US3789729A - Apparatus and method for the storage and launching of a missile - Google Patents

Apparatus and method for the storage and launching of a missile Download PDF

Info

Publication number
US3789729A
US3789729A US00228577A US3789729DA US3789729A US 3789729 A US3789729 A US 3789729A US 00228577 A US00228577 A US 00228577A US 3789729D A US3789729D A US 3789729DA US 3789729 A US3789729 A US 3789729A
Authority
US
United States
Prior art keywords
shoes
missile
container
rails
central
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
US00228577A
Other languages
English (en)
Inventor
R Aupy
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.)
MINI DEFENSE
MINISTRE D ETAT CHARGE de la DEFENSE NAT DELEGATION FR
Original Assignee
MINI DEFENSE
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 MINI DEFENSE filed Critical MINI DEFENSE
Application granted granted Critical
Publication of US3789729A publication Critical patent/US3789729A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket

Definitions

  • ABSTRACT A container of square or rectangular sections receives [30] F i Application p i Data two slide rails which are fixed therein, the missile Feb 24 1971 France 71 06207 being held in the rails by means of front, central and rear shoes composed of polyurethane foam blocks.
  • the missile rails rear shoes and central shoes are as- 52 US. Cl 89 1.8 91.81 8 5 Int Cl 8 Moldd outside the container andthen inserted inside [58] Field of 1 819 the container whereupon the rails are secured to the container. Covers at the rear and front of the container are made of plastic, the front cover having a [56] References Cited central weak zone which is destroyed under the thrust of the front shoes when the missile is launched.
  • An object of this invention is to provide apparatus for the storage and launching of missiles which allows such drawbacks to be obviated.
  • the invention contemplates the provision of a container of rectangular or square cross-section for the storage and launching of a missile comprising longitudinal rails slidably supporting the missile in the interior of the container, said longitudinal rails being attachable to the walls of said container by quick-disconnect means, and plastic slide shoes arranged between the missile and the rails.
  • the rails and the plastic shoes are arranged in at least two opposed groups.
  • the launching rails are composed of lightweight alloy caissons arranged on opposite sides of the missile.
  • the plastic shoes are each composed of a rear shoe section cemented to the rails so-as to define at the rear of the missile a clear region for receiving a launching connection, a central shoe section entrained by the missile and sliding on thelaunching rails, and a front shoe section entrained by the central shoe.
  • the material of these shoes is a rigid polyurethane foam of a density opproximately equal to 0.12.
  • the container is composed of panels formed of juxtaposed thicknesses of a lightweight alloy and rigid plastic, said panels being joined along their longitudinal edges through the intermediary of hollow corner members.
  • a front cover of the container is made of metallized plastic and is cambered outwardly, presenting a zone of minimum resistance constituting a pre-fragmentation zone which is opened under the thrust of the front shoe section on blast-off.
  • the front shoe section surrounds the front tip of the projectile and is made of at least two portions abutting one another on the axial plane of the container, the portions being seperable from one another so as to allow their separation from the missile on launching.
  • the invention is also directed to a method for mounting the missile in a container as described.
  • the method comprises assembling outside the container: the projectile, the rear and central shoe sections, the rails and the launching plug, then introducing this assembly into the container and securing the rails to the container.
  • FIG. 1 is a longitudinal section taken along line ll-ll in FIG. 2 showing the assembly of a missile in a container;
  • FIG. 2 is a transverse section taken along line 2-2 in FIG. 1;
  • FIG. 3 is a longitudinal section taken along line 3-3 in FIG. 4 showing the container without the missile;
  • FIG. 4 is a transverse section taken along line 4-4 in FIG. 3;
  • FIG. 5 is a longitudinal section taken along line 5-5 in FIG. 6 showing the missile assembly without the container;
  • FIG. 6 is a front view of the missile assembly before introduction into the container
  • FIG. 7 is a longitudinal section taken along line 7-7 in FIG. 8 showing a stage in the introduction of the missile into the container;
  • FIG. 8 is a front view of the assembly in FIG. 7 after introduction into the container;
  • FIG. 9 is an end view of a detachable front brace equipped with rollers
  • FIG. 10 is a front view of the front end of the container
  • FIG. 11 is a section taken along line HH in FIG. 10;
  • FIG. 12 is a front view of a front shoe section; and FIG. 13 is a section taken on line 1313 in FIG. 12.
  • FIG. 1 therein is seen a container 1 for the storage and launching of a missile 2.
  • the container has a rectangular cross-section and is constituted by four panels joined together at the comers. Each panel is composed of juxtaposed thicknesses of a lightweight alloy and a suitable plastic material such as rigid polyurethane foam of a density equal to 0.12. Guide members 7 and rear attachment members 8 are-affixed to the container for a purpose to be described later.
  • a rear cover 9 and a front cover 10 are respectively joined to the container by means of screws.
  • the container is sealed by means of O-rings' 11 at the ends. When assembled, the container is hermetically closed and free of surface roughness or indentations which could promote corrosion.
  • the missile 2 Secured within the container is the missile 2 and its appurtenant structure constituted by guide shoes and launching rails 3.
  • the shoes and launching rails are first assembled with the missile outside the container, and
  • the launching rails 3 are made of unmachined lightweight alloy material and the shoes of a plastic material such as rigid, polyurethane foam of 0.12 density.
