but correspondingly modular control knobs 12.
    2 shows a longitudinal section corresponding to the axis of rotation 5 of the actuating element 1 partially shown in perspective. Here, first of all, the previously described jointly rotatable parts of the adjusting knob 12 of the actuating element 1 can be seen. These are, above all, the carrier sleeve 3 with the second, third, fourth index elements 8, 9, 10 attached thereto and the cap ring 11 held on top thereof
    Adjustment knob 12 is finally transmitted to a spindle 15 which is rotatably mounted in a locking housing 16 about the rotation axis 5 in a thread. The locking housing 16 is in turn screwed into a corresponding opening of the tube 2 of the riflescope, the spindle 15 protruding from the bottom of the locking housing 16. As is well known in the art, the spindle 15 presses on an inner tube (not shown) disposed in the barrel 2 of the riflescope which carries the aiming mark. Depending on the extent to which the spindle 15 protrudes from the latching housing 16, the inner tube is oriented more or less obliquely relative to a longitudinal axis 17 of the tube 2. Thus, a screwing in or unscrewing the spindle 15 allows a change in the position of the target or the reticle when looking through the scope. As also known from the prior art, such an adjustment causes a change in the spatial position of the sighting line of the telescopic sight relative to the barrel axis of the firearm on which the scope is mounted.
    The modular construction of the actuating element 1 according to the invention can be better seen from the illustrations of FIGS. 3 to 5. FIG. 3 shows a head module 18 and FIG. 4 shows a trunk module 19 of the actuating element separately. Finally, Fig. 5 shows the fuselage module 19 with a locking mechanism 20 of the head module 18 attached thereto (Fig. 3). For reasons of clarity, the other parts of the head module 18 are not shown.
    The head module 18 has an intermediate housing 21 as a housing part fixed to the body module 19. The intermediate housing 21 has as components of its shape a substantially tubular portion 22 and an adjoining inwardly facing collar in the form of an annular disc-shaped portion 23. The adjusting knob 12 is rotatably mounted on the intermediate housing 21, in which the support sleeve 3 is inserted into the collar-shaped portion 23 of the intermediate housing 21 and fixed by a securing ring 24 in the axial direction (the axis of rotation 5). For this purpose, a groove 26 formed on the outer circumference for receiving the securing ring 24 is provided in a lower sleeve section 25 of the carrier sleeve 3.
    The support sleeve 3 can be roughly divided into the lower sleeve portion 25, an upper sleeve portion 27 and an attaching between the lower sleeve portion 25 and the upper sleeve portion 27 outwardly projecting collar 28. At the periphery of the collar 28 of the support sleeve 3 is already mentioned in the introduction scale 4 attached.
    For forwarding or transmitting a rotational movement upon actuation of the adjusting knob 12 to the spindle 15 of the actuating element 1, the lower sleeve portion 25 of the support sleeve 3 an internal toothing 29. In the mounted state on the fuselage module 19 (FIG. 2), this toothing 29 of the carrier sleeve 3 engages with a complementary outer toothing 30 of a latching hub 31 rotatably mounted in the fuselage module 19. In addition to an upper pipe section 32, the locking hub 31 has a disk portion 33 projecting outwards (FIG. 4). With the help of this disc portion 33, the locking hub 31 is rotatably mounted at an upper edge 34 of the cup-shaped locking housing 16. The upper, outer edge 34 of the latching housing 16 is also encompassed by a positioning ring 35 with a screw ring 36. The positioning ring 35 is mounted in the manner of a union nut on the edge 34 of the locking housing 16. The upper edge 34 of the locking housing 16 on the one hand and the screw ring 36 on the other hand close the disc portion 33 and thus determine the axial position of the locking hub 31. The locking housing 16, the positioning ring 35 and the screw ring 36 so form a bearing for the locking hub 31, the order the common rotation axis 5 is rotatable.
