• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    32ABSTRACTFiring direction limitation device (15) for controlling the allowed launch angle range ofa directable firing device (10) tiltable between at least two allowed maximum launchangles (MaxLA1, MaxLA2) defining a launch sector (4), wherein the firing directionIimitation device (15) comprises a moveable limiting structure (16) configured to bearranged in connection to the directable firing device (10), where the limitingstructure (16) is configured to be moveable between a first position (P1) and asecond position (P2), wherein, when the limiting structure (16) is set in the firstpositon (P1), the directable firing device (10) is moveable within a first launch anglerange (LARa1), and when the limiting structure (16) is set in the second positon (P2),the directable firing device (10) is moveable within a second launch angle range(LARa2), wherein the second launch angle range (LARa2) is limited in relation to thefirst launch angle range (LARa1), whereby the allowed launch angle of the directable firing device (10) is controllable. (Fig. za)
    公开号:SE1651465A1
    申请号:SE1651465
    申请日:2016-11-08
    公开日:2017-11-18
    发明作者:Zätterqvist Christer
    申请人:Saab Ab；
    IPC主号:
    专利说明:

    1FIRING DIRECTION LIMITATION DEVICE TECHNICAL FIELD The present invention relates to a firing direction limitation device for preventing thate.g. flares, chaff, shotgun shots, pellet loads or similar are fired in a direction exposing friendly personnel or vehicles to danger.BACKGROUND ART Arrangements for storing and launching payloads, such as countermeasures, whichare designed to be mounted on aircrafts such as helicopters or fighters, arepreviously known. The countermeasures are connected to a firing control device forfeeding firing signals to the countermeasures. The countermeasures may consist ofpassive means, such as chaff foil, but can also consist of for example IR flares, orother 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 thelaunch angle of a countermeasure is fixed to a set angle which is believed to beoptimal for the intended use. Depending on the purpose of the countermeasure, itmay be of advantage to use different firing directions. lf chaff is released, a preferredlaunch direction may be upwards towards a helicopter rotor, if flares are released, apreferred launch direction may be somewhat forwards and downwards. A dispensermounted on a helicopter may therefore be provided with several magazines, directedin different directions. A solution with a fixed launch angle may be a good solution foran aeroplane, which has a known flight direction and a known speed range. For ahelicopter, a fixed launch angle is however not optimal, since both flight angle, flightspeed and the orientation of the aircraft may vary considerably. Helicopters may beprovided with several magazines holding cartridges with countermeasures. Eachmagazine may be positioned at a predefined position and pointing in a predefineddirection on the helicopter, such that several magazines will cover a larger firingrange, i.e. launch angle range. lt would in some situations also be possible to steer the helicopter such that a desired firing direction of a countermeasure is obtained. 2 ln this description the forward direction of an aircraft is defined as a direction ofwhere the nose of the aircraft is pointing when flying. Thus, when referring to ahelicopter the forward direction is defined as the direction in which the nose of thehelicopter essentially is pointing when flying, which is essentially parallel to thehorizontal plane, i.e. floor and the rotor of the helicopter are essentially parallel to thehorizontal plane.
    A solution at least partially alleviating or eliminating the drawbacks and problemsassociated with prior art solutions, disclosed in previously filed applications, is toarrange 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 referredto as having a variable magazine. However, having a directable variable magazinefor 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 incertain directions there may be an imminent risk that the aircraft itself, friendlyaircrafts or personnel are exposed to danger, i.e. might get hit or damaged. This isparticularly problematic since countermeasure arrangements firing flares or chaffmay be activated automatically and might respond to incoming threats without activeaircrew consent. Controlling such functionality by means of software is possible, butverifying the reliability of such software, and configuring such software to be fail safeat all times, is difficult and costly.
    Thus, there is still a need of improvements and further development.SUMMARY OF THE INVENTION An object of the present invention is to at least partially alleviate or eliminatedrawbacks associated with the solutions known in the prior art. Another object is toprovide a firing direction limitation device for an aircraft, wherein the firing directionlimitation device can be used to prevent that in certain situations, such as duringloading or unloading of personnel or material, when flying in formation or duringnormal operation flares, chaff, shotgun shots, pellet loads or similar are not fired inan undesirable direction whereby personnel, the fuselage of the aircraft, main/tailrotors, wings, friendly aircrafts or similar may be damaged. A further object of the present invention is to provide a countermeasure arrangement comprising such a 3firing direction Iimitation device. A further object of the present invention is to providemethods for controlling the allowed launch angle range of a directable firing deviceby means of such a firing direction Iimitation device. Yet another object of the invention is to provide an aircraft comprising a firing direction Iimitation device.
    The solution to the problem according to the invention is described in thecharacterizing portion of the independent claim referring to a firing direction Iimitationdevice. Further independent claims refer to a countermeasure arrangementcomprising a firing direction Iimitation device, an advantageous method forcontrolling the allowed launch angle range of a directable firing device and an aircraftcomprising a firing direction Iimitation device. The dependent claims containadvantageous embodiments and further developments of firing direction Iimitationdevices, countermeasure arrangements and methods for controlling the allowedlaunch angle range of a directable firing device. Please note, the term 'directable' is herein defined as 'being capable of being directed'.
    Even though the invention herein primarily will be disclosed in association with adirectable firing device capable of firing e.g. flares, chaff or shotgun shots, whereinthe directable firing device is disclosed as preferably being a variable magazine,comprising a number of cartridge cases, for which the allowed launch angle rangecan be controlled, it is considered to be apparent that the inventive concept ofpresent invention is just as applicable for other directable firing devices, such as e.g.canons or machine guns, as well. However, as also is apparent from the followingdisclosure of the present invention, controlling the allowed launch angle range of adirectable firing device in form of a variable magazine requires additionalinventiveness and development than for controlling the allowed launch angle rangeof a directable firing device in form of e.g. a canon or a machine gun. Thus, it is notapparent that means for controlling the allowed launch angle range of e.g. a canonor a machine gun can be used to control the allowed launch angle range of avariable magazine. This will be discussed more in detail in the following detailed description.
    Allowed launch angles or allowed target area of a directable firing device canobviously be controlled by means of software developed for defining what, when andwhere firing is allowed. Controlling allowed launch angle ranges by means of 4software obviously has its advantages in that the software e.g. can be updatedrapidly and offers great flexibility. However, for safety arrangements, such as for afiring direction limitation device, it may be preferable to avoid systems based onsoftware. Software based systems generally uses numerous sensors and there isalways a risk of malfunctioning software and/or malfunctioning sensors or incorrectsensor inputs. Also, software based application can potentially be hacked and forsoftware based safety arrangements it is hard to verify the reliability, which mayprevent 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 directablefiring device refers to firing device firing shotgun shots, bullets or like.
    The present invention refers to a mechanical firing direction Iimitation device forcontrolling the allowed launch angle range of a directable firing device configured tobe tiltable between at least two allowed maximum launch angles, i.e. between twomaximum outwardly directed positions, defining a launch sector. The firing directionIimitation device comprises a moveable limiting mechanical structure configured tobe arranged in connection to the directable firing device. The limiting structure isconfigured to be moveable between at least a first position and a second position.When the limiting structure is set in the first positon the directable firing device ismoveable, by being tilted, within a first launch angle range, and when the limitingstructure is set in the second positon the directable firing device is moveable within asecond launch angle range. The second launch angle range is limited in relation tothe first launch angle range, whereby the allowed launch angle range of thedirectable firing device is controllable.
