Control device for projectile
The control device addresses the issue of unreliable projectile imbalance assessments by using pneumatic circuits to rotate projectiles in a levitating state, providing accurate empirical measurements that ensure high-quality performance for high-precision and long-range projectiles.
Patent Information
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- BALANCE SYST SRL
- Filing Date
- 2025-12-17
- Publication Date
- 2026-07-02
AI Technical Summary
Existing methods for evaluating projectile imbalance are inadequate as they do not simulate the actual conditions of ejection from a firearm, leading to unreliable and predictive assessments of projectile quality, particularly for high-precision and long-range projectiles.
A control device that uses pneumatic circuits to rotate the projectile in a levitating state, allowing for empirical measurements of vibrations and imbalances without external contact, mimicking the conditions of ejection from a firearm.
Enables reliable empirical measurements of projectile quality, ensuring high precision and quality assurance for high-precision and long-range projectiles by simulating the ejection conditions, thereby improving the accuracy and performance of these projectiles.
Smart Images
Figure IB2025063071_02072026_PF_FP_ABST
Abstract
Description
[0001] DESCRIPTION
[0002] CONTROL DEVICE FOR PROJECTILE
[0003] The present invention relates to a control device for a projectile of the type specified in the preamble of the first claim.
[0004] In particular, the present invention relates to a control device, in particular used for high-precision and long-range projectiles, suitable for measuring the vibrations and imbalances of the projectile in order to assess its manufacturing quality and, consequently, the level of performance achievable during use.
[0005] As is known, the projectile is generally a body intended to be launched, by applying an appropriate force, along a predetermined direction.
[0006] Normally, the projectile is ejected from a firearm which, by virtue of an explosive reaction generated in the combustion chamber present in the cartridge containing the projectile, imparts to it a very high propulsion force directed, at least initially, along the axis of extension of the barrel of the firearm.
[0007] In particular, a projectile exiting the barrel of a rifle, for example a precision rifle, can rotate up to 300,000 revolutions per minute.
[0008] It is clear that an imbalance, even of a few milligrams, can generate a considerable energy dissipation, limiting or altering the trajectory and precision following the ejection from the firearm.
[0009] Therefore, in order to measure the imbalances on any rotating member, it is first necessary to set the projectile in rotation.
[0010] As can be readily understood, measuring the imbalance of a projectile is not straightforward and cannot even be equated with the balancing of any rotating member, such as armatures, rotors, turbines, or others, where the constraint or even just the support of the piece on its shaft or on its mounting hole does not influence, or compromise, the measurements made during rotation.
[0011] At present, the evaluation of imbalances is carried out, at best, through optical checksIM
[0012] of the projectile set in rotation by a shaft or other rotating system attachable to the tail of the projectile itself. Alternatively, the evaluation may be carried out by non -destructive static checks performed dimensionally on the projectiles.
[0013] As already evident, the known technique described includes some significant drawbacks.
[0014] In particular, it is not possible to perform checks on a projectile simulating the actual rotation thereof in the air, since the latter is always constrained to an external structure that can set it in rotation or support it.
[0015] Or, if the measurement is exclusively entrusted to the accuracy of the measuring instruments on the stably supported projectile, the actual effectiveness in the air of the projectile is determined exclusively in a predictive and not empirical manner.
[0016] In this situation, the technical object underlying the present invention is to devise a control device for projectiles capable of substantially overcoming at least part of the aforementioned drawbacks.
[0017] Within the scope of said technical object, an important aim of the invention is to obtain a control device for projectiles that allows measurements to be made on the projectile simulating as closely as possible the conditions of ejection from the firearm.
[0018] Another important aim of the invention is to implement a control device for projectiles that is therefore highly reliable, giving the user the possibility to perform empirical measurements on the projectile that allow determining its quality realistically.
[0019] In conclusion, a further object of the invention is to obtain a control device for projectiles that allows ensuring the high quality of projectiles, based on selected criteria, especially for high-precision and long-range projectiles that are ejected at high rotational speeds. The technical object and the specified aims are achieved by a control device for projectiles as claimed in the appended claim 1.
[0020] Preferred technical solutions are highlighted in the dependent claims.
[0021] The characteristics and advantages of the invention are clarified below by the detaileddescription of preferred embodiments of the invention, with reference to the accompanying drawings, in which:
[0022] Fig. 1 shows a simplified diagram of a control device for projectiles according to the invention;
[0023] Fig.2 illustrates a schematic view of a first preferred configuration of the movement means of a control device for projectiles according to the invention;
[0024] Fig. 3a is a top perspective view of a second preferred configuration of the movement means of a control device for projectiles according to the invention;
[0025] Fig. 3b shows a bottom perspective view of the control device for projectiles of Fig.
