IL299992B1 - Remotely controllable fuzing arrangements - Google Patents

Description

REMOTELY CONTROLLABLE FUZING ARRANGEMENTS FIELD OF THE INVENTION The present invention generally relates to an aerial munition comprising more than one controllable attack mode. BACKGROUND OF THE INVENTIONAerial munition units (e.g., missiles, projectiles) mounted on aircrafts are chosen to meet certain requirements relating to air-to-ground missions which may be pre-designated or unpredicted such as during wartime. Among the many modes of fuzing systems, proximity sensing and impact fuzing systems are most common. While proximity fuzing allows detonation within a preset distance from a target, impact fuzing or impact/delay fuzing involves detonation upon impact, or at a preset time after impact. In order to have maximal effect, aerial munitions with different fuzing systems are utilized for targeting specific destinations. Aerial munitions comprising impact/delay fuzing systems may be used for targets with a rigid exterior surface (e.g., bunker, naval vehicle, tank), yet for targets having a "soft" exterior surface (e.g., shed, trees), or no exterior surface (e.g., unit of troops) impact triggering may not be effective, requiring aerial munitions to be equipped with proximity sensor fuzing systems. Using aerial munition with fuzing systems unsuitable for a particular target or mission is much less effective, and often completely ineffective, resulting in a waste of resources and a potentially failed or unsuccessful aerial attack. US Patent No. 3,722,416 discloses a selective multi-mode fuze firing circuit for a missile, wherein the multi-mode fuze comprises: A. a select voltage input terminal means for accepting any one of three sct voltages for selecting any one of proximity, impact- instantaneous and impact-delay modes of operation, B. a fuze voltage supply input, C. a proximity signal input, D. an instantaneous detonation means, E. a delay detonation means, F. an impact fuzing means, G. a two-position three-section switch means, H. first and second fuse links, I. a gas diode which will ignite in either direction at a specific potential, J. a firing capacitor, K. the first section being closed to ground and the second and third sections being open in the first position of said three-section switch means, L. first and second charging resistors, M. one side of each of said fuse links, firing capacitor and one side of the third section of said three-section switch means being connected to the select voltage input terminal through said first charging resistor, N. said delay detonation means being connected between the other side of the third section of said three-section switch means and ground, O. first and second diode rectifiers, P. first and second bleeder resistors each connected to a respective opposite side of said firing capacitor, Q. the other side of said first fuse link being connected to said proximity signal input, the cathode of said diode rectifier and one side of said gas diode; the other side of said gas diode being connected to ground, R. the other side of said second fuse link being connected to the anode of said diode rectifier and one side of the second section of said three-section switch means, S. said instant detonation means being connected between the other side of the second section of said three-section switch means and ground, T. said impact fusing means being connected between the other side of said firing capacitor and ground, U. one side of the first section of said three-section switch means being connected to the cathode of said second diode rectifier, V. the other side of the first section of said three-section switch means being connected to the other side of said firing capacitor for connecting said capacitor to ground when the switch means is in a first position and to the cathode of said second diode rectifier when in its second position, W. said second charging resistor being connected between the anode of said second rectifier and said fuze voltage supply input, X. whereby each of any of said three select voltages applied to said select voltage input terminal will select a particular one of any of proximity, impact-delay and impact-instantaneous modes of operation. PUBLICATIONS[ 1 ] US Patent No. 3,722,4 SUMMARY OF THE INVENTION Limitation on aerial munition loading and the availability of different types of fuzing systems enabling different attack modes that are tailored for different targets and missions, combined with the versatility and unpredictability of aerial missions, motivates a need for an aerial munition system that combines both proximity and impact (or delayed impact) detonation capabilities and allows a pilot or a crew member to select, switch or otherwise determine the detonation capabilities of any of the aircraft loaded munitions in real time, at any time during an aerial mission. By providing the mission crew with a real-time ability to render any given munition with a proximity or impact fuze capability, performance of versatile missions may be greatly improved, limited only by the loading capacity of the aircraft. 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. As a person versed in the art would realize, the technology of the invention allows for maximizing a munition load of an aircraft, by loading a single hybrid-type or dual-mode munition. Switching between the munition or operation modes (i.e., between proximity operation mode and impact operation mode, or vice versa) may be done before weapon release, once the characteristics of the target or the mission are realized. As the switching is reversible, the technology allows for immediate adaptation to mission variations, thereby increasing mission capabilities. In a first of its aspects, the invention provides a fuzing system or a fuze arrangement 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 to render the aerial munition operable in a proximity fuze mode or an impact fuze mode during flight and prior to munition release. As used herein, the expression " to render the aerial munition operable in a proximity fuze mode or an impact fuze mode " refers to activation of the proximity sensor such that detonation is triggered at 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. When in the proximity operation mode, detonation in response to impact or after impact may still be possible in case proximity detonation has failed. However, when in the impact operation mode, detonation triggered by the proximity sensor is inactivated. The invention further provides a fuzing system for an aerial munition, the fuzing system comprises a proximity sensor adapted to be mounted on the munition nose and a fuze arrangement comprising an impact sensor and a remotely controllable fuze setter or a fuze switch 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, wherein each of the proximity and impact sensors are electrically associated with the fuze setter.

