US3015992A - Launching means for rocket-propelled missiles - Google Patents

Launching means for rocket-propelled missiles Download PDF

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Publication number
US3015992A
US3015992A US793840A US79384059A US3015992A US 3015992 A US3015992 A US 3015992A US 793840 A US793840 A US 793840A US 79384059 A US79384059 A US 79384059A US 3015992 A US3015992 A US 3015992A
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US
United States
Prior art keywords
missile
rocket
launching
launching means
tail
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
US793840A
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English (en)
Inventor
Ransom Richard Sutton
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.)
Short Brothers PLC
Original Assignee
Short Brothers and Harland Ltd
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 Short Brothers and Harland Ltd filed Critical Short Brothers and Harland Ltd
Application granted granted Critical
Publication of US3015992A publication Critical patent/US3015992A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F41F3/052—Means for securing the rocket in the launching apparatus
    • 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

  • the invention relates to rocket-propelled missiles, particularly though not exclusively such missiles as are provided with individual containers which will afford protection against damage in transport or during storage, or due to adverse climatic conditions, and of which the section enclosing the after end of the missile incorporates means by which the missile may be mounted on a launching support.
  • the object of this invention is to provide improved means for supporting the tail of the missile upon a launching platform preparatory to discharge.
  • the invention provides a rigid base.- member which is adapted for connection to the launching platform, said base-member being provided on its inner face with a plurality of spaced lugs arranged to engage correspondingly spaced projections on the missile tail and thereby to locate the missile in the correct position for launching, and a single link attachment between anchorages respectively on the missile and said base-member at positions off-set from the longitudinal axis of the former, said link incorporating a shear pin which, when the propulsion rocket is fired, will immediately sever to release the missile.
  • FIG. 1 is a longitudinal elevation of a missile together with its container and launcher attachment
  • FIG. 2 is a fragmentary elevation of the rear of the base-member
  • FIG. 3 is a detail of the link attachment drawn to a larger scale.
  • the base member of the means by which the tail of the missile is supported upon the launching platform takes the form of the aluminium alloy disc 10, which isprovided on its outer face with a plastic end closure panel 11, and a plurality of slotted lugs 12, 12 by which the basemember is secured to similarly disposed projections provided upon the launching platform.
  • Spaced equiangularly about the centre of the panel 11 on the inner face are a number of recessed bosses 13 which are adapted to receive a correspondingly arranged set of rearwardly extending projections 14 on the tail 15 of the missile, the body of which is outlined in chain-dotted lines 16.
  • the panel 11 is adapted to be blown out of its mounting by the thrust of the efiiux gases when the rocket is discharged.
  • the missile is positively attached to the disc by means of a link which takes the form of a bolt 17, the head of which is passed through a countersunk hole 101 in the disc and having its shank threaded into a socket 18 which is pivotally connected by a shear pin 19 to 2.
  • lug 20 on the missile tail 15, the bolt-hole 101 in the disc 10 and the tail lug 20 being off-set from the longitudinal axis of the missile, such that the direction of the breaking force on the shear pin 19 lies in a plane containing the centreof-gr-avity of the missile the position of which is indicated at 161 of FIG. 1.
  • the arrangement, of said bosses 13 is symmetrical in relation to the longitudinal 3,015,992 Patented Jan. 9, 1962 axis of the missile, such that when the missile is held by said link 17, 18 with its projections 14 seated firmly against the saidbosses 13, the missile is located correctly for launching.
  • the missile When the rocketis ignited, the missile tends to pivot slightly about the most heavily loaded locating boss 13, and the consequent increase in tension on said link 17, 18 overcomes the shear strength of the pin 19, so that the connection is severed and the missile is free. It should be noted that the recesses in the bosses 13 which engage with the locating projections 14 on the missile are so shaped that no support for the missile is provided after the shear pin 19 is fractured.
  • the base disc 10 may be made as an integral part of a container for the missile, as shown in FIG. I.
  • Said container comprises a casing 21 for enclosing the after part of the missile, which casing 21 is attached at its rear end to the periphery of said disc 10, and a fore-end casing 22 which is attached by suitable releasable fasteners at 2211 to the forward end of the casing 21.
  • Said casing 22 incorporates rigid hoops 222, 223 upon which the missile and its container may be rolled during stowage, a lifting lug 224, and handles 225. In the forward end of the easing 22 the nose of the missile rests upon a shock-absorbing pad 23.
  • Container for storing or launching a rocket propelled missile which is adapted to be connected to a launching platform, the missile having a tail with spaced projections, comprising: a casing for retaining the missile, a base member joined to the rearward end of said casing, said base member including a plurality of slotted lugs extending rearwardly therefrom for engagement with a launching platform, and further including a longitudinal aperture therethrough for expelling exhaust gases, a blowout panel operatively secured to the rearward end of said base member, a plurality of lugs disposed on the innersurface of said base member and arranged to engage the correspondingly spaced projections on the missile tail to thereby locate the missile in correct position for launching, means carried by said base member for releasably attaching the missile to said base member at one point, said attachment means being disposed on an axis ofiset from the longitudinal axis of the missile and including a shear pin so that when the propulsion rocket is discharged, said shear pin will be severed
  • said attachment means comprises: means defining a' counter sunk hole in said base member offset from the longitudinal axis of said missile, bolt means disposed in said counter sunk hole and socket means .threadably engaged with the bolt means and adapted to be pivotally secured to the lug at the tail of the missile by the shear pin at a position offset from the longitudinal axis of the missile.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Pallets (AREA)
US793840A 1958-02-25 1959-02-17 Launching means for rocket-propelled missiles Expired - Lifetime US3015992A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB6055/58A GB843038A (en) 1958-02-25 1958-02-25 Improved launching means for rocket-propelled missiles

