EP0117373A1 - Vorrichtung zum Sichern von Drallgeschosszündern - Google Patents

Vorrichtung zum Sichern von Drallgeschosszündern Download PDF

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Publication number
EP0117373A1
EP0117373A1 EP83402314A EP83402314A EP0117373A1 EP 0117373 A1 EP0117373 A1 EP 0117373A1 EP 83402314 A EP83402314 A EP 83402314A EP 83402314 A EP83402314 A EP 83402314A EP 0117373 A1 EP0117373 A1 EP 0117373A1
Authority
EP
European Patent Office
Prior art keywords
washer
axis
latch
relative
gyration
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.)
Granted
Application number
EP83402314A
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English (en)
French (fr)
Other versions
EP0117373B1 (de
Inventor
Jacques Nicolas
Jean Paul Oberle
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.)
Manurhin Defense SA
Original Assignee
Manufacture de Machines du Haut Rhin SA MANURHIN
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Manufacture de Machines du Haut Rhin SA MANURHIN filed Critical Manufacture de Machines du Haut Rhin SA MANURHIN
Priority to AT83402314T priority Critical patent/ATE25769T1/de
Publication of EP0117373A1 publication Critical patent/EP0117373A1/de
Application granted granted Critical
Publication of EP0117373B1 publication Critical patent/EP0117373B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/20—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin
    • F42C15/22—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin using centrifugal force

