US3098446A - Openable fin arrangement - Google Patents

Openable fin arrangement Download PDF

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Publication number
US3098446A
US3098446A US122988A US12298861A US3098446A US 3098446 A US3098446 A US 3098446A US 122988 A US122988 A US 122988A US 12298861 A US12298861 A US 12298861A US 3098446 A US3098446 A US 3098446A
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United States
Prior art keywords
projectile
ring
fins
opening
gases
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US122988A
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English (en)
Inventor
Jasse Joseph Raymond
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hotchkiss Brandt SA
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Hotchkiss Brandt SA
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Publication of US3098446A publication Critical patent/US3098446A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—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
    • F42B10/20—Stabilising 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

Definitions

  • the present invention relates to openable n arrangements for self-propelled projectiles yshot from a launching tube, which implies that the fins of the Ifin-arrangement must be folded toward the axis of the projectile to permit the latter to travel through the tube, the fins opening out or unfolding as soon as the projectile leaves the tube.
  • the invention more particularly relates to a iin arrangement of the type in which the ns open out by pivoting in longitudinal radial planes about pivot 4axes which are orthogonal to the longitudinal axis of the fin arrangement and located toward the forward ends of the fins, the forward direction corresponding to the direction of motion of the projectile on its trajectory.
  • the object of the invention is to provide an arrangement of this type which is so improved as to be simple in construction and faultless in operation.
  • the iin arrangement according to the invention comprises fins combined with a thrust device which is concentric with and movable along the longitudinal axis of the iin arrangement between a forward position in which the ns are folded back and a rear position in which the fins ⁇ are opened out and maintained in this opened out or unfolded position by the thrust device, the latter being combined with means for exerting thereon an axial thrust which tends to shift the thrust device from the forward position to the rear position.
  • the thrust device comprises a series of pistons or push-rods movable in cylindrical apertures formed in a iin support, the axes of the apertures being parallel with the longitudinal laxis of the fin arrangement, the thrust device further comprising a ring concentric with the axis of the iin arrangement and interposed between the push-rods and fins.
  • the scope of the invention is not limited to this preferred embodiment.
  • FIG. 1 is a longitudinal sectional view of a lin arrangement according to the invention, the fins being in the folded back position.
  • FIG. 2 is a corresponding rear end view
  • FIG. 3 is a longitudinal sectional View of the n arrangement, the tins being in the opened out position;
  • FIG. 4 is a sectional view taken Ialong line 4 4 of FIG. 3',
  • FIG. 5 is a half longitudinal sectional view of a iirst alternative embodiment of the invention, the lins being in the folded back position;
  • FIG. 6 is a half rear end view of the embodiment shown in FIG. 5;
  • FIG. 7 is a half longitudinal sectional view of the embodiment shown in FIG. 5, with the ns in the opened out position;
  • FIG. 8 is a half sectional view taken along a line 8 8 of FIG. 7;
  • FiGS. 9 and 10 are longitudinal sectional views of a second alternative embodiment of the invention, the ns being shown folded back and opened out respectively;
  • FIG. 11 is a half longitudinal sectional View of a third 3,098,446 Patented July 23, 1963 alternative embodiment of the invention with the ns folded 'back in the state of rest;
  • FIG. l2 is a corresponding half rear end view
  • FIG. 13 is a half longitudinal sectional view of the third alternative embodiment with the tins opened out.
  • FIG. 14 is a lhalf sectional view taken along a line 14-14 of FIG. 13.
  • the forward ⁇ direction corresponds to that in which the projectile travels on its trajectory; in FIGS. 1, 3, 5, 7, 9, 10, ll and 13 the forward end is situated on the left.
  • the device according to the invention which constitutes both the propelling jet nozzle and the iin arrangement, is adapted to be fixed in the rear of the body C of a self-propelled projectile, and in particular a rocket, which is shot from a launching tube.
  • This device comprises a metal support 1 provided at the forward end with an external screw thread 2 for screwing into the tapped rear end of the body C.
  • the support y1 has an axial stepped aperture having an axis X-X corresponding to the axis of the body C.
  • This aperture comprises a large counterbore 3, a smooth portion 4 of smaller diameter, a tapped portion 5 of slightly smaller diameter forming with the portion 4 a shoulder 6, and a smooth rear portion 7.
  • a ring 8 constituting the convergent portion and neck of a single axial nozzle, generally designated by the reference character T, provided for the ejection of the propelling gases emanating from the usual propelling charge (not shown in the drawing) disposed within the body C of the projectile.
  • the nozzle T is completed by a rear nozzle body 9 having an axial aperture throughout in a lform of a rearwardly divergent passageway 10.
  • the body 9 is screwed in the tapped portion 5 of the axial aperture of the support 1 and is provided at its rear end with the usual small inner fins 11 which impart a rota-ry motion to the projectile about the longitudinal axis X-X thereof.
