REMOTELY CONTROLLABLE FUZING ARRANGEMENTS

Abstract

The technology subject of the present application generally concerns an aerial munition unit comprising a proximity fuze functionality and an impact fuze functionality, selectable by a crew member of an aircraft bearing the munition, after the aircraft has taken off and prior to munition release, to render active or operable the proximity fuze functionality or the impact fuze functionality.

Claims

1-47. (canceled)

48. A fuzing system for an aerial munition configured for mounting on an underwing region of an aircraft, the fuzing system comprises a remotely controllable fuze setter or a fuze switch configured for association to the underwing pylon tail solenoid through a lanyard and operable for rendering the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release.

49. The system according to claim 48, wherein the fuze setter is operated from an aircraft flight deck or from a ground flight operation deck.

50. The system according to claim 48, wherein rendering the aerial munition operable in a proximity fuze mode or an impact fuze mode comprises activation of the proximity sensor such that detonation is triggered within a preset distance from a target, or activation of the impact sensor such that detonation is triggered upon impact, or at a preset time after impact.

51. The system according to claim 48, the system comprising a proximity sensor, a fuze arrangement comprising an impact sensor and a controllable fuze setter, and a Turbine Alternator Unit (TAU), wherein both the proximity sensor and the fuze arrangement are electrically associated through a corresponding set of electric wires with the TAU provided between the proximity sensor and the fuze arrangement.

52. The system according to claim 48, wherein the proximity sensor is provided in a front radome, or the proximity sensor is mounted on a nose plug element.

53. The system according to claim 48, wherein the fuze arrangement is configured to set off detonation of the main explosive in response to triggering by the proximity sensor or the impact delay sensor.

54. The system according to claim 48, wherein the fuze arrangement is configured to be actuated from a default state to operate in a default operating mode being either a proximity operation mode or an impact delay operation mode or in an alternative mode being the other of the proximity operation mode and the impact delay operation mode.

55. The system according to claim 54, wherein the fuze arrangement comprises a fuze setter operable to switch the fuze arrangement from the default operating mode to the other of the two operating modes.

56. An aerial munition comprising a fuzing system comprising a remotely controllable fuze setter or a fuze switch for association to an aircraft underwing pylon tail solenoid through a lanyard and operable to render the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release.

57. The munition according to claim 56, the munition comprising a body shell and a tail positioned at the rear end of the body shell and forming an integral part thereof, wherein the tail comprises a plurality of fins, the body shell comprises a proximity sensor positioned at a front end or nose of the munition, the fuzing system being internally positioned within the shell at the back end of the munition and a turbine alternator positioned between the proximity sensor and the fuzing system and being in electrical communication with the proximity sensor and the fuzing system, wherein the fuzing system comprises the fuze setter and an impact delay sensor, wherein each of the proximity and impact sensors are electrically associated with the fuze setter and wherein the fuze setter is configured for association to an aircraft underwing pylon tail solenoid through a lanyard and operable to be remotely switched between a proximity fuze mode and an impact fuze mode, or vice versa, to render the aerial munition operable in a proximity operational mode or an impact operational mode.

58. A method for arming an aircraft with a plurality of aerial munitions, the method comprising mounting to an underwing region of the aircraft at least one aerial munition comprising a system according to claim 48.

59. The method according to claim 58, comprising mounting said at least one aerial munition on a pylon provided in an underside hardpoint region of the aircraft wing.

60. The method according to claim 59, wherein the pylon is provided with an interface arrangement configured and operable to communicate the pylon status with the aircraft's systems.

61. The method according to claim 58, wherein a lanyard connected to and extending from a controllable fuze setter provided in the system is connected to a pylon tail solenoid, wherein the pylon tail solenoid is remote-controllable.

62. The method according to claim 58, wherein the mounting further comprises connecting the aerial munition to at least two connection points provided for carrying or securely holding the munition in place.

63. The method according to claim 58, wherein a turbine alternator provided on the munition is connected with a lanyard to the pylon via a pylon nose solenoid.

