EP1355120A1 - Vorrichtung zur provisorischen Verbindung und zum pyrotechnischen Trennen von zwei Elementen, ohne Bruch - Google Patents

Vorrichtung zur provisorischen Verbindung und zum pyrotechnischen Trennen von zwei Elementen, ohne Bruch Download PDF

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Publication number
EP1355120A1
EP1355120A1 EP03101062A EP03101062A EP1355120A1 EP 1355120 A1 EP1355120 A1 EP 1355120A1 EP 03101062 A EP03101062 A EP 03101062A EP 03101062 A EP03101062 A EP 03101062A EP 1355120 A1 EP1355120 A1 EP 1355120A1
Authority
EP
European Patent Office
Prior art keywords
elements
connecting piece
pyrotechnic
connection
face
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
EP03101062A
Other languages
English (en)
French (fr)
Other versions
EP1355120B1 (de
Inventor
Patrick Comtesse
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.)
EADS Space Transportation SA
Original Assignee
EADS Launch Vehicles SA
EADS Space Transportation SA
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Filing date
Publication date
Application filed by EADS Launch Vehicles SA, EADS Space Transportation SA filed Critical EADS Launch Vehicles SA
Publication of EP1355120A1 publication Critical patent/EP1355120A1/de
Application granted granted Critical
Publication of EP1355120B1 publication Critical patent/EP1355120B1/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 invention relates to a device suitable for provide a temporary link between two elements and using a pyrotechnic expansion tube for separate these elements, without requiring the breaking of a any piece.
  • Such a device can in particular be used in the aeronautics and space industries, for order in a very short time the separation of two structural elements, while ensuring transmission possible significant effort between these two elements, before failure is made.
  • Pyrotechnic separation devices usually include an expansion tube pyrotechnic, i.e. a waterproof metal tube and deformable, in which a detonating cord circulates.
  • a flexible material such as rubber is interposed between the detonating cord and the tube that envelops it. before firing, the tube has a section oblong, for example in the shape of an ellipse or a circle flattened.
  • the expansion tube pyrotechnic is used to cut one of the two elements according to a given cutting line, in order to separate the two elements from each other.
  • the elements to be separated are metal, it is known to house the expansion tube pyrotechnic in the bottom of a sectioned recess U shape practiced in one of these elements. The other element is then fixed in the entry of this recess, for example by means of bolts or the like. The updating fire from the detonating cord causes the two to break lateral branches of the hollow element, along lines defined by zones of reduced thickness.
  • the documents FR-A-2 598 796 and EP-A-0 273 061 illustrate devices of this type.
  • the object of the invention is to produce a pyrotechnic separation device, the original design allows it to separate elements in any material, in particular metallic, without causing any part to break.
  • a temporary connection device and pyrotechnic separation comprising a tube pyrotechnic expansion mounted in a space provided in a connection zone between two elements to be separated, said space being delimited in part by a piece of integral connection of a first of said elements, said connecting piece normally ensuring a connection by pressure between said elements and being able to deform, when using the expansion tube pyrotechnic, to release said connection by pressure, characterized in that the connecting piece has a base part attached to one side of the first element and at least one active part, one of which end is able to maintain a heel of the second element resting against a complementary footprint formed on the first element, to form said pressure bonding, said space being formed in the first item or in the heel of the second item and opening out in front of the active part of the connection, between the base part and the end.
  • the aforementioned end of the active part of the connecting piece is shaped like hook, so as to be normally received in a notch formed in the heel of the second element.
  • the connecting piece and the face of the first element preferably cooperate between them by complementary surfaces with wedge, able to slightly move said end in hook shape towards the base part, when tightening of means for fixing said base part based on the first element.
  • the connecting piece comprises advantageously a plurality of active parts made in one piece with the base part and able to deform away from said face, when an implementation of the pyrotechnic expansion tube.
  • the two elements can be annular and arranged end to end or constituted by panels arranged end to end.
  • the connecting piece encircles the junction zone.
  • the connecting piece overlaps the area of junction.
  • FIG. 1 to 3 There is shown in Figures 1 to 3 a mode preferred embodiment of a connecting device 10 temporary and pyrotechnic separation, placed between a first element 12 and a second element 14.
  • the first element 12 and the second element 14 are advantageously constituted either as two annular elements, substantially of the same diameter, either by two panels of any shape. In the two cases, elements 12 and 14 are provided to be assembled end to end.
