US3805702A - Detachable connection between a projectile and a propellant-charge case - Google Patents

Detachable connection between a projectile and a propellant-charge case Download PDF

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Publication number
US3805702A
US3805702A US00338894A US33889473A US3805702A US 3805702 A US3805702 A US 3805702A US 00338894 A US00338894 A US 00338894A US 33889473 A US33889473 A US 33889473A US 3805702 A US3805702 A US 3805702A
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United States
Prior art keywords
propellant
detachable connection
charge case
connection according
recess
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
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US00338894A
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English (en)
Inventor
A Voss
H Kroschel
M Strunk
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Dynamit Nobel AG
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Dynamit Nobel AG
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Publication date
Priority claimed from DE19722210869 external-priority patent/DE2210869C3/de
Application filed by Dynamit Nobel AG filed Critical Dynamit Nobel AG
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/067—Mounting or locking missiles in cartridge cases
    • F42B5/073—Mounting or locking missiles in cartridge cases using an auxiliary locking element
    • D—TEXTILES; PAPER
    • D06—TREATMENT OF TEXTILES OR THE LIKE; LAUNDERING; FLEXIBLE MATERIALS NOT OTHERWISE PROVIDED FOR
    • D06M—TREATMENT, NOT PROVIDED FOR ELSEWHERE IN CLASS D06, OF FIBRES, THREADS, YARNS, FABRICS, FEATHERS OR FIBROUS GOODS MADE FROM SUCH MATERIALS
    • D06M23/00—Treatment of fibres, threads, yarns, fabrics or fibrous goods made from such materials, characterised by the process

