EP0246958B1 - Dispositif de séparation pyrotechnique de deux éléments - Google Patents

Dispositif de séparation pyrotechnique de deux éléments Download PDF

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Publication number
EP0246958B1
EP0246958B1 EP87401102A EP87401102A EP0246958B1 EP 0246958 B1 EP0246958 B1 EP 0246958B1 EP 87401102 A EP87401102 A EP 87401102A EP 87401102 A EP87401102 A EP 87401102A EP 0246958 B1 EP0246958 B1 EP 0246958B1
Authority
EP
European Patent Office
Prior art keywords
fixing means
cavity
portions
screw
plates
Prior art date
Legal status (The legal status 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 status listed.)
Expired - Lifetime
Application number
EP87401102A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0246958A1 (fr
Inventor
Hubert Vaillant De Guelis
Jean Langlois
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Group SAS
Original Assignee
Airbus Group SAS
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Filing date
Publication date
Application filed by Airbus Group SAS filed Critical Airbus Group SAS
Publication of EP0246958A1 publication Critical patent/EP0246958A1/fr
Application granted granted Critical
Publication of EP0246958B1 publication Critical patent/EP0246958B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • F42B15/38—Ring-shaped explosive elements for the separation of rocket parts

Definitions

  • the present invention relates to a device for the separation of two elements by means of a pyrotechnic charge usable in particular for separating elements in the form of panels in aeronautical or spacecraft.
  • the plates have, on their faces opposite to this housing, grooves defining a thinned zone, therefore weakened, along which the fracture must take place. These grooves are located at the central part of the plates, therefore towards the middle of the cavity in which is placed the deformable envelope which contains the detonating cords. When the detonating cord is ignited, this causes the deformable envelope to expand. This tends to take a circular configuration, which has the effect of deforming the central part of the two plates connecting the panels to be separated and causing rupture along the weakened sections. If such a device is satisfactory, it does however make it possible to break only relatively small sheet thicknesses, for example of the order of 1 mm.
  • the aim of the present invention is to remedy these drawbacks by proposing a device for pyrotechnic separation between two elements, for example elements in the form of panels, making it possible to cut a sheet metal thickness then large with the same charge of explosive.
  • document US-A 3,362,290 describes a device for pyrotechnic separation of two elements to be separated.
  • a pyrotechnic charge (40) is placed in a deformable envelope, itself placed in a cavity formed by the two projecting parts of a part attached to the first element and a second part attached to the second element and penetrating between the two projecting parts.
  • the two attachments are fixed to each other by means of a pin.
  • the separation is done by shearing of the pin which holds together the two parts constituting the connecting member between the elements to be separated.
  • document US-A 3,486,410 describes a pyrotechnic separation device for cutting a panel.
  • the pyrotechnic charge is maintained by a part fixed to the panel.
  • a weakening notch is provided on the panel.
  • document US-A 3,453,960 describes a device by linear explosive separation in which the rings to be separated themselves form the cavity or cavities containing the explosive elements. A thinned part is located on a wall constituting the cavity or cavities.
  • the invention relates to a pyrotechnic separation device between a first element and a second element using a pyrotechnic charge placed in a deformable envelope.
  • the first element comprises, according to the preamble of claim 1, two projecting parts which define between them a certain space, the device further comprising first fixing means for fixing the first element on the second via said projecting parts, thus defining a cavity in which said deformable casing is placed, this cavity having a first end close to said first fixing means and a second end remote from these first fixing means.
  • the first element has thinned parts which rupture when the pyrotechnic charge explodes and the thinned parts are located approximately at the second end of said cavity.
  • the envelope deforms and causes rupture at these thinned parts.
  • the deformable envelope acts at the time of the explosion on a relatively large lever arm corresponding to the length of the projecting parts: this makes it possible to have better efficiency, for a given load, than with a device such as that described in document US-A 3,698,281.
  • the weakened parts of the connection plates are located at the middle of these, so halfway between the plate fixings on the elements to be separated, and the lever arm is weaker.
  • the first fixing means comprise at least one screw passing through a hole made in each projection and a hole made in the second element, and a nut, the tightening of this nut on the screw causing the application of said projecting parts on the second element.
  • at least one stirrup a part of which at least partially surrounds the deformable envelope while being in contact with the latter and of which another part has a hole through which the screw can pass.
  • the detonating cord and the deformable envelope are of elongated shape and there are several fixing devices such as that which has just been described with screws, nuts and possibly stirrups, regularly distributed along the separation zone.
  • the projecting parts form an integral part of the first element and are connected to the rest of this element by thin connection zones which constitute said thinned parts.