[0026] 3a;
[0027] Fig. 4a shows a longitudinal sectional view, parallel to the main axis, of the support of the control device for projectiles of Figs. 3a-3b in which the second path of the one or more circuits is shown in detail;
[0028] Fig. 4b illustrates a transverse sectional view, parallel to the main plane, of the support of the control device for projectiles of Figs. 3a-3b in which the exhaust ports radial to the main axis are shown in detail;
[0029] Fig. 4c is a transverse sectional view, parallel to the main plane, of the support of the control device for projectiles of Figs. 3a-3b in which the second paths of the one or more circuits developing partly radially to the main axis are shown in detail, and the third paths formed in the body without the corresponding delivery nozzles that implement the movement means are also shown;
[0030] Fig.4d shows a longitudinal sectional view, parallel to the main axis, of the support of the control device for projectiles of Figs. 3a-3b in which the fourth paths of the one or more circuits developing parallel to the main axis are shown in detail, and in which the delivery nozzles that implement the movement means are not present;
[0031] Fig. 5 shows a longitudinal sectional view, parallel to the main axis, of the support of a further embodiment of a control device for projectiles according to the invention in whichtwo different groups of second paths are present, at different distances from the bottom of the cavity, and in which auxiliary exhaust ports developing parallel to the second paths on the opposite side are present;
[0032] Fig. 6a illustrates a bottom perspective view of the support of the control device for projectiles of Fig. 5;
[0033] Fig. 6b is a top perspective view of the control device for projectiles of Figs. 5-6 in which the delivery nozzles that implement the movement means in use on the tip of a projectile are present;
[0034] Fig. 7 represents a top view of the housing suitable for accommodating the support of a control device for projectiles according to the invention configured as a cartridge, and in which the concentric barriers forming the separate pneumatic transmission chambers are shown; and
[0035] Fig. 8 shows a perspective view of a control device for projectiles according to the invention comprising a cartridge-type support as shown in Figs. 3a-6b inserted in the housing of Fig. 7.
[0036] In the present document, the measurements, values, shapes, and geometric references (such as perpendicularity and parallelism), when associated with words such as “about” or other similar terms such as “approximately” or “substantially,” are to be understood as subject to measurement errors or inaccuracies due to production and / or manufacturing errors and, above all, as subject to a slight deviation from the value, measurement, shape or geometric reference to which they are associated. For example, such terms, if associated with a value, preferably indicate a deviation not exceeding 10% of the value itself.
[0037] Furthermore, when used, terms such as “first,” “second,” “upper,” “lower,” “main” and “secondary” do not necessarily identify an order, a priority of relationship or relative position, but may simply be used to more clearly distinguish between different components.
[0038] Unless otherwise specified, as results from the following discussions, terms such as “processing,” “computing,” “determining,” “calculating,” or similar, are considered to refer tothe action and / or processes of a computer or similar electronic computing device that manipulates and / or transforms data represented as physical quantities, such as electronic quantities of registers of a computer system and / or memories into other data similarly represented as physical quantities within computer systems, registers or other storage, transmission or display devices.
[0039] The measurements and data reported herein are to be considered, unless otherwise indicated, as carried out in the ICAO Standard Atmosphere (ISO 2533:1975).
[0040] With reference to the Figures, the control device for a projectile according to the invention is globally denoted by the number 1.
[0041] The device 1 is suitable for assessing the balancing quality of a projectile 10. The latter, as is known, is an object having a tapered shape that extends from a substantially flat end, defining a bottom adapted to be housed in the shell of a cartridge adjacent to the combustion chamber, to a wedge-shaped end, i.e., the tip adapted to penetrate objects when it comes into contact with them at high speed.
[0042] The device 1 , therefore, comprises at least one support 2.
[0043] The support 2 is substantially the supporting element of the projectile 10.
[0044] It preferably defines a main axis 2a and a main plane 2b.
[0045] The main axis 2a is substantially a virtual axis, preferably barycentric, of the support 2. Preferably, the main axis 2a is suitable, when the device 1 is in use, for being preferably, but not necessarily, aligned with the gravitational gradient.
[0046] The main plane 2b is preferably orthogonal to the main axis 2a. Therefore, the main plane 2b is preferably adapted to extend perpendicularly also to the gravitational gradient.
[0047] Therefore, the support 2 includes at least one cavity 20. The cavity 20 is substantially a hollow portion of support 2 within which the projectile 10 can be housed.
[0048] Preferably, the cavity 20 is configured in such a way as to allow housing of the projectile 10 centred with respect to the main axis 2a. Therefore, the projectile 10 can be inserted into the cavity 20, when the device 1 is in use, by gravity.The support 2 may also comprise, in detail, other elements.
