WO2005106379A1 - Appareil de lancement - Google Patents

Appareil de lancement Download PDF

Info

Publication number
WO2005106379A1
WO2005106379A1 PCT/IB2005/001219 IB2005001219W WO2005106379A1 WO 2005106379 A1 WO2005106379 A1 WO 2005106379A1 IB 2005001219 W IB2005001219 W IB 2005001219W WO 2005106379 A1 WO2005106379 A1 WO 2005106379A1
Authority
WO
WIPO (PCT)
Prior art keywords
plate
launch
flat element
capsule
hollow seat
Prior art date
Application number
PCT/IB2005/001219
Other languages
English (en)
Italian (it)
Inventor
Giuseppe Centrone
Original Assignee
Giuseppe Centrone
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 ITMO20040105 external-priority patent/ITMO20040105A1/it
Priority claimed from ITMO20050107 external-priority patent/ITMO20050107A1/it
Application filed by Giuseppe Centrone filed Critical Giuseppe Centrone
Priority to EP05735735A priority Critical patent/EP1756510A1/fr
Priority to JP2007512563A priority patent/JP2007536496A/ja
Priority to CA002564823A priority patent/CA2564823A1/fr
Priority to US11/579,488 priority patent/US20070214948A1/en
Priority to AU2005238724A priority patent/AU2005238724A1/en
Publication of WO2005106379A1 publication Critical patent/WO2005106379A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B4/00—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
    • F42B4/02—Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes in cartridge form, i.e. shell, propellant and primer
    • 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
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/58—Electric firing mechanisms
    • F41A19/59—Electromechanical firing mechanisms, i.e. the mechanical striker element being propelled or released by electric means
    • 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
    • F41F1/06—Mortars