    The directable firing device may at a general level be defined as a device capable offiring e.g. flares, chaff, shotgun shots, pellet loads or similar, having a fixedattachment point around which the directable firing device is tiltable. Thereby thefiring or launch direction of the directable firing device is directable over at least alaunch angle range extending between the two maximum launch angles. The launchangles between which the directable firing device is tiltable define the launch sector,thus the area over which e.g. countermeasures can be launched. According to thepresent invention the second launch angle range is smaller than the first launch 5 angle range. The area over which the directable firing device is capable of firing orIaunching is herein defined as launch sector.
    The moveable limiting structure is configured to be arranged in connection to thedirectable firing device. Being arranged “in connection to” is here defined as beingarranged such that by moving between the first and second position the limitingstructure can affect the freedom of the directable firing device to move in at least onedirection.
    The present invention has the exemplary advantage that when the limiting structureis set in the second position the allowed launch angle range of the directable firingdevice 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 meansof a mechanical system, i.e. mechanically moving the limiting structure from a firstposition to a second position, whereby challenges associated with software basedsystems are avoided. The firing direction limitation device of the present inventionmay also offer a less expensive system for which the reliability is easier to verify.
    This in turn has the advantage that the present invention may be used as a safetyarrangement used to control in what direction e.g. flares, chaff, shotgun shots, pelletloads 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 theaircraft may be hit even if the directable firing device is moveable.
    Also, setting the limiting structure of the firing direction limitation device in thesecond position may be used to define a safe zone. Such a safe zone may e.g. beused to secure that personnel etc. is prevented from being hit when loading orunloading cargo. Such a safe zone may also be used to secure that friendly aircraftscannot be hit when flying in formation.
    The limiting structure is configured to restrict the movements of the directable firingdevice in at least one direction. The limiting structure may be configured to restrictthe movements of the directable firing device in elevation direction, azimuth directionor preferably in both elevation and azimuth direction. As previously mentioned, theallowed launch angle range over which the directable firing device is capable offiring/Iaunching becomes limited when the limiting structure is set in the second 6 position. The effect the limited allowed launch angle range provides in terms of howthe directable firing device is restricted from firing is obviously dependent on whereand how the directable firing device, provided with the firing direction limitationdevice, is arranged at the aircraft. Thus, how the limitation structure should beconfigured is directly dependent on where and how the directable firing device,provided with the firing direction limitation device, is intended to be arranged at theaircraft and should be configured accordingly. Thus, the intended positioning on theaircraft must be considered when using a firing direction limitation device to providea safe zone when a directable firing device is used.
    According to one exemplary aspect of a firing direction limitation device, the secondlaunch angle range is limited in azimuth direction in relation to the first launch anglerange, and according to another aspect of a firing direction limitation device thesecond launch angle range is limited in elevation direction in relation to the firstlaunch angle range.
    According to a preferred exemplary aspect of the present invention, the secondlaunch angle range is limited in both azimuth and elevation direction in relation to thefirst launch angle range. Thereby a limited area, defined in both elevation andazimuth direction, defining how the directable firing device may be tilted in azimuthand elevation direction around an attachment point is defined.
    This exemplary aspect of the present invention has the exemplary advantage thatwhen the limiting structure is set in the second position the allowed launch angles inboth azimuth and elevation direction of e.g. flares, chaff, shotgun shots, pellet loadsor similar can be limited in relation to the allowed launch angles of the first position.
    This will be disclosed more in detail in the detailed description.
    As previously mentioned, according to yet another exemplary aspect of a firingdirection limitation device according to the present invention, the directable firingdevice is a variable magazine. The variable magazine comprises a plurality oflongitudinal cartridge cases forming the variable magazine, wherein each cartridgecase comprises side walls and a front opening, and wherein the side walls of twoadjacent cartridge cases are arranged to each other in a slidable manner in alongitudinal direction. The variable magazine comprises a tilting means adapted to 7tilt the cartridge cases such that the openings of the cartridge cases can be directedin a selected direction. Controlling how the variable magazine can be directed, i.e.the allowed maximum launch angles and the allowed launch angel range, requiresthat additional factors and aspects are considered than for controlling how e.g. acanon or a machine gun can be directed. A variable magazine has, depending onthe number of cartridge cases forming the magazine, a defined spatial extension notonly 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. Thus, the variable magazine has a definedspatial extension in the XZ-plane. Also, since a variable magazine has multiplecartridge openings from which e.g. flares, chaff, shotgun shots, pellet loads or similarmay 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, differsignificantly 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 takenin consideration when the limiting structure should be configured in order to providea desired allowed launch angle range limitation, determining e.g. a desired safe zoneduring loading/unloading of a helicopter. Thus, if the directable firing device is avariable magazine this requires that the limiting structure has to be configureddifferently, and that additional aspects have to be considered, than if the directable firing device is e.g. a canon or a machine gun.
    According to one exemplary aspect of the present invention, the present inventionrefers to a firing direction limitation device wherein the moveable limiting structure isprovided in form of an encircling portion having an inner delimitation surface,wherein the inner delimitation surface determines the second launch angle range.Providing the limiting structure in form of an encircling portion, i.e. in form of a framestructure restricting the tilting movements of the directable firing device in X- and Z-direction (if the directable firing device is directed essentially in the Y-direction) whenset in the second position, is an advantageous way to achieve controllability of theallowed launch angle range of the directable firing device. The tilting movements ofthe directable firing device are restricted by the inner delimitation surface of thelimiting structure. 8According to further exemplary aspects of the present invention, the presentinvention refers to a firing direction limitation device wherein the inner delimitationsurface of the encircling portion is essentially circular, essentially square, essentiallyrectangular or irregularly shaped.
    The shape of the inner delimitation surface of the limiting structure, of the firinglimitation device, is preferably configured in accordance to the intended mountingposition of the directable firing device, for which the firing direction limitation deviceis applied, and according to over what area/in what angles it is desirable to preventlaunching or firing. Thereby the allowed firing angles of the directable firing devicecan be controlled such that e.g. a safe zone is provided when the limiting structure isset in the second position. Depending on current conditions and the configuration orthe directable firing device the most suitable shape of the inner delimitation surfacemay be e.g. essentially circular, essentially square, essentially rectangular orirregularly shaped.
    According to yet another exemplary aspect of the present invention the presentinvention refers to a firing direction limitation device wherein the moveable limitingstructure is in form of a sector portion having an outer delimitation surface, whereinthe outer delimitation surface determines the second launch angle range. Thus, it isalso possible to use a limiting structure which is formed by a portion of a circle,square etc. Such limiting structure has the drawback that only tilting movements incertain angles of a directable firing device can be limited, but has the exemplaryadvantage that such limiting structure requires less space.
    The various aspects of limiting structures possible are discussed more in detail in thedetailed description.
    According to an exemplary aspect of the present invention, the present inventionrefers to a firing direction limitation device wherein the movements of the limitingstructure are projecting and retracting movements and wherein theprojecting/retracting movements are controllable by means of at least one actuator.The actuator is preferably directly controlled by a switch or a control unit operatingthe actuator without any involvement of software. As will be shown in the detaileddescription, according to advantageous aspects of the present invention, the limiting structure is configured such that the movement between the first position and the 9 second position of the limiting structure are projecting and retracting movements,and that these movements are controlled by means of at least one actuator.
    According to another exemplary aspect of the present invention, the presentinvention refers to a firing direction limitation device comprising at least one solenoidactuator. Solenoid actuators are a suitable type of actuator for this specificimplementation, even if also other actuators, or devices providing the samefunctionality as an actuator, are possible. lt may be preferable that if the at least one actuator fails, breaks, stop working, losepower or become inoperative in any other way, the default setting of the limitationstructure of the firing direction limitation device is the second position, thus that thelimited launch angle range will be the default launch angle range.