64. The method according to claim 58, the method comprising connecting the at least one aerial munition to at least two connection points provided in an underwing region of the aircraft wing for carrying or securely holding the munition in place and connecting or associating a lanyard extending from a controllable fuze setter provided in said munition to a pylon tail solenoid provided in the underwing region of the aircraft wing, wherein the pylon tail solenoid is remote-controllable.

65. A method of operating an aerial munition mounted onto an underside region of an aircraft wing, the aerial munition comprising a fuzing system comprising a proximity sensor mounted on the munition nose, a fuse arrangement comprising an impact sensor and a controllable fuze setter, and a TAU unit, wherein the proximity sensor and the fuze arrangement are electrically associated through a corresponding set of electric wires with a TAU unit provided between the proximity sensor and the fuze arrangement, wherein the controllable fuze setter is associated to the aircraft underwing pylon tail solenoid through a lanyard the method comprising remotely causing the fuze setter to switch into an operating mode of choice during flight and prior to release of the munition.

66. The method according to claim 65, wherein the fuze setter is switched electrically by a crew selectable mechanism.

67. The method according to claim 65, the method comprises mounting onto the aircraft one or a plurality of munitions, at least one of said munitions being a munition comprising a proximity sensor, an impact sensor and a fuzing system comprising a remotely controllable fuze setter or a fuze switch configured and operable to render the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release, connecting the fuze setter to the aircraft underwing pylon tail solenoid through a lanyard; in flight determining or obtaining information regarding a target profile, and prior to release of the munition, setting a flight deck fuzing mechanism to set the fuze setter in a proximity fuze mode or an impact fuze mode to thereby render the aerial munition operable in the proximity fuze mode or the impact fuze mode.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0075] The invention may be more clearly understood when considering the following non-limiting exemplary embodiments, with reference to the following drawings, in which:

[0076] FIG. 1 is a flowchart presenting stages of operation of an aerial munition unit in accordance with embodiments of the present invention.

[0077] FIG. 2 is a schematic side view of an aerial munition unit comprising a fuzing system for selecting an operating mode in accordance with certain embodiments of the present invention.

[0078] FIG. 3 is a schematic blow-up view of a front portion of a sensor assembly in an aerial munition unit according to certain embodiments of the present invention.

[0079] FIG. 4 is a schematic presentation of a missile provided with a fuzing system of the invention.

[0080] FIG. 5 provides a depiction of a rear end of an exemplary fuze arrangement used according to certain embodiments of the present invention.

[0081] FIG. 6 provides a depiction of a rear end of an exemplary fuze arrangement including a fuze setter.

DETAILED DESCRIPTION OF EMBODIMENTS

[0082] The following detailed description of embodiments of the invention refers to the accompanying drawings referred to above. Dimensions of components and features shown in the figures are chosen for convenience or clarity of presentation and are not necessarily shown to scale. Wherever possible, the same reference numbers will be used throughout the drawings and the following description to refer to the same and like parts.

[0083] As disclosed and exemplified herein, the invention provides a fuzing system for an aerial munition configured for mounting on an underwing region of an aircraft, the fuzing system comprises a remotely controllable fuze setter or a fuze switch configured for association to the underwing pylon tail solenoid through a lanyard and operable for rendering the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release.

[0084] In any system of the invention, the fuze setter may be operated from an aircraft flight deck or from a ground flight operation deck.

[0085] In any system of the invention, rendering the aerial munition operable in a proximity fuze mode or an impact fuze mode may comprise activation of the proximity sensor such that detonation is triggered within a preset distance from a target, or activation of the impact sensor such that detonation is triggered upon impact, or at a preset time after impact.

[0086] In any system of the invention, the system may comprise a proximity sensor, a fuze arrangement comprising an impact sensor and a controllable fuze setter, and a Turbine Alternator Unit (TAU), wherein both the proximity sensor and the fuze arrangement are electrically associated through a corresponding set of electric wires with the TAU provided between the proximity sensor and the fuze arrangement.

[0087] In any system of the invention, the impact sensor may be configured to initiate an explosion upon impact of the munition against a target.

[0088] In any system of the invention, the impact sensor may be configured to detect impact through vibrations formed due to impact or through direct contact with a hard surface.

[0089] In any system of the invention, the impact sensor may be a piezoelectric sensor or a mechanical sensor.