Definitions

  • the invention relates to a launch apparatus.
  • a known launch device comprises one or more pipes or mortar tubes, inside which a respective projectile is placed to be launched.
  • Each projectile consists of a shell that contains the material to be launched, of a charge of launch powders made up- together with the shell in a wrapping that is normally of paper.
  • the launch of a projectile occurs by igniting the charge of launch powders that explode and thus supply the propulsive force for the shell; ignition of the launch powders occurs by means of electric igniters actuated by a command.
  • Each electric igniter comprises a tubular body at an end of which a head for ignition by incandescence is provided that is supplied with a pair of wires that extends inside and beyond the tubular body for a suitable length to reach a power plant provided with pairs of connecting terminals.
  • the ignition head of the electric igniter is generally inserted directly into the charge of launch powders of a projectile during assembly of- the latter or it is connected to a fuse that, in turn, is inserted into the charge of launch powders already during assembly of the projectile.
  • the ignition head ignites, directly igniting in the first case the launch powders and in the second case the fuse, which in turn ignites the latter.
  • Known launch devices generally comprise a great number of launch tubes that are combined together, whether they are used for example to remove birds from a zone in which they cannot be or to launch fireworks .
  • An example of zones in which birds cannot be, are airports because, as is known, if birds are accidentally sucked up inside the engines of aircraft, especially when the latter are subjected to maximum stress during the take-off phase, the engines may suddenly lose power and the aeroplane may risk having to abort the task or even risk falling to the ground.
  • the launch devices must be secure, both when they are used and when they are transported.
  • the preparation, positioning and activation of the launch devices require the intervention of a considerable number of operators who have to load the projectiles into the launch devices and connect the latter with the power plants, which are provided with terminals connecting each pair of wires to each electric igniter.
  • the power plant is, in turn, connected to a control apparatus that is manoeuvrable by an operator, by operating which the launches of the projectiles of each launch apparatus are actuated.
  • Actuation of the launch devices thus requires the drawing up and positioning of a large number of electric wires.
  • a first drawback is that when the launch devices are numerous to cover a vast operating zone from which it is necessary to remove birds, the mass of electric wires to handle and to arrange for the connections between the igniters and the power plants becomes significant and requires, as already said, the intervention or more than one operator assigned to this work: this adversely affects the total costs of use of the known launch devices.
  • Another drawback is that the launch devices are generally placed over long distances, reaching, in the case of take-off and landing runways of airports, several kilometres: the lengths of connecting wires are therefore proportionally great and their positioning requires fatiguing and repeated displacements of operators between the power plants and the different launch devices.
  • Another drawback is that if the number of wires necessary for the connections between the electric igniters and the control panels is high, and if the distances to be covered are significant, the cost of the igniters and of the wires becomes noticeable.
  • known launch devices are constructed, as said previously, with specific structural features, that are determined by the uses for which they are intended and are not able to launch projectiles that are different from those for which they were constructed.
  • a further drawback is that known launch devices do not enable it to be ascertained with certainty whether the launch of a projectile occurred correctly without proceeding to a direct inspection of the launch device, with serious danger for those performing this operation if a projectile has remained inside a launch device although the launch command has been given.
  • Another drawback is that by using known launch devices, it is very difficult to make planned launch sequences because in order to obtain these sequences it is necessary to set up power plants equipped with a large number of pairs of terminals for attaching all the terminal ends of numerous pairs of wires that come from all the igniters of all the launch devices used.
  • Another drawback is that in order to be able to be launched with known launch devices, the projectiles have to be prepared in a complete manner and already ready to be launched, i.e.
  • the object of the invention is to improve the state of the art.
  • An object of the invention is to make a launch apparatus that is usable for many uses without requiring any structural adaptation.
  • Another object of the invention is to make a launch apparatus that does not require connections by means of wires between projectiles and power plants.
  • a further object of the invention is to make a launch apparatus that enables launches to be made according to preset or presettable sequences.
  • a further object of the invention is to make a launch apparatus that enables it to be ascertained easily and without risk to operators whether the launch of a projectile has occurred correctly.
  • Another object of the invention is to make a launch apparatus that enables it to be remotely actuated, individually or with other models of the same type, using a single control unit, e.g. a computer.
  • Another object of the invention is to make a launch apparatus that can operate with projectiles that are actuatable only at the moment of the launch, whilst during their assembly and transport, they can remain substantially inert, considerably increasing the safety of operators.
  • an apparatus comprising: loading means for loading projectiles for civilian use, in particular for fireworks displays, to be launched by propellant means, characterised in that communicating with said loading means there is provided housing means for receiving capsule means containing actuating means of said propellant means.