In a typical operation of a proximity sensor the munition is set to automatically trigger detonation when the distance to the target becomes smaller than a predetermined value. To enable a continuous distance estimation, a proximity sensor is positioned at the nose of the munition and is configured to uninterruptedly and continuously measure the distance to the target. An impact or impact delay munition that is configured to trigger detonation upon impact or after a delay following penetration (a firing delay), typically requires the use of a hard solid nose plug that is configured to allow penetration. While the impact sensor is positioned away from the nose plug so as not to be damaged during impact and maintain delayed detonation, the hard solid plug is mounted at the nose of the munition, occupying a space immediately adjacent to the proximity sensor. To maintain both capabilities, namely provide a munition having both a front proximity sensor that is uninterruptedly operable and a solid plug that is associated with the impact sensor that allows for delayed detonation, a unique munition has been devised which comprises a proximity sensor positioned, assembled or provided on a front end of a solid nose plug that is configured as a penetrating nose plug, wherein the plug is arranged and configured to fit into a fuze well provided in a variety of munitions, e.g., any standard munition type that has a front fuze well, such as, for example munitions of the MK-80 series. A turbo alternator TAU is further provided, as disclosed herein. The nose section is arranged for mounting or association, or is configured for association, typically via mechanical association with the solid nose plug. The association between the nose section and the plug may be by threading the plug into a threaded internal surface of the nose section. The plug section is configured to tightly associate or assemble into a recipient nose well present in a front end of the munition. The assembly of the plug into the nose well of the munition body may similarly be achieved by threading. The nose section and the plug may be associated to each other by any means, e.g., screw threading, to be integrally formed into a unit that can be assembled to a nose well of the munition. The integrally formed unit, wherein the nose section is associated with the plug section by any means, such as mechanical means, magnetic means, electric means etc., comprises the proximity sensor which is electrically associated with the fuze arrangement comprising the remotely controllable fuze setter. The electrical association between the proximity sensor and the fuze arrangement may be achievable by electric wiring. A Turbine Alternator Unit (TAU) may be provided between the proximity sensor and the fuze arrangement and is intended to arm the fuze arrangement by an air driven turbine alternator, once certain environmental conditions are met after the munition has been released, to provide electrical power for arming the fuze. These environmental conditions may comprise flight altitude, air turbulence, temperature, speed and others, all of which providing indication that the munition has been released from the aircraft. In some embodiments, a fuzing system of the invention, for aerial munition, comprises a proximity sensor, 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. Thus, in another aspect, there is provided a fuzing system for an aerial munition, the fuzing system comprises 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. The impact sensor is a member or a device that is configured to initiate an explosion upon impact of the munition against a target. The impact sensor may detect impact through vibrations formed as a result of the impact or through direct contact with a hard surface. The impact sensor may be of any desired type, for example, a piezoelectric sensor or a mechanical sensor. In some configurations, the impact sensor may be an impact delay sensor, whereby detonation occurs after a predetermined time period following impact. The proximity sensor may be a radio frequency sensor (a radar), an optical sensor, an acoustic sensor, a magnetic sensor, a pressure sensor or any other sensor known in the art for electronic target detection. The proximity sensor may be alternatively 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. In other words, a 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. The fuze arrangement typically positioned or attached to the end of the munition is an assembly of components that are directly or in association responsible for detonation of the munition main explosive. The fuze arrangement may be an arrangement of analogue electrical circuitry with appropriate components, a digital processor, or any combination thereof, and may also include various mechanical components, as is known in the art. The fuze arrangement may be configured to set off the detonation of the main explosive in response to triggering by the proximity sensor or the impact delay sensor. The fuze arrangement is therefore configured to be actuated to operate in either of a proximity operation mode or an impact delay operation mode. The dual-mode fuzing system of the invention, which provides dual mission modes of proximity sensing and impact delay in a single warhead configuration, is configured to allow a pilot or another crew member to controllably render a variety of aerial munitions, such as air to ground munitions, operative in one of the two attack modes. Aerial munitions may be any aircraft deployed munitions including, for example, air-to-surface missiles, attack-UAVs and air-to-surface bombs carried by manned or unmanned aircrafts, all for use against surface targets, whether land based or sea-based. In accordance with typical operating parameters, the munition is mounted on a pylon provided in an underside hardpoint region of the aircraft wing (herein regarded as an underwing region of an aircraft). The pylon has an interface box which includes the electronics needed to communicate its status with the aircraft systems, the kind of payload it holds, the firing protocol, whether a firing was successful, etc. A conventional pylon is provided with a plunger that is provided with a small explosive cartridge aimed to ensure that on release, the munition is given sufficient downward relative velocity so that it safely detaches. The pylon may also be provided with a launcher which serves as a rail where the missile can slide on and electro-mechanically locked in. At least two connection points are provided in an underwing region of any aircraft for carrying or securely holding a munition in place. In a munition according to the invention, the turbine alternator is connected with a lanyard to the pylon via a pylon nose solenoid. The pylon nose solenoid can be activated by the pilot or by an air crew member on board of the aircraft or 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 controlling the pylon nose solenoid. A lanyard connected to and extending from the controllable fuze setter positioned in the fuze arrangement is connected to the pylon through a different slot on the pylon and sequentially to a pylon tail solenoid. The pylon tail solenoid is remote-controllable, from the cockpit, to switching between the operation modes, as disclosed herein. The switching between the fuze operating modes may be achieved from the aircraft cockpit by a switch member or other selection mechanism that is electrically associated through the pylon tail solenoid with the fuze setter positioned in the fuze arrangement. The switching between the modes may be reversible as long as the munition has not been released. In some configurations of a system of the invention, an aerial munition may be set with a default operable fuze operating mode, i.e. proximity sensing mode. At loading, the pilot is aware of the set or default operating mode and following target selection and understanding of the target’s features or characteristics or generally the target’s profile, which may be known in advance or may be determined during mission, and may select the most effective operating mode for a given munition unit. In case the suitable operating mode is the default operating mode, there is no need to remotely operate the fuze switch. Alternatively, the pilot may be required to activate the fuze by selecting the alternative operating mode for the aerial munition unit. Following selecting the appropriate operation mode, the pilot may release the aerial munition, which subsequently advances in a direction of the target for detonation. The target’s profile based on which a pilot or a crew member may select the most effective operating mode for a given munition unit may include any targeting intelligence collected by data collecting means such as sensors, satellites, ground-based radar stations and personal which are on or off the aircraft that is delivering the munitions. These data regarded as " target profile " may include specific information relating to mission particulars (airspeed of the aircraft, vector and heading of the aircraft, windspeed, number and type of aircrafts in the combat theatre, number and type of anti-aircraft weapons in the theatre, command directives, etc), the target itself (e.g., size and height of the target, the type of the target, structures around the target, populations around the target, etc), environmental conditions around the target (e.g., weather data, temperature, humidity, visibility, etc) and other factors which may have an effect on the pilot or crew decision making.