  • the body 1 of the lin yarrangement comprises at the forward end in the -counterbore 2, a ring 12 of a heat insulating material adapted to protect this support from the heat and support the ⁇ self-propelling powder block (not shown in the drawing). Disposed between the ring 12 and the support 6 is a metal washer 13 and a washer 14 composed of a heat insulating material.
  • a forwardly convergent aperture 17 having an axis X-X exelnded by a cylindrical aperture 18 visible in particular in Formed in the rear portion of the support 1 Iare radi-al and longitudinal recesses 19 which make therebetween equal angles x (FIG. 4).
  • -A fin 21 of the iin arrangement is disposed in each of the recesses 19; each fin is pivotab-le in its longitudinal middle plane of symmetry, such as Y-X (FIG. 4), labout a transverse axis, such as Z-Z, which is orthogonal to the longitudinal axis X-X of the projectile and iin arrangement.
  • a pin 22 having ⁇ an axis Z-Z is engaged in a blind hole formed in the support 1 (FIG. 4).
  • the fins 21 are pivotable about their respective axes Z-Z between the folde-d back position shown .in FIGS. l and 2 and the unfolded or opened out position shown in FIGS. 3 and 4.
  • the fins are maintained i-n the folded position shown in FIGS. 1 .and 2 and have lsuch shape that in this folded position the inner edge 3 the body C of the projectile.
  • the fins are held in this folded position by an outer ring 27 (FIG. 1) adapted to be removed when the projectile is placed in the launching tube.
  • This thrust device comprises in combination, on the one hand, a single ring 29 slidable in an annular space between the cylindrical face 24 of the body 9 and the cylindrical aperture 18 of the support 1, and, on the other hand, a series of cylindrical push-rods 30 constituted by pistons movable in cylindrical apertures 31 in the support 1 which are disposed on a circle concentric lwith the nozzle T and ⁇ are parallel with the axis X-X, each of the cylindrical apertures 31 communicating with the :forward face of the support 1 in alignment with an aperture 32 which is formed in the washer 13 and thus puts the corresponding aperture in permanent communication with the interior of the body C of the projectile.
  • Each push-rod 30 is provided with a sealing ring 33 and the cylindrical apertures 31 are so disposed that each push-rod or piston 30 bears at its rear end against the ring 29.
  • the latter comprises a at rear face 34, a cylindrical outer lface 35 and an outer flange 36 at its forward end. These various faces of the ring 29 are adapted to cooperated with a forward cam portion of each fin 21.
  • This .forward portion has, when viewed from the side (FIGS. 1 and 3), a substantially ogival shape in that it is defined by an outer convex edge 37 and a flat inner edge 38 in which a notch 39 forms a pointed portion 40.
  • the device according to the invention operates in the following manner:
  • the projectile When being stored, the projectile has its tins folded back in the position shown in FIGS. 1 and 2, their being held in this position by the ring 27.
  • the ring 29 of the thrust -device is then in its extreme forward position against the end of the bore 18 in the support 1 and the push-rods 30 are in their extreme forward position in the immediate vicinity of the apertures 32 in the ring 13.
  • the tin arrangement which is perfectly locked in the open position, stabilizes the projective on its trajectory not only during the acceleration period due to the continued ejection through the nozzle T of the gases produced from the combustion of the ⁇ self-propelling charge, but also during the deceleration period after combustion of the propelling charge, in other words, from the instant of launching until impact on the target.
  • the device is proof against any mishap and in particular any wedging of the folded fins, the latter being opened without use of the usual iin opening spring or springs which are always fragile elements.
  • FIGS. 5 to 8 show a lirst alternative embodiment of the invention-in which the nozzle T1 is in one piece and screwed at 41 in a n suppotr 1a -consisting of three elements 42, ⁇ 43 and 44.
  • the element 42 is provided with an external screw thread ⁇ for screw-threadedly engaging the device constituting the nozzle and iin arrangement in the rear tapped end of the body C of the projectile.
  • the element 43 is screwed-threadedly engaged at 45 on the element 42 and comprises recesses 19EL each of which is adapted to receive one of the lins 21a.
  • the element 43 has a peripheral shoulder 46 which faces forwardly and constitutes the rear portion of a groove adapted to receive a ring 47, the other portion of the groove being formed by the rear -face 48 of the third element 44.
  • rIlhe latter is provided with recesses 19b each of which is in alignment with a recess 19a of the element 43 to permit the free movement of the fins 21a about the ring 47 which constitutes a pivot pin for each lin.
  • the iin 21a co-operates with a thrust device comprising, as in the rst embodiment, a single ring 29a combined with push-rods or pistons 30 movable in cylindrical apertures 31 which are provided in the element 42 and communicate with the interior of the nozzle body by way of a radial recess 49.
  • the edge of the forward end of each n 21' consists of two straight portions 50 and 51 forming a cam and the ring 29a comprises two conical chamfers, namely a rear chamfer 52 and a forward chamfer 53, the latter being provided on the rear face of an outer liange.
  • the ring 29a bears by its chamfer 52 against the straight portion 50 of each tin 21a in the folded position, and when the ring 29EL is shifted rearwardly by the push-rods 30 the chamfer 52 causes the ns to swing open until the position shown in F-IG. 7 is reached, in which there occurs a locking of the ring 29a and the fins 23.5L by the bearing of the portion 50 of the edge of each fin against the cylindrical outer face of the ring 29a, on the one hand, and by the contact between the chamfer 53 of the ring and the portion 51 of the edge of the iin on the other hand.