  • the apparatus thus enables projectiles intended for civilian and different use to be launched with a single apparatus following, when required, preset launch sequences; the apparatus furthermore enables projectiles to be launched for civilian use to be transported that are substantially inert until the moment of launch.
  • the apparatus can furthermore be remote-controlled without cable connections having to be made by electric igniters and connecting power plants.
  • Figure 1 is a schematic longitudinal section view of an apparatus for launching projectiles for civilian use, taken along a plane I-I in Figure 4;
  • Figure 2 is a fragmentary view on- an enlarged scale of a detail of the launch apparatus
  • Figure 3 is a fragmentary schematic view of an enlarged detail of the launch apparatus in Figure 1 and in which signal emitting means are visible;
  • Figure 4 is a schematic view from above of the launch apparatus in Figure 1;
  • Figure 5 is a schematic longitudinal section view of a launch apparatus, taken along a plane I-I of Figure 4 in a second possible embodiment;
  • Figure 6 shows a fragmentary view of a launch apparatus placed in a tilted position
  • Figure 7 is a perspective view of a launch apparatus in a third possible embodiment
  • Figure 8 is a fragmentary view of a vertical section of the launch device in Figure 7, taken along a plane VIII-VIII;
  • Figure 9 is a vertical section view of a fourth possible embodiment of a launch apparatus.
  • FIG 10 is fragmentary transverse section view of an upper portion of the launch apparatus in Figure 9, taken along a plane X-X.
  • 1 indicates a launch apparatus that comprises a series of mortar bodies 6 for containing projectiles 2 to be launched.
  • the latter comprise a shell 308b and a base in which a volume 308a of launch powder is contained.
  • the mortar bodies 6 define an internal chamber 7 that has smooth walls and which are normally parallel to one another, a bottom 307 and an opposite open first end 107; in the proximity of the bottom 307 there is arranged an explosive capsule 9, known hereinafter as "capsule” 9 for the sake of brevity, which is housed in a hollow seat 40 that, in the embodiment of the launch apparatus illustrated in Figures 1 to 6, is obtained in the bottom 307, in a substantially centred position thereof.
  • the capsule 9 is actuatable by means of a striker member 13 that is mounted slidable on the inside of a solenoid 114; the latter is positioned axially aligned on the corresponding hollow seat 40 and is supported in this position, as will be better disclosed below.
  • an additional layer 308 of launch powder can be placed between the explosive capsule 9 and the projectile 2.
  • the solenoid 114 is actuatable by means of signals coming from a wireless emitter 309 and received by a command element 15 comprising, for example, an electronic card 115 connected to the latter; as visible in Figure 3, the emitter 309 can be controlled by a device that is in itself known, such as, for example, computer “C” or a camera “T” or also a photocell “F”, to emit signals that are received by the solenoid 114, which creates a magnetic field such as to move the striker member 13 to the capsule 9 to hit it and make it explode.
  • the striker member 13 when it moves towards the capsule 9 to hit it, axially crosses the solenoid 114 and is contrasted in its movement by an elastic return spring 313 that is interposed between the solenoid 114 and an abutment 314 mounted on the striker member 13; in the case illustrated, the spring 313 is wound around an end of the striker member 13, turned in an opposite direction to the capsule 9.
  • the launch apparatus 1 may be fitted, together with other identical parts, as shown in Figure 1, on a box frame 3 that has a substantially parallelepipedon shape and which has side walls 22 and a lower wall 23 and is closed at the top by a plate 30.
  • an intermediate wall 103 on which all the solenoids 114 are constrained, which are in turn connected to the electronic card 115; the intermediate wall 103 has passage openings 24 at each of the latter to enable the passage of each respective striker member 13.
  • Each mortar body 6 is constrained on the plate 30 with constraining means that comprises an opening 4 obtained in the plate 30 and equipped, for example, with an internal thread 5 and with a further thread obtained perimeterally on the outside of the mortar body 6 at the bottom 307 in such a way as to make the latter screwable into the respective opening 4 and. connected to the plate 30.
  • the constraint means may comprise a bayonet fitting, not illustrated in the drawings because known to those skilled in the art, interposed between the bottom 307 and the respective opening 4 in which a mortar body 6 has to be inserted and fixed.
  • the constraint means may comprise a snap fitting, placed between the bottom 307 and the respective opening 4.
  • a flat element 10 designed to run on a lower face 118 of the plate 30 facing the intermediate wall 103 and supported on the latter by brackets 25.
  • This flat element 10 is slidable in relation to the plate 30 and is provided with small through holes 26 and with larger through holes 126 that are alternatively alignable or misalignable with the hollow seats 40, in such a way as to open or close them partially, or if required, completely: in this case none of the small through holes 26 or large through holes 126 is aligned on the hollow seats 40.
  • the small holes 26 have smaller dimensions than the dimensions of the capsules 9 whereas the large holes 126 have greater dimensions than those of the capsules 9.
  • each bottom 307 forms a raised shank 8 that extends to the respective opening 4; the shank 8 is threaded on the perimeter with a thread 105 that is screwable into the latter and is axially crossed by a passage 211.
  • the seat 40 in which the capsule 9 is placed is obtained inside the shank 8, coaxially with the passage 211.
  • Each first end 107 is closable after a projectile 2 to be launched has been inserted through the first end 107 into the respective mortar body 6, with a removable cap 28 that is dragged away when the projectile 2 is launched.
  • each solenoid 114 is connected to a capacitor 29, which is in turn connected to the electronic card 115; by means of the latter nearly all the capacitors 29 are loaded and actuated in such a way as to supply the pulses to the solenoids 114 according to set sequences, for example from a launch execution programme installed in a computer "C".