[0090] In any system of the invention, the impact sensor may be an impact delay sensor, whereby detonation occurs after a predetermined time period following impact.

[0091] In any system of the invention, the proximity sensor may be configured to sense proximity over a wide range of angles, or a plurality of angular ranges, spanning both forward and lateral regions.

[0092] In any system of the invention, the proximity sensor may be configured to generate a trigger output in response to proximity either in response to forward proximity of a target located ahead of the munition along the direction of travel of the munition, or in response to proximity of a target located laterally with respect to the munition.

[0093] In any system of the invention, the proximity sensor may be selected from a radio frequency sensor (a radar), an optical sensor, an acoustic sensor, a magnetic sensor, or a pressure sensor.

[0094] In any system of the invention, the proximity sensor may be provided in a front radome.

[0095] In any system of the invention, the proximity sensor may be mounted on a nose plug element.

[0096] In any system of the invention, the fuze arrangement may be configured to set off detonation of the main explosive in response to triggering by the proximity sensor or the impact delay sensor.

[0097] In any system of the invention, the fuze arrangement may be configured to be actuated from a default state to operate in a default operating mode being either a proximity operation mode or an impact delay operation mode or in an alternative mode being the other of the proximity operation mode and the impact delay operation mode.

[0098] In any system of the invention, the fuze arrangement may comprise a fuze setter operable to switch the fuze arrangement from the default operating mode to the other of the two operating modes.

[0099] In any system of the invention, the aerial munition may be an aircraft deployed munition selected from air-to-surface missiles, attack-UAVs and air-to-surface bombs carried by manned or unmanned aircraft.

[0100] In any system of the invention, the fuzing system for an aerial munition may be or may comprise a proximity sensor adapted to be mounted on the munition nose, a fuse arrangement comprising an impact sensor and a controllable fuze setter, and a TAU unit, wherein the proximity sensor and the fuze arrangement are electrically associated through a corresponding set of electric wires with the TAU unit provided between the proximity sensor and the fuze arrangement, wherein the controllable fuze setter is configured for association to an aircraft underwing pylon tail solenoid through a lanyard and operable to render the aerial munition operable in a proximity fuze mode or an impact fuze mode.

[0101] Any system of the invention may be included in an aerial munition. Thus an aerial munition is provided which comprises a fuzing system comprising a remotely controllable fuze setter or a fuze switch for association to an aircraft underwing pylon tail solenoid through a lanyard and operable to render the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release.

[0102] In any munition of the invention, the munition may comprise a body shell and a tail positioned at the rear end of the body shell and forming an integral part thereof, wherein the tail comprises a plurality of fins, the body shell comprises a proximity sensor positioned at a front end or nose of the munition, the fuzing system being internally positioned within the shell at the back end of the munition and a turbine alternator positioned between the proximity sensor and the fuzing system and being in electrical communication with the proximity sensor and the fuzing system, wherein the fuzing system comprises the fuze setter and an impact delay sensor, wherein each of the proximity and impact sensors are electrically associated with the fuze setter and wherein the fuze setter is configured for association to an aircraft underwing pylon tail solenoid through a lanyard and operable to be remotely switched between a proximity fuze mode and an impact fuze mode, or vice versa, to render the aerial munition operable in a proximity operational mode or an impact operational mode.

[0103] In any munition of the invention, the proximity sensor may be provided on a solid impact nose plug configured to allow for penetration of a target.

[0104] In any munition of the invention, the impact nose plug may be mounted in a fuze well.

[0105] In any munition of the invention, the proximity sensor may be provided in a radome associated with the impact nose plug element.

[0106] In any munition of the invention, the radome may be associated by threading onto an external periphery of the impact nose plug element or into a threaded internal surface of the plug element.

[0107] In any munition of the invention, the impact nose plug element may be configured to tightly associate or assemble into a recipient fuze well provided in a front end of the aerial munition.

[0108] In any munition of the invention, the impact nose plug element may have an internal elongated cavity for receiving therethrough electrical wiring from the proximity sensor.

[0109] In any munition of the invention, the electrical wiring electrically may associate the proximity sensor and a Turbine Alternator Unit (TAU).

