EP0898146B1 - Connexion de deux pièces de coque d'un missile - Google Patents

Connexion de deux pièces de coque d'un missile Download PDF

Info

Publication number
EP0898146B1
EP0898146B1 EP98114354A EP98114354A EP0898146B1 EP 0898146 B1 EP0898146 B1 EP 0898146B1 EP 98114354 A EP98114354 A EP 98114354A EP 98114354 A EP98114354 A EP 98114354A EP 0898146 B1 EP0898146 B1 EP 0898146B1
Authority
EP
European Patent Office
Prior art keywords
fuselage
connection
edge
fuselage portion
set forth
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
EP98114354A
Other languages
German (de)
English (en)
Other versions
EP0898146A3 (fr
EP0898146A2 (fr
Inventor
Dirk Bross
Klaus-Dieter Knapp
Peter Gerd Fisch
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.)
Bodenseewerk Geratetechnik GmbH
Original Assignee
Bodenseewerk Geratetechnik GmbH
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 Bodenseewerk Geratetechnik GmbH filed Critical Bodenseewerk Geratetechnik GmbH
Publication of EP0898146A2 publication Critical patent/EP0898146A2/fr
Publication of EP0898146A3 publication Critical patent/EP0898146A3/fr
Application granted granted Critical
Publication of EP0898146B1 publication Critical patent/EP0898146B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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

Definitions

  • the invention relates to a connection for connecting two tubular body parts of a missile according to the preamble of claim 1.
  • the known type of pipe connection is particularly unsatisfactory Connecting tubular fuselage parts of highly agile missiles. Kick at these extreme stresses on the pipe connections.
  • Pipe connection is known in which the edge regions to be connected each consist of two Circumferential sections with different diameters exist. The The inner diameter of one circumferential section corresponds to an assembly tolerance the outer diameter of the other peripheral portion. They have Pipe parts the same design of the edge area, but by 180 ° around Connection axis rotated. The pipe connection is made by the pipe parts are pushed into each other and screwed with radial connecting screws become.
  • the pipe connection has an asymmetrical radial screw connection and has the The advantage that it brings about a good form fit.
  • US-A-3 781 042 discloses a connection for connecting two tubular ones Fuselage parts of a missile according to the preamble of claim 1.
  • this Connection are clamping elements along the inner circumference of the second fuselage part intended.
  • Each clamping element is provided with a threaded hole in which one connecting screw each can be screwed in.
  • the clamping elements cooperate Inclined surface so that the two fuselage parts when tightening the screws move axially against each other and are thus tightened together.
  • the invention has for its object a high-strength and highly rigid connection to create two tubular fuselage parts of a missile.
  • connection should be detachable.
  • the connection should enable easy assembly. Costs and manufacturing effort should be low.
  • the construction volume should be small.
  • the connection should leave a large free cross section. Increases in the outside diameter due to the pipe connection should be avoided.
  • the connection should continue to be free of play.
  • the clamping segments are separate peripheral sections of a ring, the outer diameter of which is the inner diameter of the second body part corresponds, the threads are not in the inner part of the fuselage, but in the Clamping segments.
  • connection has a high pressure due to the high load-bearing components Rigidity and strength.
  • the wall thickness of the Connecting edge of the second part of the fuselage is slight. Through this and through the division into several clamping segments can achieve higher preloads. This leads to higher ones sustainable operational forces before the connection takes off.
  • Embodiments of the invention are the subject of the dependent claims.
  • the figure shows a perspective view of the connection.
  • a first fuselage part of a missile is designated by 10 in FIG.
  • the first part of the fuselage 10 is to be connected to a second fuselage part 12 of a missile.
  • the Fuselage parts 10 and 12 are tubular parts of the fuselage of a missile.
  • the fuselage part 12 has an edge 14.
  • the edge 14 has a smaller one Diameter than the remaining part 16 of the fuselage part 12.
  • In the edge 14 are Bores 18 in two rows 20 along the circumference of the edge 14.
  • the fuselage part 10 has an edge 22.
  • the edge 22 has an inner diameter that except for a small assembly tolerance the outer diameter of the edge 14 of the corresponds to other fuselage part 12. This inner diameter can be smaller than that Inner diameter of the remaining part 24 of the fuselage part 10.
  • In the edge 22 there are Bores 26 in two rows 28 along the circumference of the edge 22. The bores 26 are designed so that the heads of screws 30 which are inserted into the holes 26 are retractable.
  • clamping segments 32 For the connection of the two fuselage parts 10 and 12 there are clamping segments 32 intended.
  • the assembled Clamping segments 32 a ring.
  • This ring has an outer diameter that corresponds to the Corresponds to the inner diameter of the edge 14 of the fuselage part 12.
  • the clamping segments 32 there are bores 34 which run along two rows 36 the circumference are arranged.
  • the holes 34 are provided with internal threads that correspond to the thread of the connecting screws 30.
  • the holes 18 in the Edge 14, the holes 26 in the edge 22 and the holes 34 in the Clamping segments 32 are arranged with respect to one another such that they lie one above the other when the fuselage parts 10 and 12 are pushed together and the clamping segments lie within the edge 14.
  • the connecting screws 30 are then through the Bores 26 and 18 in the thread of the bore 34 in the clamping segment screwed.