  • the shank 8 that extends from the bottom 307 can be screwed into a seat 41 obtained inside a tilted base 321 that protrudes above the plate 30.
  • the opening 4 is obtained directly in the plate 30.
  • the opening 4 has a third open end 104 and a fourth open end 204, opposite said third end 104.
  • a mortar body 6 is fittable and fixable, for example by means of a thread 5.
  • the mortar body 6 is equipped, on the face of the bottom 307 facing the opening 4, with the shank 8 threaded externally to screw into the third end 104 of the opening 4 by means of the thread 5.
  • the plate 30 is mounted slidably in the frame 3 on suitable guides 150 and in it there is obtained, as an extension of the opening 4, but on the opposite side to the plate 30, substantially corresponding coaxially with the opening 4, a hollow seat 40 inside which the capsule 9 is insertable.
  • the flat element 10 is slidably mounted that, also in this case, can slide in substantial contact with the lower face 118 of the plate 30 and which at the hollow seat 40, is traversed by a large through hole 126 that, when the flat element 10 is completely inserted into the frame 3, is substantially aligned to the hollow seat 40, or slightly out of alignment in relation to the latter.
  • the plate 30, like the flat element 10 is slidable along the frame 3: when both are slid to the outside of the frame 3 to be extracted, the hollow seat 40 is made accessible from outside to load or substitute the capsule 9.
  • the flat element 10 is in turn slidable in relation to the plate 30 and, as said before, when it is inserted completely into the frame 3, the hollow seat 40 is slightly misaligned in relation to the large through hole 126: in this way, a part of the perimeter edge that delimits it, provides a support and retaining lip for the base of the capsule 9, albeit without completely closing the passage between the hollow seat 40 and the large hole 126, so as to enable the striker member 13, when it is actuated, to reach the capsule 9.
  • the element 20 comprises a key 16 that is fittable in corresponding holes 17 and 19 obtained respectively in the plate 30 of the frame 3 and in the flat element 10, when the holes 17 and 19 are in a configuration aligned vertically on one another.
  • the launch apparatus 1 comprises a box-shaped frame 3, which is formed by an upper wall 3a traversed by at least a window 203, by side walls 22 and by a lower wall 23.
  • the upper wall 3a is removable or simply openable as indicated by the arrow A to access the inside of the box frame 3.
  • an intermediate wall 103 which is parallel to the upper wall 3a and which supports, substantially centred, a vertical shaft 206 rotatably driven by a motor unit 207, the latter also is supported on the intermediate wall 103, for example by means of brackets 208; the motor unit 207 is of the type with indexed rotation, according to angles of a preset amplitude.
  • the flat element 10 is affected by a series of large through holes 126 that are arranged according to a circular distribution that has a first radius of preset length; in the plate 30 corresponding hollow seats 40 are obtained, these also being arranged according to a circular distribution, having a second radius with a preset length and which is substantially the same as that of the first radius, in such a way as to be able to align the hollow seats 40 on the large through holes 126: both the latter and the hollow seats 40 are obtained spaced apart at equal distribution distances.
  • the intermediate wall 103 supports in an eccentric position, and more precisely at a vertical position of the large through holes 126 and of the hollow seats 40, a striker member 13 that is actuated with a solenoid 114; this is actuatable by means of a control element, indicated by 15, which pulses reach from an external wireless-type emitting device 309 which can be connected, for example to a camera, or to a remote control, or via cable to a switch or to other devices that are not shown because they are known to those skilled in the art.
  • each hollow seat 40 a capsule 9 containing explosive material is insertable; on the top end of each hollow seat 40 there is defined an opening 4 equipped with internal threading 5 in which a shank 8 is screwable that extends raised from a bottom 307 of a corresponding mortar body 6, which defines, inside itself, an internal cavity 7 that has, as in the previously disclosed embodiments, smooth walls and which is suitable for receiving a projectile 2 to launch that is loaded through a first open end 107 of the mortar body 6.
  • the shank 8 is axially traversed by a gap 221 that connects the internal cavity 7 to the respective hollow seat 40.
  • the flat element 10 being supported on the plate 30, for example by means of bracket elements 230, is rotatingly driven simultaneously to the latter by the motor unit 207: nevertheless, the flat element 10 is also rotatable by a few degrees in relation to the plate 30, as shown in detail in figure 3, so that the edges of the hollow seats 40 of the flat element 10 provide the capsules 9 with a sort of segment support lip 222 to prevent the latter falling out of the respective hollow seats 40.
  • the operation of the launch apparatus in the embodiment illustrated in Figures 1 to 6 is as follows: one or more launch apparatuses 1 mounted on respective support frames 3 are located in preset zones to carry out the launches.
  • the projectiles 2 to be launched can be conveyed before the launches with relative security, it not being necessary to make assemble them providing conventional electric igniters already mounted inside them: in fact, the explosive action is provided by the caps 9 only when they are hit by the respective striker members 13.
  • an operator rotates the plate 30 in such a way as to be able to access the inside of the box frame 3; on the plate 30 a preset number of mortar bodies 6 is constrained, for example by screwing the shanks 8 into the respective openings 4.
  • the operator slides the flat element 10 along the face 118, until the larger through holes 126 of the latter are aligned on the first hollow seats 40: in this position, the operator can insert the explosive capsules 9 into them.