    Driven by the knob 12 is finally the rotational movement of the locking hub 31 on the spindle 15, which in turn is rotatably mounted in the thread of the locking housing 16, transmitted. A special feature of the described embodiment of the actuating element 1 is also that the movements of the spindle 15 and the locking hub 31 in the direction of the axis of rotation 5 are decoupled from each other. For this purpose, the spindle 15 at its upper end region on an external toothing, which is in engagement with a corresponding internal toothing of the locking hub 31 (Fig. 4). While the spindle 15 also performs an up or down movement during a rotation, the axial position of the latching hub 31 remains unchanged. In the same way, this also applies to the adjusting knob 12 or to the entire head module 18. This has the advantage that the height of the actuating element 1, with which this projects beyond the tube 2, always remains unchanged.
    The positioning ring 35 is formed at least at one point of its circumference with a downwardly projecting nose 37. In addition, a radially outward pin 38 is attached to its periphery. In the assembled state of head module 18 and trunk module 19, the pin 38 of the positioning ring 35 comes to lie in a correspondingly axially extending recess 39 (FIG. 2) on the inside of the sleeve-shaped section 22 of the intermediate housing 21. On the other hand, in the provided in the tube 2 opening for screwing the actuating element 1, a recess 40 for receiving the nose 37 of the positioning ring 35 is provided. By the nose 37 and the pin 38 of the positioning ring 35 thus a rotation for relative alignment of the intermediate housing 21 of the head module 18 is realized in its relative position to the positioning ring 35 and the tube 2 of the riflescope. Alternatively to the described pin 38, e.g. Also be provided a key to prevent rotation.
    In the fully assembled state, that is, when both the locking housing 16 is screwed into the tube 2 and the head module 18 is mounted and secured to the fuselage module 19, the locking housing 16, the positioning ring 17 and the intermediate housing 21 together form a rotatably mounted housing. Relative to this housing, the adjusting knob 12, the locking hub 31 and the spindle 15 of the actuating element 1 are rotatable together.
    As known per se from the prior art, a latching device 41 is provided between the latching hub 31 and the latching housing 16. By the latching device 41 ensures that the rotation of the locking hub 31 is always incremented, that is, stepwise, to a predetermined, smallest angle unit. The
    Division or incrementation of the latching device 41 corresponds favorably to the graduation provided on the scale 4.
    As has already been mentioned, for securing the head module 18 on the trunk module 19, a closing mechanism 20 acting between these two modules is provided. For this purpose, the upper tube section 32 of the locking hub 31 on its inner side a circumferential groove 42. By means of the locking mechanism 20 formed in the adjusting knob 12, a blocking ball 43 is held in such a position that a positive connection is established and maintained between the locking hub 31 and the blocking ball 43 or the closing mechanism 20.
    Between the locking mechanism 20 of the head module 18 and the upper tube section 32 of the locking hub 31 of the fuselage module 19 thus a so-called locking mechanism is formed, wherein the locking ball 43 forms a bolt or the locker, which engages in the groove 42. The upper tube section 32 of the locking hub 31 acts as a so-called locking piece of the locking mechanism. By operating the closing mechanism 20, the locking ball 43 can be moved back and forth between different positions. In the position of the blocking ball 43 shown in FIG. 5, this prevents a lifting of the head module 18 in the direction of the axis of rotation 5 by a positive connection with the groove 42 of the upper tube section 32 of the locking hub 31.
    For reasons of better clarity, the fuselage module 19 is shown in FIG. 5 together with the closing mechanism 20, however, without the other parts of the head module 18 (FIG. 3). With the help of this locking mechanism 20, it is possible in a particularly simple manner to establish or release the connection between the head module 18 and the trunk module 19. In particular, no special or no additional tool is required for this purpose. To release the connection depressing the push button 14 of the locking mechanism 20 is sufficient. Both the release and the restoration of the connection is thus semi-automatic.
    The closing mechanism 20 is designed as a so-called clamping mechanism, that is, as a biased springs having switching element that can assume different stable positions. The different positions of the mechanism of the locking mechanism 20 allow a change of the locking ball 43 from an open position in which the locking ball 43 is not engaged in the groove 42 of the pipe section 32 of the locking hub 41, in a closed position in which the locking ball 43 in the Groove 42 is engaged.
