EP0297992A1 - Abwerfbarer Deckel für Raketen mit mehreren Sprengköpfen - Google Patents

Abwerfbarer Deckel für Raketen mit mehreren Sprengköpfen Download PDF

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Publication number
EP0297992A1
EP0297992A1 EP88401707A EP88401707A EP0297992A1 EP 0297992 A1 EP0297992 A1 EP 0297992A1 EP 88401707 A EP88401707 A EP 88401707A EP 88401707 A EP88401707 A EP 88401707A EP 0297992 A1 EP0297992 A1 EP 0297992A1
Authority
EP
European Patent Office
Prior art keywords
cover
edge
spring
bar
key
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.)
Withdrawn
Application number
EP88401707A
Other languages
English (en)
French (fr)
Inventor
René Thouron
Jean-François Denis
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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
Application filed by Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0297992A1 publication Critical patent/EP0297992A1/de
Withdrawn legal-status Critical Current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
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially
    • 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 closing a structure, such as for example a compartment for submunitions of a rocket.
  • This device can be ejected on command, thus achieving the opening at the desired time of the structure.
  • the current military strategy used to neutralize the enemy's vital installations has two stages: - the first consists in sending, either using a launcher tube or dropped from an aircraft, a cluster munition rocket over the area to be neutralized: - the second consists of ejecting the submunitions on command.
  • the submunitions are initially placed in closed compartments, located in the rocket. Just before the ejection of the submunitions, the compartments are opened on command.
  • the techniques for ejecting submunitions are widely known and are not described in the following.
  • the invention relates to the closing of the compartments using ejectable devices on command.
  • a known device consists of a hatch weakened in places, fixed to the edges of the compartment in other places. A push towards the outside of the compartment is carried out at the weakened places, which are broken, and which then protrude from the fuselage of the rocket.
  • the aerodynamic coefficient of resistance to advancement thereof (denoted Cx in the following) is then modified, and this difference in Cx causes a partial tearing of the hatch.
  • the hatch is only partially torn off, the opening of the compartment is poorly controlled: fragments of hatch may hinder the passage of submunitions.
  • the object of the present invention is to overcome this drawback. It relates to a device for ejecting a structure comprising: - a lid ; - means for pushing towards the outside of the structure; characterized in that it further comprises: - means for locking the cover: - Means for transmitting the thrust to said blocking means, the thrust being capable of releasing the cover from the blocking means, then of causing the complete expulsion of the cover.
  • the cover of the device according to the invention being completely expelled, the opening of the structure is perfectly controlled and reproducible.
  • the present invention more specifically relates to an ejectable closure device of a structure comprising: - a lid ; - pushing means towards the outside of the structure, characterized in that it further comprises: - means for locking the cover; - means for transmitting said thrust; the thrust being capable of releasing the cover from the locking means, then of causing the complete expulsion of the cover.
  • the rocket comprises, for example, a cylindrical part 24 where compartments for cluster munitions are located.
  • FIG. 1 represents an example of configuration of such a cylindrical part 24: the rocket comprises three compartments 23, for example identical, each containing a submunition 21.
  • the compartments 23 are closed by lids 1, situated at the periphery of the cylindrical part 24, and whose longitudinal edges are fixed according to the invention by means 22 (the transverse edges of these covers are fitted in the part 24).
  • the cylindrical part 24 comprises as many means 22 as there are covers 1: each means 22 maintains two different covers 1, and conversely, two opposite longitudinal edges of a given cover 1 are retained by two different means 22. In what follows, only the fixing of a single longitudinal edge of a cover 1 by a single assembly 22 will be described.
  • FIG. 2 shows a section of a first embodiment of the device according to the invention comprising a cover 1 of which only a part is drawn, and a means 22 fully shown.
  • This figure illustrates the configuration of the device before it is ejected.
  • the edge 8 of the cover 1 is held by the means 22 which comprises: - A part 2, called “key”, fitted into the edge 8, and enclosing the external part of this edge 8, thus blocking the cover 1; - means for pushing the key 2 and the edge 8 towards the outside of the structure, comprising an inflatable membrane 3; a part 10 of the membrane 3 is fixed, for example, by means of glue, to the edge 7 of the compartment 23: this edge 7 has the shape of a cut at the bottom of which the part 10 is glued; - Means for transmitting this thrust, comprising a rigid bar 4 and a spring leaf 5; the bar 4 is located between the key 2 and the membrane 3; the spring 5 is compressed between the bar 4 and the edge 8 of the cover 1 for the entire duration which separates the mounting of the
  • the edge 8 of the cover 1 has a bulge 28 pressing against the edge 7 of the compartment 23.
  • Figures 3 and 4 illustrate the ejection of the device of Figure 2.
  • Such an ejection is triggered by the swelling of the membrane 3, connected for example to a pyrotechnic gas generator not shown in FIGS. 2 to 4.
  • the techniques for swelling membranes intended to achieve any thrust are known in themselves and are therefore not described here.
  • By inflating the membrane 3 performs a radial and centrifugal thrust (relative to the edge 7 of the compartment 23) 9 (relative to the cylindrical part 24 of the rocket).
  • the thrust 9 is exerted on the bar 4, thus compressing the spring 5, as illustrated in FIG. 3; the shape of the bar 4 allows the key 2 to be disengaged from the edge 8: in FIG. 3, the key 2 is almost disengaged.
  • the device is disassembled.
  • the rocket is preferably subjected to a rotation around its axis, in a manner known to those skilled in the art, the resulting centrifugal force making it possible in particular to accentuate the ejection of the aforementioned elements.
  • the various elements then protrude from the fuselage of the rocket, thus modifying its Cx.
  • Figure 5 shows a section of a second embodiment of the device according to the invention, before its ejection.
  • the second embodiment differs from the first in that the edge 7 of the compartment 23 has a rim 12; the spring 5 is preloaded between the bar 4 (as in the case of FIG. 2) and this flange 12 (instead of the edge 8 of the cover 1), which ensures a greater expansion force of the spring 5 than in the case of the first embodiment.
  • the device of FIG. 5 operates like that of FIG. 2, except with regard to the spring 5. This is first compressed by the radial and centrifugal thrust caused by the swelling of the membrane 3 (as in the figure 3); once the key is disengaged, the spring 5 emerges from the rim 12 (unlike in FIG. 3), and relaxes by pressing on the edge 8 of the cover 1 (as in FIG. 4).
  • FIG. 6 represents a section of a third embodiment of the device according to the invention, before it is ejected.
  • the third embodiment differs from the second by the fact that it comprises a one-piece bar, consisting of a rigid part 34 and an elastic part 35, in place of the rigid bar 4 and the spring leaf 5.
  • the parts 34 and 35 respectively provide the same functions as the elements 4 and 5 in FIG. 5.
  • the elastic part 35 unlike the spring 5, is not at all compressed before the device is ejected. As a result, its elasticity is not likely to be reduced as a result of too long prestressing, military equipment being sometimes stored for long periods of time.
  • the device of FIG. 6 is therefore more reliable than that of FIG. 5, or that of FIGS. 2, 3 and 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Catching Or Destruction (AREA)
EP88401707A 1987-07-03 1988-07-01 Abwerfbarer Deckel für Raketen mit mehreren Sprengköpfen Withdrawn EP0297992A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8709453 1987-07-03
FR8709453A FR2617464B1 (fr) 1987-07-03 1987-07-03 Dispositif de fermeture ejectable, notamment pour roquettes a sous-munitions