Thus, the invention further provides a crew-selectable dual-moda aerial munition, the munition comprising a body shell and a tail positioned at the rear end of the body shell and which forms an integral part thereof, wherein the tail comprises a plurality of fins, e.g., 3 or more fins, the body shell comprises a proximity sensor positioned at a front end or nose of the munition, a fuze arrangement internally positioned within the shell at the back end of the munition and a turbine alternator positioned between the proximity sensor and the fuze arrangement and being in electrical communication with the proximity sensor and the fuze arrangement, wherein the fuze arrangement comprises a 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 render the aerial munition operable to be remotely switched between a proximity fuze mode and an impact fuze mode, or vice versa. In some embodiments, the proximity sensor is provided on a solid nose plug configured to allow for penetration of a target. In some embodiments, the nose plug is mounted in a fuze well. 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 nose plug element, the nose plug element being configured to fit into a fuze well of the aerial munition. In some embodiments, the proximity sensor is provided in a radome (a weatherproof enclosure that protects the proximity sensor, e.g., a radar antenna) that is associated with the solid nose plug element by threading onto an external periphery of the plug element or into a threaded internal surface of the plug element. In some embodiments, the plug element is configured to tightly associate or assemble into a recipient nose well provided in a front end of the aerial munition. In some embodiments, the nose plug assembly comprising a threaded region configured for associating by threading into the nose well. In some embodiments, the nose plug having an internal elongated cavity for receiving therethrough electrical wiring from the proximity sensor.

