• 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:
    The hollow charge comprises: - a confinement envelope (1); an explosive charge (2), placed in the envelope in the confinement envelope (1), and having a surface (2A) of Vee; - a detonator (3), placed behind the explosive charge (2); and a layer of projection material (4) placed in front of the V e surface (2A) of the explosive charge (2). A pyrogenic material layer (10) is used to heat the projection coating (4). This pyrogenic material may also be mixed with the explosive charge (2). Application to the separation of two stages of an aeronautical craft, or the neutralization of the latter.
    公开号:FR3017205A1
    申请号:FR1450855
    申请日:2014-02-04
    公开日:2015-08-07
    发明作者:Felipe Medina；Luc Preaud
    申请人:Astrium SAS；
    IPC主号:
    专利说明:

    [0001] FIELD LOAD AND APPLICATION FOR SEPARATING TWO STAGES OF AERONAUTICAL EQUIPMENT OR ITS NEUTRALIZATION DESCRIPTION FIELD OF THE INVENTION The invention relates to hollow charges, in general, for all applications in the industry, but in particular the aeronautics. PRIOR ART AND THE PROBLEM POSED The hollow charges constitute a technology used beforehand to constitute ammunition, in particular, intended to pierce armor. However, they can find many applications in the industry, for example to cut cables, or damage a link part, in order to separate two sets beforehand. Referring to Figure 1, a conventional hollow charge mainly comprises a shell 1 of hollow form, an explosive charge 2, placed inside the casing 1, a detonator 3, placed on a rear surface 2A of the explosive charge , and a metal coating 4, placed on a front surface 2B of the explosive charge. It is specified that the metal coating 4 is preferably copper. With reference to FIG. 2, the operation of the hollow charge is as follows. The detonator 3 is struck by a projected plate, as indicated by the arrow 5. The explosive charge 2 is initiated and returns to the detonation regime. A wave then propagates throughout the explosive mass of the explosive charge 2. Due to the hollow V-shape of the surface 2B of FIG. 1, a concentration of energy occurs in the axis of the hollow charge and in particular at the bottom of the V of the surface 2B of the explosive charge 2. The coating 4 is thus propelled and concentrated on the axis of the hollow charge to form a jet 6. The speed of propagation of the jet 6 is expressed by the formula next: V = 2.D.sin (a / 2), where V is the speed of the jet, and D is the velocity of the detonation. It is conceivable that such a device can have many applications in the industry, including military weapons, to drill armor. The object of the invention is to provide an improved type of hollow charge for multiple applications, but in particular aeronautics, especially for the separation of two stages of an aeronautical vehicle, such as a rocket and its launch stages. OBJECT OF THE INVENTION A first object of the invention is therefore a hollow charge comprising: a confinement envelope; an explosive charge, placed in the confinement envelope and having a concave surface in Vé; a coating of projection material, placed in front of the concave surface V of the explosive charge. According to the invention, pyrogenic material, that is to say heat generator, is used to heat the coating of projection material.
    [0002] In a first embodiment, the pyrogenic material is placed on the concave surface V e of the explosive charge, the coating of projection material being placed on the pyrogenic material. In a second embodiment of the invention, the pyrogenic material is mixed in the explosive charge.
    [0003] A second main object of the invention is a device for separating two stages of an aeronautical craft, the two stages being interconnected by a connecting part. According to the invention, use is made of a hollow charge, as defined above, of circular shape, placed around the connecting part, the pyrogenic material being placed facing an internal surface of this connecting part. A third main object is a device for neutralizing part of an aeronautical machine. According to the invention, a hollow charge is used as defined above, the pyrogenic material being placed facing an inner surface of the aeronautical machine. Two possibilities are envisaged, one being to use a circular crown of this hollow charge placed against the inner surface of a part of the aeronautical apparatus to be destroyed, while a second possibility is to use a hollow charge of rectilinear form, the latter being placed against an inner surface of the part of the aeronautical device to neutralize, that is to say destroy, this longitudinally, with respect to the axis of the aeronautical machine. List of Figures The invention and its various technical features will be better understood on reading the following description, accompanied by several figures, respectively showing: - Figure 1, in section, a hollow charge according to the prior art, before operation; - Figure 2, in section, the same hollow charge according to the prior art, but during operation; - Figure 3, in section, a hollow charge according to the invention, in a first embodiment; - Figure 4, three types of application of the hollow charge according to the invention; FIGS. 5A to 5C, three diagrams representing the application of the hollow charge according to the invention for the separation of two parts of an aeronautical launcher; and FIGS. 6A and 6C, diagrams relating to the operation of this application.