[0049] Preferably, the support 2 also comprises a body 21 and a base 22.
[0050] The body 21 is preferably a tubular element, for example in particular annular. Therefore, the body 21 bounds the cavity 20 radially to the main axis 2a so as to surround the projectile 10. Preferably, the body 21 houses the projectile 10 in such a way that there is at least a separation gap between body 21 and projectile 10 around the projectile 10 itself.
[0051] The base 22, instead, bounds the cavity 20 parallel to the main plane 2b. In particular, preferably, the base 22 is configured to bound a bottom end of the projectile 10. Therefore, preferably, when the device 1 is in use, the base 22 faces the bottom of the projectile 10 and is placed beneath it.
[0052] The device 1 further comprises movement means 3. The movement means 3 are essentially configured to move the projectile 10. Still more in detail, the movement means 3 move the projectile 10 in the cavity in rotation about the main axis 2a. However, advantageously, the movement means 3 allow the projectile 10 to be moved without coming into contact with it, as better described below.
[0053] Indeed, the device 1 also comprises one or more circuits 5. The circuits are suitably pneumatic. Therefore, they are pneumatic circuits within which a fluid, preferably gaseous, such as air, flows.
[0054] The one or more circuits 5 are preferably distributed between body 21 and base 22.
[0055] Therefore, the one or more circuits 5 are advantageously configured to apply at least a first force Fi and a second force F2 to the projectile 10.
[0056] The first force F1 is substantially a pneumatic force tangential to the projectile 10 parallel to the main plane 2b. Therefore, in at least a first embodiment, shown in Figs. 1-2, the force F1 may also generate a dragging force, at least in the adhesion portions that surround the projectile 10, which sets the projectile 10 in rotation about the main axis 2a in accordance with the direction of the first force F1.
[0057] In a second embodiment, shown in Figs. 3a-6b, therefore, through the application of the1 4
[0058] first force Fi , the one or more circuits 5 may substantially implement the movement means 3.
[0059] Furthermore, in general, they also implement at least a first bearing 5a.
[0060] The first bearing 5a is an air bearing defined around the projectile 10 parallel to the main axis 2a. Therefore, body 21 and projectile 10 remain separated, when the device 1 is in use and during the rotation of the projectile 10 in the cavity, by means of the first bearing 5a. Similarly, the second force F2 is also substantially a pneumatic force. However, the second force F2is preferably applied along the main axis 2a. This means that advantageously, the one or more circuits 5 implement, by applying the second force F2, a second bearing 5b.
[0061] The second bearing 5b is also an air bearing. Furthermore, it is placed between the projectile 10 and the base 22 to allow the floating of the projectile 10 in air with respect to the base 22. Therefore, when the device 1 is in use, preferably the projectile 10 is supported underneath by the second bearing 5b which, in synergy with the first bearing 5a, maintains the projectile 10 in motion in a levitating state with respect to the support 2.
[0062] To implement said features, in more detail, the one or more circuits 5 may comprise at least a first path 50.
[0063] If present, the first path 50 develops at least in part in the base 22. Moreover, it comprises at least a first inlet 50a and a first outlet 50b.
[0064] The first inlet 50a is preferably in fluid passage connection with an external compressed air conveyor. The first outlet 50b is preferably in fluid passage connection with the cavity 20. For example, the first outlet 50b may comprise, or be constituted by, a duct developing along or parallel to the main axis 2a.
[0065] Naturally, between inlet 50a and outlet 50b, conveying elements may be present, such as ducts and / or fittings, or other components as in any pneumatic system.
[0066] Furthermore, the one or more circuits 5 may comprise at least a second path 51.
[0067] If present, the second path 51 develops at least in part in the body 21. Moreover, it comprises at least a second inlet 51a and a second outlet 51b.1 4
[0068] The second inlet 51a is preferably in fluid passage connection with an external compressed air conveyor. The second outlet 51 b is preferably in fluid passage connection with the cavity 20.
[0069] Still more in detail, preferably, the second outlet 51 b comprises, or is constituted by, a duct developing radially to the main axis 2a so as to convey compressed air perpendicularly to the projectile 10.
[0070] When the compressed air impacts the wall of the projectile 10, it generates a boundary layer enveloping at least part of the projectile 10 so as to obtain at least the first force Fi which implements the first bearing 5a and may also generate a dragging force which sets the projectile into rotation, implementing at least part of the movement means 3, as in the embodiment of Figs. 1-2.
