US3055300A - Rocket flare head - Google Patents

Rocket flare head Download PDF

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US3055300A
US3055300A US576753A US57675356A US3055300A US 3055300 A US3055300 A US 3055300A US 576753 A US576753 A US 576753A US 57675356 A US57675356 A US 57675356A US 3055300 A US3055300 A US 3055300A
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flare
assembly
parachute
projectile
head
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US576753A
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Stoehr Donald
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Stoehr Donald
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B4/00Fireworks, i.e. pyrotechnic devices for amusement, display, illumination or signal purposes
    • F42B4/06Aerial display rockets
    • F42B4/10Aerial display rockets characterised by having means to separate article or charge from casing without destroying the casing
    • F42B4/12Parachute or flare separation

Description

Sept. 25, 1962 Filed April 6, 1956 D. sToEHR 3,055,300

ROCKET FLARE HEAD 3 Sheets-Sheet 1 INVENTOR. DONALD STOEHR 717m ATTORNEYS Sept. 25, 1962 D. sToEHR ROCKET FLARE HEAD 3 Sheets-Sheet 2 Filed April 6, 1956 INVENTOR DONALD STOEHR BY f 'KfZ/LKW, ATTORNEYS Sept. 25, 1962 D. sToEHR 3,055,300

ROCKET FLARE HEAD Filed April 6, 1956 5 Sheets-Sheet 3 INVENTOR. DONALD STOEHR mm ATTORNEYS 'Iiite States tat 3,955,3@ Patented Sept. 25, 1962 3,055,300 ROCKET FLARE I-EAD Donald Stoehr, China Lake, Calif., assigner to the United States of America as represented by the Secretary of the Navy Filed Apr. 6, 1956, Ser. No. 576,753

3 Claims. (Cl. MBZ-35.4)

(Granted under Title 3S, ILS. Code (i952), sec. 266) The invention described herein may be manufactured and used by or yfor the Government of the United States of America `for governmental purposes without the payment of any royalties thereon or therefor.

This invention relates to aerial dares, and more particularly to projectile conveyed flare heads of the type in which a projectile, as a rocket, is used to convey a are carrying head to a desired altitude and area Where a lighted flare is released and supported by parachute means to light up a desired ground objective for reconnaissance, for aerial photography, or for other purposes.

For various purposes, both military and civilian, it is desirable to light up a ground area by means of elevated illuminating candle or flare means. It has become cornmon practice to achieve this result with parachute supported illuminating flare means which are conveyed to a desired altitude and area by projectiles of various types, as for example, by rockets. In such arrangements, the projectile is provided with means allowing separation of the parachute and are therefrom at a desired time or distance after tiring of the projectile, and with means for igniting the ilare and `for causing or facilitating the opening of the parachute.

.A common difficulty with such devices has been in the fact that excessive speeds at the time of parachute operation often resulted in general mechanical failure, in tearing or fouling of the parachutes, and sometimes even in complete disconnection thereof. Many eiforts have been made to overcome these diiculties, as by utilization of auxiliary drag parachutes to slow down the ilare assem- -bly prior to opening of the -main or suspension parachute. Generally, devices resulting from these efforts involved mechanical arrangements based upon `forces exerted by a lanyard connected to the projectile body at one end and to the drag parachute of the flare assembly to open the drag parachute upon separation of the ilare assembly from the projectile, and depended upon a second lanyard, either to directly pull out the main suspension parachute or to actuate a striker to initiate a pyrotechnic delay train to operate to release or expel the main parachute after a desired delay interval. Such dependency upon tension forces developed in these lanyards resulted in poor performance and lack of dependability since the forces involved were quite violent and necessarily not uniform in strength or direction, causing parts breakage or entanglement and malfunction. Moreover, in such arrangements wherein `a pyrotechnic delay train was utilized, assembly and handling were hazardous because the tiring mechanism thereof was always essentially armed.

This yinvention depends upon the discovery that drag parachute and delayed main parachute release could be effected Without resorting to the undependable lanyard system hitherto relied upon in the prior art. The necessity for a drag parachute operating lanyard is obviated by novel design of the adapter coupling by which the flare is attached to the projectile `for conveyance thereby, said novel design resulting in release of the are assembly and opening of the drag parachute upon separation of the flare assembly from the adapter coupling Without dependence upon a lanyard. Similarly, there is no dependence upon a lanyard for main suspension parachute operation in this invention, this function being performed by the novel combination of acceleration-deceleration operated time delay fuze means in the ilare assembly, said fuze means responding to acceleration in flight (of the projectile) and to deceleration upon separation of the are assembly from the projectile to initiate a time delay pyrotechnic train which operates the main suspension parachute after a predetermined time interval (during which the are assembly container decelerates to a safer velocity).