    According to this embodiment of the actuating element 1, the closing mechanism 20 comprises a plurality of sleeve-like coaxial telescoping elements whose relative position is determined by acting between them biased springs. These elements include first a frame sleeve 44 with a telescopically sliding therein locking sleeve 45. The frame sleeve 44 together with the support sleeve 3 a fixed housing part of the locking mechanism 20 (Fig. 3). For this purpose, the frame sleeve 44 has an outwardly projecting, upper disc portion 46 with a thread, by means of which the frame sleeve 44 is screwed into the support sleeve 3. With the frame sleeve 44, a radially aligned pin 47 is further connected, which engages in an opening formed in the locking sleeve 45 slot 48 and is in engagement with the slot 48. The pin 47 forms a stop by which the range of movement of the possible displacement of the locking sleeve 45 in the direction of the axis of rotation 5 is limited.
    The locking sleeve 45 finally has at its lower end a radially aligned tunnel 49 for the locking ball 43. The tunnel 49 thus allows a change in the position of the blocking ball 43 in the radial direction.
    For the purpose of a symmetrical distribution of forces or to prevent jamming of the telescoping sleeves, it is advantageous to provide at least two or more locking balls 43 or pins 47 and slots distributed equidistantly over the circumference. According to this embodiment, three of these elements are provided distributed at an angular distance of 120 ° each over the circumference.
    The closing mechanism 20 has, in addition to the frame sleeve 44 and the locking sleeve 45, also an outer clamping sleeve 50 and an inner clamping sleeve 51, which are also displaceable axially (in the direction of the axis of rotation 5). In a lower end region of the inner clamping sleeve 51, a circumferential groove 52 for receiving the locking balls 43 is formed in the outer cylinder jacket. On the other hand, the outer clamping sleeve 50 in its lower end region on an inwardly projecting disc portion 53. Depending on the position of the lower end portion or the groove 52 of the inner clamping sleeve 51 and the disc portion 53 of the outer clamping sleeve 50 take relative to the tunnel 49 in the locking sleeve 45, the locking balls 43 are either in the groove 42 of the locking hub 31 or in the groove 52 of the inner clamping sleeve 51st
    In order to hold the different sleeves 44, 45, 50, 51 fixed relative to one another in their position, the closing mechanism 20 also has correspondingly pretensioned springs which exert a corresponding adjusting force or restraining force between them. It is a first, outer compression spring 54 which comes between the frame sleeve 44 and the outer clamping sleeve 50 to act. On the other hand, a second, inner compression spring 55 is arranged or clamped between the locking sleeve 45 and the inner clamping sleeve 51. The outer compression spring 54 and the inner compression spring 55 are each formed by a cylindrical coil spring. Accordingly, the outer compression spring 54 is disposed in a clearance between an inner diameter of the outer collet 50 and an outer diameter of the frame sleeve 44. On the other hand, the inner compression spring 55 is disposed in a cylindrical space between an inner diameter of the lock sleeve 45 and an outer diameter of the inner clamping sleeve 51. When installed, the compression springs 54, 55 exert spring forces, which are directed parallel to the axis of rotation 5. In this case, the first, outer compression spring 54 is supported upwardly against the disc portion 46 of the frame sleeve 44 and down against the disc portion 53 of the outer clamping sleeve 50. The second, inner compression spring 55 is supported at the bottom of the locking sleeve 45 and to the top towards the inner clamping sleeve 51 from. The inner clamping sleeve 51 and the locking sleeve 45 are also together with the inner compression spring 55 by a
    Screw ring 56 held in the frame sleeve 44. The screw ring 56 is screwed into the area of the disc portion 46 of the frame sleeve 44 in this.