[0071] In a preferred, though not exclusive, embodiment, the second path 51 comprises a plurality of second outlets 50b. The latter are, therefore, mutually equidistantly distributed around the main axis 2a, as shown in the example of Fig. 2 in which the second outlets 51b are each positioned at 120°, in a circumferential direction with respect to the axis 2a, from one another, so as to obtain a plurality of first forces Fi tangentially to the projectile 10 each adjacent to a respective second outlet 50b.
[0072] Moreover, whether one or more second outlets 51 b are present, the second outlet 51 b may develop on or parallel to the main plane 2b at a portion of body 21 approximately hallway up the cavity 20 along the main axis 2a.
[0073] Furthermore, for the purpose of generating the force that sets the projectile 10 in rotation, the circuits 5 may also comprise an additional circuit, better described below, in which the at least one inlet is slightly offset from the radial direction and also extends partly in a circumferential direction with respect to the axial direction given by axis 2a.
[0074] Indeed, in a further embodiment, shown in particular in Figs. 3a-6b, the one or more circuits 5 are advantageously configured to apply at least a third force F3 to the projectile 10. Thus, the third force F3 implements at least part of the movement means 3 when applied.1 4
[0075] The third force F3 is substantially a pneumatic force tangential to the projectile 10 and parallel to the main plane 2b. Therefore, the third force F3 may generate a dragging force, at least in the adhesion portions enveloping the projectile 10, which sets the projectile 10 in rotation about the main axis 2a in accordance with the direction of the third force F3. Thus, the third force F3 may replace or be added to the first force F1. In other words, the one or more circuits 5 may be configured to implement the first and second force F1, F2, or the second and third force F2, F3, or also all the forces F1 , F2, F3. In the latter case, the first force F1 may contribute to the rotational dragging of the projectile 10, or it may also only contribute to the implementation of the first bearing 5a without further contribution, for example to keep the projectile centred with the force F1 directed solely normally, or radially, to the main axis 2a.
[0076] Therefore, also in this case, through the application of the third force F3, the one or more circuits 5 may substantially implement the movement means 3.
[0077] Still more in detail, in this regard, the one or more circuits 5 comprise a fourth path 53. If present, the fourth path 53, similarly to the second path 51 , develops at least in part in the body 21. However, the fourth path 53 is adapted to convey air towards the projectile 10 also externally to the body 21.
[0078] Indeed, in this case, the support 2 preferably comprises at least one delivery nozzle 25, preferably at least a pair.
[0079] If present, the one or more delivery nozzles 25 are integral with or constrained to the body 21. Preferably, each of the delivery nozzles 25 is snap-fitted to the body 21, preferably inside a respective seat 26.
[0080] Moreover, preferably, the delivery nozzles 25 define a delivery direction 25a which is preferably skewed with respect to the main axis 2a.
[0081] Therefore, the fourth path 53 preferably develops between the body 21 and a delivery nozzle 25. Still more in detail, the fourth path 53 is in fluid passage connection with the seat 26 such that, once the delivery nozzle 25 is inserted into the seat 26, it can form the1 4
[0082] remainder of the fourth path 53 to convey outgoing air.
[0083] Still more preferably, each delivery direction 25a is orientable with respect to the main axis 2a, preferably each independently from the others if a plurality of nozzles 25 is present. In this way, it is possible to vary the dragging capacity of the third force F3, in particular by varying its moment arm of application with respect to the main axis 2a.
[0084] To implement this, preferably, each delivery nozzle 25 is loosely constrained to the body 21 in such a way that it can be rotated with respect to it, selectively, about its own orientation axis 25b parallel to the main axis 2a.
[0085] In this regard, for example, the body 21 may be provided with control means 27 accessible from the outside, for example a grub screw, which allows the orientation of the delivery direction 25a to be modified by rotating the grub screw in its seat.
[0086] Therefore, the fourth path 53 may also comprise at least a fourth inlet 53a and a fourth outlet 53b.
[0087] The fourth inlet 53a is preferably in fluid passage connection with an external compressed air conveyor. The fourth outlet 53b is preferably part of the delivery nozzle 25, in particular determining its delivery direction 25a.
[0088] Still more in detail, preferably, the fourth outlet 53b comprises, or is constituted by, a duct developing along the delivery direction 25a, and therefore part of the delivery nozzle 25, so as to convey compressed air tangentially to the projectile 10.
[0089] When the compressed air impacts the wall of the projectile 10, it generates a boundary layer which grazes at least part of the projectile 10 so as to obtain at least the third force F3 which generates a rotational dragging force of the projectile 10, as in the embodiment of Figs. 3a-6b.
[0090] Moreover, each fourth outlet 53b may develop on or parallel to the main plane 2b externally to the body 21 on the nozzle 25 approximately at the height of the tip of the projectile 10 when inserted in the cavity 20 along the main axis 2a.
[0091] In addition to what has been described, the one or more circuits 5 may also comprise a thirdIM
[0092] path 52.
