WO2017200460A1 - Dispositif et procédé de limitation de direction de tir et agencement de contre-mesure - Google Patents

Dispositif et procédé de limitation de direction de tir et agencement de contre-mesure Download PDF

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Publication number
WO2017200460A1
WO2017200460A1 PCT/SE2017/050442 SE2017050442W WO2017200460A1 WO 2017200460 A1 WO2017200460 A1 WO 2017200460A1 SE 2017050442 W SE2017050442 W SE 2017050442W WO 2017200460 A1 WO2017200460 A1 WO 2017200460A1
Authority
WO
WIPO (PCT)
Prior art keywords
firing
directable
angle range
launch angle
limiting structure
Prior art date
Application number
PCT/SE2017/050442
Other languages
English (en)
Inventor
Christer ZÄTTERQVIST
Original Assignee
Saab Ab
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from SE1651465A external-priority patent/SE1651465A1/en
Application filed by Saab Ab filed Critical Saab Ab
Priority to ES17799764T priority Critical patent/ES2889448T3/es
Priority to PL17799764T priority patent/PL3458793T3/pl
Priority to EP17799764.0A priority patent/EP3458793B1/fr
Priority to DK17799764.0T priority patent/DK3458793T3/da
Priority to US16/301,282 priority patent/US11008099B2/en
Priority to IL262828A priority patent/IL262828B/en
Publication of WO2017200460A1 publication Critical patent/WO2017200460A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A17/00—Safety arrangements, e.g. safeties
    • F41A17/08—Safety arrangements, e.g. safeties for inhibiting firing in a specified direction, e.g. at a friendly person or at a protected area
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A27/00—Gun mountings permitting traversing or elevating movement, e.g. gun carriages
    • F41A27/06—Mechanical systems
    • F41A27/08—Bearings, e.g. trunnions; Brakes or blocking arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H11/00—Defence installations; Defence devices
    • F41H11/02—Anti-aircraft or anti-guided missile or anti-torpedo defence installations or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
    • F41F1/08—Multibarrel guns, e.g. twin guns
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/70—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies for dispensing radar chaff or infrared material

Definitions

  • the present invention relates to a firing direction limitation device for preventing that e.g. flares, chaff, shotgun shots, pellet loads or similar are fired in a direction exposing friendly personnel or vehicles to danger.
  • Arrangements for storing and launching payloads such as countermeasures, which are designed to be mounted on aircrafts such as helicopters or fighters, are previously known.
  • the countermeasures are connected to a firing control device for feeding firing signals to the countermeasures.
  • the countermeasures may consist of passive means, such as chaff foil, but can also consist of for example IR flares, or other active measures.
  • the countermeasures are stored in one or more magazines, where a magazine comprises a plurality of cartridges, preferably with one countermeasure in each cartridge.
  • One problem with known dispensers and magazines mounted on aircrafts is that the launch angle of a countermeasure is fixed to a set angle which is believed to be optimal for the intended use. Depending on the purpose of the countermeasure, it may be of advantage to use different firing directions.
  • a preferred launch direction may be upwards towards a helicopter rotor, if flares are released, a preferred launch direction may be somewhat forwards and downwards.
  • a dispenser mounted on a helicopter may therefore be provided with several magazines, directed in different directions.
  • a solution with a fixed launch angle may be a good solution for an aeroplane, which has a known flight direction and a known speed range.
  • Helicopters may be provided with several magazines holding cartridges with countermeasures. Each magazine may be positioned at a predefined position and pointing in a predefined direction on the helicopter, such that several magazines will cover a larger firing range, i.e. launch angle range. It would in some situations also be possible to steer the helicopter such that a desired firing direction of a countermeasure is obtained.
  • the forward direction of an aircraft is defined as a direction in which the nose of the aircraft is pointing when flying.
  • the forward direction is defined as the direction in which the nose of the helicopter essentially is pointing when flying, which is essentially parallel to the horizontal plane, i.e. floor and the rotor of the helicopter are essentially parallel to the horizontal plane.
  • a solution at least partially alleviating or eliminating the drawbacks and problems associated with prior art solutions, is to arrange the magazine in a directable manner such that the firing direction of e.g. flares, chaff or similar can be controlled, i.e. selected, by means of what is referred to as having a variable magazine.
  • having a directable variable magazine for which the firing direction is controllable or selectable may be problematic since, depending on where the variable magazine is arranged on the aircraft, if directed in certain directions there may be an imminent risk that the aircraft itself, friendly aircrafts or personnel are exposed to danger, i.e. might get hit or damaged.
  • This is particularly problematic since countermeasure arrangements firing flares or chaff may be activated automatically and might respond to incoming threats without active aircrew consent. Controlling such functionality by means of software is possible, but verifying the reliability of such software, and configuring such software to be fail safe at all times, is difficult and costly.
  • An object of the present invention is to at least partially alleviate or eliminate drawbacks associated with the solutions known in the prior art. Another object is to provide a firing direction limitation device for an aircraft, wherein the firing direction limitation device can be used to prevent that in certain situations, such as during loading or unloading of personnel or material, when flying in formation or during normal operation flares, chaff, shotgun shots, pellet loads or similar are not fired in an undesirable direction whereby personnel, the fuselage of the aircraft, main/tail rotors, wings, friendly aircrafts or similar may be damaged.
  • a further object of the present invention is to provide a countermeasure arrangement comprising such a firing direction limitation device.
  • a further object of the present invention is to provide methods for controlling the allowed launch angle range of a directable firing device by means of such a firing direction limitation device.
  • Yet another object of the invention is to provide an aircraft comprising a firing direction limitation device.
  • the invention will further be described in association with aircrafts.
  • the invention is however suitable for use with magazines mounted to moving vehicles of all kinds and also magazines mounted in a stationary manner, either fixed on e.g. a building or on a movable stand.
