US1879840A - Bladed projectile - Google Patents

Bladed projectile Download PDF

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Publication number
US1879840A
US1879840A US493675A US49367530A US1879840A US 1879840 A US1879840 A US 1879840A US 493675 A US493675 A US 493675A US 49367530 A US49367530 A US 49367530A US 1879840 A US1879840 A US 1879840A
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United States
Prior art keywords
projectile
folded
wings
tail
blades
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Expired - Lifetime
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US493675A
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English (en)
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Brandt Edgar William
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Individual
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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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • 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
    • F42B10/02—Stabilising arrangements
    • F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
    • F42B10/16—Wrap-around fins

Definitions

  • This invention relates to improvements in bladed projectiles, and more particularly to a projectile of this type with a high specific capacity, intended to be projected by the aid of a discharging device preferably of smooth bore type.
  • the projectiles usually employed with said devices comprise substantially a body of suitable shape, terminated by a perforated tall .10' in which a propulsive cartridge is inserted,
  • the improvements forming the subject of the invention enable perfect stability to be obtained in the case of any projectile whatsoever (more particularlv, however, projectiles of high capacity) durin flight, whilst obviating the drawbacksierembefore referred to.
  • the rear of the projectile is equipped with blading, which is wholly or partially movable and is adapted to move automatically, when vthe shot is fired, from one stable position into the other, that is to say, from a neutral (or. folded) position,in which it isretained close to the body of the projectile in such a way as to cause a minimum of obstruction in the launching tube,
  • the invention also comprises various devices which assure the actuation of the blading, at the desired moment, under the influence of one or more of the following agencies; air resistance, elastic members, the gas theinertia of the blading and the like.
  • the invention also comprises blocking devices (operating by springs, inertia or the like) which assure the retention of the blading in its neutral and operative positions respectively. 35
  • the invention also contemplates various designs of blading, intended to assure optimum stabilization, whilst permitting the introduction of additional charges for the purpose of strengthening the action of the propulsive cartridge.
  • the projectile according tothe invention can be stabilized in its trajectory under the most favourable conditions, even for 93 very high-angle fire, owing to the fact that the blading, when fixed in the operative position, operates in a zone of compression. It is thus possible, in accordance with the invention, to stabilize projectile of a far greater
  • the destructive eifect of projectiles of great length in calibres is well known to those engaged in the art.
  • the projectiles according to the invention are admirably adapted for the destruction of objectives situated at acertain height above the ground, such as lines of barbed wire, which are mown down, by the fragments of theprojectile, over a far greater area than with a shorter projectile.
  • Fig. 1 is an elevation of an embodimentof a projectile according to the invention, with the wings outspread; v
  • Fig. 2 is a partial section on a larger scale
  • Fig. 3 is a partial section, with the wings folded together
  • Fig. 1 is a section along the line 4-4 of Fig. 2, looking towards the rear of the projectile;
  • Figs. 7 and 8 represent an embodiment of the device for locking the blades in the closed and expanded positions respectively;
  • Fig. 9 is a modification of said device
  • FIG. 11 is a partial elevation and partial longitudinal section of a second embodiment of the blading according to the invention, showing the wings spread out;
  • Fig. 12 is a partial end view and cross section along the line 12-12 of Fig. 11, with the wings spread out;
  • Fig. 13 is a partial elevation, showing the complete blading in the folded condition
  • Fig. 14 is an end view of the blading of Fig. 13
  • Fig. 15 is a section, along the line 15-15 of Fig. 13, of a detail of this blading, on a larger scale;
  • Fig. 16 is a partial axial section of a third embodiment of the blading, in the closed position
  • Figs. 17 and 18 represent respectively an end view of this embodiment and a detail I of same, on a larger scale;
  • Fig. 19 is an elevation of the blading according to Fig. 16 in the operative position
  • Fig. 20 is a longitudinal section of a differeut construction of the blading according to the invention, with the blades in the closed position;
  • Fig. 21 is an end view of this blading.
  • the body 1 tapers at 4, preferably in the form of a truncated cone, the minor base of which is at the rear end. This portion is closed by a wall 5 (Fig. 2).