[0093] If present, the third path 52 develops at least in part in the base 22.
[0094] Therefore, the third path 52 preferably comprises at least a first access 52a and a second access 52b.
[0095] The first access 52a is adapted to be placed in fluid passage connection with an external compressed air conveyor or with an external environment, as explained below.
[0096] The second access 52b is in fluid passage connection with the first path 50, in particular upstream of the first outlet 50b.
[0097] Therefore, unlike the other paths 50, 51, the third path 52 comprises a switch 52c.
[0098] The switch 52c is placed upstream of the first access 52a. Therefore, it is in fluid passage connection with the external compressed air conveyor and with the external environment. Advantageously, the switch 52c is configured to be able to selectively place the first access 52a in fluid passage connection with the external compressed air conveyor or with the external environment. In this way, in the first case, the first access 52a may respectively convey further compressed air into the first outlet 50b, for example to create an overpressure in the second bearing 50b which facilitates the ejection of the projectile 10 from the cavity 20 at the end of operations, or to realise an exhaust for the first path 50. In addition to what has been described, the one or more circuits 5 may comprise further components.
[0099] For example, one or more of the first path 50 and the second path 51 may comprise a respective regulating valve 50c, 51c. If present, the regulating valve 50c, 51c is placed upstream of, respectively, the first inlet 50a and / or the second inlet 51a. Therefore, the regulating valve 50c, 51c is configured to manipulate a local pressure, that is, respectively in the first path 50 and in the second path 51 , thus also in the second bearing 5b and in the first bearing 5a, of the compressed air so as to be able to control the intensity of the second force F2and / or of the at least one first force Fi.
[0100] Similarly, the third path 53 could also comprise a respective regulating valve placedIM
[0101] upstream of the fourth inlet 53a and configured to manipulate a local pressure so as to be able to control the intensity of the third force F3.
[0102] Moreover, to avoid excessive pressures, the support 2 itself may comprise at least one exhaust port 23. If present, the exhaust port 23 is in fluid passage connection with the cavity 20; moreover, it is configured to allow the compressed air to exit from the cavity 20, preferably from the second bearing 5b.
[0103] Preferably, the support 3 comprises a plurality of exhaust ports 23. Furthermore, as shown in Fig. 4b, the exhaust ports 23 preferably develop radially to the main axis 2a. Still more in detail, the exhaust ports 23 develop along a plane parallel to the main plane 2b at a predetermined height of the cavity 20.
[0104] Additionally or alternatively, an exhaust port 23 could also be aligned with part of a second path 51 , in particular with the duct forming a second outlet 51 b of the second path and communicating with the cavity 20 on the opposite side with respect to the second outlet 51b.
[0105] In a particular embodiment, for example, the second path 51 could also comprise two groups of ducts forming the second outlets 51b at different heights parallel to the main axis 2a, as shown in Fig. 5.
[0106] Therefore, the exhaust port 23 could develop parallel to the second outlets 51 b and between the two development planes parallel to the main plane 2b, and on the side of the cavity 20 opposite the second outlets 51 b.
[0107] The device 1 preferably also comprises measurement means 4.
[0108] The measurement means 4 are configured to measure at least one vibration of the support 2. In detail, they are configured to measure a vibration in the main plane 2b and / or parallel to the main axis 2a with respect to a fixed structure, such as a floor or a frame integral with the floor. They are preferably constituted by accelerometers or other sensors known per se and used in the field of balancing.
[0109] In this regard, for example, the device 1 may also comprise a base 6.IM
[0110] If present, the base 6 is configured to rest on or be stably fastened to the fixed structure. Therefore, the base 6 is adapted to be made integral with the fixed structure. Thus, the support 2 can be connected to the base 6 and the measurement means 4 can be operatively connected to support 2 and base 6, for example between support 2 and base 6. Therefore, in this case, the measurement means 4 are preferably configured to deform proportionally to at least the vibration so as to generate a measurement signal corresponding to the deformation.
[0111] Examples of measurement means 4 of this type may be piezoelectric and / or electrodynamic and / or force sensors and / or laser displacement sensors. Such sensors are known per se to the skilled person.
[0112] In a preferred, though not exclusive, embodiment, the support 2 is preferably fastened to the base 6 by means of one or more connectors 60.
[0113] If present, the one or more connectors 60 are of the rod type, i.e., such as to comprise a thin connection rod between the support 2 and the ground so as to allow the free movement of the support.
[0114] Alternatively, the one or more connectors 60 are vibration dampers. Moreover, they separate support 2 and said base 6 parallel to the main axis 2a so as to dampen vibrations parallel to the main axis 2a. Therefore, in this configuration, the vibration is preferably measured by the measurement means 4 exclusively in the main plane 2b, for example in a direction lying on or parallel to the main plane 2b.