    Thus, according to one aspect of the present invention, the solenoid actuator isspring-loaded. Further, according to yet another exemplary aspect of the presentinvention, the spring-loading of the actuator, such as e.g. a solenoid actuator, isconfigured such that the limiting structure of the firing direction limitation device is setin the second position, thus allowing the limiting launch angle range, if the actuatorfails, breaks, stop working, lose power or in any other way become inoperative.
    The present invention also refers to countermeasure arrangements. Thus, accordingto an exemplary aspect of the present invention, the present invention refers to acountermeasure arrangement comprising a firing direction limitation deviceaccording to any aspect, or a combination of aspects, previously disclosed herein,wherein the firing direction limitation device is arranged in connection to thedirectable 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 thedirectable firing device is a variable magazine.
    The variable magazine comprises a plurality of longitudinal cartridge cases formingthe variable magazine, wherein each cartridge case comprises side walls and a frontopening. 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 openingsof the cartridge cases can be directed in a selected direction.
    The above described countermeasure arrangements disclose the same advantagesas previously disclose in relation to respective firing direction limitation device.
    The present invention further refers to methods for controlling the allowed launchangle range of a directable firing device by means of any aspect of, or a combinationof aspects of, a firing direction limitation device as previously disclosed herein.
    According to what previously has been disclosed, the directable firing device isconfigured to be tiltable between at least two allowed launch angles defining alaunch sector. The firing direction limitation device further comprises a moveablelimiting structure configured to be arranged in connection to the directable firingdevice, and wherein the limiting structure is configured to be moveable between afirst position and a second position. When the limiting structure is set in the firstposition the directable firing device is moveable within a first launch angle range, andwhen the limiting structure is set in the second position the directable firing device ismoveable within a second launch angle range. The second launch angle range islimited in relation to the first launch angle range.
    According to a first, basic exemplary aspect of the present invention, the methodsimply comprises the method step of, when it is desired to limit the allowed firingrange of the directable firing device: o setting the limiting structure in the second position.
    The first exemplary aspect of the present invention represents a basic concept of thepresent invention; when it for some reason, such as e.g. that an aircraft providedwith a firing direction limitation device according to the present invention is standingon the ground in order to be able to load/unload cargo or when an aircraft providedwith a firing direction limitation device according to the present invention is flying information surrounded by friendly aircrafts, the limiting structure is set in the secondposition. The allowed launch angle range when the limiting structure is set in thesecond 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 thefirst position. 11 As previously mentioned, according to some exemplary aspects of the presentinvention, it may be preferable that the directable firing device can be operated in asafe operation mode. Such safe operation mode may be manually selectable orautomatically selectable. Thus, according to a second exemplary aspect of thepresent invention the method comprises the method steps of: o detecting that a safe operation mode is desired, ando setting the limiting structure in the second position if it has beenidentified that a safe operation mode is desired. lf an aspect of a method is applied that automatically selects a safe operation mode,it is desirable that the detecting operation is mechanical, such as e.g. by using amechanical door switch or similar. Methods applied in which software has to beinvolved are, of reasons previously discussed, desirable to avoid.
    According to a third exemplary aspect of the present invention, a safe operationmode is detected when one operation from a predefined group of operations isinitiated, wherein the predefined group of operations comprises: o opening a side door,o opening a cargo bay door, and o detecting a predefined weight-on-wheels.
    Many aircrafts, such as e.g. helicopters, are equipped with a mechanical switchconfigured to detect when the aircraft is standing on e.g. the ground, thus when thewheel 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 safeoperation mode is desired. When a safe operation mode is detected, the limitingstructure is preferably pre-set in the second position, and will not be able to move to the first position.
    Thus, according to the third exemplary aspect of the present invention, if at least oneof the operations defined above is initiated it is detected that a safe operation modeis desired, whereby the limiting structure is set in the second position, and wherein 12 the allowed launch angle range of e.g. flares, chaff, shotgun shots, pellet loads orsimilar is limited in relation to the allowed launch angle range of the first position.
    An exemplary advantage of exemplary aspects of the present invention usingautomatically selectable safe operation mode is that by automatically setting thelimiting structure in the second position, whereby the launch sector of the directablefiring device is limited, it may e.g. be safe for personnel opening a side door to leaveor unload the aircraft even if this has not been communicated to e.g. the pilot of theaircraft.
    For aspects of the method wherein manually selecting that the directable firingdevice is to be operated in a safe mode is applied, this may e.g. be done when theaircraft is flying in formation, when approaching home base or when friendly forcesare present nearby the aircraft.
    The exemplary aspects of methods for controlling the allowed launch angle range ofa directable firing device are preferably performed by means of a control device. Thecontrol device is preferably one or more switches directly connected to an actuator,but could also be an electronic control unit comprising logic circuits. The controldevice could also e.g. comprise a device capable of executing method steps such ase.g. a computer device.
    According to yet an exemplary aspect of the present invention, the present inventionrefers to an aircraft comprising a countermeasure arrangement according to any aspect, or a combination of aspects, previously disclosed.BRIEF DESCRIPTION OF THE DRAWINGS The invention will be described in greater detail in the following detailed description, with reference to the embodiments that are shown in the attached drawings, in which Fig. 1a schematically shows a side view of an aircraft, in form of a helicopter,provided with directable firing devices in form of variable magazinesaccording to an embodiment of the present invention, Fig. 1b 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.
    Fig.
    Fig.
    Fig.
    Fig.
    Fig.
    Fig.
    Fig.
    Fig.
    Fig. 3b 4a 4b 13schematically shows a side view of an aircraft, in form of a helicopter,provided with directabie firing devices in form of variabie magazinesaccording to an embodiment of the present invention in which Iimiting structures are set in the second position, schematically shows a top view of an aircraft, in form of a helicopter,provided with directabie firing devices in form of variabie magazinesaccording to an embodiment of the present invention in which Iimiting structures are set in the second position, schematically shows an exemplary embodiment of a directabie firing device in form of a variabie magazine in an ISO view, schematically shows an exemplary embodiment of a ti|ted directabie firing device in form of a variabie magazine in an ISO view, schematically shows an exemplary embodiment of a ti|ted directabie firing device from a side view, schematically shows another exemplary embodiment of a ti|teddirectabie firing device from a side view, schematically shows an exemplary embodiment of a directabie firing device in form of a variabie magazine from a top view, schematically shows an exemplary embodiment of a firing directionIimitation device wherein the directabie firing device in form of a variabie magazine is provided with a Iimiting structure from a top view, schematically shows another exemplary embodiment of a firing directionIimitation device wherein the directabie firing device in form of a variabiemagazine is provided with a Iimiting structure from a top view, and schematically shows yet another exemplary embodiment of a firingdirection Iimitation device wherein the directabie firing device in form of avariabie magazine is provided with a Iimiting structure from a top view.
    DETAILED DESCRIPTION 14ln the following, a detailed description of the different embodiments of the inventionis disclosed under reference to the accompanying drawings. All examples hereinshould be seen as part of the general description and are therefore possible tocombine in any way in general terms. Individual features of the various embodimentsand methods may be combined or exchanged unless such combination or exchangeis clearly contradictory to the overall function of the embodiment or feature.Reoccurring reference signs refer to corresponding elements throughout the detaileddescription. Same reference signs indexed with different letters generally refers to different possible exemplary embodiments of the same feature.