  • FIGS. 9 and 10 show a second alternative embodiment of the invention which constitutes merely an openable fin arrangement.
  • This embodiment has no self-propelling gas jet nozzle and is consequently of utility on a projectile adapted to be launched or shot solely by means of a launching charge outside the projectile in the manner of a shell, or to be cast off from an aircraft.
  • the iin support 1b comprises the screw thread 2 for mounting in the body C of the projectile and the tins 2lb are mounted thereon for pivotal movement about transverse axes in recesses 19b in the support, the pivot axes being constituted by tubes 22h.
  • ns are opened out without use of a ring common to all the tins, as in the previous embodiments, but -directly by means of individual pushrods 30b movable in cylindrical blind cavities 31h.
  • Each push-rod is biased rearwardly by a spring 54 located between the end of the cavity 31*D and the end of a hole 55 in the corresponding push-rod 30h.
  • This hole 55 communicates with the rear end of the push-rod by way of an orifice 56 adapted in particular to balance the pressure prevailing in the gun tube and cavity 31".
  • the fins are opened solely by the action of the springs 54 which are compressed when the fins are folded back and extend when these fins are free to move so as to bring the latter to the position shown in FIG. in which the push-rods 30h and the ns 2lb become mutually locked.
  • the action of the springs 54 could be replaced by the pressure of the gases produced upon tiring by a certain amount of powder placed in the cavities 31b in place of, or in addition to, springs 54.
  • ignition of this powder could be achieved by way of the orifices 56 in the rear ends of the push-rods 30b and, if desired, by way of passage-ways 58 (FIG. l0) formed in the support 1b.
  • the device adapted to be fixed in the rear of the body C of the self-propelled projectile comprises a support 1c screwed at 2 in this body. Fixed to this support is the axial nozzle T2 having the convergent portion 8 and the divergent portion 9. Disposed forward of this nozzle and the support 1 are protecting washers 13 and 14.
  • each fin is pivotable about a transverse pivot pin 22 which is a force t in the iin and disposed in an annular toroidal groove 60 formed in a rear recess 61 in the support.
  • ytheir ends 62 are tapered to snit the diameter of the groove 6i) so as to fit against its curved annular surface.
  • the tins are mounted in the recesses 19c by introducing their pins 22 into the recess 61 until they engage in the groove 60, before the nozzle T2 has been screwed in position. Once the latter has been mounted together With the fin opening ring, the pins 22C can no longer leave the groove 60.
  • the assembly is completed by push-rods 30 slidable in cylindrical apertures.
  • Each push-rod is adapted to open a fin from the position shown in FIG. 1l to that shown in FIG. l3 under the effect of the thrust of part of the gases from the self-propelling charge, these gases passing through an annular slot 49 into the apertures for the push-rods.
  • the combination of an ejection nozzle for the expulsion of propelling gases and an openable iin arrangement for use on a self propelled projectile comprising a body adapted ⁇ for being connected to the projectile, the body having ⁇ a longitudinal axis and being provided with an axially extending opening passing through the body, the body being further provided with a plurality of cylindrical apertures angularly arranged around said opening at a common distance therefrom and extending parallel to the axis of the body, a fixedly supported nozzle in the opening for expelling rearwardly gases from the projectile to cause a thrust to be exerted thereon, a plurality of tins supported on said body for pivotal movement about transverse axes to enable opening and closing of said fins in longitudial radial planes, a piston slidably supported in each of said apertures and adapted for movement rearwardly in the associated aperture under the propelling action of the gases from the projectile, means defining a cylindrical bearing element rigid with and
  • said body has a rear end in which is provided an annular axial recess in part surrounding the axially extending opening, the body being provided with an annular toroidal groove coaxial with the body and accessible through said recess, said body having radial slots formed therein extending Iforwardly from said rear end in an axial direction beyond said recess -for accommodating said fins, each fin having an aperture adapted for alignment with the toroidal -groove and a pivot pin for each fin in interfering fit in the aperture of the associated iin, said pins having opposite ends extending from the fins supported in the toroidal groove to pivotally support the respective fins from the body.
  • a foldable iin arrangement for a self-propelled projectile comprising, means defining a body :having a support portion adapted for being connected to the projectile and an ejection nozzle portion rigid with the support portion, the body having a longitudinal axis, a throughway axial opening formed in the body and extending through the support and nozzle portions lfor the passage of the projectile propelling gases from the projectile, a plurality of apertures arranged on a circle concentric with said axis and formed in the support portion, the apertures extending in a direction parallel with said axis and communicating with the opening, pistons respectively mounted in the apertures Afor sliding movement in a direction parallel with said axis, a plurality of iins supported on the support portion for pivotal movement about transverse pivot axes in longitudinal radial planes relative to said body between a folded position and an unfolded position, a ycylindrical outer bearing face provided on and coaxial with the body and extending longitudinally