[0115] Alternatively, the support 2 may be configured as a cartridge. Therefore, the support 2 may be detachably fastened to the base 6 so as to allow easy insertion or removal.
[0116] In this regard, the base 6 may comprise a housing 61.
[0117] The housing 61 is therefore adapted to accommodate the support 2. Moreover, the housing 61 is configured to implement, with the support 2 inserted therein, at least part of the one or more circuits 5.
[0118] Indeed, preferably, the base 22 of the support 2 defines externally, in particular on the sideIM
[0119] opposite the cavity 20, an interface surface 22a adapted to interface with an interface bottom 61a of the housing 61 when the support 2 is inserted into it.
[0120] The interface bottom 61a is perforated so as to allow the conveyance of air, in particular thereby implementing part of the one or more circuits 5.
[0121] Still more in detail, the one or more circuits 5 define accesses to the support 2 placed at the interface surface 22a. Preferably, therefore, at least the first path 50, the second path 51 and the third path 53 define outlets at the interface surface 22a.
[0122] Still more appropriately, the paths define outlets on the interface surface 22a that are distinct and separated radially from the main axis 2a.
[0123] Moreover, the interface bottom 61a comprises, in turn, a plurality of concentric annular barriers 61b, for example gaskets, distinct and separated around the central axis 2a and configured to isolate each path 50, 51, 53 from the others. In detail, the contact between interface surface 22a and interface bottom 61a results, by virtue of the barriers 61b, in the formation of separate sealed chambers 62 that allow the air exchange between the interface bottom 61a and the paths 50, 51 , 53 of the base 22.
[0124] Therefore, the base 22 may also comprise a connecting pin 28, and the interface bottom 61a may further comprise a housing slot 63 for the pin 28, in particular to place in fluid passage connection different sections of the first path 50 axially to the main axis 2a.
[0125] The device 1 may be provided with further components.
[0126] For example, to evaluate the correct orientation of the support 2, the support 2 may comprise an orientation sensor 24.
[0127] If present, the orientation sensor 24 is integral with the support 2. Therefore, preferably, the orientation sensor 24 is configured to detect the orientation of the main axis 2a with respect to the Earth’s gravitational gradient.
[0128] An example of such a component may be a bubble level placed on the top of support 2, or otherwise visible to the user.1 4
[0129] Moreover, the device 1 may also comprise an RPM sensor 7.
[0130] If present, the RPM sensor 7 is configured to determine a rotational speed of the projectile 10 in the cavity 20 when the device 1 is in use. A sensor of this type may be, for example, an optical sensor or a Hall-effect sensor.
[0131] The device 1 may also comprise a processor 8.
[0132] If present, the processor 8 is suitably electronic. Moreover, it is accessible from a computer. Therefore, the processor 8 is preferably operatively connected to at least one or more of the regulating valves 50c, 51c, the RPM sensor 7, and the measurement means 4.
[0133] The processor 8 is therefore configured to allow the manipulation of one or more regulating valves 50c, 51c in relation to a rotational speed set by a user via the computer. The manipulation is preferably carried out by the processor 8 until the RPM sensor 7 determines that the rotational speed of the projectile 10 is equal to said set rotational speed so as to detect the vibrations of the projectile 10 at the set rotational speed. Said adjustments may also be made manually.
[0134] The operation of the control device 1 for a projectile previously described in structural terms allows the determination of a new control method for a projectile.
[0135] Indeed, the method comprises at least one insertion step.
[0136] In the insertion step, the projectile 10 is inserted by gravity into the cavity 20. In this case, therefore, preferably the main axis 2a is aligned with the gravitational gradient.
[0137] Therefore, the method advantageously comprises an impingement step.
[0138] In the impingement step, the projectile 10 is impinged with compressed air in the cavity 20. More in detail, the projectile 10 is impinged in such a way as to apply at least a first pneumatic force Fi tangential to it parallel to the main plane 2b to rotate the projectile 10 about the main axis 2a. When the first force Fi is applied, the first air bearing 5a is alsoadvantageously defined around the projectile 10 parallel to the main axis 2a.
[0139] Then, during the impingement, at least a second pneumatic force F2is also advantageously applied to the projectile 10 along the main axis 2a, defining the second air bearing 5b beneath the projectile 10 to allow it to float in air with respect to the support 2.
[0140] The method therefore includes a measurement step.
[0141] In the measurement step, preferably, at least one vibration of the support 2 is measured in the main plane 2b and / or parallel to the main axis 2a with respect to the fixed structure, such as a floor or frame integral with the floor.