    The push button 14 for manual operation of the locking mechanism 20 is connected to the inner clamping sleeve 51, wherein it is resiliently mounted in the inner clamping sleeve 51. Alternatively, the push button 14 could be rigidly connected to the inner clamping sleeve 51. According to this embodiment, the push button 14 has a formed with a longitudinal slot axle bolt 57 which is latched with locking lugs on an inwardly projecting projection of the inner locking sleeve 51, wherein the axle pin 57 is also displaceable in the direction of the axis of rotation 5. A disposed between the inner clamping sleeve 51 and the push button 14 compression spring 58 holds the push button 14 in a maximum raised position. This ensures that the downward movement of the inner clamping sleeve 51 for actuating the locking mechanism 20 is only delayed initiated. In fact, in the first phase, only compression of the compression spring 58 takes place, and only when the push-button 14 comes into contact with the upper end of the inner clamping sleeve 51, the inner clamping sleeve 51 is displaced downwards.
    The illustration according to FIG. 5 shows the closing mechanism 20 in the closed position. The outer compression spring 54 between the frame sleeve 44 and the outer clamping sleeve 50 is in its maximum compressed state. On the other hand, the inner compression spring 55 is located between the locking sleeve 45 and the inner clamping sleeve 51 and the frame sleeve 44 in a relaxed state. The locking balls 43 are engaged in the groove 42 of the locking hub 31 and is prevented by the lower edge region of the inner clamping sleeve 51 that the locking balls 43 in the tunnel 49 of the locking sleeve 45 can change their position. The locking balls 43 and the groove 42 of the locking hub 31 thus effect a positive connection between the trunk module 19 and the head module 18 of the actuating element 1, which is maintained as long as not by depressing the push button 14, the inner clamping sleeve 51 is moved downward.
    To open the locking mechanism 20 between the call module 19 and the head module 18, the push button 14 is manually depressed and takes place after overcoming the restoring force of the compression spring 58 of the push button 14 finally a downward movement of the inner clamping sleeve 51. As a result, the groove 52 is moved so far that the locking balls 43 can change their position in the tunnel 49 of the locking sleeve 45 and these are then absorbed by the groove 52 of the inner clamping sleeve 51. This change in position of the locking balls 43 is supported by the released spring force of the outer compression spring 54 between the outer clamping sleeve 50 and the frame sleeve 44. The extension of this second, outer compression spring 54 has the consequence that the entire connected to the frame sleeve 44 head module 18 of the Hull module 19 is lifted. The lower disc section 53 of the outer clamping sleeve 50 is supported on the upper tube section 32 of the locking hub 31. Together with the frame sleeve 44 thereby displaces the locking sleeve 45 relative to the outer clamping sleeve 50 further upwards and thus retracts into the interior of the outer clamping sleeve 50. The lower disc portion 43 of the outer clamping sleeve 50 comes to lie in an upper region of the fleas or the diameter of the tunnel 49 of the Sperrhüle 45. The - relative to the frame sleeve 44 - taking place downward movement of the outer clamping sleeve 50 is limited by a ring on the outer clamping sleeve 50 annular projection 59 and a corresponding step 60 on the inside of the support sleeve 3.
    The locking balls 43 remain during the opening operation of the locking mechanism 20 but only temporarily in the groove 52 of the inner clamping sleeve 51. Namely, by the locking sleeve 45 further moved out of the upper tube portion 32 of the locking hub 31, the locking balls 43 in the tunnel 49 back to the outside be moved. This is caused by the relative displacement of the inner clamping sleeve 51 relative to the locking sleeve 45 due to the expansion of the inner compression spring 55. As a result, the locking balls 43 are pushed simultaneously through the lower end portion of the inner clamping sleeve 51 to the outside. A restriction in the outer end region of the tunnels 49 (not shown) prevents the locking balls 43 from falling out of the tunnels 49. The head module 18 can finally be further lifted in its entirety by the fuselage module 19 and the two modules are completely separated from each other.
    By changing the closing mechanism 20 from the closed to the open state, the state of tension of the outer compression spring 54 is also changed. The outer compression spring 54 has experienced a change from a maximum tensioned state to a relaxed state. In contrast, the inner compression spring 55 has been compressed by the relative displacement of the inner clamping sleeve 51 relative to the locking sleeve 45, after which it has reverted to its original relaxed state.
