EP1319920A1 - Pyrotechnische Trennungsvorrichtung und damit ausgerüstetes Trennsystem - Google Patents

Pyrotechnische Trennungsvorrichtung und damit ausgerüstetes Trennsystem Download PDF

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Publication number
EP1319920A1
EP1319920A1 EP02293074A EP02293074A EP1319920A1 EP 1319920 A1 EP1319920 A1 EP 1319920A1 EP 02293074 A EP02293074 A EP 02293074A EP 02293074 A EP02293074 A EP 02293074A EP 1319920 A1 EP1319920 A1 EP 1319920A1
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EP
European Patent Office
Prior art keywords
separator
cord
parts
pyrotechnic
zones
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.)
Granted
Application number
EP02293074A
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English (en)
French (fr)
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EP1319920B1 (de
Inventor
Bernard Louis Martin
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.)
Dassault Aviation SA
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Dassault Aviation SA
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Publication date
Application filed by Dassault Aviation SA filed Critical Dassault Aviation SA
Publication of EP1319920A1 publication Critical patent/EP1319920A1/de
Application granted granted Critical
Publication of EP1319920B1 publication Critical patent/EP1319920B1/de
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 pyrotechnic separator designed to be installed along a junction line of two mechanical parts temporarily assembled and designed to separate in a predetermined direction, and, more particularly, to such a separator comprising first and second flanks assembly of said parts, enclosing between them a current crushed pyrotechnic cord along said junction line, first and second weakening zones current on said first and second flanks respectively, parallel and at vicinity of said cord, and means for selectively activating said cord and causing thus the rupture of said flanks along said weakening zones.
  • Such a separator is well known, see for example the United States patent America No. 3,698,281 in the name of Brandt, and it finds particular application in the aerospace industry, where it is used in particular to ensure the separation of elements of space launchers.
  • Figure 1 of the drawing there is shown in Figure 1 of the drawing annexed a first mechanical part 1, in the form of a ferrule, cylindrical of revolution, constituting the upper part of the casing of such a launcher, this first part being surmounted by an ovoid cap made up of second and third shaped parts 2a, 2b half-caps, this cap having the function of protecting a payload (not represented) such as an artificial satellite for example, during the crossing of the layers dense of the atmosphere.
  • a payload not represented
  • the half-caps 2a, 2b and the ferrule 1 are assembled conventionally, as described in U.S. Patent No. 3,453,960 to name of Qualls, following first and second connecting lines respectively, equipped with first and second separators 3 and 4 respectively.
  • the first separator pyrotechnic, runs along a junction line circular on which the two semi-circular half-bases of the half-caps 2a and 2b. This is why this first separator can also consist, as shown, of two semi-circular semi-separators.
  • the second separator 4 runs along a section of the cap by a plane passing through the X axis of the launcher.
  • first and second separators 3 and 4 are installed in planes P 1 and P 2 respectively, the plane P 1 being perpendicular to the axis X of the launcher while the plane P 2 passes through this axis, between the two half-caps 2a and 2b symmetrical with respect to this plane, itself perpendicular to the direction D in which the half-caps deviate from one another to release the payload carried by the launcher.
  • the separator 4 is of a known type, ensuring the lateral dislocation of the two half-caps 2a, 2b according to the arrows f 1 , f 2 respectively. It can be pyrotechnic, like the first or, alternatively, spring.
  • the separator 3 is commonly of one or the other of two known types, called “symmetrical” and “asymmetrical” respectively.
  • An example of a “symmetrical” separator is described in the aforementioned Brandt patent while an example of an "asymmetrical” separator is shown in Figures 3 and 4 of the Qualls patent also cited above. That he is the type "symmetrical” or of the "asymmetrical” type, a pyrotechnic separator comprises conventionally a pyrotechnic cord comprising an expandable tube consisting of a metal shell of oblong or "crushed" cross section, the tube being filled with a explosive charge. The tube is placed between two sides, plates, flanges or shoulders, integral with the two parts assembled by the separator.
  • one of these flanks, plates, flanges, etc. is hollowed out with a weakening line, a groove for example, at the level of the tube expandable.