  • the guide shoes are constituted of rear sections 4, central sections 5, and a front section 6.
  • the rear sections 4 are fixed to the guide rails 3 by cementing or the like. When the missile is launched, it slides on rear sections 4 of the guide shoes.
  • the rear sections 4 define an open region at the rear of the missile for reception of a launching connection 18 connected to the missile and fixed to one of the rails 3.
  • the central sections 5 are entrained by the missile for travel therewith and slide on rails 3 when the missile is launched.
  • the front section 6 is also slidable on the rails 3 and is entrained by sections 5 when the missile is launched.
  • the front section 6 is formed to surround the tip of the missile as shown in FIG. 1 and the front section 6 is engaged with front cover 10. When the missile is launched, the front section 6 causes the front cover to burst so that the missile can leave the container.
  • the front section 6 is made of two parts 6a, 6b which are in abutment at the median plane of the container.
  • a spring 20 is interposed between parts 6a and 6b to urge the same apart and when the front section leaves the container, the parts 6a and 6b are separated from the inissile by the action of spring 20.
  • the central sections 5 are automatically ejected at the moment the missile exits from the container, their ejection being facilitated by the shape of their front ends.
  • the rear of the missile reaches the front end of the rear section 4 at the instant the rear of the central section reaches the front end of the launching rails 3 so that the missile is freed simultaneously at the front and at the back.
  • the missile is mounted between the launching rails with the rear and central sections sandwiched therebetween.
  • the rails 3 are joined at the rear by a brace 13 which will subsequently be inwardly to allow them to withstand any contingent external overpressures.
  • the covers are made of plastic material which is metallized so as to make them resistant to electromagnetic radiation.
  • Apparatus for the storage and launching of a missile comprising a container, longitudinal metal rails for the slidable support of the missile within the container, said rails being rigidly secured to the container, and front, central and rear sliding shoes disposed between the missile and the rails, said sliding shoes forming a continuous sliding surface, the rear shoes being secured to the rails, the central and front shoes being slidable on said rails, the central shoes being entrained by the missile for sliding on the rails, the front shoes being entrained by the central shoes and traveling with the missile at the time of launch, and a front opening cover on said container, said cover including a zone of least resistance which is capable of opening under the pressure serted in the container to abut and be secured to parts I 8 fixed to the container.
  • a temporary brace 12 (see also FIG. 9) mounted on rollers joins the front ends of the two longitudinal rails.
  • the brace 12 will subsequently be detached inside the container after engagement of the missile assembly therewithin.
  • the launching connection is then connected to the missile and to a control unit.
  • the missile is attached at the rear of the container by means of brittle rods, or rods which can be released by means of a pyrotechnic device.
  • the missile assembly is inserted into the container, by running the rollers of the front brace 12 on slide rails temporarily arranged on thelower panel of the container. These slide rails are dismantled before the closure of the container.
  • the front and rear braces allow a lateral clearance of the rails. Tightening is determined so that the supporting force of the shoes on the missile may have a given value.
  • the guide members 7 fit into corresponding grooves in the rails and the guide members 7 are mounted in elastic supports such as rubber to provide a certain elasticity.
  • the front shoe sections are put in position on the front of the missile.
  • the front and rear covers 9 and 10 are then affixed to the container.
  • the front cover 10 is made of a plastic material and is prefragmented by the formation of grooves therein. This prefragmentation serves to facilitate separation and can be effected as shown in FIGS. 10and 11 or by any other means.
  • the rear cover is similar to the front cover, being merely provided at the center with a circular prefragmentation groove of suitable size.
  • the two covers 9 and 10 are cambered outof the front shoes when the missile is launched, said front shoes loosely surrounding the front tip of the missile, said front shoes being constituted of at least two parts joined along the axial plane of the missile and being separable from the missile upon launching, said shoes being of such length'that the rear of the missile reaches the front of the rear shoes at the same time that the rear of the central shoes reaches the front of the rails so that the missile is simultaneously freed at the front and back.
  • the container is constituted by Stratified panels formed of superposed thicknesses of a lightweight alloy and a rigid plastic foam material, and hollow profile members joining said panels together along the longitudinal edges thereof.
  • front shoes include spring means for separating the two parts of the front shoes when they have exited from the container, said spring means being engaged in said tapered front portions of the front shoes and forward of the front tip of the missile,
  • said front cover is a metallized plastic material which is outwardly curved, said zone of least resistance being formed by the placement of a diametric groove in the cover.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
  • Packaging Of Annular Or Rod-Shaped Articles, Wearing Apparel, Cassettes, Or The Like (AREA)
US00228577A 1971-02-24 1972-02-23 Apparatus and method for the storage and launching of a missile Expired - Lifetime US3789729A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7106207A FR2127109A5 (nl) 1971-02-24 1971-02-24