[0110] In any munition of the invention, the proximity sensor may be configured to sense proximity over a wide range of angles, or a plurality of angular ranges, spanning both forward and lateral regions.

[0111] In any munition of the invention, the proximity sensor may be configured to generate a trigger output in response to proximity either in response to forward proximity of a target located ahead of the munition along the direction of travel of the munition, or in response to proximity of a target located laterally with respect to the munition.

[0112] In any munition of the invention, the proximity sensor may be selected from a radio frequency sensor (a radar), an optical sensor, an acoustic sensor, a magnetic sensor, or a pressure sensor.

[0113] The invention further provides an aerial munition nose plug assembly, the nose plug assembly comprising a proximity sensor mounted on a front end of a solid impact plug element, the impact plug element being configured to fit into a fuze well of the aerial munition. In an assembly according to the invention, the nose plug assembly may comprise a threaded region configured for associating by threading into the fuze well.

[0114] An aerial munition of the invention may be provided or incorporated or comprising a nose plug assembly according to the invention. The munition may be any munition of the invention.

[0115] The munition may be a dual-mode munition further comprising an impact sensor and a fuzing system comprising a remotely controllable fuze setter or a fuze switch configured and operable to render the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release.

[0116] The invention provides a method for arming (or loading or mounting) an aircraft with a plurality of aerial munitions, the method comprising mounting to an underwing region of the aircraft at least one aerial munition comprising a system according to the invention.

[0117] In any method of the invention, the method may comprise mounting of said at least one aerial munition on a pylon provided in an underside hardpoint region of the aircraft wing.

[0118] In any method of the invention, the pylon may be provided with an interface arrangement configured and operable to communicate the pylon status with the aircraft's systems.

[0119] In any method of the invention, a lanyard connected to and extending from a controllable fuze setter provided in the system may be connected to a pylon tail solenoid, wherein the pylon tail solenoid is remote-controllable.

[0120] In any method of the invention, the mounting may further comprise connecting the aerial munition to at least two connection points provided for carrying or securely holding the munition in place.

[0121] In any method of the invention, a turbine alternator provided on the munition may be connected with a lanyard to the pylon via a pylon nose solenoid.

[0122] In any method of the invention, the method may comprise connecting the at least one aerial munition to at least two connection points provided in an underwing region of the aircraft wing for carrying or securely holding the munition in place and connecting or associating a lanyard extending from a controllable fuze setter provided in said munition to a pylon tail solenoid provided in the underwing region of the aircraft wing, wherein the pylon tail solenoid is remote-controllable.

[0123] A method is provided for operating an aerial munition mounted onto an underside region of an aircraft wing, the aerial munition comprising a fuzing system comprising a proximity sensor mounted on the munition nose, a fuse arrangement comprising an impact sensor and a controllable fuze setter, and a TAU unit, wherein the proximity sensor and the fuze arrangement are electrically associated through a corresponding set of electric wires with a TAU unit provided between the proximity sensor and the fuze arrangement, wherein the controllable fuze setter is associated to the aircraft underwing pylon tail solenoid through a lanyard, the method comprising remotely causing the fuze setter to switch into an operating mode of choice during flight and prior to release of the munition.

[0124] In any method of the invention, the fuze setter may be switched electrically by a crew selectable mechanism.

[0125] In any method of the invention, the method may comprise [0126] mounting onto the aircraft one or a plurality of munitions, at least one of said munitions being a munition comprising a proximity sensor, an impact sensor and a fuzing system comprising a remotely controllable fuze setter or a fuze switch configured and operable to render the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release, [0127] connecting the fuze setter to the aircraft underwing pylon tail solenoid through a lanyard; [0128] in flight determining or obtaining information regarding a target profile, and [0129] prior to release of the munition, setting a flight deck fuzing mechanism to set the fuze setter in a proximity fuze mode or an impact fuze mode to thereby render the aerial munition operable in the proximity fuze mode or the impact fuze mode.

[0130] In any method of the invention, the method may comprise releasing the munition from the aircraft.

[0131] In any method of the invention, the aircraft may be an unmanned aircraft, wherein optionally the flight deck is a ground positioned flight operation deck.