  • a weakening line a groove for example, at the level of the tube expandable.
  • the two sides are hollowed out in such a way weakening line, which are then arranged symmetrically to a plane separator median.
  • An asymmetrical separator offers the advantage, when used to constitute the separator 3, to contribute to the lateral dislocation of the two half-caps, by the very fact of its asymmetry.
  • the explosion of the charge contained in the pyrotechnic cord applies high-level shocks to the assembled structures, which propagate in these structures and can then damage the equipment mounted on them (in particular launcher payload).
  • a symmetrical separator offers the advantage over an asymmetrical separator apply lower level shocks to structures. However, due to its symmetrical geometry, it does not contribute to the lateral dislocation of the two half-caps, that it can even interfere.
  • the object of the present invention is therefore to produce a pyrotechnic separator suitable for constituting, in particular, the separator 3 of the cap shown in FIG. 1, this separator combining the advantages of the separators of the two types discussed above, without presenting the disadvantages.
  • the present invention also aims to provide a separation device pyrotechnics of at least first, second and third mechanical parts temporarily assembled, comprising the separator according to the invention.
  • a pyrotechnic separator designed to be installed in the along a junction line of two temporarily assembled mechanical parts and designed to separate in a predetermined direction, this separator comprising first and second assembly sides of said pieces enclosing between them a bead crushed pyrotechnics running along said junction line, first and second zones of current weakening on said first and second flanks respectively, parallel to and in the vicinity of said cord, and means for selectively activating said cord bead and thus cause the rupture of said flanks along said zones of weakness, this separator being remarkable in that said zones together define a surface fracture envelope tangent to said pyrotechnic cord and inclined at any point on said predetermined direction, said inclination being oriented so as to allow a mutual clearance of the two parts in said predetermined direction, without interference mechanical, upon activation of said cord.
  • the separator according to the invention makes it possible to constitute a separation device pyrotechnics of at least first, second and third mechanical parts temporarily assembled along first and second connecting lines equipped first and second pyrotechnic separators running between the first part and said second and third parts, and between said second and third parts, respectively, said first and second junction lines developing in first and second planes perpendicular to each other and said second and third parts being symmetrical with respect to the second plane, this device being remarkable in that said first pyrotechnic separator is as stated above and that said second pyrotechnic separator is equipped with activation means triggered by synchronism with those of the first pyrotechnic separator, to cooperate in the spacing of said second and third parts in said predetermined direction, perpendicular to said second plane.
  • FIGS. 2 and 3 of the appended drawing represent a separator pyrotechnic designed, in particular, to constitute the separator 3 of FIG. 1, this application being given by way of illustrative and nonlimiting example only.
  • the separator 3 comprises two semi-circular halves placed end to end.
  • the section views of this separator shown in Figures 2 and 3 are taken in the section plane P 3 of Figure 1, where the separator establishes a frangible connection between the part 1 in the form of a ferrule and the part 2b in the form of a half -cap.
  • the separator establishes a frangible connection between the part 1 in the form of a ferrule and the part 2b in the form of a half -cap.
  • the separator 3 comprises first and second sides 5 1 , 5 2 projecting from the part 1 in a cross section in the form of a yoke, an edge portion of the cap 2b being inserted between these two sidewalls to delimit an annular chamber in which is housed a pyrotechnic cord with an oblong straight section, or "crushed", clamped between the sides 5 1 , 5 2 .
  • the ferrule 1 and the half-cap 2b are assembled by a series of bolts such as that referenced 6 which passes through the ferrule 1 and the sides 5 1 , 5 2 .
  • the pyrotechnic cord conventionally comprises an expandable metal tube 7 internally lined with a bead of pyrotechnic material 8 centered in the tube by a setting product 9, for example.
  • Each of the two cords (7, 8, 9) forming part of the separator 3 is equipped, with each of its two ends leaving the cap 2a, 2b through windows 10a, 10b visible in FIG. 1, of conventional activation means 11 shown in more detail at Figure 4.
