US3011405A - Launching support for rocket-propelled missiles - Google Patents

Launching support for rocket-propelled missiles Download PDF

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Publication number
US3011405A
US3011405A US266A US26660A US3011405A US 3011405 A US3011405 A US 3011405A US 266 A US266 A US 266A US 26660 A US26660 A US 26660A US 3011405 A US3011405 A US 3011405A
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US
United States
Prior art keywords
missile
latch
link
rocket
shear pin
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
US266A
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English (en)
Inventor
Moss Gerard
Lundy Arthur Joseph
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
HARLAND Ltd
Original Assignee
Short Brothers PLC
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 PLC, HARLAND Ltd filed Critical Short Brothers PLC
Application granted granted Critical
Publication of US3011405A publication Critical patent/US3011405A/en
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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
    • 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

Definitions

  • the invention is concerned with launching supports for rocket-propelled missiles, and particularly though not exclusively to supports such as are described in the copending United States application of Richard Sutton Ransom serially numbered 793,840 filed February 17, 1959, wherein the missile is connected to a rigid basemember by a link incorporating a shear pin which, when the propulsion rocket is fired, immediately severs to release the missile.
  • the object of the present invention is to provide in conjunction with such a shear pin an improved arrangement by which (a) in the event of inadvertent firing of the rocket motor whilst in store, flight of the missile from its support is prevented, (b) the shear pin is protected from undue shock loads until the missile is fired deliberately, and (c) the rocket motor blast may be utilised to release the mechanism protecting the shear pin as aforesaid, when the missile is mounted upon the launching support.
  • a missile launching support in accordance with this invention comprises a beam for suspensory attachment to the missile and adapted to be mounted on a launcher platform, a link for connecting the after end of the missile to the rear end of the beam and incorporating a shear pin, a latch pivoted on the link and movable to a safety position in which the tensile and/ or compressive loads in the link are taken by the latch and by-pass the shear pin, a locking member normally adapted to hold the latch in the safety position, and release means for releasing said locking member to free the latch when the missile is positioned on the launcher platform ready for firing.
  • Said latch is preferably provided with an off-set portion positioned to receive the missile motor blast on firing and re-act to disengage the latch so that the shear pin sustains the full thrust load due to combustion of the rocket charge.
  • FIG. 1 is a part cut-away side elevation of a combined container and missile launcher support according to the. invention
  • FIG. 2 is a cross-section of a part of the apparatus in FIG. 1, showing an attachment for the missile, and
  • FIG. 3 is a plan view of the link forming part of the attachment shown in FIG. 2.
  • the apparatus shown includes a container 11, the purpose of which is to afford protection for a missile 12 during stowage, and which may be retained in position when the missile is transported to the launching site and also when it is actually mounted upon the platform of the launching apparatus.
  • the container 11 incorporates a cantilever beam 13 disposed longitudinally of the missile 12, having at one end (not shown) a depending attachment from which the missile may be suspended at a point in the region of the centre of gravity thereof, and-provided at the-rear end with a base-plate 14 by which the beam and container assembly may be rigidly attached to the platform of the launching apparatus.
  • the base-plate 14 is formed with an aperture lug 15 arranged to receive and constitute an anchorage for the rear extremity of a tension link 16, the forward extremity of which is connected to a suitably robust part 17 of the tail of the missile.
  • the connections of the link 16 at both ends preferably include ball-and-socket joints 18 and 19 permitting a sufficient degree of angular freedom to facilitate the alignment of the parts during assembly.
  • the tension link 16 is composed of two parts 20 and 21 joined end to end by a ivot pin 22 which is of such cross-sectional dimensions and material as to render it'capable of serving as a shear pin which, whilst being capable of supporting the static load of the missile 12 on the base-plate 14, will automatically shear and free the missile 12 from its anchorage to the base-plate 14 when subjected to the thrust load of the rocket motor on firing.
  • a latch lever 23 Mounted on the after part 21 of the tension link 16, with capability of rotation about an axis perpendicular to the length of the tension link 16, is a latch lever 23 which is fashioned with a hook 24 (see FIG. 3) arranged to engage about a boss 25 provided on the part 20 of link 16 and concentric with the shear pin 22 on each side of the link part 20.
  • the latch lever 23 When the latch lever 23 is engaged, as shown, the shear pin 22 is relieved of its load, and the latch lever 23 can be locked in this position by a locking lever 26 which normally engages an abutment 27 on the latch lever 23 so as to prevent the same from rotation.
  • the latch lever 23 also carries an arm 28 upon which is formed a flat surface, referred to as the palm, which depends opposite the efliux nozzle of the missile motor, so as to receive the full blast thereof when the missile is discharged.
  • the latch lever 23 is preferably mounted upon an eccentric stud 29 which can be rotated for the purpose hereinafter described.
  • the locking lever 26 is pivotally mounted upon an offset part 30 of the tension link and its extremity is coupled to a spring-loaded plunger 31 which is slidably mounted in a part 32 of the base-plate 14.
  • a spring-pressed ball catch 33 is mounted in the tension link and arranged to bear against an arcuate camlike face of the latch lever 23, said face being recessed to receive the ball attwo angularly spaced points which a respectively register with said ball catch (a) when the latch lever 23 is in the locked position above referred to, and (b) when the latch lever is rotated into an inoperative position.
  • the spring loaded plunger 31 When the missile is placed into its container 11, to be supported by the cantilever beam 13 associated herewith, the spring loaded plunger 31 is pressed against the action of its spring so as'to rotate the locking lever 26 out of the locking position.