  • the portion 4 terminates in a heel 6, to which is suitably attached a' tubular tail 7, of known type, provided with a certain number of openings 8.
  • This tail is intended to house .the propulsive cartridge, the wall of which lodges in a groove 9 when the shot is fired.
  • the tail 7 is provided, on the
  • each of these small blades is composed of an arm 13, provided with two integrally cast straight fins 14, 15 (Figs. 1-4) and a concave-convex terminal plate 16.
  • the fins 14, 15 are parallel to one another, and, when the blades are opened out, are parallel to the axis of the projectile, whereas, in that position, the medial axis AA of the terminal plate 16 (Fig. 2) is slightly inclined Fig. 10 is a detail of Fig. 2, on a larger scale;
  • a heel, such as 17 (Fig. 7), provided near the pivotal point of each blade 12 is des gned so as to come in contact with the end of the tail, in orderto retain the blade in the outspread or extended position.
  • FIG. 5 In the modification shown in Fig. 5, several series of blades 18 are provided, each series being pivoted, at the forward end, on a shaft 19, carried, for example, by a fixed blade 20. Prior to firing, the blades are retained in folded position against the body of the projectile, either by hand or by suitable accessory means, against the action of a spring 21 which causes them to extend-or spread out, like a fan, on issuing from the tube.
  • pivotal axis 22 is, placed in the rear, which: enables a widely projecting blading to be obtained in the extended or opened-out position 23.
  • the blades may be constructed in any suitable manner, such as stamping, welding, in one or more pieces, or the like; The may also be shaped in any form suitable or the parts they are to play. In order to keep the blades in position, various" devices may be employed, such as those hereinafter described.
  • the strength of the spring and the form of the notches 27 28, are designed so that, on the one hand, they hold the blades firmly in the closed position, to pre'ventthem from shaking,'or from catching while the projec-, tile is being handled, and, on the other hand, to prevent the blades, when opened out, from folding up'again when the porjectile, fired ata high angle, begins to drop. They are also designed so as to allow the blades to be released, under the action of the air resistance, at the moment the projectile is launched, and also as to enable a blade which has been locked in the opened position to be folded again by manual pressure.
  • the blades are retained in the closed and opened positions, by means of a bent spring 29, adapted to engage in the notches 30 and 31 respectively.
  • the blades may also be held in the folded position, previous to firing, by means of a locking ring 32 (Figs. 2 and 10) slidably mounted on the tail/7.
  • This ring is provided with forward clips 33 which engage the plates 16 when the ring is retained in the locking position by arched springs 34, of suitable strength, engaging in a groove 35 in the tail 7
  • arched springs 34 of suitable strength
  • the blades may be connected to ether by means of a suitable ligature 36 TFig. 3) preferably of silk or other material capable of being burned by the combustion of the propulsive charge.
  • This ligature may be replaced by a spring (not shown) provided with a certain num ber of shallow notches corresponding to the edges, such as 37, of the arms of theblades.
  • the various components ofthe pro ectile may be constructed of any suitable metal whatsoever, the body, for example, being of steel, and the wings of aluminium.
  • Figs. 11 to 15 represent another embodiment, in which the blades, such as 38, 39, of cylindrical or other shape, are arranged to pivot on axes, such as 40 parallel to the axis of the projectile.
  • the axes 40, 41 which are preferably profiled in front (42, Fig. 11) to lessen their resistance to the air;-'are'supported by rigid members, such as 43, 44, 45, suitably attached to the tail 7. Openings 46 provided in said members andin the blades, to the ri 'ht of the perforations 8 in the tail 7, allow the powder gases to pass.
  • a fusible ligature 47 (lead wire for example), preferably disposed on the front part of the tail, so as notto hinder the insertion of the cartridge, retains the blades in the folded position prior to firing, and, when the projectile is fired, disappears under the action of the heat generated by the deflagration of the powder gases.
  • the heel pieces 49 serve also to hold the additional charges, such as 51, in the recesses between the blades and the tube. 011 issuing from a the tube, the blades, liberated in this manner, are forced, by springs 48, into the outspread or extended position'represented in Figs. 11 and 12, in which their heel pieces 49 encounter the stops 50 .by which the projectile is guided in the tube (Figs. 12 and 15).
  • the blades are preferably arranged to fit one over the other, when in the closed position, (as shown in Figs. 1 4 and'15) above the supporting members, such as 43, 44.
  • the whole, firmly supported against the tail 7, thus becomes extremely rigid and prevents any distortion of the blades, both in handling and under the effect of the defiagrationthus being approximately double the area of' the exterior peripheral surface available-
  • the incurved form of the blades increases their resistance.