It is, therefore, an object of this invention to provide novel projectile-conveyed, parachute-supported are means of greater reliability of operation than was possible in the prior art.

A further object of this invention is to provide novel projectile-conveyed, parachute-supported are means wherein the use of tension lanyards to cause separation from the projectile and initiate parachute operation is obviated, thus greatly improving dependability of such devices.

A still further object of this invention is to provide projectile-conveyed ilare head means wherein a flare assembly may be separated from a projectile Without the use of a lanyard, by virtue of novel design of the adapter coupling means connecting the flare head assembly of the projectile.

Still another object of this invention is to provide novel flare head means wherein ejection of the main suspension parachute is effected -by means entirely responsive to acceleration and deceleration forces of the assembly rather than by lanyard means or other mechanical connections, as in the prior art, thereby overcoming the lack of reliability resulting from excessive and non-uniform forces occurring in the use of such prior art devices.

Still another object of this invention is to provide new and improved tlare head means adapted to be rocket projected to `desired altitudes and areas for use.

A further object of this invention is to provide mechanical timing means responsive to acceleration to be armed and responsive to deceleration to be actuated to initiate a time delay device to operate a supporting parachute, such means being eifective, as an element of a flare head, to replace lanyards or other tension operated mechanical means in initiating main suspension parachute operation in such a flare head.

These and other objects and many of the attendant advantages of the present invention will become apparent as the same become better understood from the following detailed description, taken in conjunction with accompanying drawings, in which:

FIG. 1 is a longitudinal lsectional view through a flare head incorporating the principles of this invention, the conveying projectile being shown in fragmentary fashion;

FIG. 2 is a longitudinal sectional view through the delay meehanism of the flare head of FIG. 1;

FIGS. 3 to 9, in order, are representations of the sequence of operation of the flare head which is the subject matter of the invention, FIG. 3 being a sectional View (similar to FIG. l) of the are head, as conveyed by a rocket projectile, prior to operation of the nose timer to cause separation of the flare assembly; FIG. 4 being a View similar to FIG. 3 illustrating the initial separation of the flare assembly from the projectile body; and FIGS. 5 to 8 are schematic elevational representations of the remaining steps involved in the operation of the flare assembly.

Referring now to the drawings, in which like reference numerals have been appended to like parts throughout,

attention is directed to FIG. 1 which is a sectional representation of the Hare head assembly as attached to a projectile casing P, by means of adaptor coupling means 2.

Adaptor coupling means 2 is comprised of a portion en-Y gaging the inner wall of the projectile casing as, for example, a rocket motor tube as illustrated, and screw threadedly connected thereto, as shown at 4. Coupling 2 has an expanded forward portion 3 of outer diameter matching that of the motor tube and screw threaded internally, as at 6, to engage the head base member 8 of the flare head assembly.

Head base member 8 is a stepped cap-shaped member having a transverse wall 10` which serves as a closure for the rocket motor or other projectile casing P, the transverse wall being at the after end of a reduced portion which is of a size to lit internally of the forward portion 3 of adaptor coupling 2 and which is screw threaded for engagement with the threads 6, as illustrated. Head base member 8 has a forwardly extending skirt 12 forming a pocket for a drag parachute to be later described. The skirt 12 is of an outer diameter substantially equal to the inner diameter of projectile casing P for engagement with a canister 16 which is of external and internal diameter substantially similar to that of the projectile casing P. Such relative proportions of the parts are not critical but are preferable in order that better streamlining and aerodynamic eiciency be attained.

The interior of canister 16 and the exterior of the skirt 12 are provided with matching screw threads of limited depth and length so as to be shearable upon the application of relative axial forces to the pieces, such threads being shown at 18. Canister 16 contains a are assembly which is releasable upon shearing of the threads 18 in response to axial forces applied against the canister by fuze means contained therein, as will be fully described hereinafter. In connection with this separation of canister 16 and head base 8 attention is directed to the configuration of the skirt 12 of the head base member. Skirt 12 is beveled, as by being cut away along an angular plane, to provide a pivotal surface 14 about which the are assembly (to be described hereinafter) turns in being released from the head base 8 after separation of the canister from the head base as described, thus doing away with the need for drag parachute operating lanyard means as utilized in the prior art.