Publications (1)

Publication Number Publication Date
EP0297992A1 true EP0297992A1 (de) 1989-01-04

Family

ID=9352842

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88401707A Withdrawn EP0297992A1 (de) 1987-07-03 1988-07-01 Abwerfbarer Deckel für Raketen mit mehreren Sprengköpfen

Country Status (3)

Country Link
US (1) US4879941A (de)
EP (1) EP0297992A1 (de)
FR (1) FR2617464B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641858A1 (fr) * 1989-01-17 1990-07-20 Thomson Brandt Armements Dispositif de deverrouillage pneumatique pour munitions largables a partir d'un vecteur
FR2652642A1 (fr) * 1989-09-29 1991-04-05 Aerospatiale Missile de largage de sous-munitions equipe d'un conteneur modulable.
WO2012020191A1 (fr) * 2010-08-10 2012-02-16 Astrium Sas Dispositif de fixation à verrou pyrotechnique

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5005481A (en) * 1989-06-26 1991-04-09 Olin Corporation Inflatable bladder submunition dispensing system
US5107767A (en) * 1989-06-26 1992-04-28 Olin Corporation Inflatable bladder submunition dispensing system
FR2656414B1 (fr) * 1989-12-22 1993-01-22 Thomson Brandt Armements Systemes de retenue de sous-munitions embarquees dans un vecteur.
FR2685467B1 (fr) * 1991-12-23 1994-02-04 Thomson Brandt Armements Dispositif de separation et de freinage aerodynamique de l'etage propulseur d'un missile.
US5218165A (en) * 1992-06-10 1993-06-08 The United States Of America As Represented By The Secretary Of The Army Pneumatic separation device
US5392684A (en) * 1993-06-25 1995-02-28 The Ensign-Bickford Company Explosive thrust-producing coupling
US5372071A (en) * 1993-07-13 1994-12-13 Tracor, Inc. Thrusting separation system
US5735626A (en) * 1996-09-26 1998-04-07 Mcdonnell Douglas Corp. Separating rail assembly
US5898123A (en) * 1997-05-01 1999-04-27 The Ensign-Bickford Company Sealing device and a method for assembly thereof
US6021715A (en) * 1997-05-02 2000-02-08 The Ensign-Bickford Company Manifold for coupling with a tube and method thereof
US6125762A (en) * 1997-07-03 2000-10-03 The Ensign-Bickford Company Flat-form separation devices
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
US7367738B2 (en) * 2002-09-23 2008-05-06 The Boeing Company Apparatus and method for releaseably joining elements
US7127994B2 (en) * 2003-10-24 2006-10-31 The Boeing Company Low shock separation joint
US7261038B2 (en) * 2003-10-24 2007-08-28 The Boeing Company Low shock separation joint and method therefor
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
US11713142B2 (en) * 2017-12-01 2023-08-01 Ensign-Bickford Aerospace & Defense Comany Separation device assemblies
CN109883275B (zh) * 2019-02-27 2021-05-11 上海机电工程研究所 便于拆装且防脱落的导弹尾盖