  • the spring control enables the blades to open outwithout any sudden jolt. Moreover, the absence of any projection, and the uniform arrangement of the surface of the blades, assure to the projectile the most favourable conditions of navigation on its trajectory.
  • the bladihg is-arranged so as to slide longitudinally and, on the projectile beingfircd. to move into a position beyond the vortical zone set up behind the projectile and in which the stabilizing forces acting on the blading do so with a greater amount of lever- WVith this object, the tail carrying the blades-is provided with an extension 52 (Fig. 16) suitably attached thereto, or integral therewith.
  • This extension52 is adapted to slide in a guide tube 53 centred in the axis of the projectile and is provided with a part 41, approximately i of larger diameter 55a at its forward end. Inside said guide tube is housed an inter mediate member 54 (Fig.
  • the projectile is fired, the gases of the cartridgeescape by the openings 8, cause the a bolt 59 to move inwards, and thus release the over at their outer edges 61, as shown, in order to increase their peripheral stablhzing action.
  • They are also slightly inclined on the axis of the projectile, so as to set up a drag-' s ng efl'ect under the most favourable condi tions fromv the point of View of stability of flow.
  • They are advantageously provided with ribs at 62 (Fig. 17), intended'to increase the moment of'inertia of the dangerous section'of-the blade, and with gaps 63 ensuring the equilibrium of the pressures.
  • They are preferably rounded at, their forward ends at 51a.
  • the sliding blading 64 1noves rearwards, under the action of the inertia of its mass, at the moment of firing, iii overcoming the resistance of the locking spring 65.
  • the ailerons (i6 stabilize chiefly by drag.
  • a projectile comprising a body, ivots mounted at the rear of the body para lel to the longitudinal axis of the projectile and uniformly distributed about said axis, stabilizingwings each comprising a substantially rigid structure having the form when folded V of a portion of an outwardly concave cylinder, two said wings being articulated on each said pivot and inidividually movable therearound between folded and extended positions, the said wings having in folded position a diameter less than and in extended position a diameter greater than the caliber of the projectile, awing mounted on one of ⁇ said pivots being in folded position in overlapping relationship with a wing of the adjacent pivot, the wings oneach pivot moving in opposite angular directions about the pivot in passing from folded to extended positions, interengaging elements on each wing and on the body for limiting the extending movement of the wing, and means for moving the wings from folded to
  • a projectile comprising a body, pivots" mounted at the rear of the body parallel to the axis ofthe projectile and. uniformly distributed about said axis, stabilizing wings articulated on the pivots and movable therearound between folded and extended positions, said wings having .in folded position a diameter less than-and in extended position a diameter greater than the caliber of the projectile, and leaving between them and a launching tube, when'folded, recesses to accommodate propelling" charges, and means for moving the wings from folded to extend- 1 ed position.
  • a projectile comprisingia body, a perforated tubular tail fixed at the bottom of the projectile, a propulsive charge in the tail, pivots mounted on the perforated tail Ill] parallel to the axis of the projectile and uniformly distributed around said axis, stabilizing wings articulated on the pivots "and movable therearound between folded andextended positions, said wings having in folded position adiameter less than and in extended position a diameter greater than the caliber of the projectile, andleaving between them and a, launching tube, when folded, recesses to accommodate additional propelling 12 charges, and means for moving the wings from folded to extended position.
  • a projectile comprising a body, aperforated tubular tail fixed at the bottom of the projectile, --a propulsive charge in the tail, pivots mounted on the perforated tail parallel to the axis of the projectile and uniformly distributed around said axis, stabilizing wings articulated on the pivots and movable therearo'und between folded and exm es' to accommodate additional propelling charges, means to hold said additionalpropelhng char es m said recesses, and means for moving t e wings from folded to extend-i ed position.
  • a projectile comprising a body, a perforated tubular tail fixed at the bottom of the projectile, a propulsive, charge in the tail, pivots mounted on the perforated tail parallel to the axis of the projectile and uniformly distributed around said axis, stabilizing wings articulated on the pivots and movable therearound between folded and extended position, said wings having in folded position a diameter less than and in extended position a diameter greaterthan the caliber of the projectile, and leaving between them and a launching tube, when folded, recesses to accommodate additional charges, elastic means for moving the wings from folded to extended position and coopcrating abutment members on the wings and the body for retaining the wings in extended position in opposition to the action of the said elastic means, the said abutments on the wings serving also to retain the additional propelling charges.