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Discharge By Other Means (AREA)
US122988A 1960-07-11 1961-07-10 Openable fin arrangement Expired - Lifetime US3098446A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR832688A FR1270054A (fr) 1960-07-11 1960-07-11 Empennage déployable pour projectile autopropulsé
FR865095A FR79945E (fr) 1960-07-11 1961-06-15 Empennage déployable pour projectile autopropulsé

Publications (1)

Publication Number Publication Date
US3098446A true US3098446A (en) 1963-07-23

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US122988A Expired - Lifetime US3098446A (en) 1960-07-11 1961-07-10 Openable fin arrangement

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US (1) US3098446A (de)
BE (1) BE605677A (de)
CH (1) CH370677A (de)
DE (2) DE1183834B (de)
ES (1) ES269713A1 (de)
FI (1) FI41122B (de)
FR (2) FR1270054A (de)
GB (2) GB952960A (de)
NL (3) NL113679C (de)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket
US3378216A (en) * 1966-04-29 1968-04-16 Susquehama Corp Integral fin canister-nozzle exit cone
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile
US3861627A (en) * 1972-12-30 1975-01-21 Dynamit Nobel Ag Foldable control flap unit, especially for rockets
US3944168A (en) * 1973-03-14 1976-03-16 Etat Francais Artillery projectile with spreading tail assembly
US3946969A (en) * 1974-07-30 1976-03-30 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US3986684A (en) * 1974-07-30 1976-10-19 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US3986685A (en) * 1974-07-30 1976-10-19 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US3998407A (en) * 1974-07-30 1976-12-21 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US4523728A (en) * 1983-03-07 1985-06-18 Ford Aerospace & Communications Corporation Passive auto-erecting alignment wings for long rod penetrator
US4702436A (en) * 1984-12-13 1987-10-27 Affarsverket Ffv Projectile guide mechanism
US5439188A (en) * 1964-09-04 1995-08-08 Hughes Missile Systems Company Control system
US20050116084A1 (en) * 2003-12-02 2005-06-02 Edward Nitenson Self-propelled projectile
FR2863045A1 (fr) * 2003-11-27 2005-06-03 Giat Ind Sa Dispositif de deploiement securise des ailettes d'un projectile
EP2259006A1 (de) * 2009-06-05 2010-12-08 Tda Armements S.A.S. Öffnungs- und Verriegelungsvorrichtung für Munitionsleitwerk
KR101074028B1 (ko) 2009-02-12 2011-10-17 국방과학연구소 전개된 날개 고정기구를 갖는 비행체
US20230221101A1 (en) * 2022-01-11 2023-07-13 Raytheon Company Effector having morphing airframe and method