Definitions

  • ABSTRACT A detachable connection between a projectile and a propellant-charge case for cartridge-encased ammunition adapted to be fired from a gun barrel.
  • the propellant-charge case is provided at the front end zone with at least one recess receiving a locking element radially displaceable between inner and outer end positions.
  • the element in the outer end position projects outwardly of the propellant-charge case to an extent sufficient to prevent complete introduction of the propellant-charge case into the gun barrel and is supported in this position by a movable blocking member which is displaceable against the force of a spring toward the rear of the propellant-charge case.
  • the projectile which is to be connected with the propellant-charge case is provided with a tail portion arranged for contacting the blocking member and to displace the blocking member toward the rear.
  • the tail portion is also provided with a recess adapted to be engaged by the locking element upon displacement of the blocking member such that the locking element assumes the inner end position connecting the projectile and the propellant charge case and permitting introduction of the flush connection of the projectile and the propellant-charge case into the gun barrel for support therein.
  • the present invention relates to a detachable connection between a projectile and a propellant-charge case for cartridge-encased ammunition to be shot from the barrel of a gun.
  • a characterizing feature of cartridge-encased ammunition is the connection of the projectile and the propellant charge.
  • This connection can be fixed or detachable. However, in the latter case, there must be the assurance that the connection, produced mostly by hand, is so firm that it is not released when loading the ammunition or during the transporting of the loaded gun.
  • the detachable connections are screw or plug connections. In such couplings, there is the danger that the threading or plugging step is not carried out entirely whereby a firm connection is not provided so that detachment is possible, for example, by vibration or impact. In practice, accidents have happened repeatedly because of such faulty connections or because several propellant charges were simultaneously introduced into the gun by mistake.
  • the propellant-charge case in the zone of its front end is provided with at least one locking element guided in a recess and being radially displaceable between an outer and an inner end position.
  • the locking element projects, in the outer end position, from the propellantcharge case to such an extent that it prevents the further introduction of the propellent-charge case into the gun barrel and is detained in the outer end position by resting on the inside on a blocking member arranged within the propellant-charge case.
  • the blocking member is axially rearwardly displaceable against the force ofa spring by the introduction of the tail of the projectile into the propellant-charge case, thereby permitting the locking element to engage in the inner end position thereof, a corresponding recess of the tail of the projectile.
  • the locking element is fixed in this connection, with a flust coupling of projectile and propellantcharge case, by being supported with the outer surface thereof against the inner wall of the gun barrel.
  • the propellant charge cannot detach itself from the projectile, even when the gun is set down hard, since the locking element is arrested in its inner end position wherein the projectile and the propellant-charge case are in flush connection by resting against the inner wall of the gun barrel.
  • the surface of the locking element and/or of the muzzle of the gun barrel or the recess in the tail of the projectile is formed to be inclined in the common contact zone, so that forces actually effective in the axial direction are divided in the common contact zone into force components including a radial component which makes it possible for the at least one locking element to be radially displaced.
  • Such axial forces occur during the loading of the ammunition, when the tail of the projectile is introduced into the propellant-charge case and the front end of the propellant-charge case presses the locking element against the gun muzzle.
  • the blocking member which is under a spring force, is pressed toward the front against the tail of the projectile, and the latter, in turn, is pressed correspondingly against the locking element.
  • the locking element passes over spontaneously from its outer end position into the inner end position during the loading of the ammunition, while, during the discharge, it passes over conversely spontaneously again into the outer end position in an advantageous manner, as soon as it can no longer contact the inner surface of the gun barrel.
  • the front region of the propellant-charge case equipped with the at least one locking element, is connected with the remaining portion of the propellant-charge case by way of a predetermined breaking or rupturing point.
  • the arrangement can be such that the separated front portion of the propellant-charge case remains connected to the tail of the projectile and hits the target together therewith, or falls to the ground harmlessly after a certain flight distance from the gun.
  • the provision can be made, for example, to keep the radial play between the projectile tail and the section of the case to be separated relatively small, in order to join both parts by a frictional connection.
  • the front zone of the propellant-charge case having the locking element is advantageously constructed for reasons of manufacturing technology as a separate mounting ring connected with the remaining parts of the propellantcharge case by suitable securing means such as glue, screws, or the like.
  • the blocking member is formed as a sliding sleeve coaxially arranged between the propellant-charge case and an internal socket inserted therein, wherein the internal socket, in view of the pressure effect of the propellant gases, is suitably provided with radial pressure equalization bores.
  • the invention furthermore provides that the propellant-charge case and the internal socket project past the front end of the sliding sleeve in the position for locking the locking element in the outer end position so that the sliding sleeve is protected from an immediate unauthorized access.
  • At least two locking elements are suitably disposed so that they are symmetrically distributed along the circumference of the propellant-charge case.
  • a suitable locking element may, for example, be in the form of a cylindrical pin provided on one or optionally also both ends with a lenticular, spherical, or like curvature, in order to facilitate the sliding of this pin along the muzzle of the gun barrel and/or along the rear edge of the recess in the tail of the projectile.
  • balls as locking elements.
  • the locking element can be manufactured, for example of steel, as maybe the sliding sleeve. The strength, hardness, etc. must be chosen so that the flawless functioning of the safety coupling is ensured even after repeated loading and discharging.
  • the recess for the at least one locking element provided in the zone of the front end of the propellant-charge case is constructed to be inclined, as seen from the inner end thereof, toward the rear end of the propellant-charge case.
