US2821924A - Fin stabilized projectile - Google Patents

Fin stabilized projectile Download PDF

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US2821924A
US2821924A US442456A US44245654A US2821924A US 2821924 A US2821924 A US 2821924A US 442456 A US442456 A US 442456A US 44245654 A US44245654 A US 44245654A US 2821924 A US2821924 A US 2821924A
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projectile
piston
forward
position
rear
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US442456A
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Lawrence J Hansen
Rosenberg Philip
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Lawrence J Hansen
Rosenberg Philip
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/04Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type
    • F42B12/10Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of armour-piercing type with shaped or hollow charge
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00Means 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
    • F42B10/02Stabilising arrangements
    • F42B10/14Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00Means 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
    • F42B10/02Stabilising arrangements
    • F42B10/14Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/20Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Description

Feb. 4, 195s L. J. HANSEN ET AL FIN STABILIZED PROJETILE Filed July 9, 1954 United States Patent() FIN STABILIZED PROJECTILE Lawrence J. Hansen, Palos Park, and Philip Rosenberg, Chicago, Ill., assignors, by mesne assignments, to the United States of America as represented by the Secretary of the Army Application July 9, 1954, Serial No. 442,456

3 Claims. (Cl. 102-50) The present invention relates to a n stabilized artillery projectile.

More particularly, the invention relates to a lin stabilized artillery projectile provided with a compact, foldable n arrangement containable within a standard artillery cartridge `case and which will travel through a gun tube without appreciable damage to the bore.

Ammunition of this type generally is spin stabilized, and though originally intended for anti-aircraft defense, has also been adapted for use against tanks and other ground targets as Well as water borne targets by virtue of the incorporation of armor-piercing and high explosive substances.

. For certain specific purposes, experience has indicated that better armor penetration, jet formation and more effective `destruction of a selected target is possible for lin stabilized (essentially non-rotating) rather than spinl stabilized projectiles, there being imparted to the projectile, if desired, only suicient rotation of the order of R. P. S.` to correct for manufacturing inaccuracies. An

important design consideration of any projectile in ight t is its stability, and in a iin stabilized projectile a prime design factor is the iin area since stabilization of the projectile in flight depends to a large degree upon the amount of air rushing past the tins. In projectiles of the nature contemplated, where lixed tins are used the outer diameter of the lin assembly is governed by the diametral limitation imposed by the tapered forward end of the cartridge case, hence in order to achieve more elective iin area, theprojectile is provided with a tapered boom section and decreased hub diameter. the above described design the rear larger diameter end of the cartridge case is usually provided with guide rails to engage the longitudinal edge of each tin in order 1) to prevent the tail fins from bearing against the side wall of the tapered cartridge case, (2) to guide the projectile as it leaves the case, and (3) to cut down windage and yaw to obtain less departure of the projectile from true trajectory thereby insuring less dispersion in tiring.

`The foldable iin type projectile may be designed to achieve all the accuracy obtained by the prior art projectile without the use of guide rails. At the same time greater stabilization of the projectile in ight is possible since the area of the ns in unfolded position may be increased considerably over the corresponding area of a iixed lin projectile.

It is4 accordinglyV an important aim of this invention to provide a projectile having a compact, foldable iin arrangement receivable in a standard artillery cartridge case.

@It is alsoan important object of this invention to provide-a projectile having a compact, foldable lin arrange- Consequently in ment receivable in a standard artillery cartridge case, and

Another'paramount purpose of this invention is to provide a projectile having compact foldable tins pivotably mounted on the boat-tail of the projectile, a differential pressure hollow piston translatable in the boattail of the projectile and a chamber to trap some of the propellent gases which in turn are released as the projectile is exposed to atmosphere to cause the piston to move rearwardly to thereby unfold the tins to fully open position.

A further consideration impelling the conception of this invention is the provision of a projectile having a compact, foldable iin arrangement receivable in a standard artillery cartridge case, and wherein the foldable ins in fully open position present a larger n area to atmosphere than normally prevalent in a projectile of a similar type using tixed tins, wherefore greater stability of the projectile in flight or the same degree of stability with a shorter, more compact projectile is achieved.

It is also in mind to provide a projectile having the above advantages, and also constructed and arranged to insure ease of assembly, handling and storing.