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3447852A1 (de) * 1984-12-31 1986-08-28 Heide, Marion, 4030 Ratingen Klappleitwerk fuer fluegelstabilisierte raketengeschosse
US5235930A (en) * 1992-05-08 1993-08-17 Rockwell International Corporation Self propelled underwater device with steerable fin stabilizer
GB2274904A (en) * 1993-02-05 1994-08-10 British Aerospace Deployable wing
US6559370B1 (en) * 2002-08-06 2003-05-06 The United States Of America As Represented By The Secretary Of The Navy Submarine countermeasure vehicle with folding propeller
CN113237393A (zh) * 2021-04-28 2021-08-10 北京星途探索科技有限公司 一种高精度稳定装置

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2365577A (en) * 1943-08-26 1944-12-19 Stephen A Moore Projectile
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR896502A (fr) * 1940-09-23 1945-02-23 Commerciale Caproni Comp Dispositif de commande des ailettes d'un projectile muni d'un empennage
BE552288A (de) * 1953-10-20
LU33739A1 (de) * 1955-07-21
FR1187193A (fr) * 1957-11-15 1959-09-08 Hotchkiss Brandt Empennage déployant perfectionné pour projectile
LU36192A1 (de) * 1958-05-22
NL248980A (de) * 1959-03-09

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2365577A (en) * 1943-08-26 1944-12-19 Stephen A Moore Projectile
US2801587A (en) * 1953-02-06 1957-08-06 Albert S Gould Folding fins for rockets and missiles

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3196793A (en) * 1963-01-16 1965-07-27 Milenkovic Veljko Folded fin rocket
US5439188A (en) * 1964-09-04 1995-08-08 Hughes Missile Systems Company Control system
US3378216A (en) * 1966-04-29 1968-04-16 Susquehama Corp Integral fin canister-nozzle exit cone
US3690595A (en) * 1970-11-19 1972-09-12 Sarmac Sa Self-propelled, vaned missile
US3861627A (en) * 1972-12-30 1975-01-21 Dynamit Nobel Ag Foldable control flap unit, especially for rockets
US3944168A (en) * 1973-03-14 1976-03-16 Etat Francais Artillery projectile with spreading tail assembly
US3946969A (en) * 1974-07-30 1976-03-30 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US3986684A (en) * 1974-07-30 1976-10-19 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US3986685A (en) * 1974-07-30 1976-10-19 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US3998407A (en) * 1974-07-30 1976-12-21 The United States Of America As Represented By The Secretary Of The Army Folding tail fins
US4523728A (en) * 1983-03-07 1985-06-18 Ford Aerospace & Communications Corporation Passive auto-erecting alignment wings for long rod penetrator
US4702436A (en) * 1984-12-13 1987-10-27 Affarsverket Ffv Projectile guide mechanism
FR2863045A1 (fr) * 2003-11-27 2005-06-03 Giat Ind Sa Dispositif de deploiement securise des ailettes d'un projectile
US20050116084A1 (en) * 2003-12-02 2005-06-02 Edward Nitenson Self-propelled projectile
US7083141B2 (en) * 2003-12-02 2006-08-01 Edward Nitenson Self-propelled projectile
KR101074028B1 (ko) 2009-02-12 2011-10-17 국방과학연구소 전개된 날개 고정기구를 갖는 비행체
EP2259006A1 (de) * 2009-06-05 2010-12-08 Tda Armements S.A.S. Öffnungs- und Verriegelungsvorrichtung für Munitionsleitwerk
US20100308153A1 (en) * 2009-06-05 2010-12-09 Tda Armements Sas Device for Opening and Locking a Tail Unit for Ammunition
FR2946423A1 (fr) * 2009-06-05 2010-12-10 Tda Armements Sas Dispositif d'ouverture et de verrouillage d'un empennage de munition
US8563911B2 (en) 2009-06-05 2013-10-22 Tda Armements Sas Device for opening and locking a tail unit for ammunition
US20230221101A1 (en) * 2022-01-11 2023-07-13 Raytheon Company Effector having morphing airframe and method
US11796291B2 (en) * 2022-01-11 2023-10-24 Raytheon Company Effector having morphing airframe and method

Also Published As

Publication number Publication date
FI41122B (de) 1969-04-30
GB952960A (en) 1964-03-18
ES269713A1 (es) 1962-01-01
BE605677A (fr) 1961-11-03
NL295319A (de)
FR79945E (fr) 1963-02-15
NL113679C (de)
FR1270054A (fr) 1961-08-25
DE1195204B (de) 1965-06-16
NL266892A (de)
GB945409A (en) 1963-12-23
DE1183834B (de) 1964-12-17
CH370677A (fr) 1963-07-15

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