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Publication numberUS3296929 A
Publication typeGrant
Publication dateJan 10, 1967
Filing dateSep 16, 1964
Priority dateOct 16, 1963
Also published asDE1256112B
Publication numberUS 3296929 A, US 3296929A, US-A-3296929, US3296929 A, US3296929A
InventorsGunnar Jacobson
Original AssigneeBofors Ab
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Missiles
US 3296929 A
Abstract  available in
Images(3)
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Claims  available in
Description  (OCR text may contain errors)

G. JACOBSON MISSILES 3 Sheets-Sheet 1 INVENTOR u/v/mk Iqaoa s m/ ATTORNEYS Jairi: 10, 1967 G. JACOBSON 3,296,929

MISSILES Filed Sept, 16, 1964 5 Sheets-Sheet 2 mlllllllllllllmmlll "llllllllmu A.

INVENTOR Gu/v/vm? 79c. 03: av

BY mm, W

ATTORNEYS MISSILES Filed Sept. 16,: 1954 3 Sheets-Sheet 5 Fig.3

INVENTOR -Gu-/vm2 fines.- cw

BY MM/ WM ATTORNEYS 3,296,929. MISSILES Gunnar Jacobson, Bofors; Sweden, assignor to Aktiebolaget Bofors, Bofors, Sweden, a corporation of Sweden Filed Sept. 16, 1964, Ser. No. 396,869 Claims priority, application Sweden, Oct. 16, 1963, 11,370/ 63 2 Claims. (Cl. 891.806)

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,

ated by the missile to release said engagement members i from themissile.

An embodiment of the invention is illustrated by the accompanying drawings, wherein:

"FIGAJ. showsa 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.

Referring to FIGURE 1, 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.

At theirtfront ends, 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. In the described posi tion; the, strip "ISM straight, "as seen in FIGURE 2, and

. the. length of the strip. is such that in this position, the links 8, 9 diverge slightly at the ends adjacent to strip 10.

' UhitedSxtates Patent 0 The back piece 5 and the members carried by it are suitably attached to the missile, before it is placed in the box, whereupon the missile is introduced together with the back piece into the box and secured by means of the brackets 6 and studs 17 and 18.

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.

What is claimed is:

1. 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, said device 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.

2. A device according to claim 1 wherein a frame structure is secured to the walls of the box, 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.

References Cited by the Examiner UNITED STATES PATENTS 2,831,400 4/ 1958 Hosli 89l.7 2,848,925 8/1958 Hood 89-].7 3,011,405 12/1961 Moss et al. 89-1.7 3,015,992 1/1962 Ransom 89l.7 3,138,064 6/1964 Choate et al. 89-l.7

BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2831400 *May 5, 1955Apr 22, 1958Brevets Aero MecaniquesDevices for releasably holding the rear ends of rockets
US2848925 *May 31, 1955Aug 26, 1958Hood Delos WBlast release detent
US3011405 *Jan 4, 1960Dec 5, 1961Harland LtdLaunching support for rocket-propelled missiles
US3015992 *Feb 17, 1959Jan 9, 1962Short Brothers & Harland LtdLaunching means for rocket-propelled missiles
US3138064 *Jan 22, 1963Jun 23, 1964Hesse Eastern IncRocket launcher and sight
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3769876 *Aug 2, 1972Nov 6, 1973Us NavyMissile launching canister
US4012988 *Jun 7, 1976Mar 22, 1977The United States Of America As Represented By The Secretary Of The ArmyMechanical fly-away latching mechanism
US4080868 *Feb 25, 1977Mar 28, 1978Lockheed CorporationSupport and retention mechanism for missiles in launchers
US4132150 *Aug 8, 1977Jan 2, 1979The Unites States Of America As Represented By The Secretary Of The ArmyBlast actuated detent
US4191087 *Aug 14, 1978Mar 4, 1980The United States Of America As Represented By The Secretary Of The ArmyRocket detent and release mechanism
US4304170 *Apr 16, 1979Dec 8, 1981The Boeing CompanyLocking assembly for a rocket and launch tube
US4358983 *Dec 26, 1978Nov 16, 1982Hughes Aircraft CompanyBlast enabled missile detent/release mechanism
US4550640 *Sep 16, 1983Nov 5, 1985Werkzeugmaschinenfabrik Oerlikon-Buehrle AgMissile canister restraint device
US5714708 *Sep 27, 1996Feb 3, 1998Agency For Defense DevelopmentMissile restraining apparatus
US5744745 *Dec 12, 1996Apr 28, 1998Agency For Defense DevelopmentMissile detent and release apparatus
WO1980001411A1 *Dec 26, 1979Jul 10, 1980Hughes Aircraft CoAutomatic blast actuated positive release missile detent
Classifications
U.S. Classification89/1.806, 89/1.816
International ClassificationF41G7/30, F41F3/052, F41F3/042
Cooperative ClassificationF41G7/301, F41F3/052, F41F3/042
European ClassificationF41F3/052, F41F3/042, F41G7/30B