Additional objects, advantages and features of the invention reside in the construction, arrangement and com` bination of parts involved in the embodiment of the invention as will appear from the following description and accompanying drawings, wherein:

Figure l is a side elevation, partly in section of an artillery projectile contained within a cartridge case,

Figure 2 is a longitudinal sectional View illustrating the projectile per se, the ns shown in folded position,

Figure 3 is an enlarged fragmentary sectional View, the

- fins shown in extended position,

Figure 4 is a cross section view taken on the line 4-4 of Figure 2.

Referring more particularly to the drawing wherein like reference characters have been used to designate similar or corresponding parts throughout the several views, reference character 10 generally represents an artillery shell having its rearward end containable within a standard artillery cartridge case 12.

The projectile details per se form no part of the present invention and may be brieiiy described as comprising a central tubular portion 13, forwardly threaded internally at 14 to screw threadedly receive the reduced rear end of a forwardly tapering nose 16, into the forward end of which is screwed a spit back point detonating fuse 18 to complete the forward ogive of the projectile. The forf ward end of tubular portion 13 approximately coextensively with its threaded portion 14 is seen as a slightly enlarged cylindrical annulus forming the forward bourrelet 20. Tubular portion 13 is'also provided with a thickened rear wall 22 centrally apertured at 24 to screw threadedly receive aclosure plug 26, and extending axially forwardly forward bourrelet, and an axial ash passage 34 extending between the apex of the conical cavity 32 and the base detonator 28. The shaped cavity 32 is provided with a liner 36 in the well known manner, the liner being extended as at 38 to line the passage 34. The shell 10 is also provided with a second bourrelet 40 spaced forwardly of the rear end of the shell to provide guidance for the shell as it traverses the barrel bore as is well known.

The operation of this portion of the device is readily i apparent from the above description.

As the shell is tired the arming mechanism operates to place an explosive lead (not shown) in base detonator 28 in the fully armed position, i. e. in axial alinement with ash passage 34. Upon impact the point fuse 18 is initiated and the Patented Feb. 4, g

flash, and concussion of thev detonating.. wave` travels rearwardly through the hollow space formed by nose 16 and conical cavity 32, then through the flash passage 3,4,` to set oifthe, base, detonator 28 whichv inl turnr is in` ashcommunicationwith the high explosive 3010- explode the shell upon the desired target.

The fin assembly and fin actuating mechanism forming the hubof the invention is mountedupon the boattail 42 of the projectile modifiedv to accommodate the necessary elements. This modified boattail is` seen. as a spool like member 44 having a rear rim or flange 46, and a forward rim 48 made integral with a. forwardly. extending elongated sleeve orcylindrical wall 50 adapted to snugly and tightly4 encompass the rear end of shell' 10which is reduced; in diameterA rearwardly of. rear. bourrelet 40 as at S2; cylindrical; wall 5,0,also presenting an. outer diameter slightlysrnaller than bourrelet 40 toenablebourrelet 40 to engage the barrell bore. The boat tail 42 is secured to Shell soas to provide a chamber 54 between the.. rear wall 22 and the forwardy face ofv riml 48', chamber 54 in turn communicating, witha. reduced axial bore 5,6 extending through spool 44, and into which is receiveddifferential pressure piston 60.

As clearly seen in Figure 2 hollow piston 6.0 is a two part member comprising a forward sleeve 62 which in stowed; iin position is arranged so that a, portion of its rear surface slidingly engagesthe wall of bore 56, and its forward portion annularly flanged at 64 to extend partially into chamber 54. Flange 6,4 forms an annular stop ring to limit the rearward travel of piston 60 in a manner to be later described. The rear end* of sleeve 62 is providedwith a threaded tenon 65 for screw threadedly receiving the forward end of a second-sleeve 70 of piston 60 which also slidingly engage the wall of bore 56, there being an annular space 71 provided between the rear and forward ends of sleeves 62 and 70 respectively, to receive an annular shear ring 72 integral with the wall ofl-bore 56and extending radially into space 71, wherefore sleeves 62 and 70 are normally locked against translation. To limit forward movement of piston 60, sleeve 70 is providedwith an annular flange 6L which engages av shoulder 57 formed by enlarging the rearmost end of bore 5.6,in spool 44. Sleeve 70 is in turn provided rearwardly with a rearwardly extending conical wall 74 terminating in a rearwardly axially extending reduced boss 76 which is also provided with an outwardly-struck rear flange 73 having front and rear beveled surfaces 80, 82 respectively fora purpose to be later described, there being an axial reduced bore or orifice 84 extending through boss 76 as plainly seen in Figure 2. A plurality of bifurcated rearwardly extending lugs 86 are secured in anyconvenient manner in circumferential array to the rear flat face of rim or flange 46 of spool 44, there being circumferentially alined bores formed in each bifurcated lug 86 to receive pinsv SSfor pivotally mounting a iin 90 (see Figure 4), each fin 90 being an elongated fin section having a forward flat end 92 adapted to abut the rear flat face of flange 46 and to extend radially inwardly to partially overlie, bore 56 in spool 44 when the fins are in stowed position.