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)
  • Clamps And Clips (AREA)

Claims (6)

  1. Assemblage destiné à assembler deux éléments de fuselage (10,12) en forme de tuyau d'un missile, les diamètres extérieurs des éléments de fuselage (10,12) concordant sensiblement l'un avec l'autre et pour lequel les éléments de fuselage (10,12) sont susceptibles d'être emmanchés l'un dans l'autre,
    (a) le diamètre intérieur du bord (22) du premier élément de fuselage (10) devant être assemblé avec le second élément de fuselage (12) correspondant, déduction faite d'une tolérance d'accouplement, au diamètre extérieur du bord (14) du second élément de fuselage (12) devant être assemblé avec le premier élément de fuselage (10),
    (b) les bords (22,14) des éléments de fuselage (10,12) devant être assemblés étant pourvus de perçages radiaux (26,20) destinés aux vis d'assemblage (30),
    (c) des segments de serrage (32) étant pourvus de perçages filetés (34) le long de la circonférence intérieure du second élément de fuselage (12) dans lesquels les vis d'assemblage (30) sont susceptibles d'être vissées, et
    (d) le diamètre extérieur de l'assemblage de tuyaux correspondant sensiblement aux diamètres extérieurs des éléments de fuselage (10,12) devant être assemblés,
       caractérisé par le fait que
    (e) plusieurs vis d'assemblage (30) sont susceptibles d'être vissées dans chaque segment de serrage (32), et
    (f) les segments de serrage (32) forment des segments circonférentiels d'une bague séparés les uns des autres dont le diamètre extérieur correspond au diamètre intérieur du second élément de fuselage (12).
  2. Assemblage selon la revendication 1, caractérisé par le fait que les vis d'assemblage (30) sont disposées sur deux rangées (28) le long dé la circonférence du bord (22) du premier élément de fuselage (10).
  3. Assemblage selon la revendication 1 ou 2, caractérisé par le fait que l'épaisseur de paroi du bord (14) du second élément de fuselage (12) est inférieure à l'épaisseur de paroi restante du second élément de fuselage (12).
  4. Assemblage selon l'une des revendications 1 à 3, caractérisé par le fait que l'épaisseur de paroi du bord (14) du second élément de fuselage (12) est inférieure à l'épaisseur de paroi du bord (22) du premier élément de fuselage (10).
  5. Assemblage selon l'une des revendications 1 à 4, caractérisé par le fait que les têtes des vis d'assemblage (30) sont renfoncées dans le bord (22) du premier élément de fuselage (10).
  6. Assemblage selon l'une des revendications 1 à 5, caractérisé par le fait que les segments de serrage (32) se composent d'un matériau hautement résistant.
EP98114354A 1997-08-16 1998-07-30 Connexion de deux pièces de coque d'un missile Expired - Lifetime EP0898146B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19735452A DE19735452C2 (de) 1997-08-16 1997-08-16 Rohrverbindung, insbesondere zum Verbinden zweier rohrförmiger Rumpfteile eines Flugkörpers
DE19735452 1997-08-16