    Fig. 1a discloses an exemplary embodiment of an aircraft 1, for the exemplaryembodiment of fig. 1a in form of a helicopter 1, provided with a first 10a, a second10b and a third 10c directable firing device, in the exemplary embodiment of fig.1a inform of a first, second and third variable magazine 110a, 110b, 110c. However, ashas been clearly pointed out in the Summary of the invention, the present inventionmay also be applied for other directable firing devices. 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. 1a, wherein the X-direction coincides with thelongitudinal direction of the helicopter 1, thus the indicated forward or flight directionof the helicopter 1, the Y-direction is perpendicular to the X-direction and coincideswith what is referred to as an elevation or upwards/downwards direction of thehelicopter 1. The Z-direction is perpendicular to both the X-direction and the Z-direction. The X-direction and the Z-direction defines a horizontal XZ-plane and theX-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. ln the exemplary embodiment shown in fig. 1a, one side of the helicopter 1 is shown.On this side, the first variable magazine 110a is placed at the front of the helicopter1, pointing substantially forvvards-downwards, and the second and the third variablemagazines 110b, 110c are placed at the rear of the helicopter 1, wherein the secondvariable magazine 110b points forvvards-downwards and the third variable magazine 110c points rearwards-downwards.
    An arrow 3 indicates a current direction of launching of respective directable firingdevice 10a, 10b, 10c. According to the embodiment disclosed in fig. 1a thedirectable 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 directionof launching 3, wherein a first launch angle range in the XY-plane LARa1(xy) isdefined. This is referred to as movements in elevation direction of the directablefiring device 10a, 10b, 10c in the XY-plane. The maximum allowed angle in whichthe directable firing devices 10a, 10b, 10c can be tilted in respective direction in theXY-plane is referred to as first and second maximum launch angles MaxLA1(xy),MaxLA2(xy). The first launch angle range LARa1(xy) defines an extension in the XY-plane of a first launch sector 4a(xy) over which countermeasures or like may befired/launched.
    Fig. 1b discloses top view of the aircraft 1, i.e. helicopter 1. Fig. 1b discloses that thedirectable firing devices 10a, 10b, 10c are directable, or tiltable, also in the horizontalXZ-plane about 45 degrees in resp. angular direction in relation to the currentdirection of launching 3, wherein a first launch angle range LARa1(xy) also in theXZ-plane is defined. Movements in the XY-plane of the variable magazines 110a,110b, 110c is referred to as movements in azimuth direction. The maximum allowedangle in which the directable firing devices 10a, 10b, 10c can be tilted in respectivedirection is referred to as first and second maximum launch angles MaxLA1(xz),MaxLA2(xz). The first launch angle range LARa1(xz) defines an extension in the XZ-plane of the first launch sector 4a(xz) over which countermeasures or like can befired/launched.
    A problem with using directable firing devices 10a, 10b, 10c, such as the variablemagazines 110a, 110b, 110c disclosed in the exemplary embodiment shown in fig.1a and fig. 1b, is that if incorrectly used, or if not sufficiently controlled, the possibilityof controlling the allowed launch angle range of the directable firing device may putnearby friendly forces in danger or even damage e.g. a main rotor 5, a tail rotor 50 orthe fuselage 2 of an aircraft 1.
    According to the present invention this problem is solved by means of firing directionlimitation devices 15. The firing direction limitation device 15 comprises a limitingstructure (not visible in fig. 1a, 1b, 2a and 2b). 16 The limiting structure is configured to be set in at least a first position and a secondposition. When the limiting structure is set in the first positon the directable firingdevice is moveable within a first launch angle range and when the Iimiting structureis set in the second positon the directable firing device is moveable within a secondlaunch angle range, wherein the second launch angle range is limited in relation tothe first launch angle range. Thereby the allowed launch angle range of thedirectable firing device is controllable. ln fig. 1a and 1b the limiting structure of the firing direction limitation device 15 is setin the first position wherein the allowed launch angle range is not limited, i.e. thevariable magazines 110a, 110b, 110c are free to move by being tilted over the firstlaunch angle range LARa1(xy), LARa1(xz) in elevation and azimuth direction. Thevariable magazines 110a, 110b, 110c are directable about 45 degrees in respectivedirection in both the XY-plane and the XZ-plane, i.e. in both elevation and azimuthdirection. ln fig. 2a and fig. 2b the limiting structure of the firing direction limitation device 15 isset in the second position wherein the allowed launch angle range is limited, i.e. thevariable magazines 110a, 110b, 110c cannot move freely by being tilted over thefirst launch angle range LARa1(xy), LARa1(xz) in elevation and azimuth direction, but can only move freely over a second launch angle range LARa2(xy), LARa2(xz). ln fig. 2a and fig. 2b the maximum allowed angles in which the directable firingdevices 10a, 10b, 10c can be tilted in respective direction may be referred to as firstand second limited launch angles in elevation, i.e. the XY-plane, LimLA1(xy),LimLA2(xy), and in azimuth, i.e. the XZ-plane, LimLA1(xz), LimLA2(xz). The first andsecond limited launch angles LimLA1(xy), LimLA2(xy) define the second launchangle range LARa2(xy) in the XY-plane, and the first and second limited launchangles LimLA1(xz), LimLA2(xz) define the second launch angle range LARa2(xz) inthe XZ-plane.
    The second launch angle range in the XY- and XZ-planes LARa2(xy), LARa2(xz) arelimited in relation to first launch angle range in the XY- and XZ-planes LARa1(xy),LARa1(xz). ln accordance to what has been disclosed in fig. 1a, the first launchangle range in the XY- and XZ-planes LARa1(xy), LARa1(xz) are defined by the first 17and second maximum launch angles in the XY- and XZ-plane, MaxLA1(xy),MaxLA2(xy) and MaxLA1(xz), MaxLA2(xz). This is accomplished by means of thelimiting structure of the firing direction limitation device 15. When the limitingstructure is set in the second position, the allowed launch angle is restricted to the second launch angle range in the XY- and XZ-planes LARa2(xy), LARa2(xz).
    According to the exemplary embodiment of fig. 1a, 1b, 2a and 2b the directable firingdevice 10a, 10b, 10c, which according to fig. 1a, 1b, 2a and 2b is in form of variablemagazines 110a, 110b, 110c, are moveable both in elevation direction, i.e. in theXY-plane, and in azimuth direction, i.e. in the XZ-plane, and the limiting structure ofthe firing direction Iimitation device 15 is capable of limiting the tilting movements ofthe directable firing device 10a, 10b, 10c in both the XY-plane and in the XZ-plane.However, it is also possible that the limiting structure is only configured to limit thetilting movements of the directable firing device 10a, 10b, 10c in either the XY-planeor the XZ-plane.
    Fig. 3a and 3b show an exemplary embodiment of a directable firing device 10, infig. 3a and 3b in form of a variable magazine 110, in an ISO view. The variablemagazine 110 comprises a plurality of cartridge cases 8 arranged in a matrix with anumber 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 sizeof a cartridge. The exemplary embodiment of fig. 3a and 3b comprises 3 rows ofcartridge cases 8 in 5 columns. A cartridge case 8 is designed with a longitudinalbody, preferably having a square or rectangular cross-section. The cross-section ofa 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 as is shown in fig.4a. Each cartridge case 8 has an opening 14 through which the countermeasure orlike can be launched or fired. Thus, the direction in which the opening 14 is pointingdetermines the direction in which the countermeasure or like is fired or launched.
    The variable magazine 110 comprises a base 7, which constitute the base of thevariable magazines 110 and is used to mount the variable magazines 110 to an aircraft by the use of any suitable attachment means. Each cartridge case 8 is 18 attached to the base 7 through a flexible joint 9, allowing respective cartridge case 8to 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 bearagainst each other and such that they can slide against each other in the longitudinaldirection when the variable magazine 110 is tilted. The tilting of the variablemagazine 110 is achieved by means of tilting means (not shown).