In this same stowed position the fins 90 are arranged so that a circumference corresponding to the leading edge of the tins is slightly less than the maximum circumference of flange 46, and the forward outer corner of each viin is truncated as at 94 so that the fins may be free to pivot outwardly by the rearward movement of piston 60 as later to be described. The forward trailing edge of each fin (the inner edge in stowed position as seen in Figure 2) normally abuts the side wall of boss 76, there being recesses 96 formed in each said trailing edge in registry with the flange 78, the recesses 96 being beveled to permit a predetermined rotation or folding outward of each iin whereupon there is engagement between flange 78 and the beveled surfaces of recess 96l to hold thetins in position. As shown in Figure 3 the unfolded position of the tins resultsA in approximately a 25 degree inclination between the leading edge and the longitudinal axis of the projectile.

The cartridge case 12 is provided with a large diameter elongated cylindrical rear portion 100, a forward tapering portion 102 which in turn merges with a smaller diameter cylindrical extension 104. In4 assembly extension 104 snugly engages the outer periphery of cylindrical wall 50 of spool member 44, and theouter peripheryy ofrear bourrelet 40, the forward end of extension 104 being crimped over the shoulder formed between bourrelet 40 and tubular shell wall 13. The fins normally are in stowed or folded; positiony with hollow piston 60 held in its forward position by shear ring 72, The cartridge case 12 has been filled with propellent 106 in the accepted manner, and the fins 90 are completely embedded within the loosely packed propellant. It is important to note at this time 'that forward sleeve 62 ofpiston 60- is provided with an outwardly ared or tapered surface 108 extending between the respective forward and, rear opposed facesY of rim or flange. 48Y of spool 44 and annular flange 64 of piston sleeve 62.

ln operation the propellent powder 106 is ignited and the resulting pressure acts to propel the projectile. As this pressure. increases and the shell travels the length o f the gun tube, orifice 84. admits some of the powder gas by way of hollow piston 60.into chamber 54 in the boattail. At. the same time the high differential pressure acting on the rear surface of piston 60. holds the fin. and piston assembly in place together with shear ring 72, thereby counteracting 'the effects of set back forces. As the projectile leaves the muzzle of the gun the external pres.- sure drops rapidly to. atmosphere while the gas pressure in the chamber of the, boattail remains relatively high. The entrapped pressure causes piston 60 to move rearwardly shearing annular shear ring 72 and causing tapered surface` 108 to engage the wall of bore 56 in spool 44. Ask piston 60 moves rearwardly the. beveled surfaces 80, 82. of flange 78 which are in continuous engagement with the beveled edges ofrecesses 96 in the tins 9,0 cause the fins 90 to pivot and move outwardly, the high pressure. in chamber 54 exerting an accelerating force on the piston and fins before the interference resistance of the taper becomes suflicient to noticeably counteract the forces tending. to move the piston. As the piston 60. continues. to move rearwardly the resistance offered by tapered sur.- face 108l increasel to effect deceleration ofthe piston and iins to an extent to prevent overstressing of the, mechanism when stop ring 6,4,y seats against the rear face of flange 48 o n spool 44. Also instrumental in easing thev loadf on the stop ring is the decrease in energy of the trapped gases due to the work spent in moving the piston, andthe pressure drop in the boattail chamber due to the simultaneous escape of gases through orifice 84. Asl clear.- ly seen in Figure 3, in the fully opened, position, there is an angle of approximately 25 degrees between the leading edge of each nand thelongitudinalaxisof the projectile. The fins are locked ink this fully opened position bythe keying` action between the beveled surfaces of angev 78 and the bevelededges of recesses 96l in the/fins, andthe interference fit between surface 1,08` of forward sleeve 62and the inner surface of axial bore 56, thus preventing the iins from folding inward while the projectile is in ilight.