[0132] In any method of the invention, the aircraft may be a manned aircraft, wherein optionally the flight deck is a cockpit.

[0133] In any method of the invention, the flight deck fuzing mechanism may be a mechanism by which a crew member selects the targeting mode.

[0134] In any method of the invention, the mechanism may be a physical toggle switch, a pressing a button; or an interface operated trigger.

[0135] Illustrative embodiments of the invention are described below. In the interest of clarity, not all features/components of an actual implementation are necessarily described.

[0136] FIG. 1 described stages presenting steps for effectively operating an aerial munition unit 10, according to the invention, and its advantageous capabilities. Loading 20 of an aerial munition unit 10 onto an aircraft is achieved by means known in the art. In the process of loading, the munition unit 10 is associated via a lanyard extending from the munition fuze arrangement with a pylon tail solenoid at an underside of an aircraft wing. The pylon serves to connect both electronic and mechanical systems which are essential to the operating and releasing of the munition.

[0137] After takeoff and following target selection 30, the pilot determined the target's features or characteristics or generally the target's profile 40, which may be known in advance or may be determined during mission. Based on the target profile, the pilot may determine and select 50 the most effective operating mode for the aerial munition unit 10 or for a plurality of such units and determine whether the suitable operating mode is the default operating mode of aerial munition unit 10, in which case there is no need to actively reset or switch the fuze setter, or whether the alternative operating mode of aerial munition unit 10 is preferred.

[0138] Following selection of a suitable operating mode, the munition 10 is set to the desired operating mode, and the munition is released 60, thereafter advancing to target and detonating 70. Operation parameters relating to the type of munition and the course of travel to the target are not part of the invention.

[0139] FIG. 2 shows an illustration of a side view of an aerial munition unit 10, wherein unit 10 comprises a fuzing system according to the invention. Aerial munition unit 10 is associated with weapon pylon 100 which is integrally provided onto an underside of an aircraft wing (not shown). The aerial munition unit 10 comprises a body shell 110, and tail 115 positioned at the rear end of the body shell and which forms an integral part thereof, wherein tail 115 comprises a plurality of fins, e.g., 3 or more, depicted in a 4-fin configuration comprising fins 116, 117, 118, and a fourth fin (not shown) that is positioned adjacent to the horizontal rear part of the body shell 110. Body shell 110 comprises a proximity sensor positioned in a nose plug assmebly 120 positioned at the front end or nose 126 of the unit 10, a fuze arrangement 130 internally positioned within the shell 110 at the back end of the unit 10, wiring, e.g., wires 145A and 145B connecting a turbine alternator 140 to the proximity sensor and the fuze arrangement.

[0140] As a person versed in the art world appreciate, general purpose munitions used in most aerial operations may be used with both nose and tail mechanical or electronic fuzes and conical or retarding fins. Thus, in certain configurations of a unit 10 according to the invention, the fuze assembly may be provided with a front fuze member and a back fuze member. Additionally, in certain configurations, the body shell 110 of a unit 10 may be provided with any shaped fins, with fixed position fins or with retarding fins.

[0141] As further shown in FIG. 2, wires 145A and 145B are each connected to the turbine alternator 140, at one end, while wire 145A is connected to the sensor assembly 120 on its other end, and wire 145B is connected to the fuze arrangement 130 at its other end.

[0142] Fuze arrangement 130 comprises an impact sensor (not shown), a rear end 135 (depicted in FIG. 5 and FIG. 6) comprising a controllable fuze setter or switch for selecting the fuze operating mode. Optionally, the fuze rear end 135 and the controllable fuze setter may be part of a fuze control pane comprising a number of switches or dials for controlling activation parameters of the munition unit 10, as further detailed with respect of FIG. 6.

[0143] As further depicted in FIG. 3 (in combination with FIG. 2), a munition nose plug assembly 120 comprises a radome 125 typically forming a rounded aerodynamic shape and protecting the proximity sensor 200, e.g., radar antenna, contained in the front end 126, and a solid impact nose plug element 160 which is positioned within a fuze well 170. The solid impact nose plug element comprising an elongated channel or cavity 210 for receiving thereinto electric wiring 145A electrically associating the proximity sensor and the turbine alternator 140 (FIG. 2) of the munition unit, as described herein.