    Referring to the XYZ coordinate system indicated in fig. 3a and 3b; for aspects ofvariable magazines 110 in which the cartridge cases 8 can be tilted in two directions,i.e. in the XY-plane and in the ZY-plane, the flexible joint 9 allows tilting of thecartridge cases 8 in XY-plane and ZY-plane. For such embodiments the flexible joint9 may e.g. be in form of a ball joint. For aspects of variable magazines only capableof tilting in one direction, i.e. either the XY-plane or in the ZY-plane the flexible joint may e.g. be in form of a hinge.
    Fig. 3a shows the exemplary embodiment of a variable magazine 110 wherein acartridge centre axis 6 of a cartridge case 8 is directed in parallel to the Y-axis, thusis directed to be perpendicular to the X-axis and the Z-axis. The base 7 is directed inan XZ-plane. This position is used as a reference position in this description and isreferred to as resting position. The tilt angle of the variable magazine 110, i.e. the tiltangle of the cartridge centre axis 6, is zero degrees in the resting position.
    Fig. 3b shows the exemplary embodiment of a variable magazine 110 in, what isreferred to as, an active position. ln the active position the variable magazine 110,and thus the cartridge centre axis 6, is tilted with an angle referred to as first tiltangle TA1(xy), in a first direction the XY-plane. ln fig. 3b the variable magazine 110is 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 tiltangle TA1(xy) indicates the maximum tilt angle in the first direction in the XY-planeof the variable magazine 110, thus what has been referred to as first maximumlaunch angle MaxLA1 (xy) for fig. 1a and 1b. This angle may e.g. be 45 degrees.
    Obviously the variable magazine 110 may also be tilted in the opposite, seconddirection in the XY-plane, in which direction the maximum angle in which the variablemagazine could be tilted would be the second maximum launch angle MaxLA2(xy). 19Thus, the cartridge cases 8 of the variable magazine 110 are configured to e.g. betiltable 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 slidablemanner, the variable magazine 110 can be tilted by a ti|ting means to any selected angle.
    When mounted on an aircraft such as a helicopter, the ti|ting of a variable magazinefrom a resting position to an active position may e.g. be due to that direction of thevariable magazine is configured according to a detected, incoming threat, wherebyby directing the variable magazine towards the incoming threat, countermeasurescan be Iaunched from the variable magazine towards the incoming threat. Thedirection of the variable magazine can also be used to compensate for that theorientation of the helicopter in the air changes during flight.
    A cartridge case 8 is adapted to receive a countermeasure 13 stored in a cartridge12 as is shown in fig. 4a. The countermeasure cartridge 12 may be attached to thecartridge case 8 according to any commonly known manner. The countermeasurecartridge 12 is further connected to a launch system of the aircraft, comprising afiring control. The interface between the countermeasure cartridge 12 and theelectronic control unit of the aircraft may be a mechanical system, which can onlylaunch the countermeasure, or it may be an electrical interface, comprising tvvo-way communication between the countermeasure cartridge 12 and the aircraft.
    Thus, the variable magazine comprises a plurality of longitudinal cartridge cases 8forming the variable magazine 110, wherein each cartridge case 8 comprises sidewalls 21 and a front opening 14, and wherein the side walls 21 of two adjacentcartridge cases 8 are arranged to each other in a slidable manner in a longitudinaldirection. The variable magazine 110 comprises a ti|ting means 22 adapted to tilt thecartridge cases 8 such that the openings 14 of the cartridge cases 8 can be directedin a selected direction. The ti|ting means 22 schematically shown in fig. 4a and 4b isjust one possible realization of ti|ting means out of the many possible.
    Further, fig. 4a discloses a similar exemplary embodiment of a directable firingdevice 10 in form of a variable magazine 110 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 limitingstructure 16 and a number of actuators 17. The firing direction limitation device 15,comprising the limiting structure 16, and the directable firing device 10 togetherforms a countermeasure arrangement 19 as defined according to the presentinvention. The limiting structure 16 of the firing direction limitation device 15 ismoveable between a first position P1 and a second position P2. Fig. 4a discloses thelimiting structure 16 in the first position P1, in which the limiting structure 16 isretracted.
    Fig. 4b discloses the limiting structure 16 in the second position P2, in which thelimiting structure 16 is projected. The projection movement of the limiting structure16, and also a possible subsequent retraction movement, is performed by means ofactuators 17. ln fig. 4a and 4b four actuators are visible. ln the first position P1, the variable magazine 110 may be tilted in a first direction inthe XY-plane at the maximum angle the variable magazine 110 is tiltable, i.e. firstmaximum launch angle MaxLA1(xy). The limiting structure 16 is set in the firstposition P1 and do not limit or restrict the movements of the variable magazine 110. ln fig. 4b the limiting structure 16 is projected and is set in the second position P2.When set in the second position P2, the inner delimitation surface 18 abuts the sidewall 21 of the peripheral cartridge case 8 whereby the movements of the variablemagazine the first direction in the XY-plane is restricted or limited. Thus, the secondtilt angle TA2(xy), which is the maximum angle the variable magazine 110 can betilted in the first direction in the XY-plane when the limiting structure is set in thesecond position P2, is smaller than the first tilt angle TA1(xy), which was themaximum angle the variable magazine 110 can be tilted in the first direction in theXY-plane when the limiting structure was set in the first position P1, as is shown infig. 4a.
    The actuators 17 may e.g. be solenoid actuators. According to the exemplaryembodiment of fig. 4a and 4b the actuators are spring-loaded by means of a coilspring 20. Applying spring-loaded actuators 17 has the advantage that if theactuators 17 fail the spring force exerted by the coil spring 20 allows the limitingstructure 16 to be in the second position P2. Thus, if the actuators 17 fail the more 21limited 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 cooperatingwith a threaded hole in the limiting structure.
    As in fig. 3a and 3b, in fig. 4a and 4b the limiting structure 16 is configured to bearranged in connection to the directable firing device 10, in fig. 3a, 3b, 4a and 4bprovided in form of a variable magazine 110. Further, in fig. 3a, 3b, 4a and 4b thevariable magazine 110 is only tilted in a first direction in the XY-plane, but obviouslythe variable magazine 110 can also be tilted in the opposite, second direction in theXY-plane and also in the first and second direction in an ZY-plane. The limitingstructure 16 will have the same, limiting affect when set in the second position P2also in these tilting directions.
    For an exemplary embodiment of directable firing device 10 provided in form of avariable magazine 110, the base 7, which is the base of the variable magazine 110,is used to mount the variable magazine 110 to an aircraft by the use of anattachment means. The variable magazine 110 may be mounted directly to anattachment bracket on the aircraft with suitable mounting means. lt is also possibleto mount the variable magazine 110 to an adapter bracket, which is used to createan interface for an existing mounting bracket on an aircraft. By using a suitableadapter bracket, the magazine can be mounted to an aircraft provided withstandardized mounting brackets for fixed magazines. ln this way, there is no need toupgrade the aircraft with new mounting brackets. Further, by using an adapterbracket, both fixed magazines and variable magazines can be used, depending onthe actual needs. ln addition to being used to mount the variable magazine 110 to an aircraft, the base7 is also used to absorb recoil force created when a countermeasure or similar islaunched or fired. The base 7 will absorb and distribute the created force over theentire base area of the base 7.
    Fig. 5a discloses an exemplary embodiment of a directable firing device 10 in form ofa variable magazine 110 in a top view. ln fig. 5a a variable magazine 110 comprising3 rows of cartridge cases 8 in 5 columns is shown, wherein the cartridge cases areof the dimension 1*1 inch. Also other numbers of rows and/or columns are possible, 22as well as other dimensions of the cartridge cases 8, such as e.g. 1*2 inches. Thelength of the cartridge case 8 may e.g. be 8 inches. ln fig. 5a the openings 14 of thecartridge cases 8 are directed essentially in the Y-direction. ln the shown view, a firing direction limitation device is not shown.