From the foregoing it is apparent that there has been described a projectile having a compact, foldable lin arrangement receivable in a standard artillery case, wherein the foldable iins in fully opened position present a larger n area to atmosphere than normally obtainable in a projectile having a fixed fin` arrangement, thereby achieving greater stability in flight, and wherein a novel rack andl pinion mounting for each fin enables the fins to unfold positively and without the risk of over-stressing the.

mechanism by virtue of the col-action rof the fins'with a differential pressure piston received in the modified boattail of the projectile, and movable in response to the pressure of the gases formed by the detonation of the propellent charge.

While a specific embodiment of the invention has been shown and described, it will be understood that various alterations may be made without departing from the spirit of the invention as indicated by the sub-joined claims.

We claim:

1. In a projectile of the type having a cartridge casing and shell portion comprising a boat-tail xed to the rear end of said shell and carrying a plurality of nested eX- tensible stabilizing fins, said boat-tail and said iins inclosed within said cartridge casing, said tins being embedded n the propelling charge, an axial bore formed in said boat-tail, a chamber formed in said boat-tail in axial alignment with said bore forwardly thereof and communicating therewith, a hollow piston having a restricting orifice therein slidingly fitting said bore, there being shear pin means holding said piston in a forward position whereby the forward portion of said piston extends within said chamber, the forward end of said piston within said chamber being tapered to an enlarged diameter at its forward end, said piston communicating uid under pressure to said chamber upon ignition of said propelling charge, means at the rear end of said piston operatively associated with said fins to extend said tins radially outwardly upon rearward movement of said piston in response to dilerential pressure between said chamber and the atmosphere, said piston being locked in rearward position by said tapered portion and said bore.

2. A projectile comprising a hollow body and a boattailed rear end, a hollow piston having a restrictive orifice therein slidable in an axial bore formed in said boattail, a pluralityl of foldable stabilizing tins hingedly secured to the rear face of said boattail and overlying said axial bore, said fins adapted to nestle in folded position to present no protrusion beyond the outside diameter of said hollow body, there being a chamber formed in said boattail concentric about the forward end of said hollov' piston, a cartridge casing and propelling charge therein for injecting fluid under pressure through said hollow piston and into said chamber, said piston adapted to slide axially rearwardly in response to differential pressure between said chamber and atmosphere while said projectile is in ight, whereby said piston pivots said ns outwardly to unfolded stabilizing position and means to lock said piston in said rearward position.

3. A projectile adapted to be tired from a smooth bore weapon and comprising, a hollow body having a boattailed rear end, a plurality of radially disposed unfolding vanes pivotally mounted on pins secured in circumferential array on the bottom of said boattail, said vanes adapted in folded position to enter the casing of a cartridge case forming part of said projectile, there being an axial bore formed in said boat-tail in open communication with an enlarged chamber concentric about the forward end thereof, a differential pressure piston in engagement with an overlying portion of each said vane, said piston having an axial bore therethrough with a restrictive orifice therein being axially rearwardly slidable to unfold said vanes, releasable means retaining said piston in vane folded position, a propellant charge in said cartridge case injecting a uid under pressure into said chamber through said piston bore and adjacent the forward end of said piston to release said piston for movement into vane unfolding position and means to lock said piston in said vane unfolded stabilizing position.

References Cited in the lile of this patent UNITED STATES PATENTS 1,274,281 Kowalski July 30, 1918 2,613,605 Brandt Oct. 14, 1952 FOREIGN PATENTS 10,325 Great Britain of 1912 896,502 France Mar. 2, 1944 634,090 Great Britain Mar. 15, 1950

