US3863569A - Separable container for parachute-type flare - Google Patents

Separable container for parachute-type flare Download PDF

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Publication number
US3863569A
US3863569A US259985A US25998572A US3863569A US 3863569 A US3863569 A US 3863569A US 259985 A US259985 A US 259985A US 25998572 A US25998572 A US 25998572A US 3863569 A US3863569 A US 3863569A
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United States
Prior art keywords
flare
ring portion
disc
parts
pins
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
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US259985A
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English (en)
Inventor
Bjorn Herman Olof Simmons
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Saab Bofors AB
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Bofors AB
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Publication date
Application filed by Bofors AB filed Critical Bofors AB
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Publication of US3863569A publication Critical patent/US3863569A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
    • F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
    • F42B10/56—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding of parachute or paraglider type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/42—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information of illuminating type, e.g. carrying flares

Definitions

  • Int- Cl. haped member means of an encircling leeve hay- 0f Search 34.4, 37.6, 49.4, ing an an 10251352 annular recess on the disc-shaped member. Bevelshaped pins passing through the sleeve and into the References Cited plurality of parts are held in position by the container UNITED STATES PATENTS member.
  • the present invention relates to a device forming a part of a projectile or shell.
  • the device is separable from the carrier part of the projectile or shell and comprises a charge or flare provided with a parachute, and a container which encloses one end of the charge and includes one or more side surfaces as well as a member enclosing said parachute.
  • the container In its longitudinal direction the container is divided into a number of parts, which are secured to the charge by means of securing members also forming a part of the container so that when the container is blown off the carrier part, the action of the securing members ceases and the parts are thrown to the side in relation to the continued path of the charge by the centrifugal force resulting from the rapid spinning of the projectile or shell about its longitudinal axis.
  • Said device is used, inter alia, in illuminating projectiles, in which the charge consists ofa pyrotechnical luminous composition, or flare, and in which the construction of the unit is intended to cause the flare to be ignited only a predetermined time after the unit has been separated from the projectile carrier, so that during this time it will be possible to brake the movement of the unit both along and around its axis of symmetry, so that economic ignition of the flare will be obtained.
  • the braking of the movements of the unit along the axis of symmetry usually takes place by means of a brake or drogue parachute attached to the unit, while the braking of the movements around the axis of symmetry is achieved with brake flaps or similar means.
  • the delayed ignition is achieved by allowing the expelling charge which causes the separation of the unit from the projectile also to initiate a delay charge attached to the container which, after its delay time, in turn initiates a separating charge.
  • the latter change separates the container from the other parts of the unit, and at such time the aforementioned securing means releases the ends of the parts which enclose the parachute.
  • These and the parts can then be thrown to the side by the centrifugal force, and release the main parachute for the flare, while the other ends of the parts are held together by a ring or a corresponding means which permits said ejection.
  • the main parachute can thus be opened, after which the ignited flare can slowly descend to the ground, suspended in its parachute.
  • securing members for the container parts in such a way that, to secure the parts axially, the ends of the parts of the tubular member have had cleats or corresponding means directed inwardly towards the axis of symmetry of the unit, with such cleats being engaged in corresponding recesses in the flare or in members applied to the flare, while the radical locking radially of the parts has been achieved with the container, which holds the cleats engaged in said recesses.
  • Such securing members can be used for projectiles with low or medium rates of spin, but for projectiles with high rates of spin, e.g. 13,000 rpm.
  • the container in order to withstand the centrifugal forces arising in the container must be made of such thick material that it takes up more of the space in the projectile injected for the payload than can be accepted. It might be mentioned that the radial forces are approximately twice as great at 13,000 rpm. than as at 9,000 rpm.
  • the purpose of the present invention is primarily to solve this problem so as to permit the use of thin material in the container.
  • the container will be just as cheap and economical to manufacture as for projectiles with low and medium rates of spin, while it does not need to be provided with any special reinforcements or made of any special material.
  • the securing members include an attachment which is resistant to the radial forces arising in the unit and which encloses the usually tubular member enclosing the main parachute, and in that the position and/or the possible fastening of the attachment in the parts will be actuated to achieve the release of the parts by the axial forces occurring in the unit as a result of its spinning when the container is blown away.