  • the recess for the locking element can be constructed, for example, as a circular-cylindrical bore, i.e., with a straight longitudinal axis, or also with a helically wound longitudinal axis. In any event, however,
  • the arrangement can be such that the locking element, after leaving the gun barrel, is pressed out of its recess by the thus-produced flow of propellant gases and separates away from the projectile in a controlled direction.
  • the direction is determined, for example, by the speed of the projectile, the ejection speed of the locking element, and the inclination of the recess.
  • the propellant-charge case is provided, for this purpose, in the zone of the recess for the locking element, with an inner and optionally also an outer annular groove.
  • the inner annular groove effects, after emptying of the gun barrel, a rapid escape of the propellant charge gases, especially if the front zone of the propellant-charge case carrying the locking element is provided with radial pressure equalization bores.
  • the outer annular groove in contradistinction, makes it possible, in the gun barrel, that the propellant charge gases can quickly attain access to the outside of the locking element and thus contributes toward relieving the pressure thereon.
  • the present invention furthermore provides that the locking element contacts the wall of the recess only at a few points along its periphery.
  • the locking element does not fill the cross section of the recess entirely, so that part of the propellant charge gases can flow off laterally past the locking element through the recess.
  • the recess can be formed for this purpose with a regular polygonal or hexagonal cross section, so that when a ball is employed as the locking element, this ball contacts the wall of the hexagonal cross-sectional recess only at six points.
  • the present invention further provides that the outer diameter of the front zone of the sliding sleeve is formed to be somewhat smaller than the outer diameter of the rear end of the projectile.
  • the sliding sleeve is provided in its rear zone with radial pressure equalization bores in order to prevent this part from being bent during firing under the effect of the propellant gases, or that it is torn off and thereby, in certain cases, results in a jamming of the parts of the coupling within the gun barrel after firing. Such a jamming is undesirable, since it makes the loading of the next round difficult.
  • FIG. 1 is a fragmentary longitudinal section view of a propellant-charge case and a projectile prior to connecting the same in accordance with an embodiment of the present invention
  • FIG. 2 is a fragmentary sectional view illustrating the coupled components within the gun barrel
  • FIG. 3 is a fragmentary sectional view of the propellant-charge case and the projectile in the coupled condition within the gun barrel in accordance with another embodiment of the present invention
  • FIG. 4 is a fragmentary sectional view of the zone of the recess of the locking element of the FIG. 3 embodiment on an enlarged scale;
  • FIGS. 5a and 5b are fragmentary sectional views respectively illustrating different arrangements for the front zone of the propellant-charge case.
  • FIG. 6 is a plan view of the mounting ring and the internal socket in a plan view.
  • FIG. 1 there is shown a propellant-charge case 1 and a gun barrel 2, only the front portions of which are illustrated.
  • the propellantcharge case 1 is pushed into the gun barrel 2 to such an extent that the locking elements 3, in this instance, for example, three balls arranged so that they are uniformly distributed along the periphery of the propellant-charge case, abut against the gun barrel muzzle 4.
  • the locking elements 3 are disposed within a recess 5 in the front zone of the propellant-charge case 1 with the recess 5 being constructed as a radial bore, bent over toward the inside and outside, so that the ball cannot escape from the bore on any side.
  • the front zone of the propellant-charge case 1 with the locking elements 3 is constructed as a separate mounting ring 6 having a tubular extension 7 which projects into the remaining part of the propellantcharge case 1 and is joined thereto for example by gluing.
  • the locking elements 3 rest interiorly on an axially movable sliding sleeve 8 which, in its locking position, is pressed by a spring 9 toward the front against the abutment face 10 in the mounting ring 6 and/or its extension 7.
  • the rearward portion of the spring 9 rests against an internal socket member 11, which is firmly connected with the projection 7 as, for example, by gluing.
  • the mounting ring 6 has a predetermined rupturing point 12, formed as an annular notch, at the transition to the extension 7 of the mounting ring such that during firing, the actual mounting ring 6 is separated at this rupturing point.
  • the mounting ring 6 furthermore exhibits radial pressure equalization bores 13 disposed so that they are uniformly distributed along the circumference.
  • the internal socket 11 in order to avoid an undesired deformation under the effect of the gas pressure of the reacting propellant charge housed in the interior 14 of the propellant-charge case 1, is provided with radial pressure equalization bores 15 which are covered during storage and transporting of the propellant charge by a foil of, for example, aluminum, not shown, for preventing the entrance of, for example, atmospheric humidity.
  • the sliding sleeve 8 is also provided with a sealing ring 16 of felt, for example, seated on the internal socket 11.
  • the latter carries, at its front end, an annular disk 17 of a synthetic hard foam material, for example.
  • the annular disk 17 is provided with an aperture 18 which makes it possible to ignite an additional solid-fuel rocket engine disposed in the projectile, which engine is not shown, by means of the hot propellant gases of the firing charge and is sealed until firing by means of a foil 19, for example, of aluminum.
  • the tail portion of a projectile 20, only a portion of which is illustrated and shown at a spacing from the propellant-charge case 1, has an exteriorly disposed recess 21 at the tail end which, in this embodiment, is formed as a continuous annular groove.
  • Two sealing rings 22 of Teflon, Perbunan, or the like are arranged in succession on the jacket of the tail 20 of the projectile.
  • the tall 20 of the projectile then rests with its abutment face 24 against the mounting ring 6.
  • the locking elements 3 Upon a further axial pressure on the tail 20 of the projectile, the locking elements 3 are pressed by the rounded inner edge 25 of the gun muzzle 4 toward the inside into the recess 21, so that the propellant-charge case 1, together with the projectile, can be pushed as shown in FIG. 2 into the loaded position in the gun barrel 2.
  • the locking elements 3 then connect the propellant-charge case 1 flush with the tail 20 of the projectile and are arrested in this position by supporting themselves against the inner wall of the gun barrel 2, so that a separation of projectile and propellant charge in the gun barrel 2, except for during firing, is no longer possible.