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Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2938460A (en) * 1956-09-12 1960-05-31 Energa Finned projectile
US2941470A (en) * 1955-03-02 1960-06-21 Brandt Soc Nouv Ets Self-propelled projectile
US2960035A (en) * 1958-09-15 1960-11-15 Robert W Burton Target missile
US3053184A (en) * 1959-03-09 1962-09-11 Hotchkiss Brandt Gas ejecting nozzle and projectile stabilizing fins for a self-propelled projectile
US3113285A (en) * 1961-09-27 1963-12-03 William R Edwards Wave measuring apparatus
US3113486A (en) * 1959-06-10 1963-12-10 Kongelbeck Sverre Turrent launcher
US3139794A (en) * 1962-01-08 1964-07-07 Texaco Experiment Inc Launcher and rocket
US3188954A (en) * 1958-05-14 1965-06-15 Paul G Roach Gas ejection bomb for dispersing solid particulates
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket
US3289587A (en) * 1965-07-07 1966-12-06 John J Donnelly Fin stabilized projectile
US3292879A (en) * 1965-06-25 1966-12-20 Canrad Prec Ind Inc Projectile with stabilizing surfaces
US3304030A (en) * 1965-09-24 1967-02-14 James E Weimholt Pyrotechnic-actuated folding fin assembly
US3347492A (en) * 1965-06-14 1967-10-17 Forsvarets Fabriksverk Projectile with a rearwardly directed steering tube
US3728964A (en) * 1966-09-15 1973-04-24 Us Navy Aimed warhead
US3913487A (en) * 1973-09-07 1975-10-21 George H Scherr Projectile
US3944168A (en) * 1973-03-14 1976-03-16 Etat Francais Artillery projectile with spreading tail assembly
US4023496A (en) * 1972-08-09 1977-05-17 The United States Of America As Represented By The Secretary Of The Army Ejector motor braking system
US4109884A (en) * 1976-02-12 1978-08-29 Messerschmitt-Bolkow-Blohm Gmbh Apparatus and method for storing pressure gas in a reservoir of a projectile
US4133265A (en) * 1975-12-19 1979-01-09 Dynamit Nobel Ag Training projectile
US4332360A (en) * 1980-07-21 1982-06-01 The United States Of America As Represented By The Secretary Of The Army Automatically deployed shell fins
US4702436A (en) * 1984-12-13 1987-10-27 Affarsverket Ffv Projectile guide mechanism
EP0389358A1 (en) * 1989-03-24 1990-09-26 Thomson-Brandt Armements Opening system for spreading wings on a projectile
US5615847A (en) * 1995-09-11 1997-04-01 The United States Of America As Represented By The Secretary Of The Navy Submarine launched unmanned aerial vehicle
US20040094661A1 (en) * 2000-07-03 2004-05-20 Stig Johnsson Method and arrangement for artillery missiles
US20090126523A1 (en) * 2007-11-19 2009-05-21 Fjerstad Erik A System and method for deployment and actuation
CN104089547A (en) * 2014-06-30 2014-10-08 中国航天时代电子公司 Unfolding and locking device for foldable rudder face
US9068807B1 (en) * 2009-10-29 2015-06-30 Lockheed Martin Corporation Rocket-propelled grenade
US9140528B1 (en) 2010-11-16 2015-09-22 Lockheed Martin Corporation Covert taggant dispersing grenade
US9200876B1 (en) 2014-03-06 2015-12-01 Lockheed Martin Corporation Multiple-charge cartridge
US9423222B1 (en) 2013-03-14 2016-08-23 Lockheed Martin Corporation Less-than-lethal cartridge
US9644929B1 (en) 2013-12-03 2017-05-09 Michael S. Bradbury Pilum bullet and cartridge

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191210325A (en) * 1912-05-01 1912-12-05 Boris Svistounoff Improvements in or relating to Projectiles.
US1274281A (en) * 1918-02-16 1918-07-30 Gus J Kowalski Projectile.
FR896502A (en) * 1940-09-23 1945-02-23 Commerciale Caproni Comp A control device of the fins of a projectile with a tail
GB634090A (en) * 1946-07-15 1950-03-15 William Alexander Onslow Marti Improvements in and connected with stabilizing fins for projectiles
US2613605A (en) * 1946-11-09 1952-10-14 Energa Projectile

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191210325A (en) * 1912-05-01 1912-12-05 Boris Svistounoff Improvements in or relating to Projectiles.
US1274281A (en) * 1918-02-16 1918-07-30 Gus J Kowalski Projectile.
FR896502A (en) * 1940-09-23 1945-02-23 Commerciale Caproni Comp A control device of the fins of a projectile with a tail
GB634090A (en) * 1946-07-15 1950-03-15 William Alexander Onslow Marti Improvements in and connected with stabilizing fins for projectiles
US2613605A (en) * 1946-11-09 1952-10-14 Energa Projectile