  • the invention can thus be used with magazines on ground, and may be used on a vehicle such as a landing craft, a truck or a battle tank, or may be used in a stationary position on the ground, e.g. by the use of a stand or a tripod.
  • the firing direction limitation device is in this case used with a variable magazine in order to control in which directions that the magazine can be tilted in.
  • the firing direction limitation devices controls the launch angle of a variable magazine such that it does not cover the exits of a vehicle when a persons is to exit the vehicle. Allowed launch angles or allowed target area of a directable firing device can obviously be controlled by means of software developed for defining what, when and where firing is allowed. Controlling allowed launch angle ranges by means of software obviously has its advantages in that the software e.g. can be updated rapidly and offers great flexibility. However, for safety arrangements, such as for a firing direction limitation device, it may be preferable to avoid systems based on software. Software based systems generally uses numerous sensors and there is always a risk of malfunctioning software and/or malfunctioning sensors or incorrect sensor inputs. Also, software based application can potentially be hacked and for software based safety arrangements it is hard to verify the reliability, which may prevent such systems from being implemented and/or certificated. Complex software based systems are generally also expensive.
  • Launch angle may also be referred to as firing angle, particularly when the directable firing device refers to firing device firing shotgun shots, bullets or like.
  • the present invention refers to a mechanical firing direction limitation device for controlling the allowed launch angle range of a directable firing device configured to be tiltable between at least two allowed maximum launch angles, i.e. between two maximum outwardly directed positions, defining a launch sector.
  • the firing direction limitation device comprises a moveable limiting mechanical structure configured to be arranged in connection with the directable firing device.
  • the limiting structure is configured to be moveable between at least a first position and a second position.
  • the second launch angle range is limited in relation to the first launch angle range, whereby the allowed launch angle range of the directable firing device is controllable.
  • the directable firing device may at a general level be defined as a device capable of firing e.g. flares, chaff, shotgun shots, pellet loads or similar, having a fixed attachment point around which the directable firing device is tiltable.
  • the firing or launch direction of the directable firing device is directable over at least a launch angle range extending between the two maximum launch angles.
  • the launch angles between which the directable firing device is tiltable define the launch sector, thus the area over which e.g. countermeasures can be launched.
  • the second launch angle range is smaller than the first launch angle range.
  • the area over which the directable firing device is capable of firing or launching is herein defined as launch sector.
  • the moveable limiting structure is configured to be arranged in connection with the directable firing device. Being arranged “in connection with” is here defined as being arranged such that by moving between the first and second position the limiting structure can affect the freedom of the directable firing device to move in at least one direction.
  • the present invention has the exemplary advantage that when the limiting structure is set in the second position the allowed launch angle range of the directable firing device is limited in relation to the allowed launch angle range of the first position.
  • This control, i.e. limitation, of the allowed launch angle range is achieved by means of a mechanical system, i.e. mechanically moving the limiting structure from a first position to a second position, whereby challenges associated with software based systems are avoided.
  • the firing direction limitation device of the present invention may also offer a less expensive system for which the reliability is easier to verify.
  • the present invention may be used as a safety arrangement used to control in what direction e.g. flares, chaff, shotgun shots, pellet loads or similar are fired.
  • This may be used to prevent that e.g. the aircraft fuselage, the main/tail rotor of the aircraft, if being in form of a helicopter, or other parts on the aircraft may be hit even if the directable firing device is moveable.
  • setting the limiting structure of the firing direction limitation device in the second position may be used to define a safe zone.
  • Such a safe zone may e.g. be used to secure that personnel etc. is prevented from being hit when loading or unloading cargo.
  • Such a safe zone may also be used to secure that friendly aircrafts cannot be hit when flying in formation.
  • the limiting structure is configured to restrict the movements of the directable firing device in at least one direction.
  • the limiting structure may be configured to restrict the movements of the directable firing device in elevation direction, azimuth direction or preferably in both elevation and azimuth direction.
  • the allowed launch angle range over which the directable firing device is capable of firing/launching becomes limited when the limiting structure is set in the second position.
  • the effect the limited allowed launch angle range provides in terms of how the directable firing device is restricted from firing is obviously dependent on where and how the directable firing device, provided with the firing direction limitation device, is arranged at the aircraft.
  • how the limitation structure should be configured is directly dependent on where and how the directable firing device, provided with the firing direction limitation device, is intended to be arranged at the aircraft and should be configured accordingly.
  • the intended positioning on the aircraft must be considered when using a firing direction limitation device to provide a safe zone when a directable firing device is used.
  • the second launch angle range is limited in azimuth direction in relation to the first launch angle range, and according to another aspect of a firing direction limitation device the second launch angle range is limited in elevation direction in relation to the first launch angle range.
  • the second launch angle range is limited in both azimuth and elevation direction in relation to the first launch angle range.
  • a limited area, defined in both elevation and azimuth direction, defining how the directable firing device may be tilted in azimuth and elevation direction around an attachment point is defined.
  • This exemplary aspect of the present invention has the exemplary advantage that when the limiting structure is set in the second position the allowed launch angles in both azimuth and elevation direction of e.g. flares, chaff, shotgun shots, pellet loads or similar can be limited in relation to the allowed launch angles of the first position.
  • the allowed launch angles in both azimuth and elevation direction of e.g. flares, chaff, shotgun shots, pellet loads or similar can be limited in relation to the allowed launch angles of the first position.
  • the directable firing device is a variable magazine.
  • the variable magazine comprises a plurality of longitudinal cartridge cases forming the variable magazine, wherein each cartridge case comprises side walls and a front opening, and wherein the side walls of two adjacent cartridge cases are arranged to each other in a slidable manner in a longitudinal direction.
  • the variable magazine comprises a tilting means adapted to tilt the cartridge cases such that the openings of the cartridge cases can be directed in a selected direction. Controlling how the variable magazine can be directed, i.e. the allowed maximum launch angles and the allowed launch angel range, requires that additional factors and aspects are considered than for controlling how e.g. a canon or a machine gun can be directed.