Publications (1)

Publication Number Publication Date
US3015992A true US3015992A (en) 1962-01-09

Family

ID=9807591

Family Applications (1)

Application Number Title Priority Date Filing Date
US793840A Expired - Lifetime US3015992A (en) 1958-02-25 1959-02-17 Launching means for rocket-propelled missiles

Country Status (5)

Country Link
US (1) US3015992A (de)
CH (1) CH376030A (de)
DE (1) DE1150908B (de)
FR (1) FR1225140A (de)
GB (1) GB843038A (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3072022A (en) * 1961-10-30 1963-01-08 Davis M Wood Missile container suspension system
US3145619A (en) * 1961-05-15 1964-08-25 Ozanne Jean-Claude Rocket package assembly
US3251301A (en) * 1962-09-12 1966-05-17 Lockheed Aircraft Corp Missile and launcher system
US3296929A (en) * 1963-10-16 1967-01-10 Bofors Ab Missiles

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2530331B1 (fr) * 1982-07-16 1986-12-26 Europ Propulsion Munition pour arme de tir sans recul
GB8920960D0 (en) * 1989-09-15 1990-04-25 Short Brothers Plc A missile weapon system
DE3940468A1 (de) * 1989-12-07 1991-06-13 Telefunken Systemtechnik Kappe fuer eine raketenaustrittsoeffnung

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1524273A (en) * 1917-11-17 1925-01-27 Newton Henry Trench mortar and the like
FR914341A (fr) * 1945-04-16 1946-10-04 Controles Ind Et Perfectionnements apportés aux matériels de tir pour projectiles automoteurs
US2421752A (en) * 1943-02-22 1947-06-10 Eureka Williams Corp Rocket projectile
GB732601A (en) * 1952-05-29 1955-06-29 Bendix Aviat Corp Solid propellant apparatus
CH316189A (de) * 1953-05-07 1956-09-30 Schoenenberger Paul Rakete mit Abschusseinrichtung für dieselbe
US2792756A (en) * 1952-05-06 1957-05-21 Brevin A G Soc Rocket launching support structure
US2925013A (en) * 1956-05-01 1960-02-16 North American Aviation Inc Rocket engine assembly testing and launching apparatus

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE458941C (de) * 1926-03-09 1928-04-26 Rheinische Metallw & Maschf Behaelter fuer Geschuetzmunition

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1524273A (en) * 1917-11-17 1925-01-27 Newton Henry Trench mortar and the like
US2421752A (en) * 1943-02-22 1947-06-10 Eureka Williams Corp Rocket projectile
FR914341A (fr) * 1945-04-16 1946-10-04 Controles Ind Et Perfectionnements apportés aux matériels de tir pour projectiles automoteurs
US2792756A (en) * 1952-05-06 1957-05-21 Brevin A G Soc Rocket launching support structure
GB732601A (en) * 1952-05-29 1955-06-29 Bendix Aviat Corp Solid propellant apparatus
CH316189A (de) * 1953-05-07 1956-09-30 Schoenenberger Paul Rakete mit Abschusseinrichtung für dieselbe
US2925013A (en) * 1956-05-01 1960-02-16 North American Aviation Inc Rocket engine assembly testing and launching apparatus

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3145619A (en) * 1961-05-15 1964-08-25 Ozanne Jean-Claude Rocket package assembly
DE1204973B (de) * 1961-05-15 1965-11-11 Jean Claude Ozanne Packkasten fuer selbstangetriebene Flugkoerper
US3072022A (en) * 1961-10-30 1963-01-08 Davis M Wood Missile container suspension system
US3251301A (en) * 1962-09-12 1966-05-17 Lockheed Aircraft Corp Missile and launcher system
US3296929A (en) * 1963-10-16 1967-01-10 Bofors Ab Missiles

Also Published As

Publication number Publication date
GB843038A (en) 1960-08-04
CH376030A (de) 1964-03-15
FR1225140A (fr) 1960-06-29
DE1150908B (de) 1963-06-27

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