  • the locking elements 3 are pressed again toward the outside into their locking position preventing the individual loading of the propellant charge by means of the sliding sleeve 8 under the force of the spring 9 and/or by the rear edge 26 of the recess 21 in the tail 20 of the projectile, as soon as the ammunition has been shifted toward the front to such an extent that the locking elements 3 have exited from the gun muzzle 4 and thus can no longer rest within the gun barrel 2.
  • the projectile and the propellant charge are then again separated from each other, and the propellant charge is blocked against inappropriate individual loading.
  • the locking elements 3 in the form of balls are guided in recesses 5, the longitudinal axis of the recesses being inclined with respect to the transverse axis of the propellant-charge case 1 by the angle a (FIG. 4).
  • an angle a of, for example l has proved to be advantageous.
  • the direction of the inclination is selected so that the recess 5, as seen from the interior ofthe propellant-charge case 1, points to the rear end of the propellant-charge case 1.
  • the tubular extension 7 of the mounting ring 6 is flanged over at its rear end 27 into a corresponding annular groove 28 of the internal socket 11, so the latter is securely connected with the mounting ring 6 in a shape-mating manner.
  • the sliding sleeve 8 has radial pressure equalization bores 29 provided in the rear zone thereof.
  • FIG. 4 shows, by the arrow P, the force exerted on the locking element 3, during firing, by the propellantcharge case 1 or the mounting ring 6, respectively.
  • the force P has an axial component P, and a radial component P,.
  • the latter is directed toward the interior of the-propellant-charge case 1 and thereby effects the radial relief of the locking element 3 according to this embodiment and thus results in a considerable reduction of the wear and tear on the barrel by the locking element 3 in pressure contact therewith.
  • the force exerted by the edge 26 of the tail of the projectile on the locking element 3 during firing is not illustrated for drawing clarity.
  • the outer diameter of the sliding sleeve 8 is, in its front region, smaller than the outer diameter of the rear end of the projectile to aid in its movement in the uncoupling operation.
  • the sliding sleeve 8 is provided with the rounded portion 30 to aid in the movement beneath the locking ball 3.
  • the extension 7 in accordance with this embodiment is provided with axially extending predetermind breaking points 31, constructed as a longitudinal notch, only one of which is shown in in FIG. 4.
  • the mounting ring 6 is provided, in the zone of the recess indicated in dashed lines, with the inner and outer annular grooves 32, 33 and as shown in FIG. 5b, the recess 5 formed in the mounting ring is provided for example with a hexagonal cross section.
  • FIG. 6 is a plan view illustrating the mounting ring 6 with the extension 7 surrounding the internal socket 11. As shown, the mounting ring is provided with a plurality of recesses receiving the locking elements 3 as well as a plurality of pressure equalization bores 13.
  • the mounting ring is provided with an annular predetermined breaking point 12 and axial predetermined breaking points 31, only one of which is illustrated.
  • the present invention thus provides a detachable safety coupling arrangement for a projectile and propellant charge case which ensures a flawless connection and the maintenance thereof within a gun barrel.
  • connection between a projectile and a propellant-charge case for cartridge-encased ammunition fired from a gun barrel, said propellant charge case having a front and a rear end and a longitudinal axis, said connection comprising first recess means provided in the zone of the front end of said propellant charge case, at least one locking means being received in said first recess means for guided movement therein and being radially displaceable between inner and outer end positions with respect to the longitudinal axis of said propellant charge case, said locking means in the outer end position projecting out of said propellantcharge case to an extent sufficient to prevent the complete introduction of said propellant charge case into the gun barrel, blocking means disposed in said propellant-charge case for supporting said locking means in the outer end position thereof, means biasing said blocking means into the support position and said blocking means being displaceable toward the rear end of said propellant-charge case from the support position against the force of said biasing means, said projectile having a tail portion for connection with said propellant-charge case and arranged for contacting said blocking means
  • said propellant-charge case is provided with a predetermined breaking point in the region joining the front zone with a rearwardly extending portion of said propellant-charge case whereby the front zone breaks away from the rearwardly extending portion when a predetermined force at said predetermined breaking point is exceeded.
  • said blocking means is a sliding sleeve means coaxially arranged between said propellant-charge case and an internal socket means disposed within said propellant-charge case.
  • Detachable connection according to claim 1, comprising at least two locking means and at least two first recess means provided in the front end zone of said propellant charge case receiving said locking means, said first recess means and said locking means being symmetrically positioned along the periphery of said propellant-charge case.
  • said first recess means has a cross-sectional shape which differs from the cross-sectional shape of said locking means movable therein such that said locking means contacts said first recess means only at spaced points along the periphery of said locking means.
  • said mounting ring includes the front end zone of said propellant-charge case and a tubular member extending rearwardly therefrom, said tubular member being provided with axially extending predetermined breaking points.
  • said blocking means is a sliding sleeve means coaxially arranged between said propellant-charge case and an internal socket means disposed within said propellant-charge case.
  • Detachable connection according to claim 30, comprising at least two locking means and at least two first recess means provided in the front end zone of said propellant charge case receiving said locking means, said first recess means and said locking means being symmetrically positioned along the periphery of said propellant-charge case.
  • first recess means has a cross-sectional shape which differs from the cross-sectional shape of said locking means movable therein such that said locking means contacts said first recess means only at spaced points along the periphery of said locking means.
  • sliding sleeve means is provided with a first outer diameter at the front region thereof and said tail portion of said projectile is provided with a second outer diameter in the region of said second recess means, said first outer diameter being less than said second outer diameter.
  • said mounting ring includes the front end zone of said propellant-charge case and a tubular member extending rearwardly therefrom, said tubular member being provided with axially extending predetermined breaking points.
  • said locking means is a ball member.