Cited By (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941470A (en) * 1955-03-02 1960-06-21 Brandt Soc Nouv Ets Self-propelled projectile
US2938460A (en) * 1956-09-12 1960-05-31 Energa Finned projectile
US3188954A (en) * 1958-05-14 1965-06-15 Paul G Roach Gas ejection bomb for dispersing solid particulates
US2960035A (en) * 1958-09-15 1960-11-15 Robert W Burton Target missile
US3053184A (en) * 1959-03-09 1962-09-11 Hotchkiss Brandt Gas ejecting nozzle and projectile stabilizing fins for a self-propelled projectile
DE1148160B (en) * 1959-03-09 1963-05-02 Hotchkiss Brandt Fa Nozzle and fin assembly for missiles
US3113486A (en) * 1959-06-10 1963-12-10 Kongelbeck Sverre Turrent launcher
US3113285A (en) * 1961-09-27 1963-12-03 William R Edwards Wave measuring apparatus
US3139794A (en) * 1962-01-08 1964-07-07 Texaco Experiment Inc Launcher and rocket
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket
US3347492A (en) * 1965-06-14 1967-10-17 Forsvarets Fabriksverk Projectile with a rearwardly directed steering tube
US3292879A (en) * 1965-06-25 1966-12-20 Canrad Prec Ind Inc Projectile with stabilizing surfaces
US3289587A (en) * 1965-07-07 1966-12-06 John J Donnelly Fin stabilized projectile
US3304030A (en) * 1965-09-24 1967-02-14 James E Weimholt Pyrotechnic-actuated folding fin assembly
US3728964A (en) * 1966-09-15 1973-04-24 Us Navy Aimed warhead
US4023496A (en) * 1972-08-09 1977-05-17 The United States Of America As Represented By The Secretary Of The Army Ejector motor braking system
US3944168A (en) * 1973-03-14 1976-03-16 Etat Francais Artillery projectile with spreading tail assembly
US3913487A (en) * 1973-09-07 1975-10-21 George H Scherr Projectile
US4133265A (en) * 1975-12-19 1979-01-09 Dynamit Nobel Ag Training projectile
US4109884A (en) * 1976-02-12 1978-08-29 Messerschmitt-Bolkow-Blohm Gmbh Apparatus and method for storing pressure gas in a reservoir of a projectile
US4332360A (en) * 1980-07-21 1982-06-01 The United States Of America As Represented By The Secretary Of The Army Automatically deployed shell fins
US4702436A (en) * 1984-12-13 1987-10-27 Affarsverket Ffv Projectile guide mechanism
EP0389358A1 (en) * 1989-03-24 1990-09-26 Thomson-Brandt Armements Opening system for spreading wings on a projectile
FR2644880A1 (en) * 1989-03-24 1990-09-28 Thomson Brandt Armements Opening system for a projectile empennage deployant
US5082203A (en) * 1989-03-24 1992-01-21 Thomson-Brandt Armements System for the opening of an unfolding tail unit for projectiles
US5615847A (en) * 1995-09-11 1997-04-01 The United States Of America As Represented By The Secretary Of The Navy Submarine launched unmanned aerial vehicle
US20040094661A1 (en) * 2000-07-03 2004-05-20 Stig Johnsson Method and arrangement for artillery missiles
US20070084961A1 (en) * 2000-07-03 2007-04-19 Bofors Defence Ab Method and arrangement for low or non-rotating artillery shells
US7226016B2 (en) 2000-07-03 2007-06-05 Bae Systems Bofors Ab Method and arrangement for low or non-rotating artillery shells
US20090126523A1 (en) * 2007-11-19 2009-05-21 Fjerstad Erik A System and method for deployment and actuation
US7906749B2 (en) * 2007-11-19 2011-03-15 Raytheon Company System and method for deployment and actuation
US9068807B1 (en) * 2009-10-29 2015-06-30 Lockheed Martin Corporation Rocket-propelled grenade
US9140528B1 (en) 2010-11-16 2015-09-22 Lockheed Martin Corporation Covert taggant dispersing grenade
US9423222B1 (en) 2013-03-14 2016-08-23 Lockheed Martin Corporation Less-than-lethal cartridge
US9644929B1 (en) 2013-12-03 2017-05-09 Michael S. Bradbury Pilum bullet and cartridge
US9200876B1 (en) 2014-03-06 2015-12-01 Lockheed Martin Corporation Multiple-charge cartridge
CN104089547B (en) * 2014-06-30 2016-01-27 中国航天时代电子公司 Locking means for folding and deployment of the control surfaces of the
CN104089547A (en) * 2014-06-30 2014-10-08 中国航天时代电子公司 Unfolding and locking device for foldable rudder face

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