  • the separator according to the invention comprises two weakening zones 14 1 , 14 2 , defined by notches or grooves (15a, 15b) and (16a, 16b) respectively, dug in the two faces in look of the flanks 5 1 , 5 2 respectively, at the base of these flanks.
  • the thickness of the weakening zones and the geometry of the neighboring separator of the expandable tube 7 are defined so as to minimize the pyrotechnic shock during the ignition of the pyrotechnic cord (7, 8, 9) as well as the shock due to the relaxation of the parts separated.
  • the optimization carried out relates to the stiffness and inertia of each of the sides 5 1 , 5 2 as well as to the arrangement and the thickness of the weakening zones.
  • the thickness of the sidewalls is optimized so as to make the areas work loss as much as possible in shear.
  • the thickness of the sidewalls must be at least equal to that of the pyrotechnic cord, as shown in Figure 2. We limit thus the deformation of the sidewalls during and after operation. Breaking up areas weakening is thus obtained for a small deformation of the cord, and therefore also flanks which rest on this cord.
  • these two weakening zones are arranged asymmetrically with respect to the median plane P 4 of the separator (see FIG. 2) so as to define, after their rupture, an "envelope" surface of fracture S whose trace, in the plane of Figure 3, is inclined to the direction D in which the two half-caps 2a, 2b must deviate from each other (see Figure 1).
  • This trace is defined by a straight line passing substantially through the midpoints of the weakening zones. As shown in zone 14 1 , the break in these zones is not necessarily parallel to the trace of surface S.
  • the surface S takes a frustoconical shape (when the ferrule 1 is cylindrical of revolution), the top of the cone tangent to this shape being on the axis X, on the side of the cap (2a, 2b), by compared to plan P 1 .
  • the weakening zone 14 1 the radius of which is smaller than that of the zone 14 2 , is then above the zone 14 2 when it is marked with respect to the axis X, as it is oriented in figure 1.
  • the activation of the pyrotechnic separator according to the invention takes place as seen above, using means 11 mounted at the ends of the cord (7, 8, 9), means commonly called “detonators” or " pyrotechnic transmission lines ".
  • An initiation center (not shown) coordinates and synchronizes the activations of the detonators or the transmission lines associated with the various cords forming part of the separators 3 and 4 of the device shown in FIG. 1, so as to ensure separation and ejection half-caps 2a, 2b according to the arrows f 1 and f 2 respectively.
  • the impulse required for this ejection is obtained by igniting the separator 4. Indeed, the firing of the separator 3 does not develop sufficient radial force to ensure this ejection.
  • the detonation of the pyrotechnic charge inflates the expandable tube 7 which then transmits the shock wave produced by the detonation to the sides 5 1 , 5 2 on which it is based.
  • This shock wave causes shear stresses such as these zones to break in the weakening zones 14 1 , 14 2 , causing the breaking surface S to appear.
  • the swelling of the tube 7 makes it lose its oblong shape and gives it a substantially elliptical shape (as shown in FIG. 3) which causes the tube to block against the opposite faces of the sides 5 1 , 5 2 . This is made possible by the thickness of the sides 5 1 , 5 2 , which limits their permanent deformation, after activation of the separator.
  • the tube 7 then remains integral with the ejected half-cap 2a or 2b, which avoids any dangerous dispersion of its components in the environment of the launcher.
  • the tube 7 After swelling, the tube 7 also remains tangent to the fracture surface S (see Figure 3), which allows the half-cap which it is integral to move freely from the launcher, thanks to the impulse provided by the separator 4, and this without any risk mechanical attachment to the surface facing the ferrule 1, in accordance with one of the aims of the present invention.
  • the overall geometry of the separator according to the invention remains close that of a so-called "symmetrical" separator, the advantage of the latter is also retained, know the low level of shock applied to the adjoining structure when firing the separator, especially in the frequency band from 500 Hz to 10 000 Hz approximately.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Insulating Bodies (AREA)
  • Details Of Connecting Devices For Male And Female Coupling (AREA)
  • Air Bags (AREA)
EP20020293074 2001-12-14 2002-12-12 Pyrotechnische Trennungsvorrichtung und damit ausgerüstetes Trennsystem Expired - Lifetime EP1319920B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0116196 2001-12-14
FR0116196A FR2833694B1 (fr) 2001-12-14 2001-12-14 Separateur pyrotechnique et dispositif de separation equipe d'un tel separateur