  • the operator after completing loading of the capsules 9 into the respective first hollow seats 40, recloses the plate 30 and, in order to arrange the launch apparatuses 1 for launching, slides the flat element 10 by for example acting on pickup handles provided precisely for the purpose protruding from the latter, in such a way as to align only the small through holes 26 on the first hollow seats 40.
  • the capsules 9 are retained inside the respective first hollow seats 40 as, the small through seats 26 being smaller than the capsules 9, the latter rest on the edges of the small through holes 26 without traversing them; simultaneously, the passage remains open for the striker members 13 through the small though holes 26.
  • each mortar body 6 the corresponding projectile 2 to be launched through the first end 107, then reclosing it with the cover 28.
  • the operator can then move away from the launch apparatuses 1 that are ready to launch the projectiles 2 and goes to a safety zone far from them, in which a control device is arranged, for example a computer "C”, and activates therewith the remote signal emitter 309; these signals are received by the electronic card 115 and from the latter they are transmitted to the single solenoids 114.
  • a control device is arranged, for example a computer "C”
  • the striker members 13 are made to perform a capsule 9 percussion stroke by the magnetic fields generated by the solenoids 114; the percussion stroke occurs by overcoming the contrast action of the contrast springs 313.
  • the remote signal emitter 309 in another form of use of the launch apparatus 1, for example for removing birds, can be a camera "T" which, when it detects the presence of birds in a zone to be protected, automatically actuates the emitter 309, which in turn actuates one or more of the solenoids 114, actuating the corresponding striker members 13 and causing the launch of one or more projectiles 2.
  • the camera "T” can be replaced by a photocell "F" or by another device that is in itself known.
  • the capsules 9 are loaded into the respective hollow seats 40 by extracting from the frame 3 both the plate 30 and the flat element 10.
  • the flat element 10 is slid in relation to the plate 30 in such a way as to reciprocally misalign the hollow seats 40 and the large through holes 126 so as to create with the flat element 10 a sort of bottom suitable for supporting the caps 9 inside the respective hollow seats 40.
  • both the plate and the flat element 10 are reinserted inside the frame 3, maintaining the misalignment until the hollow seats 40 are aligned on the respective striker members 13.
  • the plate 30 and the flat element 10 are locked in this position by reinserting the key 16 in the coaxially aligned holes 17 and 19.
  • a projectile 2 is then placed in the containing chamber 7 and when the solenoid 114 is actuated by the control element 15, i.e. by the electronic card 115, for example by a pulse coming from a bird-detection element, the striker member 13 hits the capsule 9, making it explode.
  • the propulsive force produced by the explosion of the capsule 9 is projected through the gap 221 and primes the launch powder usually contained in a projectile 2, igniting it and activating the thrust that launches the projectile 2 towards the sky.
  • the projectile 2 is prepared in such a way as to in turn explode when it reaches a preset height, producing, for example, a loud noise that frightens the birds that are in the zone surrounding the launch device 1, scattering them.
  • the launch powder layer is added to the internal chamber 7 between the projectile 2 and the bottom 307; when the capsule 9 is exploded, this ignites the layer 308 of launch powder, which, by exploding, provides an increase in propulsive force beyond what is provided by the launch powder present in a projectile 2 to be launched.
  • each mortar body 6 is loaded with projectiles 2 by inserting them into the internal chambers 7 through the first end 107; the capsules 9 are loaded by opening the top wall 30a and unscrewing the threaded knob 223; this frees access to the plate 30 and to the flat element 10 supported on it; both are then extracted from the box frame 3 and if necessary the capsules 9 that were already previously fired are first unloaded and subsequently the new capsules 9 are inserted inside the respective hollow seats 40; when loading is complete, the plate 30, which has a circular shape, is rotated in relation to the flat element 10 by an angle, of a few degrees such that the edges of the large through holes 126 of the flat element 10 provide a sort of base support plane 222 that retains the capsules 9 inside the respective hollow seats 40.
  • the flat element 10 and the plate 30 are refitted on the shaft 206 and the latter is rotationally locked on the shaft 206 by tightening the screw knob 223.
  • the plate 30 and the flat element 10 are connected together by brackets 230 that enable reciprocal angular rotations of a few degrees .
  • the upper closing wall 3a is then reclosed that has the window 203 that is vertically aligned both on one of the mortar bodies 6 and on the striker member 13.
  • the signal is sent from the latter that actuates the solenoid 114, which, in turn, actuates the striker member 13 that hits the capsule 9, making it explode and causing the launch of the projectile 2 through the through opening 203 towards the sky, as disclosed for the previous embodiments of the launch apparatus.
  • the motor unit 207 which is of the type with controlled motion, for example indexed rotating, this makes the plate 30 rotate by an angle suitable for carrying a new mortar body 6 that is adjacent or at least different from the one located at the opening 203 and at the striker member 13, from which the preceding projectile was launched.
  • a further pulse sent to the control means 15 causes the launch of a further projectile 2; this sequence is repeated for all the projectiles contained in the mortar bodies 6.
  • the rotation steps of the motor unit 207 are programmable and it is therefore possible to preset the sequence of launches of projectiles 2, according to specific needs.
  • the mortar bodies 6 are devoid of covers 28, the upper wall 3a protects from inclement weather the projectiles 2 loaded inside the internal chambers 7 of the respective mortar bodies 6, except for the projectile 2 that is aligned on the through opening 203.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)