  • the projecting parts consist of plates fixed to the first element by second fixing means, each of these plates having a thin zone which constitutes one of said thinned parts.
  • the first element 2 has two projecting parts 6 and 8, connected respectively to the body of element 2 by thinned zones 10 and 12.
  • the projecting parts 6 and 8 are not attached elements, but form an integral part of the body 2, the latter having been machined in order to produce the projecting parts 6 and 8.
  • the element 2, including the projecting parts 6 and 8 has, seen in section, a symmetry with respect to a plane P perpendicular to the plane of the figure, represented schematically in mixed lines.
  • the second element 4 has, along its edge closest to the first element 2, an enlarged part 14 whose width is slightly less than the width of the cavity 16 defined between the projecting parts 6 and 8.
  • the pyrotechnic charge takes the form of a detonating cord 18 placed inside a deformable envelope 20, the space between the detonating cord and the deformable envelope being filled with a flexible material 22, for example a sheath silicone rubber.
  • the sheath 22 performs several functions. First of all, it supports and maintains the detonating cord 18 in the correct position, that is to say substantially along the axis of symmetry of the envelope 20. In the particular case described here, this envelope has two parts flattened connected by semicircular parts, but it would not depart from the scope of the invention to give it another shape, for example oval. In addition, if silicone rubber is used, it behaves like a thermal insulator and protects the cord 18 from sudden temperature variations that the components of a spacecraft can undergo. Finally, the damping qualities of the rubber protect the detonating cord from the external shocks to which a spacecraft can be subjected at the time of departure or when firing certain propulsion engines.
  • the flexible sheath 22 also has the role of preventing the ignition of the second cord by shock waves due to the explosion of the first.
  • FIGS. 1 and 2 also show the means for fixing the first element 2 to the second element 4 by means of the projecting parts 6 and 8. It can be seen that the latter have, at their ends opposite to the thinned zones 10 and 12, holes 24 and 26 respectively, which can be aligned with a hole 28 formed in the enlarged part 14 of the element 4, these different holes being of the same diameter.
  • a screw 30 passes through the holes 24, 28 and 26 and it is held by a nut 32, the tightening of the nut 32 on the screw 30 having the effect of applying the projecting parts 6 and 8 of the first element on the part enlarged 14 of the second element.
  • a socket 34 can be placed inside the passage formed by the holes 24, 28 and 26, in order to better adjust the screw 30.
  • the fixing device can be completed using one or more stirrups such as 36, distributed from place to place along the deformable envelope 20.
  • stirrups such as 36
  • These can be made of any ductile material such as mild steel.
  • each stirrup 36 consists of an upper part 38 in the form of a semicircle extended by two branches 40 and 42.
  • the upper part 38 is in contact with the upper part of the deformable envelope 20 which is also in the shape of a semicircle.
  • the branches 40 and 42 they are substantially parallel and their spacing is such that they can be placed between the internal face of the projecting parts 6 and 8 and the external face of the widened part 14 of the element 4 (FIG. 1) .
  • the branches 40 and 42 of the stirrup 36 also have holes 44 and 46 respectively (FIG. 2) of the same diameter as the holes 24, 26 and 28, the screw 30 also passing through the holes 44 and 46.
  • the deformable envelope 20 is held against the internal faces of each protruding part 6 and 8, against the wall of the cavity 16 situated on the body side of the element 2 and, finally, against a boss 48 provided on the enlarged part 14 of element 4.
  • This arrangement means that the envelope 20 is held on all sides, but it would not go beyond the scope of the invention by using an equivalent assembly, provided that the envelope 20 is maintained so that the energy of the explosion causes tearing at the thinned zones 10 and 12.
  • the device which is the subject of the invention has interesting advantages, the main one of which is that it allows, for a given explosive mass, to cut a greater thickness of sheet metal than with the devices of the prior art.
  • Comparative tests were carried out with a device in accordance with that described in document US-A-3,698,281 and with a device in accordance with that of the invention, as illustrated in FIG. 1.
  • the thinned zones 10 and 12 can therefore have a relatively large thickness, which contributes to maintaining the rigidity of the assembly of the element 2.
  • the projecting parts can be an integral part of the first element, as in the embodiment described above, but can also be produced in the form of independent plates.
  • the plates are fixed to the first element by second fixing means, which can be identical to the first.
  • Each plate has an external face and an internal face, the internal faces of the plates constituting walls of the cavity containing the deformable envelope.
  • the plates have longitudinal grooves or grooves (that is to say substantially parallel to the detonating cord) formed from their external face and situated approximately at the level of the second end of the cavity.
  • the thinned parts are then formed by the zones located between the bottom of the grooves and the internal face of the plates.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Plates (AREA)
EP87401102A 1986-05-16 1987-05-15 Dispositif de séparation pyrotechnique de deux éléments Expired - Lifetime EP0246958B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8607063 1986-05-16
FR8607063A FR2598796B1 (fr) 1986-05-16 1986-05-16 Dispositif de separation pyrotechnique de deux elements