  • the device 10 according to the invention is located in the connection area between the two elements 12 and 14. It mainly includes a tube pyrotechnic expansion 16 of conventional design, as well as a connecting piece 18.
  • the tube to pyrotechnic expansion 16 is housed in a space 20 which is formed in the first element 12 and opens out on a face 22 of it. More specifically, the space 20 is materialized by a section groove rectangular and the pyrotechnic expansion tube 16 is flush with the face 22 of the first element 12 when it is placed inside said groove.
  • the first element 12 At its end located beyond space 20, the first element 12 includes an imprint 24 whose function will appear later.
  • This imprint 24 is delimited in this case by a perpendicular flank to the face 22 of the first element 12 and leading to said face, and by a sidewall parallel to face 22.
  • the face 22 of the first element 12 comprises a hollow part connected by an inclined surface 26, to the part of said face in which is formed space 20.
  • the recessed part of the face 22 of the first element 12 is crossed by holes 28 intended for passage fasteners such as screws 30 associated with nuts 44 and materializing fixing means of the connecting piece 18 on the face 22 of the first item 12.
  • the second element 14 comprises, at its end intended to be assembled to the first element 12, a heel 32.
  • This heel 32 is provided to come in support against the imprint 24 formed at the end of the first element 12. To this end, it presents surfaces complementary to those which delimit footprint 24.
  • the heel 32 of the second element 14 includes plus a notch 36, on its face 34 intended to be turned on the same side as the face 22 of the first element 12.
  • the notch 36 has the form of a rectangular section groove.
  • the connecting piece 18 comprises a part of base 38, as well as at least one and preferably several active parts 40.
  • Active parts 40 are made in one piece with the base part 38. They are designed to be able to deform when they are subjected to the effort generated by the firing of the detonating cord contained in the tube pyrotechnic expansion 16.
  • the base part 38 is intended to be fixed on the face 22 of the first element 12 using the aforementioned fixing means.
  • the part of base is traversed by holes 42 which are substantially aligned with the holes 28 when the part link 18 is put in place.
  • the screws 30 are then introduced into the aligned holes 28 and 42.
  • the nuts 44 are then screwed onto the screws 30, to complete the fixing means.
  • the face 46 of the connecting piece 18 provided to be applied to the face 22 of the first element 12 has a shape complementary to that of said face 22.
  • this face 26 of the connecting piece 18 includes an inclined surface 48 complementary to the inclined surface 26 of the face 22.
  • the inclined surfaces 26 and 48 thus form complementary corner effect surfaces, including the arrangement is such that the connecting piece 18 is moved slightly downward considering the figures, when tightening the bolts formed by the screws 30 and the nuts 44, said bolts materializing the means for fixing the connecting piece 18 to the first element 12.
  • the active parts 40 extend the part of base 38 of the connecting piece 18 so as to extend beyond the imprint 24 formed at the end of the first element 12, when the connecting piece 18 is attached to it.
  • Each of the active parts 40 comprises a hook-shaped end 50.
  • FIG. 2 This arrangement obtained after assembly of the elements 12 and 14 by the connecting pieces 18 and the fixing means 30, 44 is illustrated in FIG. 2. It makes it possible to establish a provisional link between the different parts and constitutes a "normal" state of assembly.
  • the swelling of the tube 16 with pyrotechnic expansion has the effect of bending the active parts 40 of the connecting piece 18 around of their connection zones with the base part 38 of this part, away from the first element 12. This is made possible by the rigid nature of the part of element 12 in which the space 20 is machined and by the deformable nature of the active parts 40.
  • the active parts 40 of the connecting piece 18 then open, in a very short time, to the way of the petals of a flower. This has the effect of completely release the ends 50 in the form of hooks of the notch 36 formed in the heel 32.
  • the mechanical connection between elements 12 and 14 is thus deleted. These elements can therefore separate one of the other, as shown in Figure 3.
  • the elements 12 and 14 can be either of shapes annular, either consisting of flat panels or of any other form.
  • the piece of link 18 encircles the link area between the two elements and the active parts 40 are distributed over its entire circumference.
  • the piece of link 18 overlaps the junction area of the two panels.
  • the fixing means can take different shapes (rivets, screws, etc.).
  • the expansion tube 16 pyrotechnic can also be mounted in a space machined in the heel 32 of the second part 14, between the end of the heel and the notch 36.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
EP03101062A 2002-04-19 2003-04-17 Vorrichtung zur provisorischen Verbindung und zum pyrotechnischen Trennen von zwei Elementen, ohne Bruch Expired - Lifetime EP1355120B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0204927A FR2838818B1 (fr) 2002-04-19 2002-04-19 Dispositif de liaison provisoire et de separation pyrotechnique de deux elements, sans rupture
FR0204927 2002-04-19