Publications (1)

Publication Number Publication Date
US3789729A true US3789729A (en) 1974-02-05

Family

ID=9072383

Family Applications (1)

Application Number Title Priority Date Filing Date
US00228577A Expired - Lifetime US3789729A (en) 1971-02-24 1972-02-23 Apparatus and method for the storage and launching of a missile

Country Status (6)

Country Link
US (1) US3789729A (nl)
DE (1) DE2207976A1 (nl)
FR (1) FR2127109A5 (nl)
GB (1) GB1338872A (nl)
IT (1) IT946619B (nl)
SE (1) SE392965B (nl)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5525794A (en) * 1978-08-09 1980-02-23 Gen Dynamics Corp Rear cover of large area for launching tube
US4470336A (en) * 1982-08-05 1984-09-11 General Dynamics, Pomona Division Armored missile launch/shipping container
US4498368A (en) * 1983-10-06 1985-02-12 The United States Of America As Representedby The Secretary Of The Navy Frangible fly through diaphragm for missile launch canister
US4572463A (en) * 1981-09-20 1986-02-25 Aryeh Ashkenazi Telescopic projectile and apparatus for firing same
US4653379A (en) * 1983-07-06 1987-03-31 Commissariat A L'energie Atomique Filament deployment means
US4970937A (en) * 1988-05-20 1990-11-20 British Aerospace Public Limited Company Anti-ice protection for projectiles
JPH0571692U (ja) * 1992-02-12 1993-09-28 株式会社日本製鋼所 ミサイル用キャニスタの前側セルカバー
US5993921A (en) * 1997-03-27 1999-11-30 Lockheed Martin Corporation Device and method for sealing a munition within a canister until munition launch
EP1710530A3 (en) * 2005-04-07 2006-11-22 MBDA ITALIA S.p.A. Housing-transportation-launch assembly for vertical-launch missiles, method of producing such an assembly, and ground missile launcher
US20070175323A1 (en) * 2006-01-30 2007-08-02 Agency For Defense Development Lateral support device system for canister-launched missile
BG65338B1 (bg) * 2002-07-31 2008-02-29 Страхил ГУШЛЕВ Учебно-боен реактивен снаряд и пусково устройствоза изстрелването му
US7624888B1 (en) * 2005-08-15 2009-12-01 The United States Of America As Represented By The Secretary Of The Army Low pressure venting munitions container
US20110072957A1 (en) * 2007-09-24 2011-03-31 Raytheon Company Methods and apparatus for a control surface restraint and release system
US20150101479A1 (en) * 2013-07-25 2015-04-16 Alexander Dankwart Essbaum Rocket launch tower
WO2016113463A1 (en) * 2015-01-14 2016-07-21 Surma Oy A mine storage and handling unit
US20180216912A1 (en) * 2015-08-05 2018-08-02 Mbda France Flexible cover for a missile container
CN108534602A (zh) * 2018-05-29 2018-09-14 湖北三江航天万峰科技发展有限公司 小口径发射箱双v型导轨的调试方法及其装调机构
US11236969B2 (en) * 2018-09-07 2022-02-01 Mitsubishi Heavy Industries, Ltd. Launch tube and method of launching flying object