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  • Engineering & Computer Science (AREA)
  • Textile Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Closures For Containers (AREA)
US00338894A 1972-03-07 1973-03-07 Detachable connection between a projectile and a propellant-charge case Expired - Lifetime US3805702A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19722210869 DE2210869C3 (de) 1972-03-07 1972-03-07 Lösbare Verbindung zwischen Geschoß und Treibladungshülse
DE2232866A DE2232866C3 (de) 1972-03-07 1972-07-05 Lösbare Verbindung zwischen Geschoß und Treibladungshülse

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US3805702A true US3805702A (en) 1974-04-23

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US00338894A Expired - Lifetime US3805702A (en) 1972-03-07 1973-03-07 Detachable connection between a projectile and a propellant-charge case

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US (1) US3805702A (it)
BE (1) BE796400A (it)
DE (1) DE2232866C3 (it)
FR (1) FR2220768B1 (it)
GB (1) GB1383135A (it)
IT (1) IT979712B (it)
NL (1) NL7303202A (it)
NO (1) NO133289C (it)
SE (1) SE385404B (it)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259319A (en) * 1992-03-20 1993-11-09 Richard Dravecky Reusable training ammunition
US20020111643A1 (en) * 1999-07-28 2002-08-15 Aesculap Ag & Co. Kg Surgical clip
US20030136293A1 (en) * 2000-04-27 2003-07-24 Werner Torsten Reusable grenade cartridge
US20110023742A1 (en) * 2009-07-31 2011-02-03 Schaefer Alan R Pressure seal
US9329008B1 (en) * 2013-08-08 2016-05-03 The United States Of America As Represented By The Secretary Of The Army Low collateral damage kinetic energy projectile