  • a projectile comprising a body, a perforated tubular tail fixed at the bottom of the projectile, a propulsive charge in the tail, pivots mounted on the perforated tail parallel to the axis of the projectile and uniformly distributed around said axis,stabilizing wings articulated on the pivots and movable therearound between folded and extended position,said wings having in folded position a diameter less than and in extended position a diameter greater than the caliber of the projectile, and leaving between them and a launching tube, when folded, recesses to accommodate additional propelling charges, elastic means for moving the wings from folded to extended position, and cooperating abutment members on the wings and the body for retaining the wings in extended position in opposition to the action of the said elastic means, the said abutments on the body serving also to guide the projectile in the firing tube.
  • a projectile comprising a body, pivots mounted at the rear of the body parallel to the axis of the projectile and uniformly dis tributed about said axis, stabilizing wings articulated on'the pivots and movable therearound between folded and extended positions, said wings having in folded position a diameter less than and in extended position a diameter greater than the caliber of the projectile,each wing comprising a substantially rigid structure having, when folded, the form of a portion of an outwardly conpropelling" cave cylinder, and means for moving the wings from folded to extended position.
  • a projectile comprisin a body, a. erforated tubular tail fixed at the bottom 0 the projectile, a propulsive charge in the tail, pivots mounted on the perforated tail parallel to the axis of the projectile and uniformly distributed around said axis, stabilizing wings articulated on the pivots and movable therearound between folded and extended positions, said wings having in folded position a diameter less than and in extended position a diameter greater than the caliber of the proj ectile, the said wings resting on one another when folded and being further provided with perforations opposite the perforations in the tail'when the wings arefolded, the wings leaving between them and a launching tube, when folded, recesses to accommodate additional propelling charges, and means for moving the wings from folded to extended position;
  • a projectile comprising a body, a perforated tubular tail fixed-at'the bottom of the projectile, a propulsive charge in the tail, pivots mounted on the perforated tail parallel to the axis of the projectile and uniformly distributed around said axis, stabilizing wings articulated on the pivots and movable therearound between folded and extended positions, said wings having in folded position a diameterless than and in extended position a diameter greater than the caliber the projectile, a propulsive charge in the tail,
  • disruptible ligatures connecting the wings and the perforated tubular tail for retaining the wings in folded position; said ligatures passing through the said perforated tubular tail and being disrupted upon the firing of the charge, and means for extending the wings after disruption of the said connecting ligatures.
  • a projectile comprising a body, pivots mounted at the rear of the body substantially parallel to the axis of the projectile and disdiameter less t tributed about said axis, stabilizing wings articulated on the pivots and movable therearound between folded and extended ositions, said win shaving in' folded posit1ona llan and in extended'position a diameter greater than the caliber of the projectile, each wing comprising a substantially rigid structure presenting, when in folded position, an outwardly open recess,
  • a projectile comprising a body, pivots mounted at the rear of the body substantially parallel to the axis of the pro ectile and distributed about said axis, pairs of stabilizing f wings jointed on each said pivot, the wings of each pair being movable about the common pivot for said pair in opposite angular directions between folded and, extended posieter less than and in extended position a diameter greater than the caliber of the projectile, each wing comprising a substantially rigid structure presenting, when in folded position, an outwardly open recess,
  • a projectile comprising abody, pivots mounted at the rear of the body substantially parallel to the axis of the projectile and distributed about said axis, pairs of stabilizing'wings jointed on each said pivot, the
  • each pair being movable about the common pivot for sald palr 1n opposite angu- 5 lar directions between folded and extended positions and having in folded position a diameter less than and in extended position a diameter greater than the caliber of the projectile, and van individual torsion spring surrounding each said pivot and operating upon both the wings of the pair thereon for moving the wings from folded to extended position.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Emergency Lowering Means (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
US493675A 1930-05-22 1930-11-05 Bladed projectile Expired - Lifetime US1879840A (en)