  • FIG. 1 shows, in a vertical view, a cross-section of a first embodiment of the device applied to a partly shown unit that can be expelled from a projectile;
  • FIG. 2 shows, in a corresponding way, a vertical view and cross-section of a second embodiment
  • FIG. 3 shows, in a way corresponding to FIG. 1, a vertical view and cross-section of a third embodiment.
  • FIG. 1 there are shown only those parts of a unit that are expelled from the carrier of a projectile.
  • the reference character 1 illustrates a tubular member or casing which is formed of a number of separableparts so that each part, in its secured position, will be parallel with the axis of symmetry 2 of the unit.
  • the ends 1a of the parts 1 are secured to a disc-shaped part 3, which in a suitable manner is fastened to a flare 4, and a main parachute is stored in a space 5 inside the multi-part tubular container.
  • a sleeve 6 is affixed, which sleeve is resistant to the centrifugal forces in the unit caused by its spinning about axis 2.
  • the parts I are kept attached to the flare 4 by'an edge 6a of the sleeve 6 which is turned inwardly towards the axis of symmetry 2 and engages in a corresponding recess in the part 3.
  • the sleeve 6 is then also fastened to the parts 1 by means of pins 7 or the like which extend inwardly from the sleeve with oblique surfaces 7a into the parts 1.
  • the pins or corresponding devices are kept in place by the container 8, which thus need be dimensioned only to resist the centrifugal force acting on said pins.
  • the pins When the container 8, by means of a separating charge not shown, is separated from the unit, the pins will thus be released, and because of their oblique surfaces 7a will be pressed outwardly by the axial forces arising in the flare 4 and parts comprising the tubular member I, which are achieved by means of a brake or drogue parachute fastened to the parts, which strives to brake the unit longitudinally, to subsequently provide for economic ignition of the flare.
  • the pins 7 have become disengaged, the parts 1 can now be separated from the other elements in the unit and particularly from the encircling and restraining sleeve 6. The various parts of the device can then be thrown to the side in relation to the continued path of the flare.
  • FIG. 2 shows an alternative embodiment of the device according to the invention in which pins 7 of corresponding means are utilized.
  • the securing members comprise an element 9 fastened to the flare 4, which has a flange-like edge 90 extending in the longitudinal direction of the unit, inside of which edge the ends Ia are located.
  • the parts 1 are turned in so that they are located inside the edge 9a.
  • the element 9 is also fastened to the flare 4, as well as to the parts, by means of said pins 7, which extend in from the flange-formed edge of the parts with the above-mentioned oblique surfaces.
  • the container 8 is located outside of the element 9 and keeps the pins 7 in place. In this case also the pins are released when the container is blown away, after which the pins can be pressed out by the axial forces.
  • the position of the securing means can be influenced so as to produce the same result.
  • the device according to FIG. 3 is intended to show an example of this.
  • the securing means comprises of a ring 10 which can be displaced axially between two end positions. In one of these end positions (i.e. the position according to FIG. 3) it is held in place by the container, e.g. by a turnedin part 8a, and in a similar way as described above it encloses the end la of the parts 1 of the tubular member.
  • ring 10 releases the ends la so that the parts 1 can be released, as described above, from the flare.
  • the parts 1 are detachably secured to a part 11 which is fastened in the flare, and the parts 1 at one end have a cleat 1c turned inwards which engages in a corresponding recess in the part 11.
  • the cleat can, of course, be located on the part II and the recess in the parts I.
  • the part I] also has a space or recess Ila intended for the ring when this in its other end position, and in order to facilitate the axial displacement of the ring it is ap intestinalte to make it with an oblique surface 10a.
  • the container can have cleats, a flange, or corresponding means at its outer end, which will ensure that the container will pull the ring towards its other end position when it is blown away.
  • a parachute-type flare adapted to be fired in a trajectory with a high rate of spin and including a means which is separated from a carrier part, with said means including a pyrotechnic flare portion and a tubular casing formed of a plurality of separable casing parts detachably secured to the flare portion and housing a parachute, the improvement in means for detachably securing said casing parts to said flare portion comprising:
  • said engaging means being responsive to removal of said annular container from its normal encircling portion to permit longitudinal movement of said ring portion relative to said casing parts to thereby free said casing parts for outward radial movement.
  • said engaging means comprising a plurality of pins passing through said annular ring portion and into said casing parts, said pins having bevelled end portions.
  • said engaging means comprises an annular protuberance on said annular container frictionally engaging an annular recess on said annular ring portion.
  • a parachute-type flare adapted to be fired in a trajectory with a high rate of spin and including a means which is separated from a carrier part, with said means including a pyrotechnic flare portion and a tubular casing formed of a plurality of separable casing parts which is detachably secured to the flare portion and houses a parachute, the improvement in means for detachably securing said casing parts to said flare portion comprising:

