US3296929A - Missiles - Google Patents

Missiles Download PDF

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Publication number
US3296929A
US3296929A US396869A US39686964A US3296929A US 3296929 A US3296929 A US 3296929A US 396869 A US396869 A US 396869A US 39686964 A US39686964 A US 39686964A US 3296929 A US3296929 A US 3296929A
Authority
US
United States
Prior art keywords
missile
locking
box
strip
release
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
US396869A
Other languages
English (en)
Inventor
Jacobson Gunnar
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Application granted granted Critical
Publication of US3296929A publication Critical patent/US3296929A/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
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • 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
    • 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 present invention relates to an improvement in a missile which, is disposed in a portable box which serves both as a support for the missile during transport and as i r a barrel forlaunching the missile.
  • a broad object of the invention is to provide a simple and reliable device for mounting the missile in the box
  • FIGAJ. shows a perspective View of the missile disposed FIG.; 2 shows a perspective view, with parts broken 3 away,f the rear end of the box; and
  • FIG. 3 illustratesthe function of the device when the missile is launched.
  • the missile 1 is shown dis- V posed in an elongate box 2, which is suitably provided withmcarrying means to enable it to be carried on the back of a person.
  • the box 2 is also intended to support and guide the missile when it is launched and for this purpose .it should suitably be provided with means for placing it in a suitable position for launching.
  • the box 2 has zafront .cover 3 and a rear cover 4 which are removed when the missile is made ready for launching.
  • the missile l is secured in the box 2 only at its rear end.
  • the means for this purpose are provided in a frame, structure or back piece 5 which is attached to the walls of the box by brackets. 6.
  • the back piece 5 also carries two bars 7 whichserve to carry electrical conductors extending to the missile for transmitting electric signals for its guidance.
  • the back, piece 5 carries a hinged strap comprising upperand; lower links .8 and 9 respectively and a joining rear. strip 10. which is hingedly connected to the rear ends of the links 8 and 9 at 11 and 12 respectively.
  • the links 81and9 arepivotally attached by means of pivots 13, 14 to two plates 15, 16 carried by the back piece 5.
  • the links 8 and 9 carry studs 17, 18,; which. are directed toward each other and in the mounting position enter holes 19,20 in the rear end 31 of the missile, said end forming anexhaust nozzle for the starting motor of the missile.
  • the links 8 and 9 carry studs 17, 18,; which. are directed toward each other and in the mounting position enter holes 19,20 in the rear end 31 of the missile, said end forming anexhaust nozzle for the starting motor of the missile.
  • the. length of the strip. is such that in this position, the links 8, 9 diverge slightly at the ends adjacent to strip 10.
  • the missile When the missile is to be launched, its starting rocket motor is started and the combustion gases thereof flow out backwardly as shown with arrows in FIGURE 3.
  • the strip 10 while sufficiently rigid to retain its shape under normal stresses occurring in transport and handling, is sufficiently flexible to be bent out rearwardly by the pressure of the gases, as shown in FIGURE 3. Thereby, the rear ends of the links 8, 9 will be pulled closer together, which results in their front ends bearing studs 17 and 18 being moved further apart, so that the studs are Withdrawn from the holes 19, 20, whereby the missile is released.
  • the hinged strap 8, 9, 10 gives the missile a limited desired freedom of movement within the box in the vertical direction.
  • a corresponding freedom of movement in the transverse direction is obtained by the studs 13, 14 having such length that they can be displaced slightly axially with respect to the plates 15, 16.
  • a device for securing a rocket-type missile in a box constituting a support for the missile when in transport and a launching barrel for the missile comprising releasable locking means for locking the box and a missile therein to each other, said locking means including two locking members pivotally mounted within the 'box on opposite sides thereof in reference to the lengthwise position of the missile, each of said locking members being pivotal into and out of locking engagement with the body of the missile and a release means for pivoting said locking means from the locking position into the release position, said release means including a flexible strip secured at each end to one of said locking members and extending across the path of gases generated by the missile when launched, said strip having an initial effective length such that the two locking members are held in locking engagement and being deformable by the impact of the gases into a curved configuration in which the effective length of the strip between the locking members is reduced to a length such that the locking members are pivoted out of locking engagement with the body of the missile.
  • each of said locking members comprising a two-arm lever pivotally mounted on the frame structure, one arm of each of said levers being engageable with the body of the missile and the other being secured to the respective end of the strip.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
US396869A 1963-10-16 1964-09-16 Missiles Expired - Lifetime US3296929A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE1137063 1963-10-16

Publications (1)

Publication Number Publication Date
US3296929A true US3296929A (en) 1967-01-10

Family

ID=20293839

Family Applications (1)

Application Number Title Priority Date Filing Date
US396869A Expired - Lifetime US3296929A (en) 1963-10-16 1964-09-16 Missiles

Country Status (10)