The canister 16 has a thickened forward wall in the ogival nose section thereof providing a shoulder which serves as a seat for a disc 22, as shown. Disc 22 holds the nose fuze 20 in the forward ogival chamber and serves as the forward closure for the remainder of the flare assembly with which it is slidable relative to the interior of the canister 16. Disc 22 is provided with through passageways 23 to conduct gases and flame from the fuze to a flare candle 24 which is supported in proximity to the disc. The are candle 24 is attached to a main suspension parachute 30 by any suitable means, as by attachment of the shroud lines 32 thereof to a ring 27 formed in a post 26 imbedded in flare candle 24, as illustrated.

The specific composition and construction of are candle 24 is not critical, any known illuminating pyrotechnic being suitable, and any known covering or other side burning inhibiting material being usable as desired to control the nature of the burning of the candle. Two different variations of flare candle are depicted, by way of examples, in FIG. l and in FIGS. 3 and 4. In each instance a suitable pyrotechnic (such as a mixture of nely divided magnesium powder and an oxidizer held together by a plastic binder) material is molded about post 26 as previously described, the post being threaded or knurled (as in FIG. 1) if desired. The flare candle of FIG. 1 is wrapped circumferentially with corrugated paper or cardboard, which may be impregnated with an inhibiting compound, if desired, and has its ends covered by paper discs 29, 29a, with openings in the forward disc 29 matching the passageways 23 in the pressure disc 22 to allow gas passage therethrough. This assembly, provided with a cardboard backing 29h, is enclosed in a steel outer casing 25 which is open at the front end as illustrated, this casing being tted within canister 16, as shown.

The are candle of FIGS. 3 and 4 is of simpler construction and has been found suitable in use. It comprises a pyrotechnic compound molded about a post 26 having a backing piece 29b and an open ended paper covering 25a.

The suspension parachute 30 has a pilot parachute 34 attached thereto, and these parachutes are folded and compressed within an inner case member 36, being retained in this position by a closure member 38, the closure member in turn being clamped into position as a closure for inner casing 36 by a retaining cap 40. Retaining cap 4@ is internally threaded, as at 42 for connection with corresponding threads on the outer surface of the inner case 36 and the threads are of such extent and depth as to be frangible or shearable upon the application of relative force between the cap member 42 and the retaining cap 4i? by means and for purposes to be later described.

The inner case closure member 38 is of generally stepped configuration to provide a chamber 44 in which a delay timing device 46 is retained. Time delay device 46 is illustrated in `detail in FIG. 2 and will be described in detail hereinafter, it being suicient at this stage to merely describe the function thereof, i.e., to generate gas pressure at a given time to cause separation of retaining cap 40 from the inner case 36, expulsion of the delay device from chamber 44, and separation of closure 38 from inner case 36 with resulting withdrawal of pilot parachute 34 from the inner case as graphically represented in FIG. 7. Pilot parachute withdrawal is facilitated by attaching a string leader element 48 to the closure member 3S and loosely interfolding said string leader element within the folds of the pilot parachute 34 so that the. said parachute is pulled out of the inner case to some extent as the closure 38 falls away from the remainder of the assembly.

The rearward external wall of retaining cap 40 is provided with an integral ring 50 to which are attached the shroud lines of a drag parachute 52 which is folded within the space provided `within the skirt portion 12 of the head base 8 as illustrated in the drawing. At this point attention is again directed to the function of the bevel surface 14 of head base 8 and to the fact that the are assembly is pivotally released over this surface 14 upon separation of canister 16 and head base `8 as shown in a comparison of FIGS. 4 and 5.

As discussed hereinabove, two separate fuze or time delay means are utilized in this invention, namely the nose fuze 20 :and the time delay 46. Considering the present invention in its broadest aspects the specic nature of these fuzes is less important than the functions required thereof and fuzes other than those disclosed herein are available for performance of such functions. The function of nose fuze 20 is to insure a time or distance delay between the firing of the rocket or other projectile and the operation of the flare. Such devices, Well known in the prior art, have long been utilized to initiate warhead explosion or flare operation, and generally include a timing mechanism and a pyrotechnic train operated thereby to cause the evolution of hot gases and or flame, either to ignite a warhead material or to perform some other function. Such fuzes are described, for example, in page 592 of Elements of Ordnance by T. J. Hayes, published in 1938 by Iohn Wiley & Sons, Inc.