In some embodiments, the electrical wiring associates the proximity sensor and a Turbine Alternator Unit (TAU). In some embodiments, the proximity sensor is configured to sense proximity over a wide range of angles, or a plurality of angular ranges, spanning both forward and lateral regions. In some embodiments, the proximity sensor is 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. In some embodiments, the proximity sensor is selected from a radio frequency sensor (a radar), an optical sensor, an acoustic sensor, a magnetic sensor, a pressure sensor or any other sensor known in the art for electronic target detection. The invention further provides an aerial munition provided with a nose plug assembly according to the invention. In some embodiments, the aerial munition is 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, according to aspects and embodiments of the invention. The invention further provides a method for arming (or loading or mounting) an aircraft with a plurality of aerial munitions, the process comprising mounting at least one aerial munition according to the invention. In some embodiments, the process comprising mounting said at least one aerial munition according to the invention on a pylon provided in an underside hardpoint region of the aircraft wing. In some embodiments, the pylon is provided with an interface arrangement configured and operable to communicate the pylon status with the aircraft’s systems. In some embodiments, a lanyard connected to and extending from the controllable fuze setter is connected to a pylon tail solenoid, wherein the pylon tail solenoid is remote-controllable. Thus, the invention provides a method for arming (or loading or mounting) an aircraft with a plurality of aerial munitions, the process comprising mounting at least one aerial munition according to the invention and connecting or associating a lanyard extending from a controllable fuze setter provided in said munition to a pylon tail solenoid provided in an underwing region of the aircraft wing, wherein the pylon tail solenoid is remote-controllable. In some embodiments, the mounting further comprises connecting the aerial munition to at least two connection points provided for carrying or securely holding the munition in place. Thus, in some embodiments, the method comprises mounting at least one aerial munition according to the invention, 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. In some embodiments, a turbine alternator provided on the munition is connected with a lanyard to the pylon via a pylon nose solenoid. The invention further provides 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 operation mode of choice during flight and prior to release of the munition. As noted herein, the fuze setter may be switched into the operation mode of choice, being a proximity mode or an impact mode or an impact delay mode by the pilot or an aircrew member. In some embodiments, the fuze setter is caused to switch into a desired operating mode by remotely setting a switch member or other selection mechanism that is electrically associated through the pylon tail solenoid with the fuze setter positioned in the fuze arrangement. The invention further provides a method for operating an aerial munition mounted onto an underside region of an aircraft wing or for setting an operating mode of an aerial munition mounted onto an aircraft, the method comprising: in an aerial munition comprising a body shell and a tail positioned at the rear end of the body shell and which forms an integral part thereof, wherein the tail comprises a plurality of fins, e.g., 3 or more fins, the body shell comprises a proximity sensor positioned at a front end or nose of the munition, a fuze arrangement internally positioned within the shell at the back end of the munition and a turbine alternator positioned between the proximity sensor and the fuze arrangement and being in electrical communication with the proximity sensor and the fuze arrangement, wherein the fuze arrangement comprises a 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 associated 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; remotely causing the fuze setter to switch into a fuze mode of choice during flight and prior to release of the munition. In some embodiments, the fuze setter is switched electrically by a crew selectable mechanism. In some embodiments, 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, as defined herein, 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.