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2188713B (en) * 1984-05-04 1988-05-25 British Aerospace Missile storage and launch arrangements
DE19643829A1 (de) * 1996-10-30 1998-05-07 Wegmann & Co Gmbh Abschußvorrichtung für selbstangetriebene Flugkörper, insbesondere Artillerieraketen
RU2460030C1 (ru) * 2011-04-01 2012-08-27 Открытое акционерное общество "Конструкторское бюро специального машиностроения" Корабельный контейнер для хранения и пуска ракеты
CN105910492B (zh) * 2016-04-15 2017-10-24 中国运载火箭技术研究院 一种有翼导弹垂直热发射内圆外方形同心筒结构
CN113237395B (zh) * 2021-04-26 2022-11-08 上海机电工程研究所 基于杠杆机构的固弹装置

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2817272A (en) * 1951-05-10 1957-12-24 Dwight F Gunder Rocket launcher
US3135162A (en) * 1961-11-27 1964-06-02 Kamalian Neubar Water-borne missile launcher
US3140638A (en) * 1962-07-27 1964-07-14 Hawley Products Co Fairing
US3160062A (en) * 1964-12-08 Flexible foam support
US3225655A (en) * 1964-05-25 1965-12-28 Gen Dynamics Corp Controlled tip-off launcher
US3610095A (en) * 1967-06-29 1971-10-05 Us Army Rocket means for driving a free punch

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3160062A (en) * 1964-12-08 Flexible foam support
US2817272A (en) * 1951-05-10 1957-12-24 Dwight F Gunder Rocket launcher
US3135162A (en) * 1961-11-27 1964-06-02 Kamalian Neubar Water-borne missile launcher
US3140638A (en) * 1962-07-27 1964-07-14 Hawley Products Co Fairing
US3225655A (en) * 1964-05-25 1965-12-28 Gen Dynamics Corp Controlled tip-off launcher
US3610095A (en) * 1967-06-29 1971-10-05 Us Army Rocket means for driving a free punch