    Conversely, when the head module 18 of the actuating element 1 is to be reconnected to the fuselage module 19, there is a change in the voltage states of the two compression springs 54, 55, respectively, in the reverse order. When placing the head module 18 on the fuselage module 19 first come the locking balls 43, and the locking elements 43 to lie on the inside of the upper pipe section 32 of the locking hub 31. The upper pipe sections 32 of the locking hub 31 is preferably formed at its inner edge with a chamfer. Now, the head module must first be pressed under the resistance of the inner compression spring 55 down. As a result, the locking sleeve 45 moves axially in the frame sleeve 44 upwards until the locking balls 43 are pressed into the circumferential groove 52 of the inner clamping sleeve 51. Subsequently, now also the lower disc portion 53 of the outer clamping sleeve 50 comes to rest on the upper tube portion 32 of the locking hub 31 of the fuselage module 19 and now the resistance of the outer compression spring 54 must be overcome. Once the head module 18 is pushed so far down that the locking balls 43 can escape into the circumferential groove 42 of the locking hub 31, they are pressed under the action of the inner compression spring 55 in this. The inner compression spring 55 moves the inner clamping sleeve 51 so far back to the top that its lower end, the locking balls 43 in the groove 42 of the locking hub 31 latched holds. Thus, the closed state of the locking mechanism 20 is restored.
    When placing the head module 18 on the fuselage module 19 so first, the locking sleeve 45 is moved relative to the inner clamping sleeve 51 and against the action of the inner compression spring 55 to the top. The locking balls 43 perform a sequence of movements in the tunnels 49 first in the groove 52 of the inner clamping sleeve 51 into it, finally to re-enter the groove 42 of the locking hub 31. The lower end region of the inner clamping sleeve 51 then assumes a position relative to the tunnels 49, which prevents the locking balls 43 from being able to move away from the groove 42 of the latching hub 31 again. The locking mechanism 20 of the actuating element 1 is then again in its original, closed state, in which between the locking balls 43 and the groove 42 of the locking hub 31, a positive connection is maintained.
    The axial mobility of the locking sleeve 45, the inner clamping sleeve 55 and the outer clamping sleeve 54 relative to each other and relative to the frame sleeve 44 and the interaction of the spring forces of the outer compression spring 54 and the inner compression spring 55 allow the placement of the head module 18 only by pressing the selbigen , without that the push button 14 must be pressed. The thus formed locking mechanism 20 allows a particularly comfortable operation of the actuating element 1 by a user. To assemble the head module 18 and the trunk module 19, it is sufficient to grasp the head module 18 on its outer circumference, to put it on the trunk module 19 and to press it down while the locking mechanism 20 automatically engages.
    The structural design of the connection between the head module 18 and fuselage module 19 by a fully extending groove 42 and trained as balls locker (locking balls 43) has a particular advantage that the connection between the locking sleeve 45 and the locking hub 31 for any relative angular positions with respect Rotation axis 5 can be produced. For the relative angular position between the head module 18 and the fuselage module 19 are in this embodiment, only the pin 38 in the positioning ring 35 and provided for this axially extending recess 39 on the inside of the intermediate housing 21 of the head module 18 determining. When placing the head module 18 on the fuselage module 19 therefore first the recess 39 and the pin 38 of the positioning ring 35 are aligned with each other. That is, a further assembly of the two modules 18, 19 can only take place when the pin 38 of the positioning ring 35 is received in the recess 39 of the intermediate housing 21.
    According to the embodiment described above, the locking mechanism 20 is formed with the push button 14 for performing the required switching movements of its individual parts. However, according to alternative embodiments, the locking mechanism 20 may be operated by other controls instead of the push button 14. Thus, for example, a rotary knob or rotary handle but also a linearly displaceable in the axial direction operating ring or a sliding sleeve may be provided as an operating element.