    Fig. 5b, 5c and 5d schematically discloses how various embodiments of firingdirection limitation devices 15b, 15c, 15d comprising various configurations oflimiting structures 16b, 16c, 16d arranged in connection to directable firing devices10,11, in fig. 5b to 5d in form of variable magazines 110,111, may be configured.
    Fig. 5b discloses an exemplary embodiment of a firing direction limitation device 15bwherein the directable firing device 11 in form of a variable magazine 111 is providedwith a limiting structure 16b in a top view. The embodiment of a variable magazine111 of fig. 5b comprises 3 rows of cartridge cases 8 in 4 co|umns. The limitingstructure 16b has an inner de|imitation surface 18. When the limiting structure 16b isset in the second position P2, thus is projected by means of actuators 17, the innerde|imitation surface 18 of the limiting structure 16b will restrict the movements in theX-direction in the XY-plane and in the Z-direction in the ZY-plane of the variablemagazine 111. Thereby, the second launch angle range both in the X-direction in theXY-plane and in the Z-direction in the ZY-plane will be restricted. ln fig. 5b fouractuators 17 are arranged in the corners of the limiting structure 16b. The restrictionof movement in different directions may differ, such that it may e.g. be +30 degreesand - 15 degrees in the X-direction and +- 25 degrees in the Z-direction. The firingdirection limitation device 15b is further provided with an additional restriction section24 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.ln the shown example, the restriction section will limit the movement of the variablemagazine in the -Z-direction when the variable magazine is tilted less than e.g. 5degrees in the +X-direction, and will limit the movement of the variable magazine inthe -X-direction when the variable magazine is tilted more than e.g. 10 degrees inthe -Z-direction. Such 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 limitationdevice 15c wherein the directable firing device 10 in form of a variable magazine 110 23 is provided with a limiting structure 16c in a top view. The embodiment of a variablemagazine 110 of fig. 5c comprises 3 rows of cartridge cases 8 in 5 columns. Thelimiting structure 16c has an inner delimitation surface 18. When the limitingstructure is set in the second position P2, thus is projected by means of actuators17, the inner delimitation surface 18 of the limiting structure 16c will restrict themovements in the X-direction in the XY-plane and in the Z-direction in the ZY-planeof the variable magazine 110. Thereby 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. lnfig. 5c six actuators 17 are arranged to enable the limiting structure 16c to movebetween a projected and a retracted position, i.e. the first position and the secondposition.
    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 additionalrestriction sections 25a, 25b and 25c that will limit the movement of the variablemagazine additionally along the X-direction and the Z-direction in dependency of theactual tilt angle in a specific direction. ln the shown example, the restriction section25a 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 willbe proportional to the tilt angle of the variable magazine in the -X-direction. Therestriction 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 ofthe aircraft.
    Compared to the exemplary embodiment of a directable firing device 11, provided inform of a variable magazine 111, of fig. 5b the exemplary embodiment of adirectable firing device 10, provided in form of a variable magazine 110, of fig. 5chas a larger spatial extension in the X-direction due to that the variable magazine offig. 5c comprises 5 columns of cartridge cases 8. This, i.e. the spatial extension, issomething that needs to be considered when the limiting structure is configured forrespective implementation of the present invention. The spatial extension in the Z-direction is the same since both the exemplary embodiment of fig. 5b and 5ccomprises 3 rows of cartridge cases 8. Also, the spatial extension in the X-direction 24and in the Z-direction needs to be considered since the point of launch/firing willdiffer significantly between individual cartridge cases 8 of a variable magazine 110.These are aspects that do not have to be considered when providing a firingdirection limitation device for a directable firing device provided in form of e.g. a canon or a machine gun.
    Fig. 5d schematically shows yet another exemplary embodiment of a firing directionlimitation device 15d wherein the directable firing device 10 is in form of a variablemagazine 110 is provided with a |imiting structure 16d in a top view. The |imitingstructure 16d disclosed in fig. 5d is provided in form of a sector portion having aninner delimitation surface 23, wherein the inner delimitation surface 23, when the|imiting structure is set in the second position, determines the second launch anglerange. The sector portion of the |imiting structure 16d of fig. 5d is provided in form ofa portion of a square, here an L-shaped structure, wherein the |imiting structure 16d,when set in the second position, will only affect the freedom of movement of thevariable magazine 110 in certain directions, i.e. the second launch angle range willonly be limited in certain directions. As seen in fig. 5d, the variable magazine 110 willbe limited in the -X-direction and in the -Z-direction. The possible movement in thepositive X-direction will be the same as when the |imiting structure 16d is in the firstposition, and the possible movement in the positive Z-direction will be the same aswhen the |imiting structure 16d is in the first position.
    The terminology used herein is for the purpose of describing particular exemplaryaspects or embodiments only and is not intended to be |imiting of the invention. Asused herein, the singular forms "a", "an" and "the" are intended to include the pluralforms as well, unless the context clearly indicates otherwise. lt should further beunderstood that the terms "comprises" "comprising," "includes" and/or "including"when used herein, specify the presence of stated features, integers, steps,operations, elements, and/or components, but do not preclude the presence oraddition of one or more other features, integers, steps, operations, elements,components, and/or groups thereof.
    Unless otherwise defined, all terms, including technical and scientific terms, usedherein have the same meaning as commonly understood by one of ordinary skill inthe art to which this invention belongs. lt should further be understood that terms used herein should be interpreted as having a meaning that is consistent with theirmeaning in the context of this specification and the relevant art and will not beinterpreted in an idealized or overly formal sense unless expressly so defined herein. 26 REFERENCE SIGNS 1 : Aircraft/Helicopter 2: Aircraft fuselage 3: Direction of launch 4(a-b): Launch sector 5: Main rotor 6: Cartridge centre axis 7: Base 8: Cartridge case 9: Flexiblejoint 10: Directable firing device 10a: First directable firing device10b: Second directable firing device10c: Third Directable firing device11: Fourth directable firing device12: Countermeasure cartridge 13: Countermeasure 14: Opening 15(b-d): Firing direction Iimitation device16(b-d): Limiting structure 17: Actuator 18: Inner delimitation surface 19: Countermeasure arrangement20: Spring 21: Side walls 22: Tilting means 23: Inner delimitation surface 24: Restriction section 25(a-c): Restriction section 27 50: Tail rotor 110: Variable magazine 110a: First variabie magazine110b: Second variable magazine110c: Third variabie magazine111: Fourth variabie magazineMaxLA1*: First maximum launch angleMaxLA2*: Second maximum launch angleLimLA1*: First limited launch angleLimLA2*: Second limited launch angleLARa1*: First launch angle rangeLARa2*: Second launch angle rangeTA1*: First tilt angle TA2*: Second tilt angle P1 : First position P2: Second position * = the reference signs may be indexed in order to indicate in what plane in a systemof coordinates they indicate movements, angles etc.