In some embodiments, the method comprises releasing the munition from the aircraft. In some embodiments, the aircraft is an unmanned aircraft, wherein optionally the flight deck is a ground positioned flight operation deck. In some embodiments, the aircraft is a manned aircraft, wherein optionally the flight deck is a cockpit. The aircraft crew may be a pilot or any crew member in a manned aircraft or any person on ground, on a naval vessel, or in another aircraft, capable of operating the munition in accordance with the invention. In some embodiments, the aircraft crew is the pilot or any crew member of a manned aircraft. The flight deck fuzing mechanism is any crew-selectable means that the targeting mode of the munition can be switched or selected by a crew member, as defined. The fuzing mechanism is the mechanism by which a crew member selects the targeting mode. This mechanism may be broadly contemplated and could include any mechanism known in the art where a pilot or crewmember indicates their choice using an interface. In some configurations, the mechanism may be a physical toggle switch. In other configurations, it may be a pressing a button; or an interface operated trigger. Alternatively, the fuzing may be invoked by blinking one’s eyes, by spoken word or sound, by haptic interface, gesture or by other equivalent means for selection as by using a computer interface to indicate the crew member’s selection preference. While the present technology is described with respect to two alternative operating modes, namely proximity sensing mode and an impact/delay mode, it should be noted that other operating modes may also be provided. Furthermore, general purpose munitions used in most aerial operations may be used with both nose and tail mechanical, electromechanical or electronic fuzes and conical or retarding fins. Thus, in certain configurations of a munition according to the invention, the fuze arrangement may be provided with a front fuze member and a back fuze member. Additionally, in certain configurations, the munition may be provided with any shaped fins, with fixed position fins or with retarding fins. BRIEF DESCRIPTION OF THE DRAWINGSThe invention may be more clearly understood when considering the following non-limiting exemplary embodiments, with reference to the following drawings, in which: Fig. 1 is a flowchart presenting stages of operation of an aerial munition unit in accordance with embodiments of the present invention. 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. 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. Fig. 4 is a schematic presentation of a missile provided with a fuzing system of the invention. Fig. 5 provides a depiction of a rear end of an exemplary fuze arrangement used according to certain embodiments of the present invention. Fig. 6 provides a depiction of a rear end of an exemplary fuze arrangement including a fuze setter. DETAILED DESCRIPTION OF EMBODIMENTS 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. 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. In any system of the invention, the fuze setter may be operated from an aircraft flight deck or from a ground flight operation deck. 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.

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. In any system of the invention, the impact sensor may be configured to initiate an explosion upon impact of the munition against a target. 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. In any system of the invention, the impact sensor may be a piezoelectric sensor or a mechanical sensor. 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. 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. 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. 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. In any system of the invention, the proximity sensor may be provided in a front radome. In any system of the invention, the proximity sensor may be mounted on a nose plug element. 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. 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. 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. 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. 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. 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. 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. 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. In any munition of the invention, the impact nose plug may be mounted in a fuze well. In any munition of the invention, the proximity sensor may be provided in a radome associated with the impact nose plug element. 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. 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. 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. In any munition of the invention, the electrical wiring electrically may associate the proximity sensor and a Turbine Alternator Unit (TAU). 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. 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. 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. 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. 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. 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. 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. 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. 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. 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. 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. 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. 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.

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. In any method of the invention, the fuze setter may be switched electrically by a crew selectable mechanism. In any method of the invention, the method may comprise -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. In any method of the invention, the method may comprise releasing the munition from the aircraft. 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. In any method of the invention, the aircraft may be a manned aircraft, wherein optionally the flight deck is a cockpit. In any method of the invention, the flight deck fuzing mechanism may be a mechanism by which a crew member selects the targeting mode. In any method of the invention, the mechanism may be a physical toggle switch, a pressing a button; or an interface operated trigger.

Illustrative embodiments of the invention are described below. In the interest of clarity, not all features/components of an actual implementation are necessarily described. 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. 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 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. 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. 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 assmebly120 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.

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. 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. Fuze arrangement 130 comprises an impact sensor (not shown), a rear end 135 (depicted in Fig. 5and 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 . 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. 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. 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.

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 1and 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. 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. 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. 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 1comprising 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. 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.

Claims (47)

1./ CLAIMS: 1. 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.

2. The system according to claim 1, wherein the fuze setter is operated from an aircraft flight deck or from a ground flight operation deck.

3. The system according to claim 1 or 2, 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.

4. The system according to any one of the preceding claims, 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.

5. The system according to any one of the preceding claims, wherein the impact sensor is configured to initiate an explosion upon impact of the munition against a target.

6. The system according to any one of claims 1 to 4, wherein the impact sensor is configured to detect impact through vibrations formed due to impact or through direct contact with a hard surface.

7. The system according to any one of claims 1 to 6, wherein the impact sensor is a piezoelectric sensor or a mechanical sensor.