Publications (3)

Publication Number Publication Date
EP0898146A2 EP0898146A2 (fr) 1999-02-24
EP0898146A3 EP0898146A3 (fr) 1999-05-26
EP0898146B1 true EP0898146B1 (fr) 2001-10-10

Family

ID=7839101

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98114354A Expired - Lifetime EP0898146B1 (fr) 1997-08-16 1998-07-30 Connexion de deux pièces de coque d'un missile

Country Status (3)

Country Link
US (1) US6098928A (fr)
EP (1) EP0898146B1 (fr)
DE (2) DE19735452C2 (fr)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10141169A1 (de) † 2001-08-22 2003-03-13 Diehl Munitionssysteme Gmbh Artillerierakete
RU2249131C1 (ru) * 2003-10-17 2005-03-27 Общество с ограниченной ответственностью "АВВИ" Способ соединения деталей
US7325771B2 (en) * 2004-09-23 2008-02-05 The Boeing Company Splice joints for composite aircraft fuselages and other structures
US7681834B2 (en) * 2006-03-31 2010-03-23 Raytheon Company Composite missile nose cone
FR2915458B1 (fr) * 2007-04-25 2010-01-01 Airbus France Assemblage de panneaux de fuselage d'un avion
US20080296432A1 (en) * 2007-06-04 2008-12-04 Kernkamp Industries Corporation Method of extending length of aircraft to increase interior space
DE102009021369A1 (de) * 2009-05-12 2010-11-18 Airbus Operations Gmbh Verfahren zur Herstellung eines Flugzeugrumpfes und Flugzeugrumpf
DE102013102812B4 (de) * 2013-03-19 2017-01-26 Airbus Operations Gmbh Rumpfstruktur für ein Verkehrsmittel, Verkehrsmittel und Verfahren zum Herstellen einer Rumpfstruktur für ein Verkehrsmittel
CN103759597B (zh) * 2014-01-14 2015-06-17 北京航空航天大学 一种导弹舱段径向单斜衬套螺栓连接结构
US10634473B2 (en) * 2014-01-29 2020-04-28 Raytheon Company Internally coupleable joint
US8894011B1 (en) * 2014-02-14 2014-11-25 The Boeing Company Aircraft fuselage constructed of aircraft fuselage sections screwed together
US20170241460A1 (en) * 2014-09-10 2017-08-24 Gripple Limited Stiffening assembly
DE102015106761A1 (de) * 2015-04-30 2016-11-03 Airbus Operations Gmbh Montage von Strukturelementen in der Luftfahrt
US10920811B2 (en) 2018-02-15 2021-02-16 Raytheon Company Component assembly for high-precision joining of components
CN111332492B (zh) * 2020-03-06 2021-06-01 北京机电工程研究所 一种飞行器舱段无缆对接装置及其对接方法
RU2738623C1 (ru) * 2020-06-16 2020-12-15 Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" Узел стыковки отсеков
CN112344808A (zh) * 2020-10-11 2021-02-09 中国运载火箭技术研究院 插接结构及舱段组件

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US759834A (en) * 1902-12-03 1904-05-10 Benjamin M Steele Means for uniting sheet-metal parts.
GB106153A (en) * 1916-05-22 1917-05-17 Accles & Pollock Ltd A New or Improved Joint or Coupling for Connecting Tubes, Tubing, and the like.
DE692866C (de) * 1937-04-23 1940-06-27 Benno Schilde Blechstossverbindung
US2945704A (en) * 1957-07-23 1960-07-19 Hughes Aircraft Co Nose section-quick disconnect
DE1173736B (de) * 1960-05-20 1964-07-09 Inst Stahlbau Stossverbindung fuer Geruestrohre od. dgl.
US3345946A (en) * 1960-11-02 1967-10-10 Gen Motors Corp Rocket stage separator
DE1500729A1 (de) * 1966-11-26 1969-06-04 Freytag Franz Juergen UEberlappverbindung fuer Formteile aus Kunststoff
US3572778A (en) * 1969-05-26 1971-03-30 Cassel Thomas Richard Pipe coupling
US3781042A (en) * 1970-09-30 1973-12-25 Raytheon Co Joint having force converting means
US4556591A (en) * 1981-09-25 1985-12-03 The Boeing Company Conductive bonded/bolted joint seals for composite aircraft
DE19615716A1 (de) * 1996-04-22 1997-10-23 Bodenseewerk Geraetetech Rohrverbindung, insbesondere zum Verbinden zweier rohrförmiger Rumpfteile eines Flugkörpers
US5884864A (en) * 1996-09-10 1999-03-23 Raytheon Company Vehicle having a ceramic radome affixed thereto by a compliant metallic transition element