    [0004] DETAILED DESCRIPTION OF THE INVENTION With reference to FIG. 3, the hollow charge according to the invention comprises, like that of the prior art, an envelope 1, in which an explosive charge 2 is placed, always with a concave shape in V shape. , revolution or elongated, and covered with a projection coating 4 which is metallic. Of course, a detonator 3 is placed behind the explosive charge 2 to be able to detonate the hollow charge. According to the invention, in the first embodiment according to the invention, a pyrogenic material layer 10 is placed on the V-shaped surface 2B of the explosive charge 2, and behind the projection coating 4. In other words, the pyrogenic material 10 is sandwiched between the spray coating 4 and the explosive charge 2. This pyrogenic material 10, that is to say heat generator, is preferably thermite, or nanothermites. During the detonation regime of the explosive charge 2 by triggering the detonator 3, a propagation wave propagates throughout the explosive charge 2 and reaches the concave surface Ve 2B. The pyrogenic material layer 10, which then begins to be peeled off and heated very rapidly. The jet 6, described in FIG. 2, is then formed, with an amalgam of pyrogenic material 10 and the projection coating 4. Under the action of the shock wave, there is therefore a gradual raising of the entire pyrogenic material 10 and projection coating 2, with a very rapid heating and melting of this amalgam. To the mechanical projection effect of jet 6 (FIG. 2), a thermal effect is thus added, making it possible to melt the target more easily.
    [0005] The choice of the projection coating 4 is preferably made according to the target and the density thereof. We can define this choice by the following formula: P = L .. 117i / pc, where ID, is the density of the material of the projection coating, pc is the density of the target, L is the length of the jet, and P being the penetration length of the jet into the target. The choice of the nanothermites or thermites constituting the pyrogenic material 10 is a function of the material of the coating of projection 4, as well as the travel time of the jet, which is strongly a function of the density of the coating of projection material 4 and the explosive charge 2. The objective is to reach a maximum of temperatures, at the moment of impact of the jet, on the target. With reference to FIG. 4, the front of an aeronautical machine is represented. On the wall 20 thereof, are represented three dark portions 22, 24 and 26. The parts 22 and 24 are parts of revolution bonded to the inner surface of the wall 20 of the aeronautical machine. They each consist of a ring comprising a hollow charge as described above. The concave surface V e, covered with the projection coating, is directed against this inner surface of the wall 20 of the aeronautical machine. The ring 22 is placed on the cylindrical part of the aeronautical machine, where it is decided to practice an intrusion to neutralize, that is to say destroy the craft.
    [0006] The ring 24 is placed inside the front part of the aeronautical machine, on an inner surface which is not cylindrical, but of conical or ogival shape, for example the bottom of a tank. The coating of projection material is always directed against the inner surface of the wall 20 of this aeronautical machine.