[0144] According to some configurations, the proximity sensor included in the assembly 120 is screwed onto the nose plug element 160, and nose plug element 160 is screwed into the fuze well 170.

[0145] Turbine alternator 140 is connected with a lanyard 180 to pylon 100 at a slot 185 via a pylon nose solenoid (as shown in FIG. 2). The pylon nose solenoid is controllable remotely and may be positioned in the cockpit, or elsewhere on the aircraft, or on pylon 100. According to the present invention, the pylon nose solenoid can be activated by the pilot or by an air crew member on board of the aircraft or on ground by a distant operator monitoring the pylon nose solenoid positioned outside of the aircraft (e.g., on ground, on another airborne vehicle), or by remote sensors system controlling the pylon nose solenoid.

[0146] Lanyard 190 is connected to the controllable fuze setter positioned in the fuze arrangement 130 through the rear end 135 of the arrangement. The controllable fuze setter can be activated by lanyard 190. Lanyard 190 is connected to pylon 100 through slot 195 and sequentially to a pylon tail solenoid (not shown). The pylon tail solenoid is controllable remotely, and may be positioned in the cockpit, or elsewhere on the aircraft, or on pylon 100.

[0147] According to some configurations, aerial munition unit 10 has a default operating mode, i.e., proximity sensing fuzing mode; however, subject to activation of the controllable fuze setter the alternative operable fuzing mode may be selectable. Thus, activation of the fuze setter will determine that the operable fuzing mode is selected to be the impact/delay fuzing system instead of the default operable system, i.e., proximity sensing fuzing system.

[0148] The ability to select a desirable operating mode at any stage is due to the coexistence of two (or optionally more than two) operating fuzing modes, and the fact that the wiring layout which comprises wires 145A and 145B, as well as lanyards 180 and 190 allows selecting the desired operating fuzing mode. All elements including the nose plug assembly 120, fuze arrangement 130, wiring and lanyards, turbine alternator 140, constitute the fuzing system of the present invention.

[0149] FIG. 3 is a blown-up view of a nose plug assembly 120 including a proximity sensor 200 within a radome 125 forming the rounded aerodynamic shape, being optionally a radar antenna, contained in the front end, and a nose plug element 160. Wiring 145A connecting the proximity sensor and the turbine alternator 140 passes through an elongated cavity or a channel 210 formed in the nose plug element 160. The assembly 120 comprising the radome 125, the proximity sensor 200, and the nose plug element may be formed by associating the components by threading one onto the other and placing the assembly within the fuze cavity 170 provided in the munition nose.

[0150] FIG. 4 shows a depiction of an air-to-ground missile 300 representing a munition unit according to the invention. Missile 300 is shown with a sensor assembly 310 (shown in detail in FIG. 3) positioned at the nose end of the missile, a lanyard 320 configured for connecting the missile 300 to the pylon nose solenoid (not shown) and a lanyard 330 which extends from the fuze arrangement internally contained in the missile (not shown) to a pylon tail solenoid. A depiction of a rear end of the fuze arrangement is provided in FIG. 5, showing presence of several electronic components 410 and a lanyard 420 extending from the fuze setter 430 to the pylon tail solenoid (not shown).

[0151] FIG. 6 presents a blown-up depiction of the rear end 135 of the fuze arrangement 130 discussed in FIG. 1. As shown in FIG. 6, the fuze rear end 135 comprises several electronic elements, including a delay after height of burst detection switch 500, a communication connector 510, an impact fire delay switch 520, a height of burst switch 530, ARM time delay switch 540, and a controllable fuze setter 550. The controllable fuze setter 540 may be connected to the tail lanyard 420 shown in FIG. 5 for determining the operating mode

[0152] It should be understood that the above description is merely exemplary and that there are various embodiments of the present invention that may be devised, mutatis mutandis, and that the features described in the above-described embodiments, and those not described herein, may be used separately or in any suitable combination; and the invention can be devised in accordance with embodiments not necessarily described above.