The time delay device 46 has the function of interjecting a time delay between the operation of the nose fuze and the evolution of gases to effect release of the main suspension parachute so `that deceleration forces (made possible by the operation of the nose fuze) may be effective to slow down the assembly so that said parachute may be safely operated. For this purpose, many expedients could be utilized, as for example, means similar to nose fuze 20 but operating on a longer preset time period or including a longer delay in the powder train thereof. The particular novel time delay device illustrated in FIG. 2 has been developed particularly for safer and more eicient performance of the time delay function and is preferred over prior art time delay devices because it incorporates a pluralit-y of safety features not available in combination in such prior art devices, although, as stated hereinabove, prior art time delays of various types could be used if desired.

Time delay device 46 comprises an outer casing 54 of a size to fit within the chamber 44 of closure member 3-3. Casing 54 is open at both ends, the forward wall 55 being thickened and shaped to provide a forward facing charnber and a connecting narrower passageway, the chamber being filled with a gas producing black powder charge 56 and the passageway having a time delay pyrotechnic train assembly 58 suitably held therein, as by the turning in of a portion of the Wall adjoining the passageway, as at 60'. Black powder charge 56 is retained in the forward chamber by a frangible closure seal 62. The rearward portion of the casing 54 is hollow, providing a chamber 63 for housing a time delay rotor 64 and its associated operating parts, the central portion of forward wall 55 extending into said chamber 63 to provide a seat for coil spring 66, as shown. Rotor 64 is a known type of acceleration responsive integrating timing device forming the basis for a widely used family of fuzes and timing devices and forms a part of the disclosure in the application of W. F. Sapp, Serial No. 342,039, filed March l2, 1953, now Patent No. 2,948,219, in which the operation and construction thereof is fully described. iRotor 64 is mounted for rotary movement on stanchions 69 which are rigidly connected to a member 68 fixed in an annular sleeve member 70 which is free for axial sliding movement within the casing 54. Such movement of the sleeve 7 il is limited by the shoulder 72 formed on the casing wall, and is opposed by the coil spring 66.

As is common in such devices (as more fully explained in the Sapp application identified above) rotor 64 is provided with rotor locking means in the form of a motion restraining assembly or rotor lock 74 and set back spring means 76 which urge the rotor into locking engagement with motion restraining assembly 74 to restrain rotary motion of the rotor. The arrangement of the set back springs, rotor and rotor lock is such that upon firing of the projectile acceleration forces cause the rotor 64 to move rearwardly (compressing set back springs 76) to be disengaged from rotor lock 74, and to be simultaneously rotated. Rotor 64 is thus rotated clockwise, as seen in FIG. 2, to a position in which a firing pin 75 thereon is aligned with pyrotechnic delay train 5S. At the end of the acceleration period, as the projectile is decelerated by ejection of the outer canister the annular sleeve 70, carrying the rotor assembly, is forced forward by deceleration forces (inertia) against the force of spring 66 until it contacts the shoulder 72. at which point the firing pin strikes the detonator of delay train 58 to initiate burning thereof. The rotor is so shaped and its parts so positioned that, with the annulus 70 in contact with shoulder 72, no portion of the rotor other than an extending 55 firing pin (in the rotated position of the rotor) can possibly strike the detonator of Ithe pyrotechnic delay train. Thus, in order for the pyrotechnic train 5-8 to be ignited three conditions or events must occur in a definite order,

namely, initial acceleration to free lthe rotor for rotation 60 by set-back forces on springs 76; continued acceleration for a predeterminable period sufficient to allow acceleration forces to turn the rotor 64 to align a firing pin with the delay train; and deceleration to permit the timing mechanism to move forward against the pressure of 65 spring 66 to cause the firing pin to cause ignition of the delay train 58.