8. The system according to any one of claims 1 to 7, wherein the impact sensor is an impact delay sensor, whereby detonation occurs after a predetermined time period following impact.

9. The system according to any one of claims 1 to 8, wherein the proximity sensor is configured to sense proximity over a wide range of angles, or a plurality of angular ranges, spanning both forward and lateral regions.

10. The system according to any one of claims 1 to 8, wherein the proximity sensor is configured to generate a trigger output in response to proximity either in response to 299992/ 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.

11. The system according to any one of claims 1 to 10, wherein the proximity sensor is selected from a radio frequency sensor (a radar), an optical sensor, an acoustic sensor, a magnetic sensor, or a pressure sensor.

12. The system according to any one of claims 1 to 11, wherein the proximity sensor is provided in a front radome.

13. The system according to any one of claims 1 to 12, wherein the proximity sensor is mounted on a nose plug element.

14. The system according to any one of the preceding claims, 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.

15. The system according to any one of the preceding claims, 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.

16. The system according to claim 15, 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.

17. The system according to any one of the preceding claims, wherein the aerial munition is an aircraft deployed munition selected from air-to-surface missiles, attack-UAVs and air-to-surface bombs carried by manned or unmanned aircraft.

18. The system according to claim 1, the system being for an aerial munition and comprising 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. 299992/

19. 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.

20. The munition according to claim 19, 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.

21. The munition according to claim 19 or 20, wherein the proximity sensor is provided on a solid impact nose plug configured to allow for penetration of a target.

22. The munition according to claim 21, wherein the impact nose plug is mounted in a fuze well.

23. The munition according to any one of claims 20 to 22, wherein the proximity sensor is provided in a radome associated with the impact nose plug element.

24. The munition according to claim 23, wherein the radome is associated by threading onto an external periphery of the impact nose plug element or into a threaded internal surface of the plug element.

25. The munition according to any one of claims 20 to 24, wherein the impact nose plug element is configured to tightly associate or assemble into a recipient fuze well provided in a front end of the aerial munition. 299992/

26. The munition according to any one of claims 20 to 25, wherein the impact nose plug element having an internal elongated cavity for receiving therethrough electrical wiring from the proximity sensor.

27. The munition according to claim 26, wherein the electrical wiring electrically associates the proximity sensor and a Turbine Alternator Unit (TAU).

28. The munition according to any one of claims 20 to 27, wherein the proximity sensor is configured to sense proximity over a wide range of angles, or a plurality of angular ranges, spanning both forward and lateral regions.

29. The munition according to any one of claims 20 to 27, wherein the proximity sensor is 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.

30. The munition according to any one of claims 20 to 27, wherein the proximity sensor is selected from a radio frequency sensor (a radar), an optical sensor, an acoustic sensor, a magnetic sensor, or a pressure sensor.

31. The system according to claim 13, wherein the element proximity sensor is 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.

32. The system according to claim 31, wherein the impact plug element comprising a threaded region configured for associating by threading into the fuze well.

33. 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 any one of claims 1 to 18.

34. The method according to claim 31, comprising mounting said at least one aerial munition on a pylon provided in an underside hardpoint region of the aircraft wing.

35. The method according to claim 34, wherein the pylon is provided with an interface arrangement configured and operable to communicate the pylon status with the aircraft’s systems.

36. The method according to any one of claims 33 to 35, 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. 299992/

37. The method according to any one of claims 33 to 36, 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.

38. The method according to any one of claims 33 to 37, wherein a turbine alternator provided on the munition is connected with a lanyard to the pylon via a pylon nose solenoid.

39. The method according to any one of claims 33 to 38, 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.

40. 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.

41. The method according to claim 40, wherein the fuze setter is switched electrically by a crew selectable mechanism.

42. The method according to claim 40, 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 299992/ -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.

43. The method according to claim 42, wherein the method comprises releasing the munition from the aircraft.

44. The method according to any one of claims 33 to 43, wherein the aircraft is an unmanned aircraft, wherein optionally the flight deck is a ground positioned flight operation deck.

45. The method according to any one of claims 33 to 43, wherein the aircraft is a manned aircraft, wherein optionally the flight deck is a cockpit.

46. The method according to claim 42, wherein flight deck fuzing mechanism is a mechanism by which a crew member selects the targeting mode.

47. The method according to claim 46, wherein the mechanism is a physical toggle switch, a pressing a button; or an interface operated trigger.