  • the latch lever 23 is now free to be rotated into an inoperative position, where it is yieldably held by the ball catch 33.
  • the assembly is capable of transmitting tension loads between the missile 12 and the baseplate 14 without loading the shear pin 22, and during stowage the assembly is intended to remain locked in this condition.
  • the rocket motor be fired inadvertently during stowage, movement of the latch lever 23 is prevented by the locking lever 26, which can only be disengaged by a deliberate retraction of the springloaded plunger 31 with which the locking lever 26 is connected.
  • the shear pin 22 remains by-passed through the latch lever 23 and is protected against the rocket thrust load.
  • the assembly When mounted on the launching platform, the assembly is automatically unlocked by the presence of a fixed pin 40 (shown in broken lines in FIGURE 2) located on said platform against the end of the spring-loaded plunger 31, causing this to be retracted and thereby releasing the locking lever 26 from locking engagement with the latch lever 23.
  • the blast from the rocket motor on firing reacts against the palm 28 of the latch lever 23, causing the latch lever 23 to'be rotated into a position in which its hook 24 is disengaged from the tension link boss 25 and the shear pin 22 is subjected to the full thrust load on the missile of the rocket motor.
  • the shear pin 22 is severed and the missile freed to move under the propulsive effect of the rocket.
  • the spring-loaded plunger 31 is released and the locking lever 26 is restored to the position in which the latch lever 23 is locked against movement, so that the shear pin 22 being by-passed again, it is safe to remove the missile 12 with the container.
  • the link assembly may be adapted to sustain compression loads as Well as tension loads by substituting a rigid connection to the missile for the ball-and-socket joints hereinbefore referred to, and providing an eccentric screw to draw the missile eyebolt against an abutment; in this arrangement the shear pin would require a large degree of clearance to enable the required adjustment to be made without pre-loading the shear pin.
  • a missile launching support adapted to carry a rocket propelled missile and be mounted on a launcher platform
  • the improvement comprising: a beam for suspensory attachment of the missile; a link member for connecting the after end of the missile to the rear end of the beam, said link comprising a first part, a second part, and a shear pin connecting said first part to said second part; latch means detachably connecting said first part to said second part of said link whereby loads implied through said link by-pass said shear pin; locking means normally locking said last-mentioned latch means in a safety position when assuming the loads applied through said link; and release means for releasing said locking means from said latch means when the missile is positioned on the launcher platform for firing whereby said latch means may be released from connecting said first part to said second part of said link.
  • a missile launching support of the character described in claim 1 including means on said latch means operable by a blast of said missile for releasing said latch means from connecting said first part to said second part of said link.
  • said latch means includes a latch pivotally connected to one of said first and second parts, said latch having a hook on its free end, and an enlarge ment on the other of said first and second parts about which the hook of said latch engages to detachably connect said first and second parts of said link.
  • a missile launching support of the character described in claim 4 wherein said enlargement on the other of said parts is arranged concentric with said shear pin connecting said first and second parts together.
  • a launching support of the character described in claim 1 including an eccentric pin carried by one of said first and second parts, and wherein said latch means includes a. latch pivotally connected on said eccentric pin, said latch having a hook at its free end, and an enlargement on the other of said first and second parts about which the hook of said latch engages to detachably connect said first and second parts of said link, said eccentric pin being pivotable with respect to said latch whereby any clearance between the hook of said latch and the enlargement may be taken up.
  • a missile launching supporting adapted to carry a rocket propelled missile and be mounted on a launcher platform, the improvement comprising: a container; a beam mounted on one end of said container for suspensory attachment of the missile within. the container; a link member for connecting the after end of the missile to the rear end of the beam, said link comprising a first part, a second part, and a shear pin connecting said first part to said second part; latch means detachably connecting said first part to said second part of said link whereby loads implied through said links by-pass said shear pin; locking means normally locking said last-mentioned latch means in a safety position when assuming the loads applied through said link; and release means for releasing said locking means from said latch means when the missile is in position on the launcher platform for firing whereby said latch means may be released from connecting said first part to said second part of said link, said release means being carried Within said container and operable from outside of said container.
  • a missile launching support adapted to carry a rocket propelled missile and be mounted on alauncher platform, the improvement comprising: a beam for suspensory attachment of the missile; a link member for connecting the after end of the missile to the rear end of the beam, said link comprising a first part, a second part, and a shear pin connecting said first part to said second part; latch means detachably connecting said first pant to said second part of said link whereby loads implied through said link by-pass said shear pin; said latch means including a latch element pivotally connected to one of said first and second parts and having a hook on its free end, and an enlargement on the other of said first and second parts about which said hook.
  • said last-mentioned means including an offset portion on said latch positioned to receive and be moved by the blast of said missile on firing whereby the latch is disengaged from the enlargement so that the shear pin sustains full thrust of the load on said link.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Pinball Game Machines (AREA)
US266A 1959-01-22 1960-01-04 Launching support for rocket-propelled missiles Expired - Lifetime US3011405A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB248959 1959-01-22