    Also as an alternative to the embodiment described above, instead of the locking balls 43 and differently shaped locking elements may form components of the coupling mechanism and the locking mechanism 20. Such an alternative blocking element could be, for example, an elongated pin with rounded ends, which is mounted in the tunnel 49. Such a pin could also be designed with a cross section other than a circular one. Accordingly, the cross-section of the tunnel 49 to form such a profiled pin would be complementary with a profiled cross-section.
    According to another embodiment, it is also possible in an alternative embodiment, deviating from the radial orientation of the tunnels 49 to provide obliquely upwardly or obliquely downwardly extending tunnels 49.
    As an alternative to the arrangement of the groove 42 on the inner circumference of the pipe section 32 of the locking hub 31, a groove for receiving the locking balls 43 could also be provided on an outer circumference of the locking hub 31.
    Another possibility of an alternative embodiment of the Betätigungsele-mentes 1 is to provide the locking mechanism 20 instead integrated in the head module 18 in the fuselage module 19.
    In principle, the design of the actuating element 1 by a head module 18 and a fuselage module 19, which is interconnected by the described coupling mechanism or the closing mechanism 20, of particular advantage, because accordingly structurally identical adjusting knobs 12 light, that is without the use of additional tools, can be exchanged.
    So it is possible in this embodiment of the actuating element 1, in the product to be sold with the scope first a simpler knob 12 (for example, without additional index elements 8, 9, 10) deliver. Should this be desired, then the actuator 1 can be retrofitted later by adjusting knobs 12 which are equipped with index elements 8, 9, 10.
    In particular, the inventive design of the actuating element 1 by a head module 18 and a trunk module 19 also allows retrofitting with additional functions to be provided in the control knobs 12. For example, a retrofitted setting knob 12 could be equipped with functional elements or operating elements of a range finder, a compass, a lamp or else a laser pointer.
    But it is also advantageous that in the event of damage to the adjusting knob 12, this can be removed separately and brought to repair, while the scope or weapon equipped with it can remain with the user.
    The embodiments show possible embodiments of the actuating element 1, wherein it should be noted at this point that the invention is not limited to the specifically illustrated embodiments thereof, but also various combinations of the individual embodiments are mutually possible and this variation possibility due to the teaching of technical action representational invention in the skill of those skilled in this technical field.
    Furthermore, individual features or combinations of features from the different exemplary embodiments shown and described can also represent independent, inventive or inventive solutions.
    The task underlying the independent inventive solutions can be taken from the description. All statements of value ranges in the present description should be understood to include any and all sub-ranges thereof, e.g. is the statement 1 to 10 to be understood that all sub-areas, starting from the lower limit 1 and the upper limit 10 are included, ie. all sub-areas begin with a lower limit of 1 or greater and end at an upper limit of 10 or less, e.g. 1 to 1.7, or 3.2 to 8.1, or 5.5 to 10.
    Above all, the individual embodiments shown in the figures can form the subject of independent solutions according to the invention. The relevant objects and solutions according to the invention can be found in the detailed descriptions of these figures.
    For the sake of order, it should finally be pointed out that for a better understanding of the construction of the actuating element 1, this or its components have been shown partially unevenly and / or enlarged and / or reduced in size.
    LIST OF REFERENCE NUMERALS 1 actuating element 31 detent hub 2 tube 32 tube section 3 carrier sleeve 33 disc section 4 scale 34 edge 5 rotation axis 35 positioning ring 6 index ring 36 screw ring 7 zero index 37 nose 8 second index element 38 pin 9 third index element 39 recess 10 fourth index element 40 recess 11 cap ring 41 locking device 12 adjusting knob 42 groove 13 locking ring 43 locking ball 14 push button 44 frame sleeve 15 spindle 45 locking sleeve 16 locking housing 46 disc section 17 longitudinal axis 47 pin 18 head module 48 slot 19 trunk module 49 tunnel 20 closing mechanism 50 outer clamping sleeve 21 intermediate housing 51 inner clamping sleeve 22 section 52 groove 23 section 53 disc section 24 retaining ring 54 outer compression spring 25 lower sleeve portion 55 inner compression spring 26 groove 56 screw ring 27 upper sleeve portion 57 axle pin 28 collar 58 compression spring 29 toothing 59 projection 30 toothing 60 stage
    权利要求:
    Claims (25)
    [1]
    1. actuating element (1) for adjusting the position of a target of a riflescope with a head module (18) and with a fuselage module (19), characterized in that the head module (18) and the trunk module (19) are interconnected by a coupling mechanism wherein the coupling mechanism for separating the head module (18) from the trunk module (19) is manually operable.