Abstract

L'invention concerne un appareil comprenant : un moyen de chargement (6) permettant le chargement de projectiles (2) à usage civil, en particulier de feux d'artifice, destinés à être lancés par un moyen propulsif (308a ; 308), un moyen de logement (40) communiquant avec ledit moyen de chargement (6) étant prévu pour recevoir un moyen d'actionnement (9) contenant des capsules dudit moyen propulsif (308a ; 308). Le moyen d'actionnement (9) peut être actionné au moyen d'une tige de percuteur (13) fonctionnant à l'aide d'un solénoïde commandé sans fil (114).
PCT/IB2005/001219 2004-05-04 2005-05-04 Appareil de lancement WO2005106379A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP05735735A EP1756510A1 (fr) 2004-05-04 2005-05-04 Appareil de lancement
JP2007512563A JP2007536496A (ja) 2004-05-04 2005-05-04 発射装置
CA002564823A CA2564823A1 (fr) 2004-05-04 2005-05-04 Appareil de lancement
US11/579,488 US20070214948A1 (en) 2004-05-04 2005-05-04 Launch Apparatus
AU2005238724A AU2005238724A1 (en) 2004-05-04 2005-05-04 Launch apparatus

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
ITMO2004A000105 2004-05-04
ITMO20040105 ITMO20040105A1 (it) 2004-05-04 2004-05-04 Apparato di lancio
ITMO20050107 ITMO20050107A1 (it) 2005-05-02 2005-05-02 Apparato di lancio.
ITMO2005A000107 2005-05-02

Publications (1)

Publication Number Publication Date
WO2005106379A1 true WO2005106379A1 (fr) 2005-11-10

Family

ID=34968111

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2005/001219 WO2005106379A1 (fr) 2004-05-04 2005-05-04 Appareil de lancement

Country Status (6)

Country Link
US (1) US20070214948A1 (fr)
EP (1) EP1756510A1 (fr)
JP (1) JP2007536496A (fr)
AU (1) AU2005238724A1 (fr)
CA (1) CA2564823A1 (fr)
WO (1) WO2005106379A1 (fr)

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CN103115530A (zh) * 2013-03-15 2013-05-22 南通天地通网络工程有限公司 无线遥控的弹射式电子礼花爆竹
DE102020119231A1 (de) 2020-07-21 2022-01-27 Krauss-Maffei Wegmann Gmbh & Co. Kg Militärische Wurfanlage

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US9228803B2 (en) * 2013-05-20 2016-01-05 Csi-Penn Arms, Llc Universal tube launched munitions system
KR101689950B1 (ko) * 2014-02-13 2016-12-26 박종배 불꽃놀이 보조기구
US9429398B2 (en) * 2014-05-21 2016-08-30 Universal City Studios Llc Optical tracking for controlling pyrotechnic show elements
DE102016000122B4 (de) 2016-01-08 2022-03-03 Drew Defense GmbH Vorrichtung zur Gefechtssimulation
US10060689B2 (en) * 2016-01-11 2018-08-28 Martin Grier Firearm system and method
IT201800003551A1 (it) * 2018-03-14 2019-09-14 Monetti S R L Sistema di accoppiamento e trasmissione di corrente per un accenditore elettrico, in particolare per fuochi d’artificio di tipo single shot.
CN109696081A (zh) * 2019-01-11 2019-04-30 中国人民解放军66329部队 一种基于电磁击发的集束式自动化信号弹发射器
CN115280095B (zh) 2020-03-11 2023-01-31 斯瑞特利特效有限责任公司 烟火发射装置和系统

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CN103115530A (zh) * 2013-03-15 2013-05-22 南通天地通网络工程有限公司 无线遥控的弹射式电子礼花爆竹
DE102020119231A1 (de) 2020-07-21 2022-01-27 Krauss-Maffei Wegmann Gmbh & Co. Kg Militärische Wurfanlage
DE102020119231B4 (de) 2020-07-21 2022-07-21 Krauss-Maffei Wegmann Gmbh & Co. Kg Militärische Wurfanlage

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US20070214948A1 (en) 2007-09-20
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AU2005238724A1 (en) 2005-11-10
EP1756510A1 (fr) 2007-02-28

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