  • variable magazine has, depending on the number of cartridge cases forming the magazine, a defined spatial extension not only in the intended firing direction, which may be considered to be in essentially Y- direction, but also in the two directions which are perpendicular to the firing direction, accordingly X-direction and Z-direction.
  • the variable magazine has a defined spatial extension in the XZ-plane. Also, since a variable magazine has multiple cartridge openings from which e.g.
  • flares, chaff, shotgun shots, pellet loads or similar may be fired and the positioning of such cartridge openings in X-direction and Z- direction, to use the same system of coordinates as previously used, differ significantly depending on from which individual cartridge case the flare, chaff, shotgun shots or similar is fired, the launch angle of each cartridge has to be taken in consideration when the limiting structure should be configured in order to provide a desired allowed launch angle range limitation, determining e.g. a desired safe zone during loading/unloading of a helicopter.
  • the directable firing device is a variable magazine this requires that the limiting structure has to be configured differently, and that additional aspects have to be considered, than if the directable firing device is e.g. a canon or a machine gun.
  • the present invention refers to a firing direction limitation device wherein the moveable limiting structure is provided in form of an encircling portion having an inner delimitation surface, wherein the inner delimitation surface determines the second launch angle range.
  • the present invention refers to a firing direction limitation device wherein the inner delimitation surface of the encircling portion is essentially circular, essentially square, essentially rectangular or irregularly shaped.
  • the shape of the inner delimitation surface of the limiting structure, of the firing limitation device is preferably configured in accordance to the intended mounting position of the directable firing device, for which the firing direction limitation device is applied, and according to over what area/in what angles it is desirable to prevent launching or firing. Thereby the allowed firing angles of the directable firing device can be controlled such that e.g. a safe zone is provided when the limiting structure is set in the second position.
  • the most suitable shape of the inner delimitation surface may be e.g. essentially circular, essentially square, essentially rectangular or irregularly shaped.
  • the present invention refers to a firing direction limitation device wherein the moveable limiting structure is in form of a sector portion having an inner delimitation surface, wherein the inner delimitation surface determines the second launch angle range.
  • the moveable limiting structure is in form of a sector portion having an inner delimitation surface, wherein the inner delimitation surface determines the second launch angle range.
  • the present invention refers to a firing direction limitation device wherein the movements of the limiting structure are projecting and retracting movements and wherein the projecting/retracting movements are controllable by means of at least one actuator.
  • the actuator is preferably directly controlled by a switch or a control unit operating the actuator without any involvement of software.
  • the limiting structure is configured such that the movement between the first position and the second position of the limiting structure are projecting and retracting movements, and that these movements are controlled by means of at least one actuator.
  • the present invention refers to a firing direction limitation device comprising at least one solenoid actuator.
  • Solenoid actuators are a suitable type of actuator for this specific implementation, even if also other actuators, or devices providing the same functionality as an actuator, are possible. It may be preferable that if the at least one actuator fails, breaks, stop working, lose power or become inoperative in any other way, the default setting of the limitation structure of the firing direction limitation device is the second position, thus that the limited launch angle range will be the default launch angle range.
  • the solenoid actuator is spring-loaded.
  • the spring-loading of the actuator such as e.g. a solenoid actuator, is configured such that the limiting structure of the firing direction limitation device is set in the second position, thus allowing the limiting launch angle range, if the actuator fails, breaks, stop working, lose power or in any other way become inoperative.
  • the present invention also refers to countermeasure arrangements.
  • the present invention refers to a countermeasure arrangement comprising a firing direction limitation device according to any aspect, or a combination of aspects, previously disclosed herein, wherein the firing direction limitation device is arranged in connection with the directable firing device such that the allowed launch angle range of the directable firing device is controllable.
  • Another exemplary aspect refers to a countermeasure arrangement whereof the directable firing device is a variable magazine.
  • the variable magazine comprises a plurality of longitudinal cartridge cases forming the variable magazine, wherein each cartridge case comprises side walls and a front opening.
  • the side walls of two adjacent cartridge cases are arranged to each other in a slidable manner in a longitudinal direction, and wherein the variable magazine comprises a tilting means adapted to tilt the cartridge cases, such that the openings of the cartridge cases can be directed in a selected direction.
  • the present invention further refers to methods for controlling the allowed launch angle range of a directable firing device by means of any aspect of, or a combination of aspects of, a firing direction limitation device as previously disclosed herein.
  • the directable firing device is configured to be tiltable between at least two allowed launch angles defining a launch sector.
  • the firing direction limitation device further comprises a moveable limiting structure configured to be arranged in connection with the directable firing device, and wherein the limiting structure is configured to be moveable between a first position and a second position.
  • the limiting structure is set in the first position the directable firing device is moveable within a first launch angle range
  • the limiting structure is set in the second position the directable firing device is moveable within a second launch angle range.
  • the second launch angle range is limited in relation to the first launch angle range.
  • the method simply comprises the method step of, when it is desired to limit the allowed firing range of the directable firing device: • setting the limiting structure in the second position.
  • the first exemplary aspect of the present invention represents a basic concept of the present invention; when it for some reason, such as e.g. that an aircraft provided with a firing direction limitation device according to the present invention is standing on the ground in order to be able to load/unload cargo or when an aircraft provided with a firing direction limitation device according to the present invention is flying in formation surrounded by friendly aircrafts, the limiting structure is set in the second position.
  • the allowed launch angle range when the limiting structure is set in the second position is limited, thus allows less movements of the directable firing device, in relation to the allowed launch angle range when the limiting structure is set in the first position.
  • the directable firing device can be operated in a safe operation mode.
  • safe operation mode may be manually selectable or automatically selectable.