Delay train 58 may be variously constituted of known pyrotechnics to give any desired delay time and such delay is, of course, instituted by deceleration of the flare as- 70 sembly in response to recoil forces exerted on the assembly by ejection of canister 16. The operating times of the various fuzes and time delay trains are, of course, optional. For example, the nose fuze could be arranged to have about a five second delay, and the over-all operation of the device will now be described, using such time intervals as exemplary. FIGS. 3 to 9 of lthe drawing illustrate the various phases of operation, FIG. 3 showing the flare head assembly attached to a projectile (as a rocket motor) prior to firing (or prior to operation of nose fuze 20). When the projectile is launched, the delay timer rotor 64 is released by setback and rotated and the operation of the timing means in nose fuze 2t) is initiated. Ten seconds later the fuze 20' functions causing hot gases under pressure to be formed inside the forward fuze compartment of the canister I6. Such hot gases pass through the passageways 23 in the disc 22, ignite the flare candle 24, and serve to apply pressure against disc 22 to vigorously push the outer canister forward, shearing off the screw threads 13 in the process, as depicted in FIG. 4. This gas pressure is sufiicient to impel or eject the canister completely away from the flare assembly as shown in FIG. 5 and recoil from this ejection causes a momentary high deceleration in the remainder of the round to cause the rotor element 64 of delay timer 46 (which had been previously released by firing set back and rotated by acceleration) to act under inertia forces to overcome the force of spring 66 and slide forward so that the rotors firing pin strikes initiating detonating means on delay train 58 to institute the five second delay period therein.

As soon as the outer case is ejected the flare load tumbles free of the projectile casing P as a result of the bevel i4 on head base 8, the flare candle 24 having been ignited by this time, and the disc 22 falling away, all as illustrated in FIG. 5. As the flare load tumbles, the drag parachute 52 withdrawn from the cavity in head base 8, opens (see FIG. 6) and serves to reduce the forward velocity of the flare load from its released velocity (about G feet per second) to a velocity which the main parachute can withstand, (about 400 feet per second, or less). This deceleration of the flare load by drag parachute 52 occurs during the five second delay action of delay train S8 of the time delay device 46. At the end of the five lsecond delay period the delay train 58 burns through to the powder charge 56 (see FIG. 2) and ignites said charge causing the evolution of gases which rupture closure seal 62 and pressurize the chamber 44 to cause the threads 42 to be sheared and ejecting cap` 40 to which drag parachute 52 is attached, the delay device 46 being also released or blown from chamber 44, as shown in FIG. 7. The closure member 38 then falls away and withdraws the pilot parachute 34 by means of the string leader 48 loosely enfolded within the pilot parachute, as shown in FIG. 8, said pilot parachute then opening to withdraw the main suspension parachute 3ft to the final flare supporting posidelay means operative to allow deceleration of the are candles having burning times in the order of slightly more than one minute in such devices and this affords illumination suitable for photographic reconnaissance, or other purposes.

`It should be obvious from the above that the present invention provides novel flare head means for rockets and other projectiles, said flare head means being characterized in their efliciency and dependability of operation by virtue of the elimination of the lanyard drag and pilot parachute opening means generally utilized in prior art devices of this type, and by virtue of the provision of time delay means operative to allow decelerations of the flare means to a safe speed before operation of the main suspension parachute of the flare.

While only one basic illustrative example of devices according to the present invention has been specically described herein, it is obvious that many variations and modifications thereof are possible within the scope of the teachings of this disclosure. It is therefore to be understood that the scope of the invention is not intended to be limited by the specific illustrative example described but a ten second time delay and the delay element 46 to have 75 rather by the Scope and language 0f the appended Claims- What is claimed is:

l. In combination, a projectile body, an outer canister, a head end assembly attached to the projectile body, said head end assembly having a relatively short forwardly protruding cylindrical hollow skirt portion, said canister and skirt portion having interengaging frangible connecting means, a flare Iassembly contained in said canister with a portion thereof within the hollow skirt portion, said canister having a chamber in the forward end thereof, fuze means in said chamber responsive to acceleration forces to develop pressure gases within said canister to ignite said are assembly and to cause said frangible connecting means to be broken and said canister to be ejected forwardly away from said head end assembly and said are assembly freeing said are assembly to fall out of said hollow skirt portion for independent operation, the cylindrical hollow skirt portion of said head end assembly also having an angular cut-away portion providing a beveled surface over which the llare assembly pivots in falling from the skirt portion, thereby facilitating separation of the are assembly from the skirt portion.