    [0007] Finally, the portion 26 is an elongate portion consisting of a bar formed of hollow charge, as described above, the projection coating being directed also against the inner surface of the wall 20 of the aeronautical machine. These different crowns and bars are placed in front of the part that one wishes to destroy and / or neutralize. FIG. 5A represents the stages 8 of an aeronautical launcher, equipped with several thrusters 12A and 12B, placed at the base of the stages 8 of the aeronautical launch vehicle. FIG. 5B shows a detail of this assembly, in particular at the level of the upper part of the thrusters 12A and 12B. Indeed, it can be seen that the central thruster 12B is surmounted by the stages 8. This connection is effected by a connecting ring 13, which is shown separately from FIG. 5C. The operation of the separation device according to the invention is illustrated in FIG. 6A, in detailed section, at the level of the connecting ring 13. The latter comprises, on its inner wall 14, a hollow charge crown 15. The latter consists mainly of the envelope 1, ring and open on the side of its outer diameter. It is filled by the explosive charge 2 containing or being covered by the pyrogenic material and by the projection coating. Referring to Figure 6B, the firing of the hollow charge 15 causes a sudden heating, until the melting of the parts of the connecting ring 13, lying opposite. The heating of this portion of the connecting ring 13, to its melting point, causes the separation of this ring 13, in two parts. These two parts are shown in Figure 6C, an upper portion 13A and a lower portion 13B. It will be understood in this FIG. 6C that the hollow charge 15 has been previously fixed by one of the edges 1A of the casing 1, on the wall 14 of the connecting ring 13. Therefore, after the separation of the two lower parts 13B and upper 13A of the connecting ring 13, the hollow charge 15 remains integral with one of the two parts, in this case the lower part 13B of the connecting ring 13. In fact, in the application to an aeronautical launcher it is chosen that the hollow charge 15 remains attached to the lower stage, which does not continue the flight of the aeronautical craft and falls back to earth. This prevents the structure continuing the flight is heated for longer than necessary. In two different embodiments of the device according to the invention, the connecting ring 13 may be a separate piece, that is to say not part of either a first element or a second element, which must be separated, namely the stages 8 and the central thruster 12B. This connecting ring 13 is then welded, by these two ends, to each of these two elements. In a second embodiment, it is provided that the connecting ring 13 is an integral part of the wall of one of the two elements, preferably the lower element, namely the central thruster 12B. In other words, in this case, the connecting ring 13 is the extension of the outer wall of this central thruster 12B. Remote pyrotechnic trip means are provided to initiate the explosion of the hollow charge 15.
    权利要求:
    Claims (7)
    [0001]
    CLAIMS1) A hollow charge (15) comprising: - a confinement envelope (1); an explosive charge (2), placed in the confinement envelope (1), having a surface (2B) of V e; - a detonator (3), placed behind the explosive charge (2); and a projection coating (4) placed in front of the concave surface (2B) of the explosive charge (2), characterized in that a pyrogenic material (10) is used for heating the projection coating (4) .
    [0002]
    2) Load (15) hollow according to claim 1, characterized in that the pyrogenic material (10) is placed on the concave surface V e (2B) of the explosive charge (2), the projection coating (4) being placed on the pyrogenic material (10).
    [0003]
    3) charge (15) hollow according to claim 1, characterized in that the pyrogenic material is mixed in the explosive charge (2).
    [0004]
    4) Device for separating two stages of an aeronautical machine (10, 12B) interconnected by a connecting part (13), characterized in that a hollow charge (15) according to any one of the claims is used. 1 to 3, of circular shape and placed against the connecting portion (13), the projection material (4) being placed facing an inner surface (14) of the connecting portion (13).
    [0005]
    5) Device for neutralizing a part of a spacecraft, characterized in that a hollow charge (15) according to one of claims 1 to 3 is used, the material being placed against an inner surface of the wall (20) of the aeronautical craft.
    [0006]
    6) Neutralization device according to claim 5, characterized in that the hollow charge (22, 24) is of revolution and surrounds the aeronautical machine (20).
    [0007]
    7) Neutralization device according to claim 5, characterized in that the hollow charge (26) is elongate and is placed on a generatrix of the inner surface of the wall (20) of the aeronautical machine.