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FR711464T 1930-05-22

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US579088A Expired - Lifetime US1890175A (en) 1930-05-22 1931-12-04 Projectile having guide tails

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US (2) US1879840A (fr)
BE (1) BE379532A (fr)
CH (2) CH154854A (fr)
DE (2) DE552877C (fr)
FR (3) FR711464A (fr)
GB (3) GB362381A (fr)
NL (2) NL34616C (fr)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2421752A (en) * 1943-02-22 1947-06-10 Eureka Williams Corp Rocket projectile
US2426239A (en) * 1942-12-28 1947-08-26 Henry M Renner Rocket shell
US2430896A (en) * 1944-01-08 1947-11-18 Edward G Uhl Rocket stabilizing fins
US2458475A (en) * 1943-04-02 1949-01-04 Charles C Lauritsen Rocket device
US2465401A (en) * 1943-09-23 1949-03-29 Leslie A Skinner Rocket fin assembly
US2480927A (en) * 1944-03-16 1949-09-06 Raymonde Briggs Hopkins Aerial torpedo
US2538333A (en) * 1946-10-30 1951-01-16 Schermuly Conrad David Signal or smoke rocket
US2630066A (en) * 1945-02-08 1953-03-03 Speers G Ponder Incendiary bomb
US2661689A (en) * 1948-05-10 1953-12-08 Bristol Aeroplane Co Ltd Holding means for projectile fins
US2666387A (en) * 1949-12-07 1954-01-19 United Aircraft Corp Stabilizing fins for missiles
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US2792756A (en) * 1952-05-06 1957-05-21 Brevin A G Soc Rocket launching support structure
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles
US2925966A (en) * 1957-10-08 1960-02-23 Kongelbeck Sverre Folding fin or wing for missiles
DE1103813B (de) * 1953-04-27 1961-03-30 Luxembourgeoise De Gestion Et Geschoss fuer Granatwerfer
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles
US3139794A (en) * 1962-01-08 1964-07-07 Texaco Experiment Inc Launcher and rocket
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
US3478686A (en) * 1967-08-25 1969-11-18 Fairchild Hiller Corp Target marking device
US3622103A (en) * 1968-07-11 1971-11-23 Oerlikon Buehrle Ag Twistless projectile with launching tube
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile
US3756539A (en) * 1970-07-11 1973-09-04 Tampella Oy Ab Stabilization fins for projectiles
US3918664A (en) * 1973-08-24 1975-11-11 Rheinmetall Gmbh Launchable missile having a tail unit
US4262862A (en) * 1978-02-18 1981-04-21 Messerschmitt-Bolkow-Blohm Gesellschaft mit beschraankter Haftung Apparatus for changing the wing positions of swingable wings of a missile
US4295617A (en) * 1979-10-02 1981-10-20 The United States Of America As Represented By The Secretary Of The Army Selectable drag brakes for rocket range control
FR2572513A1 (fr) * 1984-10-26 1986-05-02 Messerschmitt Boelkow Blohm Dispositif pour corriger l'orientation d'une munition
US4586681A (en) * 1983-06-27 1986-05-06 General Dynamics Pomona Division Supersonic erectable fabric wings
US20050082419A1 (en) * 2003-06-27 2005-04-21 Richard Dryer Projectile with propelling charge holder
US8151711B1 (en) * 2009-03-07 2012-04-10 Lockheed Martin Corporation Supercavitating projectile with reduced-drag control surfaces

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2494885A (en) * 1944-07-01 1950-01-17 Lax Walter Lennard Bomb and other stores containers for dropping from aircraft
US2466528A (en) * 1946-05-31 1949-04-05 Gulf Research Development Co Dirigible bomb
US2519123A (en) * 1947-07-10 1950-08-15 Dwyer Martin Hand-operated rocket type device for signaling and other purposes
BE533456A (fr) * 1953-12-21 Brandt Soc Nouv Ets
NL95893C (fr) * 1954-03-22
US2942545A (en) * 1954-11-23 1960-06-28 Gordon L Fogal Stabilizing system for mine dropped from aircraft
US2858765A (en) * 1956-08-07 1958-11-04 Dale E Startzell Spring-loaded, locking hinge fin assembly
DE1067340B (fr) * 1956-08-11
DE1083155B (de) * 1957-12-07 1960-06-09 Ilyana Von Thyssen Bornemisza Granatwerfergeschoss
DE1134316B (de) * 1958-04-04 1962-08-02 Bombrini Parodi Delfino Societ Raketengeschoss mit Klappenleitwerk
DE1099907B (de) * 1959-04-25 1961-02-16 Baronin Ilyana Von Thyssen Bor Fluegelstabilisierte Moersergranate
GB1523963A (en) * 1976-02-26 1978-09-06 Hawker Siddeley Dynamics Ltd Method and means for auxiliary control of vehicle direction
FR2864612B1 (fr) * 2003-12-24 2007-11-23 Giat Ind Sa Dispositif de deploiement des ailettes d'un projectile