  • the method comprises the method steps of:
  • a safe operation mode is detected when one operation from a predefined group of operations is initiated, wherein the predefined group of operations comprises:
  • detecting a predefined weight-on-wheels Many aircrafts, such as e.g. helicopters, are equipped with a mechanical switch configured to detect when the aircraft is standing on e.g. the ground, thus when the wheel of the aircraft are exposed to a predefined weight (by the helicopter). This, and e.g. that a side or cargo door is opened, can be used to detect that a safe operation mode is desired.
  • the limiting structure is preferably pre-set in the second position, and will not be able to move to the first position.
  • the limiting structure is set in the second position, and wherein the allowed launch angle range of e.g. flares, chaff, shotgun shots, pellet loads or similar is limited in relation to the allowed launch angle range of the first position.
  • An exemplary advantage of exemplary aspects of the present invention using an automatically selectable safe operation mode is that by automatically setting the limiting structure in the second position, whereby the launch sector of the directable firing device is limited, it may e.g. be safe for personnel opening a side door to leave or unload the aircraft even if this has not been communicated to e.g. the pilot of the aircraft.
  • this may e.g. be done when the aircraft is flying in formation, when approaching home base or when friendly forces are present nearby the aircraft.
  • the exemplary aspects of methods for controlling the allowed launch angle range of a directable firing device are preferably performed by means of a control device.
  • the control device is preferably one or more switches directly connected to an actuator, but could also be an electronic control unit comprising logic circuits.
  • the control device could also e.g. comprise a device capable of executing method steps such as e.g. a computer device.
  • the present invention refers to an aircraft comprising a countermeasure arrangement according to any aspect, or a combination of aspects, previously disclosed.
  • Fig. 1 a schematically shows a side view of an aircraft, in form of a helicopter, provided with directable firing devices in form of variable magazines according to an embodiment of the present invention
  • Fig. 1 b schematically shows a top view of an aircraft, in form of a helicopter, provided with directable firing devices in form of variable magazines according to an embodiment of the present invention
  • Fig. 2a schematically shows a side view of an aircraft, in form of a helicopter, provided with directable firing devices in form of variable magazines according to an embodiment of the present invention in which limiting structures are set in the second position,
  • Fig. 2b schematically shows a top view of an aircraft, in form of a helicopter, provided with directable firing devices in form of variable magazines according to an embodiment of the present invention in which limiting structures are set in the second position,
  • Fig. 3a schematically shows an exemplary embodiment of a directable firing device in form of a variable magazine in an ISO view
  • Fig. 3b schematically shows an exemplary embodiment of a tilted directable firing device in form of a variable magazine in an ISO view
  • Fig. 4a schematically shows an exemplary embodiment of a tilted directable firing device from a side view
  • Fig. 4b schematically shows another exemplary embodiment of a tilted directable firing device from a side view
  • Fig. 5a schematically shows an exemplary embodiment of a directable firing device in form of a variable magazine from a top view
  • Fig. 5b schematically shows an exemplary embodiment of a firing direction limitation device wherein the directable firing device in form of a variable magazine is provided with a limiting structure from a top view
  • Fig. 5c schematically shows another exemplary embodiment of a firing direction limitation device wherein the directable firing device in form of a variable magazine is provided with a limiting structure from a top view, and
  • Fig. 5d schematically shows yet another exemplary embodiment of a firing direction limitation device wherein the directable firing device in form of a variable magazine is provided with a limiting structure from a top view.
  • Fig. 1 a discloses an exemplary embodiment of an aircraft 1 , for the exemplary embodiment of fig. 1 a in form of a helicopter 1 , provided with a first 10a, a second 10b and a third 10c directable firing device, in the exemplary embodiment of fig.1 a in form of a first, second and third variable magazine 1 10a, 1 10b, 1 10c.
  • the aircraft 1 is further provided with an aircraft fuselage 2, a main rotor 5 and a tail rotor 50.
  • a coordinate system is indicated in fig.
  • the X-direction coincides with the longitudinal direction of the helicopter 1 , thus the indicated forward or flight direction of the helicopter 1
  • the Y-direction is perpendicular to the X-direction and coincides with what is referred to as an elevation or upwards/downwards direction of the helicopter 1
  • the Z-direction is perpendicular to both the X-direction and the Y- direction.
  • the X-direction and the Z-direction defines a horizontal XZ-plane and the X-direction and Y-direction defines a vertical XY-plane. Motion in the vertical XY- plane is defined as motion in elevation direction and motion in the horizontal XZ- plane is referred to as motion in azimuth direction.
  • one side of the helicopter 1 is shown.
  • the first variable magazine 1 10a is placed at the front of the helicopter 1 , pointing substantially forwards-downwards
  • the second and the third variable magazines 1 10b, 1 10c are placed at the rear of the helicopter 1 , wherein the second variable magazine 1 10b points forwards-downwards and the third variable magazine 1 10c points rearwards-downwards.
  • An arrow 3 indicates a current direction of launching of respective directable firing device 10a, 10b, 10c.
  • the directable firing devices 10a, 10b, 10c are directable, or tiltable, in the vertical XY- plane about 45 degrees in resp. angular direction in relation to the current direction of launching 3, wherein a first launch angle range in the XY-plane LARal (xy) is defined. This is referred to as movements in elevation direction of the directable firing device 10a, 10b, 10c in the XY-plane.
  • the maximum allowed angle in which the directable firing devices 10a, 10b, 10c can be tilted in respective direction in the XY-plane is referred to as first and second maximum launch angles MaxLA1 (xy), MaxLA2(xy).
  • the first launch angle range LARal (xy) defines an extension in the XY- plane of a first launch sector 4a(xy) over which countermeasures or like may be fired/launched.
  • Fig. 1 b discloses top view of the aircraft 1 , i.e. the helicopter 1 .