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2611888A1 (fr) * 1987-03-02 1988-09-09 Roche Kerandraon Oliver Munitions a propulsion par haute pression de faible duree et lanceurs associes sans recul
FR2620214B1 (fr) * 1987-09-09 1990-04-13 France Etat Armement Bague de liaison entre un projectile et une douille

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2529504A (en) * 1948-04-26 1950-11-14 William J Kroeger Ammunition for recoilless firearms
US2993444A (en) * 1945-08-02 1961-07-25 Charles E Hablutzel Sabot retainer
US2998778A (en) * 1945-08-02 1961-09-05 Charles E Hablutzel Sabot retainer
US2998780A (en) * 1956-05-28 1961-09-05 William B Anspacher High velocity, fin stabilized projectile, rifled barrel gun system
US2998779A (en) * 1944-07-10 1961-09-05 Donald T Macroberts Projectile
GB1023998A (en) * 1962-08-24 1966-03-30 Dynamit Nobel Ag Improvements in or relating to cartridges for use in recoilless weapons
US3359905A (en) * 1965-04-01 1967-12-26 Oerlikon Buehrle Holding Ag Sabot projectile

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE306404C (it) *

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2998779A (en) * 1944-07-10 1961-09-05 Donald T Macroberts Projectile
US2993444A (en) * 1945-08-02 1961-07-25 Charles E Hablutzel Sabot retainer
US2998778A (en) * 1945-08-02 1961-09-05 Charles E Hablutzel Sabot retainer
US3100448A (en) * 1945-08-02 1963-08-13 Charles E Hablutzel Sabot retainer
US2529504A (en) * 1948-04-26 1950-11-14 William J Kroeger Ammunition for recoilless firearms
US2998780A (en) * 1956-05-28 1961-09-05 William B Anspacher High velocity, fin stabilized projectile, rifled barrel gun system
GB1023998A (en) * 1962-08-24 1966-03-30 Dynamit Nobel Ag Improvements in or relating to cartridges for use in recoilless weapons
US3359905A (en) * 1965-04-01 1967-12-26 Oerlikon Buehrle Holding Ag Sabot projectile

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5259319A (en) * 1992-03-20 1993-11-09 Richard Dravecky Reusable training ammunition
US20020111643A1 (en) * 1999-07-28 2002-08-15 Aesculap Ag & Co. Kg Surgical clip
US20030136293A1 (en) * 2000-04-27 2003-07-24 Werner Torsten Reusable grenade cartridge
US6832557B2 (en) * 2000-04-27 2004-12-21 Comtri Teknik Ab Reusable grenade cartridge
US20110023742A1 (en) * 2009-07-31 2011-02-03 Schaefer Alan R Pressure seal
US8297626B2 (en) 2009-07-31 2012-10-30 The United States Of America As Represented By The Secretary Of The Navy Pressure seal
US8297191B2 (en) 2009-07-31 2012-10-30 The United States Of America As Represented By The Secretary Of The Navy Pressure seal
US9329008B1 (en) * 2013-08-08 2016-05-03 The United States Of America As Represented By The Secretary Of The Army Low collateral damage kinetic energy projectile

Also Published As

Publication number Publication date
NO133289C (it) 1976-04-07
IT979712B (it) 1974-09-30
DE2232866A1 (de) 1974-01-17
DE2232866C3 (de) 1980-10-02
FR2220768B1 (it) 1977-09-02
SE385404B (sv) 1976-06-28
BE796400A (fr) 1973-07-02
NL7303202A (it) 1973-09-11
NO133289B (it) 1975-12-29
FR2220768A1 (it) 1974-10-04
GB1383135A (en) 1975-02-05
DE2232866B2 (de) 1980-01-17

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