[0142] Following the measurement step, a selection step may be carried out, in which only projectiles with a certain degree of balance are selected, or such projectiles are separated from the others or sorted into categories. Finally, a balancing step may also be carried out, in which the balancing of the projectiles 10 is improved through the addition or removal of material.
[0143] Therefore, the control device 1 for a projectile according to the invention achieves important advantages.
[0144] Indeed, the control device 1 for a projectile makes it possible to carry out measurements on the projectile simulating as closely as possible the conditions of ejection from a firearm, namely rotating the projectile in air without any contact with external objects.
[0145] Thus, the control device 1 for a projectile is highly reliable, giving the user the possibility to carry out empirical measurements on the projectile that allow its quality to be realistically assessed.
[0146] In conclusion, the control device 1 for a projectile allows the high quality of the projectiles to be ensured, according to selected criteria, especially for high-precision and long-range projectiles that are ejected at high rotational speeds, which can be set by the user viacomputer.
[0147] The invention is susceptible to variants falling within the scope of the inventive concept defined by the claims. Moreover, the device 1 may also be used to measure or control other objects that are not projectiles and that require balancing.
Claims
CLAIMS1. Control device (1) for measuring vibration or imbalance of a projectile (10), comprising:- a support (2) defining a main axis (2a) and a main plane (2b) orthogonal to said main axis (2b) and including:- a cavity (20) suitable for housing a projectile (10) centred with respect to said main axis (2a),- a tubular body (21) bounding said cavity (20) radially to said main axis (2a) so as to surround said projectile (10),- a base (22) bounding said cavity (20) parallel to said main plane (2b) so as to face a bottom end of said projectile (10);- movement means (3) configured to move said projectile (10) in said cavity (20) rotating about said main axis (2a); and- measurement means (4) configured to measure at least one vibration of said support (2) in said main plane (2b) and / or parallel to said main axis (2a) with respect to a fixed structure, such as a floor or frame integral with said floor;- one or more compressed air circuits (5) distributed between said body (21) and said base (22), configured to apply at least a second pneumatic force (F2) to said projectile (10) along said main axis (2a), defining a second air bearing (5b) between said projectile (10) and said base (22) to allow floating of said projectile (10) in air with respect to said base (22), and characterised in that- said one or more circuits (5) are also configured to alternatively or simultaneously:- apply at least a first pneumatic force (F1) normal to said main axis (2a) and / or tangential to said projectile (10) parallel to said main plane (2b), defining at least a first air bearing (5a) around said projectile (10) parallel to said main axis (2a), and- apply at least a third pneumatic force (F3) tangential to said projectile (10) parallel to said main plane (2b), implementing at least part of said movement means (3).
2. Device (1) according to claim 1, wherein said one or more circuits (5) comprise a first path (50) developing at least partially in said base (22) and comprising at least a first inlet (50a) in fluid passage connection with an external compressed air conveyor and a first outlet (50b) in fluid passage connection with said cavity (20).
3. Device (1) according to any one of the preceding claims, wherein said one or more circuits (5) comprise a second path (51) developing at least in part in said body (21) and comprising at least a second inlet (51a) in fluid passage connection with an external compressed air conveyor and at least a second outlet (51b) in fluid passage connection with said cavity (20), including a duct developing radially to said main axis (2a) so as to convey said compressed air perpendicularly to said projectile (10) and generate a boundary layer enveloping at least part of said projectile (10) so as to obtain said at least one first force (Fi).
4. Device (1) according to the preceding claim, wherein said second path (51) comprises a plurality of said second outlets (51b) mutually equidistantly distributed around said main axis (2a) so as to obtain a plurality of said first forces (Fi) tangential to said projectile (10), each adjacent to a respective said second outlet (50b).
5. Device (1) according to any one of claims 3-4, wherein said second outlet (51b) runs on or parallel to said main plane (2b) at the level of a portion of said body (21) about halfway up said cavity (20) along said main axis (2a).
6. Device (1) according to any one of the preceding claims, wherein said one or more circuits (5) comprise a fourth path (53) developing at least in part in said body (21) and comprising at least a fourth inlet (53a) in fluid passage connection with an external compressed air conveyor and at least a fourth outlet (53b) including a duct developing outside said body (21) along a delivery direction (25a) skewed with respect to said main axis (2a) so as to convey said compressed air tangentially to said projectile (10) and generate a boundary layer grazing at least part of said projectile (10) so as to obtain said at least one third force (F3).1 47. Device (1) according to the preceding claim, wherein said support (2) comprises at least one delivery nozzle (25) including said fourth outlet (53b) and loosely constrained to said body (21) in such a way as to be able to rotate selectively with respect to said body (21) about its own orientation axis (25b) parallel to said main axis (2a) and, thus, to orient said delivery direction (25a) with respect to said main axis (2a), varying the dragging capability of said third force (F3).