  • Fig. 1 b discloses that the directable firing devices 10a, 10b, 10c are directable, or tiltable, also in the horizontal XZ-plane about 45 degrees in resp. angular direction in relation to the current launch direction 3, wherein a first launch angle range LARal (xy) also in the XZ-plane is defined. Movements in the XY-plane of the variable magazines 1 10a, 1 10b, 1 10c is referred to as movements in azimuth direction.
  • the maximum allowed angle in which the directable firing devices 10a, 10b, 10c can be tilted in respective direction is referred to as first and second maximum launch angles MaxLA1 (xz), MaxLA2(xz).
  • the first launch angle range LARal (xz) defines an extension in the XZ- plane of the first launch sector 4a(xz) over which countermeasures or like can be fired/launched.
  • a problem with using directable firing devices 10a, 10b, 10c, such as the variable magazines 1 10a, 1 10b, 1 10c disclosed in the exemplary embodiment shown in fig. 1 a and fig. 1 b, is that if incorrectly used, or if not sufficiently controlled, the possibility of controlling the allowed launch angle range of the directable firing device may put nearby friendly forces in danger or even damage e.g. a main rotor 5, a tail rotor 50 or the fuselage 2 of an aircraft 1 .
  • the firing direction limitation device 15 comprises a limiting structure.
  • the limiting structure is configured to be set in at least a first position and a second position.
  • the directable firing device is moveable within a first launch angle range and when the limiting structure is set in the second positon, the directable firing device is moveable within a second launch angle range, wherein the second launch angle range is limited in relation to the first launch angle range.
  • the allowed launch angle range of the directable firing device is controllable.
  • the limiting structure of the firing direction limitation device 15 is set in the first position wherein the allowed launch angle range is not limited, i.e. the variable magazines 1 10a, 1 10b, 1 10c are free to move by being tilted over the first launch angle range LARal (xy), LARal (xz) in elevation and azimuth direction.
  • the variable magazines 1 10a, 1 10b, 1 10c are directable about 45 degrees in respective direction in both the XY-plane and the XZ-plane, i.e. in both elevation and azimuth direction.
  • the limiting structure of the firing direction limitation device 15 is set in the second position wherein the allowed launch angle range is limited, i.e. the variable magazines 1 10a, 1 10b, 1 10c cannot move freely by being tilted over the first launch angle range LARa1 (xy), LARal (xz) in elevation and azimuth direction, but can only move freely over a second launch angle range LARa2(xy), LARa2(xz).
  • first and second limited launch angles in elevation i.e. the XY-plane, Liml_A1 (xy), Liml_A2(xy), and in azimuth, i.e. the XZ-plane, Liml_A1 (xz), Liml_A2(xz).
  • the first and second limited launch angles Liml_A1 (xy), Liml_A2(xy) define the second launch angle range LARa2(xy) in the XY-plane
  • the first and second limited launch angles Liml_A1 (xz), Liml_A2(xz) define the second launch angle range LARa2(xz) in the XZ-plane.
  • the second launch angle range in the XY- and XZ-planes LARa2(xy), LARa2(xz) are limited in relation to first launch angle range in the XY- and XZ-planes LARal (xy), LARal (xz).
  • the first launch angle range in the XY- and XZ-planes LARal (xy), LARal (xz) are defined by the first and second maximum launch angles in the XY- and XZ-plane, MaxLA1 (xy), MaxLA2(xy) and MaxLA1 (xz), MaxLA2(xz).
  • the allowed launch angle is restricted to the second launch angle range in the XY- and XZ-planes LARa2(xy), LARa2(xz).
  • the directable firing device 10a, 10b, 10c which according to fig. 1 a, 1 b, 2a and 2b is in form of variable magazines 1 10a, 1 10b, 1 10c, are moveable both in elevation direction, i.e. in the XY-plane, and in azimuth direction, i.e. in the XZ-plane, and the limiting structure of the firing direction limitation device 15 is capable of limiting the tilting movements of the directable firing device 10a, 10b, 10c in both the XY-plane and in the XZ-plane.
  • Fig. 3a and 3b show an exemplary embodiment of a directable firing device 10, in fig. 3a and 3b in form of a variable magazine 1 10, in an ISO view.
  • the variable magazine 1 10 comprises a plurality of cartridge cases 8 arranged in a matrix with a number of rows and a number of columns.
  • a suitable number of rows may e.g. be 4 - 8 and a suitable number of columns may e.g. be 5 - 12, e.g. depending on the size of a cartridge.
  • a cartridge case 8 is designed with a longitudinal body, preferably having a square or rectangular cross-section.
  • the cross-section of a cartridge may e.g. be 1 * 1 or 1 * 2 inches and the length may e.g. be 8 inches.
  • Cartridge cases are adapted to receive e.g. countermeasures such as e.g. flares, chaff, shotgun shots, pellet loads or similar, stored in a cartridge 12 as is shown in fig. 4a.
  • Each cartridge case 8 has an opening 14 through which the countermeasure or like can be launched or fired. Thus, the direction in which the opening 14 is pointing determines the direction in which the countermeasure or like is fired or launched.
  • the variable magazine 1 10 comprises a base 7, which constitute the base of the variable magazines 1 10 and is used to mount the variable magazines 1 10 to an aircraft, to a vehicle or in a stationary position by the use of any suitable attachment means.
  • Each cartridge case 8 is attached to the base 7 through a flexible joint 9, allowing respective cartridge case 8 to be tilted in at least one direction in relation to the base 7.
  • the cartridge cases 8 are slidably arranged to each other such that they bear against each other and such that they can slide against each other in the longitudinal direction when the variable magazine 1 10 is tilted.
  • the tilting of the variable magazine 1 10 is achieved by means of tilting means (not shown).
  • the flexible joint 9 allows tilting of the cartridge cases 8 in XY-plane and ZY-plane.
  • the flexible joint 9 may e.g. be in form of a ball joint.
  • the flexible joint may e.g. be in form of a hinge.