Also Published As

Publication number Publication date
DE19735452C2 (de) 1999-07-22
EP0898146A3 (fr) 1999-05-26
EP0898146A2 (fr) 1999-02-24
US6098928A (en) 2000-08-08
DE59801680D1 (de) 2001-11-15
DE19735452A1 (de) 1999-03-04

Similar Documents

Publication Publication Date Title
DE19735452C2 (de) Rohrverbindung, insbesondere zum Verbinden zweier rohrförmiger Rumpfteile eines Flugkörpers
DE4205063C2 (de) Rohrflansch für ein Kühlmittelrohr
DE102010040419A1 (de) Schellenloser Klemmverband
DE3116289A1 (de) Spanndorn mit einer hydraulisch dehnbaren spannhuelse
EP2478234B1 (fr) Articulation à rotule et feuille lisse pour la rotule
DE102017218016A1 (de) Bolzenanordnung, Verbindungsanordnung und Verfahren zum Demontieren einer Verbindungsanordnung
DE3838935A1 (de) Kupplungsstueck
DE1500942B1 (de) Anwendung einer schnellkupplung bei einer schraubverbindung
EP2882600A1 (fr) Structure de roue d'une automobile
CH663832A5 (de) Rohrschelle zum verbinden zweier rohrenden.
EP0803675B1 (fr) Raccord pour tubes en particulier pour connecter des éléments tubulaires du fuselage d'un corps volant
EP1776539A1 (fr) Bague coupante metallique
DE1231979B (de) Arbeitszylinder fuer Druckmittelanlagen
EP0078048B1 (fr) Elément d'assemblage à jonction détachable pour barres, tuyaux de gauche ou parallèles ou pour éléments analogues
DE3882467T2 (de) Dichtung mit variablen Durchmessern für die Abdichtung zwischen einem äusseren Rohr und inneren Rohren oder Stangen.
DE4206781A1 (de) Nach dem stuelpprinzip arbeitendes deformationselement
WO1982003440A1 (fr) Raccordement etanche de tubes en matiere plastique resistant aux forces de poussee
DE102018127682B4 (de) Anordnung mit einer Justagevorrichtung zur Lageeinstellung zweier miteinander verbundener Bauteile
DE60101708T2 (de) Montagesystem für Komponenten
WO2010124815A1 (fr) Corps cylindrique à base d'une matière synthétique renforcée de fibre
DE2529138A1 (de) Flansch-platten-anordnung, sowie verfahren zu deren herstellung
DE2839761C2 (de) Knoten zur Verbindung mehrerer stabförmiger Elemente
EP0108722A1 (fr) Manchon pour tuyaux
DE102024133180B3 (de) Vorrichtung zur Trennung zweier Raketenstufen
DE19526085A1 (de) Gelenkige Verbindung zweier Rohre einer Abgasanlage

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): DE FR GB IT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 19990422

AKX Designation fees paid

Free format text: DE FR GB IT SE

17Q First examination report despatched

Effective date: 20000823

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT SE

REF Corresponds to:

Ref document number: 59801680

Country of ref document: DE

Date of ref document: 20011115

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20011220

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20150626

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20150923

Year of fee payment: 18

Ref country code: GB

Payment date: 20150721

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20150721

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20150727

Year of fee payment: 18

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 59801680

Country of ref document: DE

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160730

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160801

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170201

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160731

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20170331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160730

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160730