    权利要求:
    Claims (1)
    [1] 1. _ Firing direction Iimitation device (15) for controlling the allowed launch anglerange of a directable firing device (10) tiltable between at least two allowedmaximum launch angles (MaxLA1, MaxLA2) defining a launch sector (4),where the firing direction Iimitation device (15) comprises: o a moveable limiting structure (16) configured to be arranged in connection to the directable firing device (10), characterized in thatthe limiting structure (16) is configured to be moveable between a first position(P1) and a second position (P2), where,when the limiting structure (16) is set in the first positon, (P1) the directablefiring device (10) is moveable within a first launch angle range (LARa1), andwhen the limiting structure (16) is set in the second positon (P2), the directablefiring device (10) is moveable within a second launch angle range (LARa2),where the second launch angle range (LARa2) is limited in relation to the firstlaunch angle range (LARa1),whereby the allowed launch angle range of the directable firing device (10) is controllable. _ Firing direction Iimitation device (15) according to claim 1, characterized in thatthe second launch angle range (LARa2) is limited in azimuth direction in relation to the first launch angle range (LARa1). Firing direction Iimitation device (15) according to claim 1 or 2, characterized in that the second launch angle range (LARa2) is limited in elevation direction inrelation to the first launch angle range (LARa1). Firing direction Iimitation device (15) according to any one of the precedingclaims,characterized in that 29 the directable firing device (10) is a variable magazine (110), where thevariabie magazine (110) comprises a plurality of Iongitudinal cartridge cases (8)forming the variabie magazine (110), where each cartridge case (8) comprisesside walls (21) and a front opening (14), where the side walls (21) of twoadjacent cartridge cases (8) are arranged to each other in a slidable manner ina Iongitudinal direction, and where the variabie magazine (110) comprises atilting 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. 5. Firing direction Iimitation device (15) according to any one of thepreceding ciaims, characterized in that the moveable |imiting structure (16) is in form of a sector portion having aninner delimitation surface (23), where the inner delimitation surface (23)determines the second launch angle range (LARa2). Firing direction Iimitation device (15) according to any one of claim 1 to 4,characterized in that the moveable |imiting structure (16) is in form of an encircling portion having aninner delimitation surface (18), where the inner delimitation surface (18)determines the second launch angle range (LARa2). Firing direction Iimitation device (15) according to claim 6,characterized in thatthe inner delimitation surface (18) of the encircling portion is essentially circular, essentially square, essentially rectangular or irregularly shaped. Firing direction Iimitation device (15) according to any one of the precedingciaims, characterized in that the movements of the |imiting structure (16) are projecting and retractingmovements and where the projecting/retracting movements are controllable bymeans of at least one actuator (17). 10. 11. 12. Firing direction Iimitation device (15) according to claim 8,characterized in that the at least one actuator (17) is a solenoid actuator. Countermeasure arrangement (19), characterized in that the countermeasurearrangement (19) comprises a firing direction limitation device (15) according toany one of claims 1 to 10, and a directable firing device (10), where the firingdirection Iimitation device (15) is arranged in connection to the directable firingdevice (10) such that the allowed launch angle range of the directable firing device (10) is controllable. Countermeasure arrangement (19) according to claim 10, characterized in that the directable firing device (10) is a variable magazine (110), where thevariable magazine (110) comprises a plurality of longitudinal cartridge cases (8)forming the variable magazine (110), where each cartridge case (8) comprisesside walls (21) and a front opening (14), where the side walls (21) of twoadjacent cartridge cases (8) are arranged to each other in a slidable manner ina longitudinal direction, and where the variable magazine (110) comprises atilting 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. Method for controlling the firing direction of a directable firing device (10) bymeans of a firing direction Iimitation device (15), wherein the directable firingdevice (10) is tiltable between at least two allowed launch angles (MaxLA1,MaxLA2) defining a launch sector (4), wherein the firing direction Iimitationdevice comprises: o a moveable limiting structure (16) configured to be arranged inconnection to the directable firing device (10), and wherein the limiting structure (16) is configured to be moveable between a firstposition (P1) and a second position (P2), and wherein, when the limiting structure (16) is set in the first positon (P1), thedirectable firing device (10) is moveable within a first launch angle range(LARa1), and 13. 14. 15. 31 when the limiting structure (16) is set in the second positon (P2), the directablefiring device (10) is moveable within a second launch angle range (LARa2),wherein the second launch angle range (LARa2) is limited in relation to the firstlaunch angle range (LARa1), wherein the method comprises the method step of, when it is desired to limitthe allowed launch angle range of the directable firing device (10): o setting the limiting structure (16) in the second position (P2). Method according to claim 12, wherein the method comprises the additional method steps of: o detecting that a safe operation mode is desired, o setting the limiting structure (16) in the second position (P2) when it has been detected that a safe operation mode is desired. Method according to claim 13, wherein the safe operation mode is detectedwhen one operation from a predefined group of operations is initiated, wherein the predefined group of operations comprises: o opening a side door,o opening a cargo bay door, ando detecting a defined weight-on-wheels. An aircraft (1 ), countermeasure arrangement (19) according to any one of claims 10 or 11. characterized in that the aircraft (1) comprises a
    类似技术:
    公开号 | 公开日 | 专利标题
    SE1651465A1|2017-11-18|Firing direction limitation device
    US9523548B2|2016-12-20|Operational control logic for harmonized turret with gimbaled sub-systems
    US20090072076A1|2009-03-19|System and method for attitude control of a flight vehicle using pitch-over thrusters
    US10684099B2|2020-06-16|Magazine, cartridge and method for launching a countermeasure
    EP2422161B1|2020-03-18|Countermeasure arrangement
    EP3458801B1|2021-07-28|Magazine, cartridge and method for variable projectile cluster density of a countermeasure
    GB2025009A|1980-01-16|Airborne weapons system
    US9169015B2|2015-10-27|Countermeasure decoy system intended to be mounted on an aircraft
    KR101935262B1|2019-01-04|Operating method of drone intelligence munitions and flight vehicle for close-in weapon system against missile, drone intelligence munitions or drone for close-in weapon system against missile
    WO2017200460A1|2017-11-23|Device and method for firing direction limitation and a countermeasure arrangement
    US10683092B2|2020-06-16|Magazine and method for launching countermeasures
    KR101924863B1|2018-12-04|Drone intelligence munitions and flight vehicle for close-in weapon system against missile
    IL213934A|2014-12-31|Method for controlling a warshot missile
    CN111017193A|2020-04-17|Carrying aircraft and load delivery method
    US10793275B2|2020-10-06|Rotatable and extendable deployment system
    WO2021094712A1|2021-05-20|A weapon system
    US3797360A|1974-03-19|Telescoping airborn launch tube
    RU2530461C1|2014-10-10|Air target