Country Link
US (1) US3296929A (da)
AT (1) AT248290B (da)
BE (1) BE653451A (da)
CH (1) CH415363A (da)
DE (1) DE1256112B (da)
DK (1) DK115382B (da)
FI (1) FI41624C (da)
FR (1) FR1426177A (da)
GB (1) GB1028057A (da)
NL (1) NL6411556A (da)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3769876A (en) * 1972-08-02 1973-11-06 Us Navy Missile launching canister
US4012988A (en) * 1976-06-07 1977-03-22 The United States Of America As Represented By The Secretary Of The Army Mechanical fly-away latching mechanism
US4080868A (en) * 1977-02-25 1978-03-28 Lockheed Corporation Support and retention mechanism for missiles in launchers
US4132150A (en) * 1977-08-08 1979-01-02 The Unites States Of America As Represented By The Secretary Of The Army Blast actuated detent
US4191087A (en) * 1978-08-14 1980-03-04 The United States Of America As Represented By The Secretary Of The Army Rocket detent and release mechanism
WO1980001411A1 (en) * 1978-12-29 1980-07-10 Hughes Aircraft Co Automatic blast actuated positive release missile detent
US4304170A (en) * 1979-04-16 1981-12-08 The Boeing Company Locking assembly for a rocket and launch tube
US4358983A (en) * 1978-12-26 1982-11-16 Hughes Aircraft Company Blast enabled missile detent/release mechanism
US4550640A (en) * 1983-09-16 1985-11-05 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Missile canister restraint device
US5714708A (en) * 1995-09-29 1998-02-03 Agency For Defense Development Missile restraining apparatus
US5744745A (en) * 1995-12-15 1998-04-28 Agency For Defense Development Missile detent and release apparatus
CN116336869A (zh) * 2023-03-13 2023-06-27 上海机电工程研究所 导轨式发射箱箱体精度实现装置及安装方法

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH524802A (fr) * 1970-05-21 1972-06-30 Sarmac Sa Ensemble comprenant une arme d'infanterie et sa munition
CH527405A (fr) * 1970-07-10 1972-08-31 Sarmac Sa Ensemble comprenant un projectile autopropulsé empenné et son étui
CH528058A (fr) * 1970-08-06 1972-09-15 Sarmac Sa Caisson de transport et de tir pour projectiles autopropulsés
CN114543591B (zh) * 2022-03-08 2023-09-26 鲁东大学 一种海上火箭运输发射方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2831400A (en) * 1954-05-20 1958-04-22 Brevets Aero Mecaniques Devices for releasably holding the rear ends of rockets
US2848925A (en) * 1955-05-31 1958-08-26 Delos W Hood Blast release detent
US3011405A (en) * 1959-01-22 1961-12-05 Short Brothers Launching support for rocket-propelled missiles
US3015992A (en) * 1958-02-25 1962-01-09 Short Brothers & Harland Ltd Launching means for rocket-propelled missiles
US3138064A (en) * 1961-11-13 1964-06-23 Hesse Eastern Inc Rocket launcher and sight

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL80990C (da) * 1953-07-01
DE1141210B (de) 1959-06-09 1962-12-13 Boelkow Entwicklungen Kg Starteinrichtung fuer rueckstossgetriebene Flugkoerper

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2831400A (en) * 1954-05-20 1958-04-22 Brevets Aero Mecaniques Devices for releasably holding the rear ends of rockets
US2848925A (en) * 1955-05-31 1958-08-26 Delos W Hood Blast release detent
US3015992A (en) * 1958-02-25 1962-01-09 Short Brothers & Harland Ltd Launching means for rocket-propelled missiles
US3011405A (en) * 1959-01-22 1961-12-05 Short Brothers Launching support for rocket-propelled missiles
US3138064A (en) * 1961-11-13 1964-06-23 Hesse Eastern Inc Rocket launcher and sight

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3769876A (en) * 1972-08-02 1973-11-06 Us Navy Missile launching canister
US4012988A (en) * 1976-06-07 1977-03-22 The United States Of America As Represented By The Secretary Of The Army Mechanical fly-away latching mechanism
US4080868A (en) * 1977-02-25 1978-03-28 Lockheed Corporation Support and retention mechanism for missiles in launchers
US4132150A (en) * 1977-08-08 1979-01-02 The Unites States Of America As Represented By The Secretary Of The Army Blast actuated detent
US4191087A (en) * 1978-08-14 1980-03-04 The United States Of America As Represented By The Secretary Of The Army Rocket detent and release mechanism
US4358983A (en) * 1978-12-26 1982-11-16 Hughes Aircraft Company Blast enabled missile detent/release mechanism
WO1980001411A1 (en) * 1978-12-29 1980-07-10 Hughes Aircraft Co Automatic blast actuated positive release missile detent
US4304170A (en) * 1979-04-16 1981-12-08 The Boeing Company Locking assembly for a rocket and launch tube
US4550640A (en) * 1983-09-16 1985-11-05 Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag Missile canister restraint device
US5714708A (en) * 1995-09-29 1998-02-03 Agency For Defense Development Missile restraining apparatus
US5744745A (en) * 1995-12-15 1998-04-28 Agency For Defense Development Missile detent and release apparatus
CN116336869A (zh) * 2023-03-13 2023-06-27 上海机电工程研究所 导轨式发射箱箱体精度实现装置及安装方法

Also Published As

Publication number Publication date
DK115382B (da) 1969-09-29
NL6411556A (da) 1965-04-20
FR1426177A (fr) 1966-01-28
GB1028057A (en) 1966-05-04
BE653451A (da) 1965-01-18
AT248290B (de) 1966-07-25
FI41624C (fi) 1969-12-10
DE1256112B (de) 1967-12-07
FI41624B (da) 1969-09-01
CH415363A (de) 1966-06-15

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