    [2]
    Second actuating element (1) according to claim 1, characterized in that for indicating a predeterminable position of the target, the head module (18) comprises a scale (4) and the trunk module (19) has a zero index (7).
    [3]
    3. Actuator (1) according to claim 1 or 2, characterized in that the head module (18) comprises a carrier sleeve (3), wherein the scale (4) on the carrier sleeve (3) is mounted.
    [4]
    4. Actuating element (1) according to one of the preceding claims, characterized in that at least one index element (8, 9, 10) for identifying a predeterminable position of the target on the support sleeve (3) is fixed against rotation.
    [5]
    5. Actuating element (1) according to one of the preceding claims, characterized in that the fuselage module (19) has a latching housing (16), a in the latching housing (16) about a rotation axis (5) rotatably mounted spindle (15) and one to the Rotary axis (5) rotatable locking hub (31) for moving the spindle (15).
    [6]
    6. actuating element (1) according to one of the preceding claims, characterized in that the carrier sleeve (3) with the locking hub (31) is rotationally coupled.
    [7]
    7. Actuator (1) according to one of the preceding claims, characterized in that the coupling mechanism forms part of a closing mechanism (20), wherein the closing mechanism (20) comprises a clamping mechanism with prestressed springs (54, 55).
    [8]
    8. Actuating element (1) according to claim 1, characterized in that the closing mechanism (20) comprises a control element, which is in operative connection with the clamping mechanism, wherein by actuation of the operating element, the connection between the head module (18) and the fuselage module (19) can be solved.
    [9]
    9. actuating element (1) according to one of the preceding claims, characterized in that the operating element of the locking mechanism (20) by a push button (14) is formed.
    [10]
    10. Actuating element (1) according to one of the preceding claims, characterized in that the clamping mechanism of the locking mechanism (20) with respect to the rotation axis (5) coaxially arranged and slidable sleeves comprises.
    [11]
    11. Actuating element (1) according to one of the preceding claims, characterized in that the closing mechanism (20) comprises a frame sleeve (44) and in the frame sleeve (44) displaceable locking sleeve (45), wherein in a lower end region of the locking sleeve (45 ) at least one radially extending tunnel (49) is formed and in the tunnel (49) at least one blocking ball (43) is arranged, and wherein the at least one blocking ball (43) in the radial direction is movable back and forth.
    [12]
    12. Actuating element (1) according to one of the preceding claims, characterized in that the locking sleeve (45) at least one axially extending- the slot (48) and the frame sleeve (44) at least one with the slot (48) in engagement pin ( 47).
    [13]
    13. Actuating element (1) according to one of the preceding claims, characterized in that the locking hub (31) comprises an upper tube portion (32) having on an inner side a circumferential groove (42).
    [14]
    14. Actuating element (1) according to one of the preceding claims, characterized in that the coupling mechanism comprises at least the locking sleeve (45) with the locking balls (43) and the upper tube section (32) of the locking hub (31) with the groove (42).
    [15]
    15. Actuating element (1) according to one of the preceding claims, characterized in that in a connected state of head module (18) and body module (19) of the lower end portion of the locking sleeve (45) in the upper tube portion (32) of the locking hub (31) is received, wherein the at least one locking ball (43) in the groove (42) of the locking hub (31) is engaged.
    [16]
    16. Actuator (1) according to one of the preceding claims, characterized in that the closing mechanism (20) comprises an outer clamping sleeve (50) and a first, outer compression spring (54), wherein the first, outer compression spring (54) between the frame sleeve (44) and the outer clamping sleeve (50) is arranged and held clamped.
