|Publication number||US3296929 A|
|Publication date||Jan 10, 1967|
|Filing date||Sep 16, 1964|
|Priority date||Oct 16, 1963|
|Also published as||DE1256112B|
|Publication number||US 3296929 A, US 3296929A, US-A-3296929, US3296929 A, US3296929A|
|Original Assignee||Bofors Ab|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (5), Referenced by (11), Classifications (11)|
|External Links: USPTO, USPTO Assignment, Espacenet|
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.
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US2831400 *||May 5, 1955||Apr 22, 1958||Brevets Aero Mecaniques||Devices for releasably holding the rear ends of rockets|
|US2848925 *||May 31, 1955||Aug 26, 1958||Hood Delos W||Blast release detent|
|US3011405 *||Jan 4, 1960||Dec 5, 1961||Harland Ltd||Launching support for rocket-propelled missiles|
|US3015992 *||Feb 17, 1959||Jan 9, 1962||Short Brothers & Harland Ltd||Launching means for rocket-propelled missiles|
|US3138064 *||Jan 22, 1963||Jun 23, 1964||Hesse Eastern Inc||Rocket launcher and sight|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3769876 *||Aug 2, 1972||Nov 6, 1973||Us Navy||Missile launching canister|
|US4012988 *||Jun 7, 1976||Mar 22, 1977||The United States Of America As Represented By The Secretary Of The Army||Mechanical fly-away latching mechanism|
|US4080868 *||Feb 25, 1977||Mar 28, 1978||Lockheed Corporation||Support and retention mechanism for missiles in launchers|
|US4132150 *||Aug 8, 1977||Jan 2, 1979||The Unites States Of America As Represented By The Secretary Of The Army||Blast actuated detent|
|US4191087 *||Aug 14, 1978||Mar 4, 1980||The United States Of America As Represented By The Secretary Of The Army||Rocket detent and release mechanism|
|US4304170 *||Apr 16, 1979||Dec 8, 1981||The Boeing Company||Locking assembly for a rocket and launch tube|
|US4358983 *||Dec 26, 1978||Nov 16, 1982||Hughes Aircraft Company||Blast enabled missile detent/release mechanism|
|US4550640 *||Sep 16, 1983||Nov 5, 1985||Werkzeugmaschinenfabrik Oerlikon-Buehrle Ag||Missile canister restraint device|
|US5714708 *||Sep 27, 1996||Feb 3, 1998||Agency For Defense Development||Missile restraining apparatus|
|US5744745 *||Dec 12, 1996||Apr 28, 1998||Agency For Defense Development||Missile detent and release apparatus|
|WO1980001411A1 *||Dec 26, 1979||Jul 10, 1980||Hughes Aircraft Co||Automatic blast actuated positive release missile detent|
|U.S. Classification||89/1.806, 89/1.816|
|International Classification||F41G7/30, F41F3/052, F41F3/042|
|Cooperative Classification||F41G7/301, F41F3/052, F41F3/042|
|European Classification||F41F3/052, F41F3/042, F41G7/30B|