Publications (2)

Publication Number Publication Date
EP1319920A1 true EP1319920A1 (de) 2003-06-18
EP1319920B1 EP1319920B1 (de) 2005-06-29

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Family Applications (1)

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EP20020293074 Expired - Lifetime EP1319920B1 (de) 2001-12-14 2002-12-12 Pyrotechnische Trennungsvorrichtung und damit ausgerüstetes Trennsystem

Country Status (4)

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EP (1) EP1319920B1 (de)
DE (1) DE60204836T2 (de)
ES (1) ES2243674T3 (de)
FR (1) FR2833694B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1739384A1 (de) * 2005-06-27 2007-01-03 Diehl BGT Defence GmbH & Co.KG Abwerfbare Vorsatzhaube sowie Flugkörper mit abwerfbarer Vorsatzhaube
FR2957143A1 (fr) * 2010-03-02 2011-09-09 Astrium Sas Dispositif de raccordement a rupture pyrotechnique
US10934029B2 (en) * 2017-05-04 2021-03-02 Paragon Space Development Corporation Thermally isolating joint assembly in a space vehicle
CN113566659A (zh) * 2020-04-29 2021-10-29 大连理工大学 一种横纵分离一体化级间线式分离装置及其应用
US20230010986A1 (en) * 2021-07-08 2023-01-12 Saab Bofors Dynamics Switzerland Ltd. Release mechanism

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012110450B4 (de) * 2012-10-31 2014-07-17 Deutsches Zentrum für Luft- und Raumfahrt e.V. Objekt für eine Mission in den Weltraum
CN105007994B (zh) 2013-03-06 2018-05-15 庞巴迪公司 在灭火剂管道与飞行器货舱之间的接口
FR3028609B1 (fr) 2014-11-19 2017-05-05 Dassault Aviat Separateur pyrotechnique comprenant deux elements structurels independants assembles l'un a l'autre, et procede de fabrication associe
FR3028608B1 (fr) 2014-11-19 2017-05-05 Dassault Aviat Separateur pyrotechnique comprenant un organe d'absorption de chocs

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3427047A (en) * 1966-11-30 1969-02-11 Nasa Tubular coupling having frangible connecting means
US3453960A (en) 1967-12-11 1969-07-08 Gen Dynamics Corp Noncontaminating linear explosive separation
US3633456A (en) * 1969-07-03 1972-01-11 Mc Donnell Douglas Corp Power-actuated separation system
US3698281A (en) 1970-02-27 1972-10-17 Lockheed Aircraft Corp Explosive system
US6298786B1 (en) * 1997-12-16 2001-10-09 Lockheed Martin Corporation Frangible access panel system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3427047A (en) * 1966-11-30 1969-02-11 Nasa Tubular coupling having frangible connecting means
US3453960A (en) 1967-12-11 1969-07-08 Gen Dynamics Corp Noncontaminating linear explosive separation
US3633456A (en) * 1969-07-03 1972-01-11 Mc Donnell Douglas Corp Power-actuated separation system
US3698281A (en) 1970-02-27 1972-10-17 Lockheed Aircraft Corp Explosive system
US6298786B1 (en) * 1997-12-16 2001-10-09 Lockheed Martin Corporation Frangible access panel system

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1739384A1 (de) * 2005-06-27 2007-01-03 Diehl BGT Defence GmbH & Co.KG Abwerfbare Vorsatzhaube sowie Flugkörper mit abwerfbarer Vorsatzhaube
FR2957143A1 (fr) * 2010-03-02 2011-09-09 Astrium Sas Dispositif de raccordement a rupture pyrotechnique
WO2011107690A1 (fr) * 2010-03-02 2011-09-09 Astrium Sas Dispositif de raccordement a rupture pyrotechnique
US20120318125A1 (en) * 2010-03-02 2012-12-20 Jean-Yves Cousin Connecting device having pyrotechnic rupture
US8776661B2 (en) 2010-03-02 2014-07-15 Astrium Sas Connecting device having pyrotechnic rupture
US10934029B2 (en) * 2017-05-04 2021-03-02 Paragon Space Development Corporation Thermally isolating joint assembly in a space vehicle
CN113566659A (zh) * 2020-04-29 2021-10-29 大连理工大学 一种横纵分离一体化级间线式分离装置及其应用
CN113566659B (zh) * 2020-04-29 2024-01-16 大连理工大学 一种横纵分离一体化级间线式分离装置及其应用
US20230010986A1 (en) * 2021-07-08 2023-01-12 Saab Bofors Dynamics Switzerland Ltd. Release mechanism
US11572203B2 (en) * 2021-07-08 2023-02-07 Saab Bofors Dynamics Switzerland Ltd. Release mechanism

Also Published As

Publication number Publication date
ES2243674T3 (es) 2005-12-01
DE60204836T2 (de) 2006-01-12
EP1319920B1 (de) 2005-06-29
FR2833694A1 (fr) 2003-06-20
FR2833694B1 (fr) 2006-02-03
DE60204836D1 (de) 2005-08-04

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