Publications (2)

Publication Number Publication Date
EP1355120A1 true EP1355120A1 (de) 2003-10-22
EP1355120B1 EP1355120B1 (de) 2006-06-21

Family

ID=28459926

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03101062A Expired - Lifetime EP1355120B1 (de) 2002-04-19 2003-04-17 Vorrichtung zur provisorischen Verbindung und zum pyrotechnischen Trennen von zwei Elementen, ohne Bruch

Country Status (6)

Country Link
US (1) US20030196544A1 (de)
EP (1) EP1355120B1 (de)
JP (1) JP2003315000A (de)
DE (1) DE60306245T2 (de)
ES (1) ES2266724T3 (de)
FR (1) FR2838818B1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004027343A1 (en) * 2002-09-23 2004-04-01 The Boeing Company Apparatus and method for releaseably joining elements
WO2005040713A2 (en) * 2003-10-24 2005-05-06 The Boeing Company Low shock separation joint and method therefore
WO2005042345A1 (en) * 2003-10-24 2005-05-12 The Boeing Company Low shock separation joint and method of operation
WO2012020191A1 (fr) * 2010-08-10 2012-02-16 Astrium Sas Dispositif de fixation à verrou pyrotechnique
WO2012085389A1 (fr) * 2010-12-22 2012-06-28 Astrium Sas Pièce à rupture pyrotechnique détonante réversible
WO2015014941A1 (fr) * 2013-08-01 2015-02-05 Airbus Defence And Space Sas Procede et dispositif de liaison et de separation de deux elements avec des moyens de liaison et de separation melanges
US20160169646A1 (en) * 2013-08-01 2016-06-16 Airbus Defence And Space Sas Method and device for linear connection and separation of two elements, with offset energy means

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10303377A1 (de) * 2003-01-29 2004-08-05 Dynamit Nobel Ais Gmbh Automotive Ignition Systems Pyromechanisches Trennelement
US8230770B1 (en) * 2009-09-22 2012-07-31 The United States Of America As Represented By The Secretary Of The Navy Apparatus to energetically remove a ballistic tolerant window
US8607705B2 (en) * 2010-12-06 2013-12-17 Systima Technologies Inc. Low shock rocket body separation
DE102011013255B4 (de) 2011-03-07 2024-01-04 Zf Airbag Germany Gmbh Entriegelungsvorrichtung
CA2901900C (en) 2013-03-06 2021-09-14 Anthony EL HADDAD Interface between fire suppressant conduit and cargo compartment of an aircraft
US11713142B2 (en) * 2017-12-01 2023-08-01 Ensign-Bickford Aerospace & Defense Comany Separation device assemblies
US11787571B2 (en) 2017-12-01 2023-10-17 Ensign-Bickford Aerospace & Defense Company Separation device assemblies
US11565835B1 (en) * 2019-02-05 2023-01-31 Stratolaunch, Llc Controlled separation joint
IL284282B1 (en) * 2021-06-21 2024-10-01 Israel Aerospace Ind Ltd Connection system

Citations (10)

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US3362290A (en) 1965-04-13 1968-01-09 Mc Donnell Douglas Corp Non-contaminating thrusting separation system
US3633456A (en) * 1969-07-03 1972-01-11 Mc Donnell Douglas Corp Power-actuated separation 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
FR2598796A1 (fr) 1986-05-16 1987-11-20 Aerospatiale Dispositif de separation pyrotechnique de deux elements
EP0273061A1 (de) 1985-06-24 1988-07-06 McDONNELL DOUGLAS CORPORATION Trennungsvorrichtung
US4879941A (en) * 1987-07-03 1989-11-14 Thomson-Brandt Armements Ejectable closing device, especially for rockets with munitions
US5735626A (en) * 1996-09-26 1998-04-07 Mcdonnell Douglas Corp. Separating rail assembly
FR2779223A1 (fr) 1998-06-02 1999-12-03 Aerospatiale Dispositif de decoupe de pieces non metalliques au moyen d'un tube a expansion pyrotechnique
FR2779222A1 (fr) * 1998-06-02 1999-12-03 Aerospatiale Dispositif de liaison provisoire et de separation pyrotechnique de deux ensembles non metalliques
FR2779224A1 (fr) 1998-06-02 1999-12-03 Aerospatiale Dispositif de decoupe pyrotechnique de pieces non metalliques

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US2327951A (en) * 1941-10-11 1943-08-24 Ideal Clamp Mfg Co Inc Coupling device
US3134222A (en) * 1960-05-18 1964-05-26 Thiokol Chemical Corp Rocket engine control
US3453960A (en) * 1967-12-11 1969-07-08 Gen Dynamics Corp Noncontaminating linear explosive separation
US4648227A (en) * 1985-09-23 1987-03-10 The Boeing Company Low shock explosive joint systems
US4694544A (en) * 1986-08-22 1987-09-22 Jon Chapman Releasable connector
US5983802A (en) * 1997-12-16 1999-11-16 Lockheed Martin Corporation Separation system
US7367738B2 (en) * 2002-09-23 2008-05-06 The Boeing Company Apparatus and method for releaseably joining elements