Publications (2)

Publication Number Publication Date
EP0246958A1 EP0246958A1 (fr) 1987-11-25
EP0246958B1 true EP0246958B1 (fr) 1990-08-16

Family

ID=9335324

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87401102A Expired - Lifetime EP0246958B1 (fr) 1986-05-16 1987-05-15 Dispositif de séparation pyrotechnique de deux éléments

Country Status (5)

Country Link
EP (1) EP0246958B1 (es)
DE (1) DE3764311D1 (es)
ES (1) ES2018281B3 (es)
FR (1) FR2598796B1 (es)
WO (1) WO1987007006A1 (es)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5109749A (en) * 1988-10-25 1992-05-05 Oea, Inc. Explosively actuated separable structure
FR2665951B1 (fr) * 1990-08-20 1992-11-13 Aerospatiale Systeme de liaison cassable permettant de separer des pieces au moyen d'une charge detonante.
US5390606A (en) * 1992-11-02 1995-02-21 Orbital Sciences Corporation Frangible joint separation system
US6125762A (en) * 1997-07-03 2000-10-03 The Ensign-Bickford Company Flat-form separation devices
FR2779223B1 (fr) 1998-06-02 2000-08-11 Aerospatiale Dispositif de decoupe de pieces non metalliques au moyen d'un tube a expansion pyrotechnique
FR2779224B1 (fr) 1998-06-02 2000-08-11 Aerospatiale Dispositif de decoupe pyrotechnique de pieces non metalliques
FR2779222B1 (fr) 1998-06-02 2000-08-11 Aerospatiale Dispositif de liaison provisoire et de separation pyrotechnique de deux ensembles non metalliques
FR2838818B1 (fr) 2002-04-19 2006-12-08 Eads Launch Vehicules Dispositif de liaison provisoire et de separation pyrotechnique de deux elements, sans rupture
FR2839550B1 (fr) 2002-05-07 2004-07-30 Eads Launch Vehicles Dispositif de liaison provisoire et de separation pyrotechnique de deux elements, a organe mobile
FR2850454B1 (fr) 2003-01-24 2005-04-15 Eads Launch Vehicles Procede d'assemblage d'un dispositif de separation pyrotechnique, et dispositif de separation pyrotechnique obtenu par ce procede
FR2957143B1 (fr) * 2010-03-02 2012-05-04 Astrium Sas Dispositif de raccordement a rupture pyrotechnique
FR3028608B1 (fr) * 2014-11-19 2017-05-05 Dassault Aviat Separateur pyrotechnique comprenant un organe d'absorption de chocs
US10934029B2 (en) * 2017-05-04 2021-03-02 Paragon Space Development Corporation Thermally isolating joint assembly in a space vehicle
US11787571B2 (en) * 2017-12-01 2023-10-17 Ensign-Bickford Aerospace & Defense Company Separation device assemblies

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3362290A (en) * 1965-04-13 1968-01-09 Mc Donnell Douglas Corp Non-contaminating thrusting separation system
US3453960A (en) * 1967-12-11 1969-07-08 Gen Dynamics Corp Noncontaminating linear explosive separation
US3486410A (en) * 1968-04-18 1969-12-30 Mc Donnell Douglas Corp Explosive severance means
US3698281A (en) * 1970-02-27 1972-10-17 Lockheed Aircraft Corp Explosive system
US4137848A (en) * 1975-11-05 1979-02-06 The United States Of America As Represented By The Secretary Of The Navy Rocket engine mount

Also Published As

Publication number Publication date
DE3764311D1 (de) 1990-09-20
ES2018281B3 (es) 1991-04-01
WO1987007006A1 (fr) 1987-11-19
EP0246958A1 (fr) 1987-11-25
FR2598796A1 (fr) 1987-11-20
FR2598796B1 (fr) 1990-04-20

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