    类似技术:
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    同族专利:
    公开号 | 公开日
    JP2017504779A|2017-02-09|
    FR3017205B1|2018-08-31|
    ES2714354T3|2019-05-28|
    US10288391B2|2019-05-14|
    US20170010077A1|2017-01-12|
    JP6598787B2|2019-10-30|
    EP3102906B1|2018-12-05|
    EP3102906A1|2016-12-14|
    WO2015117945A1|2015-08-13|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2972948A|1952-09-16|1961-02-28|Raymond H Kray|Shaped charge projectile|
    US3244104A|1964-03-25|1966-04-05|Jimmie R Mills|Missile separating device|
    US4649824A|1985-06-27|1987-03-17|The United States Of America As Represented By The Secretary Of The Navy|Apparatus for aerospace vehicle separation events using a linear shaped charge|
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    US20110139505A1|2009-12-16|2011-06-16|Schlumberger Technology Corporation|Shaped charge|WO2017037246A1|2015-09-03|2017-03-09|Airbus Safran Launchers Sas|Method for the linear separation and connection of two elements|
    CN109050990A|2018-08-31|2018-12-21|上海宇航系统工程研究所|A kind of repeatable aircraft bindiny mechanism|
    US10281252B2|2014-12-15|2019-05-07|Haim Korach|Launcher redundant tank mass shedding system|US3025794A|1957-05-15|1962-03-20|Schlumberger Well Surv Corp|Perforating apparatus|
    US3721192A|1969-03-19|1973-03-20|Us Navy|Shaped charge|
    JP2789959B2|1992-09-17|1998-08-27|日産自動車株式会社|Nose fairing device for rocket|
    US7393423B2|2001-08-08|2008-07-01|Geodynamics, Inc.|Use of aluminum in perforating and stimulating a subterranean formation and other engineering applications|
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    US8443731B1|2009-07-27|2013-05-21|Alliant Techsystems Inc.|Reactive material enhanced projectiles, devices for generating reactive material enhanced projectiles and related methods|
    US8685187B2|2009-12-23|2014-04-01|Schlumberger Technology Corporation|Perforating devices utilizing thermite charges in well perforation and downhole fracing|
    GB201012716D0|2010-07-29|2010-09-15|Qinetiq Ltd|Improvements in and relating to oil well perforators|FR3063281B1|2017-02-28|2019-04-26|Airbus Safran Launchers Sas|METHOD AND DEVICE FOR LINKING AND LINEAR SEPARATING TWO GLUE ELEMENTS|
    FR3085359B1|2018-08-31|2020-11-27|Arianegroup Sas|SEPARATION-CONTROLLED LOCALIZED LINK DEVICE INCLUDING A MULTIDIRECTIONAL LINK LAYER|
    US10683735B1|2019-05-01|2020-06-16|The United States Of America As Represented By The Secretary Of The Navy|Particulate-filled adaptive capsulecharge|
    法律状态:
    2016-02-29| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-28| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-26| PLFP| Fee payment|Year of fee payment: 5 |
    2018-05-11| CD| Change of name or company name|Owner name: ARIANEGROUP SAS, FR Effective date: 20180410 |
    2018-05-11| CA| Change of address|Effective date: 20180410 |
    2018-05-25| TP| Transmission of property|Owner name: ARIANEGROUP SAS, FR Effective date: 20180424 |
    2018-06-01| CA| Change of address|Effective date: 20180425 |
    2018-06-01| CD| Change of name or company name|Owner name: ARIANEGROUP SAS, FR Effective date: 20180425 |
    2020-02-28| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-24| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-16| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450855|2014-02-04|
    FR1450855A|FR3017205B1|2014-02-04|2014-02-04|HOLLOW LOAD AND APPLICATION FOR THE SEPARATION OF TWO FLOORS FROM AN AERONAUTICAL EQUIPMENT OR ITS NEUTRALIZATION|FR1450855A| FR3017205B1|2014-02-04|2014-02-04|HOLLOW LOAD AND APPLICATION FOR THE SEPARATION OF TWO FLOORS FROM AN AERONAUTICAL EQUIPMENT OR ITS NEUTRALIZATION|
    EP15704735.8A| EP3102906B1|2014-02-04|2015-02-03|Hollow charge and use for separating two floors of an aeronautical vehicle or for the neutralization thereof|
    PCT/EP2015/052172| WO2015117945A1|2014-02-04|2015-02-03|Hollow charge and use for separating two floors of an aeronautical vehicle or for the neutralization thereof|
    JP2016548301A| JP6598787B2|2014-02-04|2015-02-03|Molded explosives and applications to separate or disable the two stages of aeronautical craft|
    ES15704735T| ES2714354T3|2014-02-04|2015-02-03|Hollow load and application for the separation of two bodies of an aeronautical device or its neutralization|
    US15/114,235| US10288391B2|2014-02-04|2015-02-03|Shaped charge and application for separating two stages of an aeronautical craft or neutralizing the same|
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