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5525794A (en) * 1978-08-09 1980-02-23 Gen Dynamics Corp Rear cover of large area for launching tube
JPS5914720B2 (ja) * 1978-08-09 1984-04-05 ジエネラル ダイナミツクス コ−ポレ−シヨン 反動推進式ビ−クル用発射組立体
US4572463A (en) * 1981-09-20 1986-02-25 Aryeh Ashkenazi Telescopic projectile and apparatus for firing same
US4470336A (en) * 1982-08-05 1984-09-11 General Dynamics, Pomona Division Armored missile launch/shipping container
US4653379A (en) * 1983-07-06 1987-03-31 Commissariat A L'energie Atomique Filament deployment means
US4498368A (en) * 1983-10-06 1985-02-12 The United States Of America As Representedby The Secretary Of The Navy Frangible fly through diaphragm for missile launch canister
US4970937A (en) * 1988-05-20 1990-11-20 British Aerospace Public Limited Company Anti-ice protection for projectiles
JPH0571692U (ja) * 1992-02-12 1993-09-28 株式会社日本製鋼所 ミサイル用キャニスタの前側セルカバー
US5993921A (en) * 1997-03-27 1999-11-30 Lockheed Martin Corporation Device and method for sealing a munition within a canister until munition launch
BG65338B1 (bg) * 2002-07-31 2008-02-29 Страхил ГУШЛЕВ Учебно-боен реактивен снаряд и пусково устройствоза изстрелването му
EP1710530A3 (en) * 2005-04-07 2006-11-22 MBDA ITALIA S.p.A. Housing-transportation-launch assembly for vertical-launch missiles, method of producing such an assembly, and ground missile launcher
US7891281B2 (en) 2005-04-07 2011-02-22 Mbda Italia S.P.A. Housing-transportation-launch assembly and method
US20100236391A1 (en) * 2005-04-07 2010-09-23 Mbda Italia S.P.A. Housing-transportation-launch assembly for vertical-launch missiles, method of producing such an assembly, and ground missile launcher
US7624888B1 (en) * 2005-08-15 2009-12-01 The United States Of America As Represented By The Secretary Of The Army Low pressure venting munitions container
US7665395B2 (en) * 2006-01-30 2010-02-23 Agency For Defense Development Lateral support device system for canister-launched missile
US20070175323A1 (en) * 2006-01-30 2007-08-02 Agency For Defense Development Lateral support device system for canister-launched missile
US20110072957A1 (en) * 2007-09-24 2011-03-31 Raytheon Company Methods and apparatus for a control surface restraint and release system
US8342070B2 (en) * 2007-09-24 2013-01-01 Raytheon Company Methods and apparatus for a control surface restraint and release system
US20150101479A1 (en) * 2013-07-25 2015-04-16 Alexander Dankwart Essbaum Rocket launch tower
US9074844B2 (en) * 2013-07-25 2015-07-07 Alexander Dankwart Essbaum Rocket launch tower
WO2016113463A1 (en) * 2015-01-14 2016-07-21 Surma Oy A mine storage and handling unit
US20180216912A1 (en) * 2015-08-05 2018-08-02 Mbda France Flexible cover for a missile container
US10584938B2 (en) * 2015-08-05 2020-03-10 Mbda France Flexible cover for a missile container
CN108534602A (zh) * 2018-05-29 2018-09-14 湖北三江航天万峰科技发展有限公司 小口径发射箱双v型导轨的调试方法及其装调机构
US11236969B2 (en) * 2018-09-07 2022-02-01 Mitsubishi Heavy Industries, Ltd. Launch tube and method of launching flying object

Also Published As

Publication number Publication date
GB1338872A (en) 1973-11-28
FR2127109A5 (nl) 1972-10-13
SE392965B (sv) 1977-04-25
DE2207976A1 (de) 1972-11-09
IT946619B (it) 1973-05-21

Similar Documents

Publication Publication Date Title
US3789729A (en) Apparatus and method for the storage and launching of a missile
SE7902890L (sv) Speciellt for utbildningsendamal anvendbar ovningsgranat
DE3666101D1 (en) Hollow charge training projectile
GB1353338A (en) Rocket vehicle
ES8603071A1 (es) Proyectil subcalibrado estabilizado de multiples aplicaciones.
GB2123934B (en) Electromagnetic projectile launcher with explosive-start and plasma drive
JPS5883199A (ja) 飛翔体
WALTERS et al. High velocity penetration of a Kevlar reinforced laminate
FR2435016A1 (fr) Tete de combat a projectiles secondaires places dans un tube de lancement
GB460842A (en) Improvements in and relating to projectiles
ES2038396T3 (es) Metodo de lanzamiento de una carga util secundaria.
FR2506923A1 (fr) Charge explosive
SE8300664D0 (sv) Drivladdningsdel
Charters The early years of aerodynamics ranges, light-gas guns, and high-velocity impact
DE55041C (de) Sprenggeschofs mit leicht zerstörbarer Wandung
CN219678866U (zh) 一种多席位模拟训练专用机柜结构
FR2534681B1 (fr) Perfectionnements apportes aux systemes d'armes lanceurs de projectiles, notamment aux charges propulsives et a la balistique interieure
DE102011016845A1 (de) Atombombenantrieb für Raumschiffe
GB2072309A (en) Small arms ammunition
Simon et al. High-performance gun projectors of 20-50 mm calibre for laboratory experiments
KR200394279Y1 (ko) 교육용 모형 총통화차 및 그 조립 키트
PILIUGIN et al. Study of the gas at and behind hypersonic bodies performed at aeroballistic ranges
Snyder Caltech's Other Rocket Project: Personal Recollections
IL66902A (en) Sub calibre projectile in which part of the propelling charge serves as a tightening means
RU2150657C1 (ru) Корабельная пусковая система