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2426239A (en) * 1942-12-28 1947-08-26 Henry M Renner Rocket shell
US2421752A (en) * 1943-02-22 1947-06-10 Eureka Williams Corp Rocket projectile
US2458475A (en) * 1943-04-02 1949-01-04 Charles C Lauritsen Rocket device
US2465401A (en) * 1943-09-23 1949-03-29 Leslie A Skinner Rocket fin assembly
US2430896A (en) * 1944-01-08 1947-11-18 Edward G Uhl Rocket stabilizing fins
US2480927A (en) * 1944-03-16 1949-09-06 Raymonde Briggs Hopkins Aerial torpedo
US2630066A (en) * 1945-02-08 1953-03-03 Speers G Ponder Incendiary bomb
US2538333A (en) * 1946-10-30 1951-01-16 Schermuly Conrad David Signal or smoke rocket
US2661689A (en) * 1948-05-10 1953-12-08 Bristol Aeroplane Co Ltd Holding means for projectile fins
US2666387A (en) * 1949-12-07 1954-01-19 United Aircraft Corp Stabilizing fins for missiles
US2671398A (en) * 1951-05-11 1954-03-09 Allen S Peck Metal pop-out stabilizing tail for small bombs
US2792756A (en) * 1952-05-06 1957-05-21 Brevin A G Soc Rocket launching support structure
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles
DE1103813B (de) * 1953-04-27 1961-03-30 Luxembourgeoise De Gestion Et Geschoss fuer Granatwerfer
US3185097A (en) * 1956-08-02 1965-05-25 Vincent J Cushing Missile stabilizing means
US2925966A (en) * 1957-10-08 1960-02-23 Kongelbeck Sverre Folding fin or wing for missiles
US3127838A (en) * 1960-10-12 1964-04-07 Bombrini Parodi Delfino Spa Retractable blade tail unit for projectiles
US3139794A (en) * 1962-01-08 1964-07-07 Texaco Experiment Inc Launcher and rocket
US3478686A (en) * 1967-08-25 1969-11-18 Fairchild Hiller Corp Target marking device
US3622103A (en) * 1968-07-11 1971-11-23 Oerlikon Buehrle Ag Twistless projectile with launching tube
US3756539A (en) * 1970-07-11 1973-09-04 Tampella Oy Ab Stabilization fins for projectiles
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile
US3918664A (en) * 1973-08-24 1975-11-11 Rheinmetall Gmbh Launchable missile having a tail unit
US4262862A (en) * 1978-02-18 1981-04-21 Messerschmitt-Bolkow-Blohm Gesellschaft mit beschraankter Haftung Apparatus for changing the wing positions of swingable wings of a missile
US4295617A (en) * 1979-10-02 1981-10-20 The United States Of America As Represented By The Secretary Of The Army Selectable drag brakes for rocket range control
US4586681A (en) * 1983-06-27 1986-05-06 General Dynamics Pomona Division Supersonic erectable fabric wings
FR2572513A1 (fr) * 1984-10-26 1986-05-02 Messerschmitt Boelkow Blohm Dispositif pour corriger l'orientation d'une munition
US20050082419A1 (en) * 2003-06-27 2005-04-21 Richard Dryer Projectile with propelling charge holder
US7024998B2 (en) * 2003-06-27 2006-04-11 Raytheon Company Projectile with propelling charge holder
US8151711B1 (en) * 2009-03-07 2012-04-10 Lockheed Martin Corporation Supercavitating projectile with reduced-drag control surfaces

Also Published As

Publication number Publication date
DE594354C (de) 1934-03-15
FR711464A (fr) 1931-09-10
CH154854A (fr) 1932-05-31
NL34616C (fr) 1934-09-15
CH161490A (fr) 1933-04-30
GB376216A (en) 1932-07-07
DE552877C (de) 1932-06-18
GB362381A (en) 1931-12-01
FR40569E (fr) 1932-07-27
GB375517A (en) 1932-06-30
NL39621C (fr) 1936-07-15
BE379532A (fr)
FR40883E (fr) 1932-09-16
US1890175A (en) 1932-12-06

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