Publications (1)

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US3011405A true US3011405A (en) 1961-12-05

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US266A Expired - Lifetime US3011405A (en) 1959-01-22 1960-01-04 Launching support for rocket-propelled missiles

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US (1) US3011405A (en))
CH (1) CH387489A (en))
DE (1) DE1142531B (en))
FR (1) FR1245965A (en))
GB (1) GB859228A (en))
NL (2) NL247342A (en))

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3296929A (en) * 1963-10-16 1967-01-10 Bofors Ab Missiles
US3345946A (en) * 1960-11-02 1967-10-10 Gen Motors Corp Rocket stage separator
US5056407A (en) * 1989-11-09 1991-10-15 Dynamit Nobel Ag Rocket retainer in a launching device
US5098236A (en) * 1989-12-14 1992-03-24 Messerschmitt-Bolkow-Blohm Gmbh Arrangement for bracing a load
FR2786860A1 (fr) * 1998-12-08 2000-06-09 Agency Defense Dev Dispositif de retenue et de deverrouillage d'un projectile utilisant une sphere rigide

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1294265B (de) * 1962-11-29 1969-04-30 Mb Associates Corp Handraketenabschussvorrichtung
CH485008A (de) * 1967-11-03 1970-01-31 Geigy Ag J R Verfahren zur Herstellung farbstarker, transparenter Perylen-Pigmente

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2440723A (en) * 1945-06-06 1948-05-04 United Shoe Machinery Corp Apparatus for launching rockets from airplanes
US2925013A (en) * 1956-05-01 1960-02-16 North American Aviation Inc Rocket engine assembly testing and launching apparatus

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE727060C (de) * 1935-03-23 1942-10-26 Donar Ges M B H Fuer Appbau Startvorrichtung fuer Raketen
DE1031684B (de) 1941-09-09 1958-06-04 Wasagchemie Ag Verfahren zur Erhoehung der Treffsicherheit von Raketen oder raketenaehnlichen Geschossen
CH318703A (de) * 1952-05-06 1957-01-15 Brevin Ag An einer Startvorrichtung aufgehängte Rakete
NL94105C (en)) * 1952-05-06

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2440723A (en) * 1945-06-06 1948-05-04 United Shoe Machinery Corp Apparatus for launching rockets from airplanes
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
US3345946A (en) * 1960-11-02 1967-10-10 Gen Motors Corp Rocket stage separator
US3296929A (en) * 1963-10-16 1967-01-10 Bofors Ab Missiles
US5056407A (en) * 1989-11-09 1991-10-15 Dynamit Nobel Ag Rocket retainer in a launching device
US5098236A (en) * 1989-12-14 1992-03-24 Messerschmitt-Bolkow-Blohm Gmbh Arrangement for bracing a load
FR2786860A1 (fr) * 1998-12-08 2000-06-09 Agency Defense Dev Dispositif de retenue et de deverrouillage d'un projectile utilisant une sphere rigide

Also Published As

Publication number Publication date
CH387489A (de) 1965-01-31
DE1142531B (de) 1963-01-17
FR1245965A (fr) 1960-11-10
GB859228A (en))
NL247342A (en))
NL107514C (en))

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