    TW201947547A|2019-12-16|Remote safe shooting control system including at least one remote control device and at least one mobile vehicle
    KR100241872B1|2000-03-02|Pylon for aircraft
    SWEETMAN1987|F-15 E- Heavyweight Eagle
    JPH06281394A|1994-10-07|Aircraft placing launcher
    JP2001116497A|2001-04-27|Missile
    同族专利:
    公开号 | 公开日
    EP3458798A4|2019-12-25|
    IL262828D0|2018-12-31|
    PL3458793T3|2021-12-13|
    EP3458793B1|2021-07-07|
    US20190092469A1|2019-03-28|
    US11008099B2|2021-05-18|
    ES2889448T3|2022-01-12|
    DK3458798T3|2021-09-13|
    US10683090B2|2020-06-16|
    EP3458798B1|2021-07-07|
    EP3458798A1|2019-03-27|
    ES2883679T3|2021-12-09|
    EP3458793A1|2019-03-27|
    EP3458793A4|2019-12-25|
    DK3458793T3|2021-09-13|
    US20200318921A1|2020-10-08|
    PL3458798T3|2021-12-13|
    IL262823D0|2018-12-31|
    WO2017200455A1|2017-11-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2434653A|1941-10-24|1948-01-20|Sperry Gyroscope Co Inc|Power-operated aircraft gun turret|
    US2434654A|1942-08-26|1948-01-20|Sperry Gyroscope Co Inc|Limit stop and fire cutoff device for gun turrets|
    US2391956A|1944-03-23|1946-01-01|United Shoe Machinery Corp|Limit stop for gun mounts|
    US2467514A|1944-05-16|1949-04-19|United Shoe Machinery Corp|Direction-controlling mechanism for guns|
    US3808940A|1964-12-24|1974-05-07|Gen Dynamics Corp|Portable decoy launcher system and rounds therefor|
    US3808595A|1973-04-11|1974-04-30|Celesco Industries Inc|Chaff dispensing system|
    US3934846A|1974-10-08|1976-01-27|The United States Of America As Represented By The Secretary Of The Air Force|Device to reduce flow induced pressure oscillations in open cavities|
    CH626163A5|1977-11-04|1981-10-30|Oerlikon Buehrle Ag|
    CA1157301A|1980-05-23|1983-11-22|Jean-Michel Schaulin|Marine firing weapon for fighting airborne targets,especially in zenith|
    US4696442A|1986-07-14|1987-09-29|The Boeing Company|Vortex generators for inlets|
    DE3902624C2|1989-01-30|1998-02-12|Blohm Voss Ag|Adjustment device for the position and size of the horizontal swivel or sweep angle of a machine gun, e.g. an MG|
    FR2650883B1|1989-08-10|1991-10-11|Hispano Suiza Sa|SITE AXLE BEARING FOR ARMING MOUNT|
    US6231002B1|1990-03-12|2001-05-15|The Boeing Company|System and method for defending a vehicle|
    US5340054A|1991-02-20|1994-08-23|The United States Of America As Represented By The Secretary Of The Navy|Suppressor of oscillations in airframe cavities|
    DE4125356C2|1991-07-31|1995-07-06|Buck Chem Tech Werke|Self-protection launcher facility|
    US5198609A|1992-04-27|1993-03-30|The United States Of America As Represented By The Secretary Of The Navy|Auxiliary target area chaff container|
    US5699981A|1996-03-18|1997-12-23|The United States Of America As Represented By The Secretary Of The Air Force|Aircraft cavity acoustic resonance suppression system|
    SE518244C2|1999-04-01|2002-09-17|Saab Ab|Method of projecting countermeasures, and device for storing and projecting countermeasures|
    US6098925A|1999-08-10|2000-08-08|Northrop Grumman Corporation|Adaptive deployable ramp for suppression of aircraft weapons bay acoustic loads|
    DE10008198A1|2000-02-23|2001-08-30|Krauss Maffei Wegmann Gmbh & C|Throwing system for fog candles, explosive devices and the like arranged on a combat vehicle. the like|
    DE10024320C2|2000-05-17|2002-09-05|Diehl Munitionssysteme Gmbh|Radar device for object self-protection|
    GB0013081D0|2000-05-24|2005-02-09|Helio Mirror Company Ltd|Munition launching assembly|
    DE10117300B4|2001-04-06|2004-04-29|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Method for reducing vibrations in a cavity and surface arrangement overflowing|
    RU2004133380A|2002-05-21|2005-06-27|Нир ПАДАН |SYSTEM AND METHOD FOR INCREASING LOAD CAPACITY, CAPACITY AND ADAPTIVE FLEXIBILITY OF EXTERNAL USEFUL LOADS INSTALLED ON THE AIRCRAFT|
    US7475853B2|2002-06-21|2009-01-13|Darko Segota|Method and system for regulating external fluid flow over an object's surface, and particularly a wing and diffuser|
    US7640858B1|2004-01-23|2010-01-05|Kilgore Flares Company, Llc|Stacked pellet flare assembly and methods of making and using the same|
    KR20100106349A|2007-11-08|2010-10-01|레이던 컴퍼니|Chaff pod dispenser|
    US8490924B2|2008-05-30|2013-07-23|Saab Ab|Arrangement and method for launching counter-measures|
    DE102008038603C5|2008-08-21|2018-04-19|Krauss-Maffei Wegmann Gmbh & Co. Kg|Gegenschuss conditioning|
    ES2792355T3|2009-04-23|2020-11-11|Saab Ab|Provision of countermeasures|
    ES2611661T3|2009-04-23|2017-05-09|Saab Ab|Distribution unit with lockable countermeasure compartments|
    DK2421753T3|2009-04-23|2017-04-03|Saab Ab|Device for storing and starting countermeasures|
    US8069767B2|2009-05-19|2011-12-06|The United States Of America As Represented By The Secretary Of The Navy|Gun mount and ejection system|
    GB0913637D0|2009-08-05|2009-09-16|Chemring Countermeasures Ltd|Launcher|
    US20120210855A1|2010-02-22|2012-08-23|Bae Systems Information And Electronic Systems Integration Inc.|System and method for launching countermeasures to missile attack|
    GB2505721B|2012-09-11|2014-07-23|Wallop Defence Systems Ltd|A countermeasure cartridge|
    ES2617682T3|2013-03-15|2017-06-19|Bae Systems Plc|Suppression of acoustic cavity tones|
    US9322613B2|2013-09-10|2016-04-26|NonLethal Technologies, Inc.|Modular system with enhanced safety mechanism for firing non-lethal projectiles for crowd control|
    SE541137C2|2013-11-18|2019-04-16|Bae Systems Bofors Ab|Method for directional restriction and directional restriction system|
    US20160121996A1|2014-03-11|2016-05-05|The Boeing Company|Spoiler for an Aircraft Bay|
    ES2886938T3|2016-05-17|2021-12-21|Saab Ab|Dispenser with a cover and procedure for launching countermeasures|
    DK3458801T3|2016-05-17|2021-10-11|Saab Ab|Magazine, cartridge and method for variable projectile cluster density of a countermeasure|
    DK3458797T3|2016-05-17|2021-09-13|Saab Ab|Magazine for firing countermeasures|
    DK3458802T3|2016-05-17|2021-09-13|Saab Ab|MAGAZINE AND CASSETTE|
    SE1651465A1|2016-05-17|2017-11-18|Saab Ab|Firing direction limitation device|ES2888975T3|2016-05-17|2022-01-10|Saab Ab|Variable Aileron Countermeasure Dispenser and Procedure for Launching a Countermeasure|
    SE1651465A1|2016-05-17|2017-11-18|Saab Ab|Firing direction limitation device|
    DK3458797T3|2016-05-17|2021-09-13|Saab Ab|Magazine for firing countermeasures|
    DK3458802T3|2016-05-17|2021-09-13|Saab Ab|MAGAZINE AND CASSETTE|
    DK3458801T3|2016-05-17|2021-10-11|Saab Ab|Magazine, cartridge and method for variable projectile cluster density of a countermeasure|
    EP3630609A4|2017-06-02|2021-03-10|Saab Ab|Dispenser module for aircraft pylon and a method for launching a countermeasure|
    法律状态:
    2018-05-08| NAV| Patent application has lapsed|
    优先权:
    申请号 | 申请日 | 专利标题
    SE1650665|2016-05-17|PCT/SE2017/050442| WO2017200460A1|2016-05-17|2017-05-05|Device and method for firing direction limitation and a countermeasure arrangement|
    PL17799764T| PL3458793T3|2016-05-17|2017-05-05|Device and method for firing direction limitation and a countermeasure arrangement|
    US16/301,282| US11008099B2|2016-05-17|2017-05-05|Device and method for firing direction limitation and a countermeasure arrangement|
    ES17799764T| ES2889448T3|2016-05-17|2017-05-05|Device and method for the limitation of the firing direction and an arrangement of countermeasures|
    EP17799764.0A| EP3458793B1|2016-05-17|2017-05-05|Device and method for firing direction limitation and a countermeasure arrangement|
    DK17799764.0T| DK3458793T3|2016-05-17|2017-05-05|Device and method for firing direction limitation and a countermeasure arrangement|
    IL262828A| IL262828D0|2016-05-17|2018-11-06|Device and method for firing direction limitation and a countermeasure arrangement|
    [返回顶部]