  • FIG. 3a shows the exemplary embodiment of a variable magazine 1 10 wherein a cartridge centre axis 6 of a cartridge case 8 is directed in parallel to the Y-axis, thus is directed to be perpendicular to the X-axis and the Z-axis.
  • the base 7 is directed in an XZ-plane. This position is used as a reference position in this description and is referred to as a resting position.
  • the tilt angle of the variable magazine 1 10, i.e. the tilt angle of the cartridge centre axis 6, is zero degrees in the resting position.
  • Fig. 3b shows the exemplary embodiment of a variable magazine 1 10 in, what is referred to as, an active position.
  • the variable magazine 1 10, and thus the cartridge centre axis 6, is tilted with an angle referred to as first tilt angle TA1 (xy), in a first direction in the XY-plane.
  • first tilt angle TA1 (xy) in a first direction in the XY-plane.
  • the variable magazine 1 10 is only tilted in the XY-plane, but the active position may also involve tilting in the ZY-plane, or tilting in both the XY-plane and in the ZY-plane simultaneously.
  • the first tilt angle TA1 (xy) indicates the maximum tilt angle in the first direction in the XY- plane of the variable magazine 1 10, thus what has been referred to as first maximum launch angle MaxLAI (xy) for fig. 1 a and 1 b.
  • This angle may e.g. be 45 degrees.
  • variable magazine 1 10 may also be tilted in the opposite, second direction in the XY-plane, in which direction the maximum angle in which the variable magazine could be tilted would be the second maximum launch angle MaxLA2(xy).
  • the cartridge cases 8 of the variable magazine 1 10 are configured to e.g. be tiltable from the resting position shown in fig. 3a to the active position shown in fig. 3b. Since adjacent cartridge cases 8 are arranged to each other in a slidable manner, the variable magazine 1 10 can be tilted by a tilting means to any selected angle.
  • a cartridge case 8 is adapted to receive a countermeasure 13 stored in a cartridge 12 as is shown in fig. 4a.
  • the countermeasure cartridge 12 may be attached to the cartridge case 8 according to any commonly known manner.
  • the countermeasure cartridge 12 is further connected to a launch system of the aircraft, comprising a firing control.
  • the interface between the countermeasure cartridge 12 and the electronic control unit of the aircraft may be a mechanical system, which can only launch the countermeasure, or it may be an electrical interface, comprising two-way communication between the countermeasure cartridge 12 and the aircraft.
  • variable magazine comprises a plurality of longitudinal cartridge cases 8 forming the variable magazine 1 10, wherein each cartridge case 8 comprises side walls 21 and a front opening 14, and wherein the side walls 21 of two adjacent cartridge cases 8 are arranged to each other in a slidable manner in a longitudinal direction.
  • the variable magazine 1 10 comprises a tilting means 22 adapted to tilt the cartridge cases 8 such that the openings 14 of the cartridge cases 8 can be directed in a selected direction.
  • the tilting means 22 schematically shown in fig. 4a and 4b is just one possible realization of tilting means out of the many possible.
  • fig. 4a discloses a similar exemplary embodiment of a directable firing device 10 in form of a variable magazine 1 10 as in fig. 3b, also in an active position, thus tilted a first tilt angle TA1 (xy), from a side view.
  • the exemplary embodiment of fig. 4a also discloses a firing direction limitation device 15 comprising a limiting structure 16 and a number of actuators 17.
  • the firing direction limitation device 15, comprising the limiting structure 16, and the directable firing device 10 together forms a countermeasure arrangement 19 as defined according to the present invention.
  • the limiting structure 16 of the firing direction limitation device 15 is moveable between a first position P1 and a second position P2.
  • Fig. 4a discloses the limiting structure 16 in the first position P1 , in which the limiting structure 16 is retracted.
  • Fig. 4b discloses the limiting structure 16 in the second position P2, in which the limiting structure 16 is projected.
  • the projection movement of the limiting structure 16, and also a possible subsequent retraction movement, is performed by means of actuators 17.
  • actuators 17 In fig. 4a and 4b, four actuators are visible.
  • the variable magazine 1 10 In the first position P1 , the variable magazine 1 10 may be tilted in a first direction in the XY-plane at the maximum angle in which the variable magazine 1 10 is tiltable, i.e. the first maximum launch angle MaxLA1 (xy).
  • the limiting structure 16 is set in the first position P1 and do not limit or restrict the movements of the variable magazine 1 10.
  • the limiting structure 16 is projected and is set in the second position P2.
  • the inner delimitation surface 18 abuts the side wall 21 of the peripheral cartridge case 8 whereby the movements of the variable magazine the first direction in the XY-plane is restricted or limited.
  • the second tilt angle TA2(xy) which is the maximum angle the variable magazine 1 10 can be tilted in the first direction in the XY-plane when the limiting structure is set in the second position P2
  • the first tilt angle TA1 (xy) which is the maximum angle in which the variable magazine 1 10 can be tilted in the first direction in the XY- plane when the limiting structure is set in the first position P1 , as is shown in fig.
  • the actuators 17 may e.g. be solenoid actuators. According to the exemplary embodiment of fig. 4a and 4b, the actuators are spring-loaded by means of a coil spring 20. Applying spring-loaded actuators 17 has the advantage that if the actuators 17 fail, the spring force exerted by the coil spring 20 allows the limiting structure 16 to be in the second position P2. Thus, if the actuators 17 fail, the more limited allowed launch angle range LARa2 will be the default launch angle range.
  • the actuators may also comprise e.g. a motor having a threaded axle cooperating with a threaded hole in the limiting structure.
  • the limiting structure 16 is configured to be arranged in connection to the directable firing device 10, in fig. 3a, 3b, 4a and 4b provided in form of a variable magazine 1 10. Further, in fig. 3a, 3b, 4a and 4b the variable magazine 1 10 is only tilted in a first direction in the XY-plane, but obviously the variable magazine 1 10 can also be tilted in the opposite, second direction in the XY-plane and also in the first and second direction in the ZY-plane. The limiting structure 16 will have the same, limiting affect when set in the second position P2 also in these tilting directions.