2. In combination, a projectile body, an outer canister, a head end assembly attached to the projectile body, said head end assembly having a relatively short forwardly protruding cylindrical hollow skirt portion, said canister and skirt portion having interengaging frangible connecting means, :a flare assembly contained in said canister with a portion thereof within the hollow skirt portion, said canister having a chamber in the forward end thereof, fuze means in said chamber responsive to acceleration forces to develop pressure gases within said canister to ignite said are assembly and to cause said frangible connecting means to be broken and said canister to be ejected forwardly away from said head assembly and said flare assembly freeing said flare yassembly to fall out of said hollow skirt portion for independent operation, said are assembly comprising an open ended tubular flare assembly container, a are candle in one open end of said container in proximity to said chamber whereby to be ignited by said gases generated by said fuze means, a main parachute assembly attached to said are candle and enfolded within the other end of said container, cap means closing said other end of said container, said cap means having a drag parachute attached thereto externally of said container, said drag parachute being positioned in the hollow skirt portion of said head end assembly whereby said drag parachute opens to assist deceleration of the closed Iflare assembly container when said container falls free of said projectile.

3. The combination of claim l, in which said are assembly comprises a tubular container having a closure cap member at the end thereof in proximity to said hollow skirt portion, said closure cap member having a drag parachute attached thereto, externally of the container, said drag parachute being positioned within said hollow skirt portion and :serving to assist in decelerating said flare assembly when it falls free from said hollow skirt portion.

References Cited in the file of this patent UNITED STATES PATENTS

US576753A 1956-04-06 1956-04-06 Rocket flare head Expired - Lifetime US3055300A (en)

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Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3515362A (en) * 1968-11-14 1970-06-02 Us Navy Parachute collapsing mechanism
US3791300A (en) * 1971-09-04 1974-02-12 Rheinmetall Gmbh Flare shell
US3834312A (en) * 1973-03-14 1974-09-10 Bofors Ab Parachute-borne flare assemblage
FR2402183A1 (en) * 1977-09-02 1979-03-30 Oerlikon Buehrle Ag PAYLOAD CARRYING SHELL
US4651648A (en) * 1986-04-01 1987-03-24 The State Of Israel, Ministry Of Defence, Israel Military Industries Pyrotechnic aircraft carried bomb
US4667600A (en) * 1986-02-25 1987-05-26 The United States Of America As Represented By The Secretary Of The Air Force Safe/arm explosive transfer mechanism
US5239927A (en) * 1991-07-25 1993-08-31 Rheinmetall Gmbh Deceleration device for submunition
US5253587A (en) * 1991-12-23 1993-10-19 Thomson-Brandt Armements Separation and aerodynamic braking device for the propulsion stage of a missile
US5347931A (en) * 1992-11-12 1994-09-20 Thiokol Corporation Combustible flare ignition system
US5386781A (en) * 1992-11-12 1995-02-07 Thiokol Corporation Parachute deployment system
FR2724221A1 (en) * 1994-09-02 1996-03-08 Lacroix Soc E Projectile with payload designed to be launched at set altitude
EP1296112A2 (en) * 2001-09-25 2003-03-26 Falken, S.A. Device with combustible charge with smoke-generating, tear-generating or signaling effects
CN102278915A (en) * 2011-09-17 2011-12-14 浏阳市余氏科技环保烟花厂 Aerial shell effective piece used for showing aerial subtitle pattern at multi-angle and in all aspects
CN102589361A (en) * 2012-04-06 2012-07-18 浏阳市余氏科技环保烟花厂 Subtitle pattern display shell capable of directional transmission
CN103697766A (en) * 2013-12-18 2014-04-02 江西省李渡烟花集团有限公司 Water borne carpet display shell
GB2517445A (en) * 2013-08-20 2015-02-25 Bae Systems Plc Illumination Munition
US20150300789A1 (en) * 2012-11-23 2015-10-22 Nexter Munitions Pyrotechnic Gas Generator Component
US20160209191A1 (en) * 2013-08-20 2016-07-21 Bae Systems Plc Common carrier munition
US20160209190A1 (en) * 2013-08-20 2016-07-21 Bae Systems Plc Frangible munition
US9778004B2 (en) 2013-08-20 2017-10-03 Bae Systems Plc Smoke payload apparatus
US10030953B2 (en) 2013-08-20 2018-07-24 Bae Systems Plc Illumination munition
US10337845B2 (en) * 2016-04-20 2019-07-02 Bae Systems Bofors Ab Supporting device for dividable parachute grenade
US10458765B2 (en) 2016-04-06 2019-10-29 Bae Systems Bofors Ab Parachute device for divisible shell