Patent Citations (10)

* 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
US3633456A (en) * 1969-07-03 1972-01-11 Mc Donnell Douglas Corp Power-actuated separation 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
EP0273061A1 (de) 1985-06-24 1988-07-06 McDONNELL DOUGLAS CORPORATION Trennungsvorrichtung
FR2598796A1 (fr) 1986-05-16 1987-11-20 Aerospatiale Dispositif de separation pyrotechnique de deux elements
US4879941A (en) * 1987-07-03 1989-11-14 Thomson-Brandt Armements Ejectable closing device, especially for rockets with munitions
US5735626A (en) * 1996-09-26 1998-04-07 Mcdonnell Douglas Corp. Separating rail assembly
FR2779223A1 (fr) 1998-06-02 1999-12-03 Aerospatiale Dispositif de decoupe de pieces non metalliques au moyen d'un tube a expansion pyrotechnique
FR2779222A1 (fr) * 1998-06-02 1999-12-03 Aerospatiale Dispositif de liaison provisoire et de separation pyrotechnique de deux ensembles non metalliques
FR2779224A1 (fr) 1998-06-02 1999-12-03 Aerospatiale Dispositif de decoupe pyrotechnique de pieces non metalliques

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006500522A (ja) * 2002-09-23 2006-01-05 ザ・ボーイング・カンパニー エレメントを解放可能に接合するための装置および方法
WO2004027343A1 (en) * 2002-09-23 2004-04-01 The Boeing Company Apparatus and method for releaseably joining elements
JP4688495B2 (ja) * 2002-09-23 2011-05-25 ザ・ボーイング・カンパニー エレメントを解放可能に接合するための装置および方法
US7367738B2 (en) 2002-09-23 2008-05-06 The Boeing Company Apparatus and method for releaseably joining elements
JP4723506B2 (ja) * 2003-10-24 2011-07-13 ザ・ボーイング・カンパニー 低衝撃分離ジョイントとその動作方法
US7127994B2 (en) 2003-10-24 2006-10-31 The Boeing Company Low shock separation joint
JP2007509000A (ja) * 2003-10-24 2007-04-12 ザ・ボーイング・カンパニー 低衝撃分離ジョイントとその動作方法
US7261038B2 (en) 2003-10-24 2007-08-28 The Boeing Company Low shock separation joint and method therefor
WO2005040713A3 (en) * 2003-10-24 2005-06-16 Boeing Co Low shock separation joint and method therefore
WO2005042345A1 (en) * 2003-10-24 2005-05-12 The Boeing Company Low shock separation joint and method of operation
WO2005040713A2 (en) * 2003-10-24 2005-05-06 The Boeing Company Low shock separation joint and method therefore
US8967030B2 (en) 2010-08-10 2015-03-03 Airbus Defence And Space Sas Attachment device with pyrotechnic bolt
FR2963803A1 (fr) * 2010-08-10 2012-02-17 Astrium Sas Dispositif de fixation a verrou pyrotechnique
WO2012020191A1 (fr) * 2010-08-10 2012-02-16 Astrium Sas Dispositif de fixation à verrou pyrotechnique
WO2012085389A1 (fr) * 2010-12-22 2012-06-28 Astrium Sas Pièce à rupture pyrotechnique détonante réversible
FR2969748A1 (fr) * 2010-12-22 2012-06-29 Astrium Sas Piece a rupture pyrotechnique detonante reversible
WO2015014941A1 (fr) * 2013-08-01 2015-02-05 Airbus Defence And Space Sas Procede et dispositif de liaison et de separation de deux elements avec des moyens de liaison et de separation melanges
FR3009284A1 (fr) * 2013-08-01 2015-02-06 Astrium Sas Procede et dispositif de liaison et de separation de deux elements avec des moyens de liaison et de separation melanges
US20160169646A1 (en) * 2013-08-01 2016-06-16 Airbus Defence And Space Sas Method and device for linear connection and separation of two elements, with offset energy means
US10184766B2 (en) 2013-08-01 2019-01-22 Airbus Defence And Space Sas Method and device for connecting and separating two elements, with combined connecting and separating means
US10228224B2 (en) * 2013-08-01 2019-03-12 Arianegroup Sas Method and device for linear connection and separation of two elements, with offset energy means

Also Published As

Publication number Publication date
ES2266724T3 (es) 2007-03-01
DE60306245D1 (de) 2006-08-03
FR2838818B1 (fr) 2006-12-08
EP1355120B1 (de) 2006-06-21
FR2838818A1 (fr) 2003-10-24
JP2003315000A (ja) 2003-11-06
DE60306245T2 (de) 2007-05-03
US20030196544A1 (en) 2003-10-23

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