    [17]
    17. Actuating element (1) according to one of the preceding claims, characterized in that the closing mechanism (20) comprises an inner clamping sleeve (51) and a second, inner compression spring (55), wherein the second, inner compression spring (55) between the locking sleeve (45) and the inner clamping sleeve (51) is arranged and held clamped.
    [18]
    18. Actuating element (1) according to one of the preceding claims, characterized in that in the connected state of the head module (18) and body module (19), a lower end portion of the inner clamping sleeve (51) on the at least one locking ball (43) rests and this in the circumferential groove (42) of the locking hub (31) holds locked.
    [19]
    19. Actuating element (1) according to one of the preceding claims, characterized in that the inner clamping sleeve (51) has on one outer side a circumferential groove (52), wherein in an intermediate position, during the separation of head module (18) and fuselage module (19) in that at least one blocking ball (43) is accommodated at least partially in the circumferential groove (52) of the inner clamping sleeve (51).
    [20]
    20. Actuating element (1) according to one of the preceding claims, characterized in that in a separate state of head module (18) and body module (19), the at least one locking ball (43) formed by a in the outer end region of the tunnel (49) constriction in its radial position in the tunnel (49) is held.
    [21]
    21. Actuating element (1) according to one of the preceding claims, characterized in that the frame sleeve (44) at an upper end region an outwardly projecting, upper disc portion (46) which is connected to the carrier sleeve (3), wherein the disc portion (46) is screwed with a thread in the carrier sleeve (3).
    [22]
    22. Actuating element (1) according to one of the preceding claims, characterized in that in the upper end region of the frame sleeve (44) a screw ring (56) is fixed, through which the inner clamping sleeve (51) with the second, inner compression spring (55). are kept clamped.
    [23]
    23. Actuator (1) according to one of the preceding claims, characterized in that the push button (14) with the interposition of a compression spring (58) with the inner clamping sleeve (51) is connected.
    [24]
    24. Actuating element (1) according to any one of the preceding claims, characterized in that the push button (14) comprises a pivot pin (57) which is formed with a longitudinal slot and latching lugs, wherein the latching lugs on an inwardly projecting projection of the inner locking sleeve (51) are engaged.
    [25]
    25. Actuator (1) according to one of the preceding claims, characterized in that the push button (14) by the between the inner clamping sleeve (51) and the push button (14) arranged compression spring (58) is held in a maximum raised position.
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    同族专利:
    公开号 | 公开日
    AT516059B1|2016-02-15|
    EP3034981B1|2019-11-06|
    US9989362B2|2018-06-05|
    EP3034981A1|2016-06-22|
    US10365100B2|2019-07-30|
    US20180252524A1|2018-09-06|
    US20160169672A1|2016-06-16|
    引用文献:
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    US20140137458A1|2012-11-21|2014-05-22|Quint Crispin|Riflescope adjustment knob with interchangeable adjustment indicator ring|EP3367044A1|2017-02-27|2018-08-29|Swarovski-Optik KG.|Adjusting element for adjusting a line of sight of an optical sighting device, and telescopic sight with the adjusting element and weapon with the telescopic sight, as well as method of positioning the line of sight|US6691447B1|2002-09-17|2004-02-17|Leupold & Stevens, Inc.|Non-telescoping riflescope adjustment mechanism|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    ATA50907/2014A|AT516059B1|2014-12-15|2014-12-15|Actuator for adjusting the target of a telescopic sight|ATA50907/2014A| AT516059B1|2014-12-15|2014-12-15|Actuator for adjusting the target of a telescopic sight|
    EP15199734.3A| EP3034981B1|2014-12-15|2015-12-14|Actuator element for adjusting the sighting mark of a target telescope|
    US14/967,573| US9989362B2|2014-12-15|2015-12-14|Actuator element for setting the target mark of a sighting telescope|
    US15/970,480| US10365100B2|2014-12-15|2018-05-03|Actuator element for setting the target mark of a sighting telescope|
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