  • the base 7, which is the base of the variable magazine 1 10, is used to mount the variable magazine 1 10 to e.g. an aircraft by the use of an attachment means.
  • the variable magazine 1 10 may be mounted directly to an attachment bracket on the aircraft with suitable mounting means. It is also possible to mount the variable magazine 1 10 to an adapter bracket, which is used to create an interface for an existing mounting bracket on an aircraft.
  • an adapter bracket By using a suitable adapter bracket, the magazine can be mounted to an aircraft provided with standardized mounting brackets for fixed magazines. In this way, there is no need to upgrade the aircraft with new mounting brackets. Further, by using an adapter bracket, both fixed magazines and variable magazines can be used, depending on the actual needs.
  • the base 7 is also used to absorb recoil force created when a countermeasure or similar is launched or fired.
  • the base 7 will absorb and distribute the created force over the entire base area of the base 7.
  • Fig. 5a discloses an exemplary embodiment of a directable firing device 10 in form of a variable magazine 1 10 in a top view.
  • a variable magazine 1 10 comprising 3 rows of cartridge cases 8 in 5 columns is shown, wherein the cartridge cases are of the dimension 1 * 1 inch. Also other numbers of rows and/or columns are possible, as well as other dimensions of the cartridge cases 8, such as e.g. 1 * 2 inches.
  • the length of the cartridge case 8 may e.g. be 8 inches.
  • the openings 14 of the cartridge cases 8 are directed essentially in the Y-direction. In the shown view, a firing direction limitation device is not shown.
  • 5b, 5c and 5d schematically discloses how various embodiments of firing direction limitation devices 15b, 15c, 15d comprising various configurations of limiting structures 16b, 16c, 16d arranged in connection to directable firing devices 10, 1 1 , in fig. 5b to 5d in form of variable magazines 1 10, 1 1 1 , may be configured.
  • Fig. 5b discloses an exemplary embodiment of a firing direction limitation device 15b wherein the directable firing device 1 1 in form of a variable magazine 1 1 1 is provided with a limiting structure 16b in a top view.
  • the embodiment of a variable magazine 1 1 1 of fig. 5b comprises 3 rows of cartridge cases 8 in 4 columns.
  • the limiting structure 16b has an inner delimitation surface 18. When the limiting structure 16b is set in the second position P2, thus is projected by means of actuators 17, the inner delimitation surface 18 of the limiting structure 16b will restrict the movements in the X-direction in the XY-plane and in the Z-direction in the ZY-plane of the variable magazine 1 1 1 .
  • the second launch angle range both in the X-direction in the XY-plane and in the Z-direction in the ZY-plane will be restricted.
  • four actuators 17 are arranged in the corners of the limiting structure 16b.
  • the restriction of movement in different directions may differ, such that it may e.g. be +30 degrees and - 15 degrees in the X-direction and +- 25 degrees in the Z-direction.
  • the firing direction limitation device 15b is further provided with an additional restriction section 24 that will limit the movement of the variable magazine additionally along the X- direction and Z-direction in dependency of the actual tilt angle in a specific direction.
  • the restriction section will limit the movement of the variable magazine in the -Z-direction when the variable magazine is tilted less than e.g. 5 degrees in the +X-direction, and will limit the movement of the variable magazine in the -X-direction when the variable magazine is tilted more than e.g. 10 degrees in the -Z-direction.
  • a limitation can e.g. correspond to the direction to a door or hatch of the aircraft.
  • Fig. 5c discloses another exemplary embodiment of a firing direction limitation device 15c wherein the directable firing device 10 in form of a variable magazine 1 10 is provided with a limiting structure 16c in a top view.
  • the limiting structure 16c comprises 3 rows of cartridge cases 8 in 5 columns.
  • the limiting structure 16c has an inner delimitation surface 18.
  • the inner delimitation surface 18 of the limiting structure 16c will restrict the movements in the X-direction in the XY-plane and in the Z-direction in the ZY-plane of the variable magazine 1 10.
  • the second launch angle range both in the X- direction in the XY-plane and in the Z-direction in the ZY-plane will be restricted.
  • six actuators 17 are arranged to enable the limiting structure 16c to move between a projected and a retracted position, i.e. the first position and the second position.
  • the restriction of movement in different directions may differ, such that it may e.g. be +15 degrees and - 25 degrees in the X-direction and +- 20 degrees in the Z- direction.
  • the firing direction limitation device 15c is further provided with additional restriction sections 25a, 25b and 25c that will limit the movement of the variable magazine additionally along the X-direction and the Z-direction in dependency of the actual tilt angle in a specific direction.
  • the restriction section 25a will limit movement of the variable magazine in the Z-direction and in the -X- direction in a combination, where the restriction of movement in the Z-direction will be proportional to the tilt angle of the variable magazine in the -X-direction.
  • restriction sections 25b and 25c will allow movement of the variable magazine in the +X-direction only when the variable magazine is not tilted in the +Z-direction or -Z- direction.
  • Such a limitation can e.g. correspond to the direction to a door or hatch of the aircraft.
  • the exemplary embodiment of a directable firing device 10 provided in form of a variable magazine 1 1 1 , of fig. 5b has a larger spatial extension in the X-direction due to that the variable magazine of fig. 5c comprises 5 columns of cartridge cases 8.
  • This, i.e. the spatial extension is something that needs to be considered when the limiting structure is configured for respective implementation of the present invention.
  • the spatial extension in the Z- direction is the same since both the exemplary embodiment of fig. 5b and 5c comprises 3 rows of cartridge cases 8.
  • the spatial extension in the X-direction and in the Z-direction needs to be considered since the point of launch/firing will differ significantly between individual cartridge cases 8 of a variable magazine 1 10.