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)
  • Bag Frames (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US259985A 1971-06-11 1972-06-05 Separable container for parachute-type flare Expired - Lifetime US3863569A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE07576/71A SE368987B (enrdf_load_stackoverflow) 1971-06-11 1971-06-11

Publications (1)

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US3863569A true US3863569A (en) 1975-02-04

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US259985A Expired - Lifetime US3863569A (en) 1971-06-11 1972-06-05 Separable container for parachute-type flare

Country Status (7)

Country Link
US (1) US3863569A (enrdf_load_stackoverflow)
FR (1) FR2141333A5 (enrdf_load_stackoverflow)
GB (1) GB1398774A (enrdf_load_stackoverflow)
IL (1) IL39475A (enrdf_load_stackoverflow)
IT (1) IT958151B (enrdf_load_stackoverflow)
NL (1) NL7207810A (enrdf_load_stackoverflow)
SE (1) SE368987B (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4226185A (en) * 1977-09-02 1980-10-07 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Projectile with a payload
US20190137246A1 (en) * 2016-04-06 2019-05-09 Bae Systems Bofors Ab Parachute device for a divisible shell
US10337845B2 (en) * 2016-04-20 2019-07-02 Bae Systems Bofors Ab Supporting device for dividable parachute grenade

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2144651C1 (ru) * 1999-06-16 2000-01-20 Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Боевая часть

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1309982A (en) * 1919-07-15 Careieb-shell
US2201482A (en) * 1934-03-28 1940-05-21 Jr Louis L Driggs Flare casing and method of sealing
US3143965A (en) * 1959-11-06 1964-08-11 Pointe Andre E La Chaff dispenser
US3374739A (en) * 1966-03-16 1968-03-26 Army Usa Payload recovery system
US3712232A (en) * 1968-10-23 1973-01-23 Us Navy Variable delay fuse for aircraft parachute flare

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1309982A (en) * 1919-07-15 Careieb-shell
US2201482A (en) * 1934-03-28 1940-05-21 Jr Louis L Driggs Flare casing and method of sealing
US3143965A (en) * 1959-11-06 1964-08-11 Pointe Andre E La Chaff dispenser
US3374739A (en) * 1966-03-16 1968-03-26 Army Usa Payload recovery system
US3712232A (en) * 1968-10-23 1973-01-23 Us Navy Variable delay fuse for aircraft parachute flare

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4226185A (en) * 1977-09-02 1980-10-07 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Projectile with a payload
US20190137246A1 (en) * 2016-04-06 2019-05-09 Bae Systems Bofors Ab Parachute device for a divisible shell
US10458765B2 (en) * 2016-04-06 2019-10-29 Bae Systems Bofors Ab Parachute device for divisible shell
US10337845B2 (en) * 2016-04-20 2019-07-02 Bae Systems Bofors Ab Supporting device for dividable parachute grenade

Also Published As

Publication number Publication date
NL7207810A (enrdf_load_stackoverflow) 1972-12-13
GB1398774A (en) 1975-06-25
IT958151B (it) 1973-10-20
IL39475A (en) 1976-01-30
SE368987B (enrdf_load_stackoverflow) 1974-07-29
FR2141333A5 (enrdf_load_stackoverflow) 1973-01-19
DE2226717A1 (de) 1972-12-14
IL39475A0 (en) 1972-08-30
DE2226717B2 (de) 1976-08-19

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