8. Device (1) according to any of the preceding claims, wherein said one or more circuits (5) comprise a third path (52) developing at least in part in said base (22) and comprising at least a first access (52a), a second access (50b) in fluid passage connection with said first path (50) upstream of said first outlet (50b), and a switch (52c) placed upstream of said first access (52a) in fluid passage connection with an external compressed air conveyor and with an external environment and configured to be able to selectively place said first access (52a) in fluid passage connection with said external compressed air conveyor or with an external environment to be able to respectively convey further said compressed air into said first outlet (50b) or to realize an exhaust for said first path (50).
9. Device (1) according to any one of the preceding claims, wherein said support (2) comprises at least one exhaust port (23) in fluid passage connection with said cavity (20) and configured to allow said compressed air to exit said cavity (20).
10. Device (1) according to the preceding claim, wherein said exhaust ports (23) are more than one in number and extend radially with respect to said main axis (2a) along a plane parallel to said main plane (2b) at a predetermined height of said cavity (20).
11. Device (1) according to any one of the preceding claims, further comprising a base (6) configured to rest on or be stably constrained to said fixed structure so as to be integral with said fixed structure, said support (2) being connected to said base (6).
12. Device (1) according to the preceding claim, further comprising measuring means (4) operatively connected to said support (2) and said base (6), and configured to measure a vibration in said main plane (2b) and / or parallel to said main axis (2a) of saidsupport (2) with respect to said fixed structure.
13. Device (1) according to any one of claims 11-12, wherein said support (2) is a cartridge releasably connected to said base (6), said base (22) externally defines, on the side opposite to said cavity (20), an interface surface (22a) on which at least said first path (50), second path (51), and third path (53) define respective outlets mutually distinct and separated radially from said main axis (2a), and said base (6) comprises at least one housing (61) configured to house said support (2) and including at least one perforated interface bottom (61a) so as to allow the conveyance of air to realize part of said one or more circuits (5), and including a plurality of concentric annular barriers (61b), distinct and separate around said main axis (2a), and configured to isolate each said path (50, 51, 53) from the others so that the contact between said interface surface (22a) and said interface bottom (61a) results in the formation of separate sealed chambers (62) allowing air exchange between said interface bottom (61a) and said paths (50, 51, 53).
14. Device (1) according to any of the preceding claims, wherein said support (2) includes an orientation sensor (24) integral with said support (2) and configured to detect the orientation of said main axis (2a) with respect to the Earth's gravitational gradient.
15. Device (1) according to at least claim 2 and / or 3, wherein one or more of said first path (50), said second path (51), and said fourth path (53) comprise a respective regulation valve (50c, 51c) placed upstream of said first inlet (50a) and / or said second inlet (51a) and / or said fourth inlet (53a), and configured to manipulate a local pressure of said compressed air so as to control the intensity of said second force (F2) and / or said at least one first force (F1) and / or said at least one third force (F3).
16. Device (1) according to any of the preceding claims, comprising an RPM sensor (7) configured to determine a rotational speed of said projectile (10) in said cavity (20) when said device (1) is in use.
17. Device (1) according to at least claims 15-16, comprising an electronic processor (8) accessible via computer and operatively connected to one or more of saidregulation valves (50c, 51c), said RPM sensor (7), and said measurement means (4), and configured to allow manipulation of one or more of said regulation valves (50a, 51c) in relation to a rotational speed set by a user via said computer, until said RPM sensor (7) determines that said rotational speed is equal to said set rotational speed, so that said vibration can be detected at said set rotational speed.
18. Method for controlling and measuring the imbalance of a projectile, characterised in that it comprises:- insertion by gravity of a projectile (10) into a cavity (20) of a support (2) along a main axis (2a) parallel to the gravitational gradient,- investing said projectile (10) with compressed air in said cavity (20) so as to apply at least a second pneumatic force (F2) on said projectile (10) along said main axis (2a), defining a second air bearing (5b) underneath said projectile (10) to allow said projectile (10) to float in air relative to said support (2), and so as to, alternatively or simultaneously:- apply at least a first pneumatic force (F1) normal to said main axis (2a) and / or tangential to said projectile (10) parallel to said main plane (2b), defining a first air bearing (5a) around said projectile (10) parallel to said main axis (2a); and- apply at least a third pneumatic force (F3) tangential to said projectile (10) parallel to said main plane (2b), realizing at least part of said movement means (3).- measuring at least one vibration of said support (2) in said main plane (2b) and / or parallel to said main axis (2a) with respect to a fixed structure, such as a floor or frame integral with said floor.