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US1365865A (en) * 1918-06-27 1921-01-18 Jaroslav A Svejda Illuminating-projectile
US1434784A (en) * 1922-06-20 1922-11-07 V M L Ex Ltd Shell

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1365865A (en) * 1918-06-27 1921-01-18 Jaroslav A Svejda Illuminating-projectile
US1434784A (en) * 1922-06-20 1922-11-07 V M L Ex Ltd Shell

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3515362A (en) * 1968-11-14 1970-06-02 Us Navy Parachute collapsing mechanism
US3791300A (en) * 1971-09-04 1974-02-12 Rheinmetall Gmbh Flare shell
US3834312A (en) * 1973-03-14 1974-09-10 Bofors Ab Parachute-borne flare assemblage
FR2402183A1 (en) * 1977-09-02 1979-03-30 Oerlikon Buehrle Ag PAYLOAD CARRYING SHELL
US4226185A (en) * 1977-09-02 1980-10-07 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Projectile with a payload
US4667600A (en) * 1986-02-25 1987-05-26 The United States Of America As Represented By The Secretary Of The Air Force Safe/arm explosive transfer mechanism
US4651648A (en) * 1986-04-01 1987-03-24 The State Of Israel, Ministry Of Defence, Israel Military Industries Pyrotechnic aircraft carried bomb
US5239927A (en) * 1991-07-25 1993-08-31 Rheinmetall Gmbh Deceleration device for submunition
US5253587A (en) * 1991-12-23 1993-10-19 Thomson-Brandt Armements Separation and aerodynamic braking device for the propulsion stage of a missile
US5347931A (en) * 1992-11-12 1994-09-20 Thiokol Corporation Combustible flare ignition system
US5386781A (en) * 1992-11-12 1995-02-07 Thiokol Corporation Parachute deployment system
FR2724221A1 (en) * 1994-09-02 1996-03-08 Lacroix Soc E Projectile with payload designed to be launched at set altitude
EP1296112A2 (en) * 2001-09-25 2003-03-26 Falken, S.A. Device with combustible charge with smoke-generating, tear-generating or signaling effects
EP1296112A3 (en) * 2001-09-25 2004-01-02 Falken, S.A. Device with combustible charge with smoke-generating, tear-generating or signaling effects
CN102278915A (en) * 2011-09-17 2011-12-14 浏阳市余氏科技环保烟花厂 Aerial shell effective piece used for showing aerial subtitle pattern at multi-angle and in all aspects
CN102278915B (en) * 2011-09-17 2014-12-31 浏阳市余氏科技环保烟花厂 Aerial shell effective piece used for showing aerial subtitle pattern at multi-angle and in all aspects
CN102589361A (en) * 2012-04-06 2012-07-18 浏阳市余氏科技环保烟花厂 Subtitle pattern display shell capable of directional transmission
US20150300789A1 (en) * 2012-11-23 2015-10-22 Nexter Munitions Pyrotechnic Gas Generator Component
US9574856B2 (en) * 2012-11-23 2017-02-21 Nexter Munitions Pyrotechnic gas generator component
GB2517445B (en) * 2013-08-20 2020-04-29 Bae Systems Plc Illumination munition
US20160209191A1 (en) * 2013-08-20 2016-07-21 Bae Systems Plc Common carrier munition
US20160209190A1 (en) * 2013-08-20 2016-07-21 Bae Systems Plc Frangible munition
GB2517445A (en) * 2013-08-20 2015-02-25 Bae Systems Plc Illumination Munition
US9778004B2 (en) 2013-08-20 2017-10-03 Bae Systems Plc Smoke payload apparatus
US9784544B2 (en) * 2013-08-20 2017-10-10 Bae Systems Plc Frangible munition
US9797698B2 (en) * 2013-08-20 2017-10-24 Bae Systems Plc Common carrier munition
US10030953B2 (en) 2013-08-20 2018-07-24 Bae Systems Plc Illumination munition
CN103697766A (en) * 2013-12-18 2014-04-02 江西省李渡烟花集团有限公司 Water borne carpet display 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

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