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern
US4455943A (en) * 1981-08-21 1984-06-26 The Boeing Company Missile deployment apparatus
EP0114602A2 (de) * 1983-01-21 1984-08-01 Rheinmetall GmbH Flugkörper
FR2557286A1 (fr) * 1983-12-27 1985-06-28 Brandt Armements Charge militaire a tetes multiples
GB2169067A (en) * 1982-06-16 1986-07-02 Hunting Eng Ltd Ejection equipment

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2489984A (en) * 1945-02-20 1949-11-29 United Aircraft Corp Explosive-release mechanism
US2809584A (en) * 1953-04-01 1957-10-15 Smith Bernard Connector ring for two stage rockets
US3070018A (en) * 1961-02-27 1962-12-25 Marcellus W Fahi Nose cone ejection system
US3362290A (en) * 1965-04-13 1968-01-09 Mc Donnell Douglas Corp Non-contaminating thrusting separation system
US3458217A (en) * 1966-11-25 1969-07-29 Joseph D Pride Jr Tubular coupling having low profile band segments with means for preventing relative rotation
US3465482A (en) * 1967-12-26 1969-09-09 Nasa Spacecraft radiator cover
US3902400A (en) * 1974-03-13 1975-09-02 Us Army Pyrotechnic band release device
DE3142313A1 (de) * 1981-10-24 1983-05-05 Rheinmetall GmbH, 4000 Düsseldorf Flugkoerper

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2920347A1 (de) * 1979-05-19 1980-11-20 Messerschmitt Boelkow Blohm Gefechtskopf mit ausstossbaren wirkkoerpern
US4455943A (en) * 1981-08-21 1984-06-26 The Boeing Company Missile deployment apparatus
GB2169067A (en) * 1982-06-16 1986-07-02 Hunting Eng Ltd Ejection equipment
EP0114602A2 (de) * 1983-01-21 1984-08-01 Rheinmetall GmbH Flugkörper
FR2557286A1 (fr) * 1983-12-27 1985-06-28 Brandt Armements Charge militaire a tetes multiples

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641858A1 (fr) * 1989-01-17 1990-07-20 Thomson Brandt Armements Dispositif de deverrouillage pneumatique pour munitions largables a partir d'un vecteur
EP0379402A1 (de) * 1989-01-17 1990-07-25 Thomson-Brandt Armements Pneumatische Entriegelungsvorrichtung für aus einem Trägergeschoss ausklinkbare Munition
US4998480A (en) * 1989-01-17 1991-03-12 Thomson-Brandt Armements Pneumatic unlocking device for munitions releasable from a carrier
FR2652642A1 (fr) * 1989-09-29 1991-04-05 Aerospatiale Missile de largage de sous-munitions equipe d'un conteneur modulable.
EP0424198A1 (de) * 1989-09-29 1991-04-24 AEROSPATIALE Société Nationale Industrielle Trägergeschoss mit einem Modulbehälter zum Abwerfen von Submunitionskörpern
US5094170A (en) * 1989-09-29 1992-03-10 Aerospatiale Societe Nationale Industrielle Missile for dropping armaments equipped with a modifiable container
WO2012020191A1 (fr) * 2010-08-10 2012-02-16 Astrium Sas Dispositif de fixation à verrou pyrotechnique
FR2963803A1 (fr) * 2010-08-10 2012-02-17 Astrium Sas Dispositif de fixation a verrou pyrotechnique
US8967030B2 (en) 2010-08-10 2015-03-03 Airbus Defence And Space Sas Attachment device with pyrotechnic bolt

Also Published As

Publication number Publication date
US4879941A (en) 1989-11-14
FR2617464A1 (fr) 1989-01-06
FR2617464B1 (fr) 1990-02-16

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