  • Fig. 5d schematically shows yet another exemplary embodiment of a firing direction limitation device 15d, wherein the directable firing device 10 in form of a variable magazine 1 10 is provided with a limiting structure 16d in a top view.
  • the limiting structure 16d disclosed in fig. 5d is provided in form of a sector portion having an inner delimitation surface 23, wherein the inner delimitation surface 23, when the limiting structure is set in the second position, determines the second launch angle range.
  • the sector portion of the limiting structure 16d of fig. 5d is provided in form of a portion of a square, here an L-shaped structure, wherein the limiting structure 16d, when set in the second position, will only affect the freedom of movement of the variable magazine 1 10 in certain directions, i.e.
  • the second launch angle range will only be limited in certain directions.
  • the variable magazine 1 10 will be limited in the -X-direction and in the -Z-direction.
  • the possible movement in the positive X-direction will be the same as when the limiting structure 16d is in the first position, and the possible movement in the positive Z-direction will be the same as when the limiting structure 16d is in the first position.
  • the terminology used herein is for the purpose of describing particular exemplary aspects or embodiments only and is not intended to be limiting of the invention.
  • the singular forms "a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise.
  • the firing direction limitation device may be mounted to moving vehicles of all kinds and may also be mounted in a stationary manner, either fixed on e.g. a building or on a movable stand.
  • MaxLAI * First maximum launch angle

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)

Abstract

La présente invention concerne un dispositif de limitation de direction de tir (15) permettant de régler la plage d'angles de lancement autorisés d'un dispositif de tir orientable (10) inclinable entre au moins deux angles de lancement maximum autorisés (MaxLAI, MaxLA2) définissant un secteur de lancement (4), le dispositif de limitation de direction de tir (15) comprenant une structure de limitation mobile (16) conçue pour être agencée en liaison avec le dispositif de tir orientable (10), la structure de limitation (16) étant conçue pour être mobile entre une première position (P1) et une seconde position (P2), lorsque la structure de limitation (16) est placée dans la première position (P1), le dispositif de tir orientable (10) étant mobile dans une première plage d'angles de lancement (LARal) et, lorsque la structure de limitation (16) est placée dans la seconde position (P2), le dispositif de tir orientable (10) étant mobile dans une seconde plage d'angles de lancement (LARa2), la seconde plage d'angles de lancement (LARa2) étant limitée par rapport à la première plage d'angles de lancement (LARal), moyennant quoi l'angle de lancement autorisé du dispositif de tir orientable (10) peut ainsi être réglé.
PCT/SE2017/050442 2016-05-17 2017-05-05 Dispositif et procédé de limitation de direction de tir et agencement de contre-mesure WO2017200460A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
ES17799764T ES2889448T3 (es) 2016-05-17 2017-05-05 Dispositivo y procedimiento para la limitación de la dirección de disparo y una disposición de contramedidas
PL17799764T PL3458793T3 (pl) 2016-05-17 2017-05-05 Urządzenie i sposób ograniczenia kierunku wystrzału oraz układ środków przeciwdziałających
EP17799764.0A EP3458793B1 (fr) 2016-05-17 2017-05-05 Dispositif et procédé de limitation de direction de tir et agencement de contre-mesure
DK17799764.0T DK3458793T3 (da) 2016-05-17 2017-05-05 Indretning og fremgangsmåde til skudretningsbegrænsning og et modforanstaltningsarrangement
US16/301,282 US11008099B2 (en) 2016-05-17 2017-05-05 Device and method for firing direction limitation and a countermeasure arrangement
IL262828A IL262828B (en) 2016-05-17 2017-05-05 A device and method for limiting the direction of fire and arranging countermeasures

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
SE1650665-1 2016-05-17
SE1650665 2016-05-17
SE1651465-5 2016-11-08
SE1651465A SE1651465A1 (en) 2016-05-17 2016-11-08 Firing direction limitation device

Publications (1)

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WO2017200460A1 true WO2017200460A1 (fr) 2017-11-23

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2391956A (en) * 1944-03-23 1946-01-01 United Shoe Machinery Corp Limit stop for gun mounts
US2467514A (en) * 1944-05-16 1949-04-19 United Shoe Machinery Corp Direction-controlling mechanism for guns
US4280394A (en) * 1977-11-04 1981-07-28 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Marine firing weapon
US4674393A (en) * 1980-05-23 1987-06-23 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Marine firing weapon for fighting airborne targets, especially in zenith
DE3902624A1 (de) 1989-01-30 1990-08-02 Blohm Voss Ag Verstellvorrichtung fuer die lage und groesse des horizontalen schwenk- oder bestreichungswinkels einer maschinenwaffe, z.b. eines mg's
EP2157398A2 (fr) * 2008-08-21 2010-02-24 Krauss-Maffei Wegmann GmbH & Co. KG Lanceur de contre-mesures
US20100294119A1 (en) * 2009-05-19 2010-11-25 James Buechler Ammunition canister and feed system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2391956A (en) * 1944-03-23 1946-01-01 United Shoe Machinery Corp Limit stop for gun mounts
US2467514A (en) * 1944-05-16 1949-04-19 United Shoe Machinery Corp Direction-controlling mechanism for guns
US4280394A (en) * 1977-11-04 1981-07-28 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Marine firing weapon
US4674393A (en) * 1980-05-23 1987-06-23 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Marine firing weapon for fighting airborne targets, especially in zenith
DE3902624A1 (de) 1989-01-30 1990-08-02 Blohm Voss Ag Verstellvorrichtung fuer die lage und groesse des horizontalen schwenk- oder bestreichungswinkels einer maschinenwaffe, z.b. eines mg's
EP2157398A2 (fr) * 2008-08-21 2010-02-24 Krauss-Maffei Wegmann GmbH & Co. KG Lanceur de contre-mesures
US20100294119A1 (en) * 2009-05-19 2010-11-25 James Buechler Ammunition canister and feed system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP3458793A4 *

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