Definitions

  • the present invention relates to a safety device with annular locking members for gyratory projectile.
  • Such projectiles are generally equipped with pyrotechnic rockets allowing their firing and, to prevent such firing from occurring inadvertently, there is provided inside the body of the projectile a movable member such as a shutter or a gyroscopic rotor able to occupy a position in which it interrupts the continuity of the pyrotechnic chain, position in which it is locked during storage, feeding into the weapon, the path in.
  • a movable member such as a shutter or a gyroscopic rotor able to occupy a position in which it interrupts the continuity of the pyrotechnic chain, position in which it is locked during storage, feeding into the weapon, the path in.
  • the weapon tube during the firing, and during the first meters of the trajectory of the projectile out of this tube, and a position in which this continuity is established, position that the movable member tends to gain automatically for example under the action centrifugal force when it is unlocked, after the course, out of the gun barrel, a sufficient distance to ensure the safety of the weapon's servants.
  • the body is dimensioned internally so that the latch releases the periphery of the washer when it comes to the end of centrifugal travel, and this washer is elastic and allows or causes a movement of translation of the finger in the opposite direction, causing the locking of the movable member in the new position thereof.
  • any mobile member other than a rotor interposed in the pyrotechnic chain of a projectile could be locked and then released as a function of the rate of turn of the projectile, by a device according to the invention.
  • the body 1 has designated a rocket body, essentially of revolution around an axis 25 which constitutes its axis of gyration; at one of its ends, the body 1 has a tubular shape and internally defines a cavity 22 open towards the outside in a determined direction 27 parallel to the axis of gyration 25, and delimited inside the body 1 by a cylindrical face 23 of resolution around the axis 25 and turned towards it and by a face 21 also having a shape of revolution around the axis 25, with respect to which it has an average transverse orientation; this face 21 is turned in the direction 27 and has a concavity which will be specified below.
  • the body 1 integrally carries a base 2 itself hollow and having internally a support 6 defining a spherical bearing, of center C located on the axis of gyration 25, for a spherical rotor 4 also centered at C and which has internally a channel 28 which passes right through it along an axis 26 and inside which is immobilized a primer-detonator 5; the axis 26 passes through the center C and defines its own axis of inertia for the rotor 4, including the initiation of the detonator 5.
  • the support 6 Downstream of the rotor housing 4, if one refers to direction 27, the support 6 is pierced with a channel 53 arranged along the axis 25 and which puts the rotor housing 4 in communication with a pyrotechnic relay fire 3 secured to the base 2 opposite the body; similarly, towards the armnt if one refers to direction 27, the housing of the rotor 4 is placed in communication with a part of the cavity 22 left free by the base 2 inside the body 1, by a bore 9 that has a wall 29 of the base, flat and oriented perpendicular to the axis 25.
  • the bore 9, cylindrical of revolution around the axis 25, passes through the wall 29 right through and it is bordered, at its mouth inside the part of the cavity 22 which is not occupied by the base 2, by an annular shoulder 12, of revolution about the axis 25 and delimited on the one hand by a plane annular face 30, oriented perpendicular to the axis 25, turned in the opposite direction to the direction 27 and adjacent to the bore 9 by its inner periphery, and on the other hand by a cylindrical face 31 of revolution around the axis 25 with a diameter greater than that of bore 9; this face 31 is turned in the direction of a distance from the axis 25 and connects the outer periphery of the face 30 to a flat face 32, oriented transversely with respect to the axis 25 and turned in the opposite direction to the direction 27, face 32 which delimits the wall 29 of the base 2 in the opposite direction to the direction 27 and is joined, by its outer periphery, to the inner face 23 of the cavity 22.
  • the faces 30 and 32 are thus placed opposite the face 2 1 of the cavity 22 of the body 1, and at a distance from this face 21 in the direction of the axis 25.
  • an axial locking finger du.rotor 4 in the form of a socket 8.
  • This socket 8 is delimited in particular by peripheral faces respectively inner 33 and outer 34, cylindrical of revolution around the axis 25 and turned respectively towards the latter and in the direction of a separation by relationship to it; at its downstream end, if one refers to direction 27, it is delimited by a flat annular face 35, oriented perpendicular to the axis 25 and joining the faces 33 and 34; at its upstream end, if one refers to the direction 27, it has an integral flange 10 oriented transversely with respect to the axis 25 and forming a projection in the direction of a distance from that -ci with respect to the face 34; this flange 10 is delimited by two flat annular faces 36 and 37, oriented perpendicular to the axis 25, facing respectively upstream and downstream if one refers to the direction 27 and adjacent by their inner peripheries respectively to the face 33 and to the face 34, and by a cylindrical outer peripheral face 38 of revolution around the axis 25 with a diameter advantageously close to that of the face 31, this face 38 joining the
  • the face 37 is thus placed facing the face 30 and the face 36 facing a central zone 48 of the face 21, and the face 34 of the sleeve 8 has a diameter approximately equal to that of the bore 9, to authorize a sliding mutual contact guiding the sleeve 8 in translation along the axis 25 relative to the integral assembly formed by the base 2 and the body 1.
  • the dimensions of the sleeve 8 parallel to the axis 25, and in particular the distance separating its faces 35 and 37, are such that, when the sleeve 8 rests on the face 37 of the flange 10 on the face 30 of the shoulder 12 of the base 2, via a central zone of a washer 11 which will be described in detail later, its downstream end defined by the face 35 penetrates inside the housing of the rotor 4, so as to be able to immobilize that here inside the support 6 in two positions defined by the engagement of this end of the socket 8 respectively in two countersinks, respectively 7 and 24, which the rotor 4 has additionally.
  • the first of these countersinks 7 is of revolution about an axis 39 of the rotor 4, passing through the center C thereof but offset with respect to its own axis of inertia 26 (see FIG. 3), the second 24 of these countersinks being in turn around the axis 26 and constituting a section of the channel 28 containing the armro-detonator 5.
  • the engagement of the socket 8 in the countersink 7 of the rotor corresponds to an initial state of safety locking, illustrated in FIG. 1, in which the own axis of inertia 26 of the rotor 4 is angularly offset relative to the axis 25.
  • a gyration of the rocket that is to say of the body 1 and of the base 2, around the axis 25 then causes a gyroscopic movement of the rotor 4 which is then reflected, as soon as the rotor 4 is released by releasing the socket 8 with respect to the countersink 7, by a progressive alignment of the own axis of inertia 26 of the rotor 4 with the axis of gyration 25, which places the countersink 24 opposite the socket 8 along l axis 25 and authorizes locking again by engagement of the socket 8 in the countersink 24, as illustrated in FIG.
  • the channel 28 of the rotor 5 communicates on the one hand with the channel 53 of the support 6 and on the other hand with the interior of the sleeve 8 and, via the latter, with a central channel 16, axis 25, which has internally, for the guidance of a striker 17 to slide along the axis 25 in particular in the direction 27, a hollow shaft 15 secured to the body 1 inside the cavity 22, which hollow shaft 15 forms a projection in the direction 27 with respect to the central zone 48 of the face 21 until it penetrates inside the socket 8; in the direction of a distance from the axis 25, the hollow shaft 15 is delimited, inside the cavity 22, by an outer peripheral face 41 cylindrical of revolution around the axis 25 with a diameter less than the diameter of the inner face 33 of the sleeve 8 so as not to hinder the possibility of translation of the latter parallel to the axis 25 by sliding in the bore 9 of the base 4.
  • the state illustrated in FIG. 3 thus constitutes a state of arming of the device, the pyrotechnic chain including the relay 3, the channel 29, the primer 5 placed in the channel 28, the interior of the socket 8, the channel 16 and the striker 17 which it contains being then formed without discontinuity.
  • the length of the hollow shaft 15 measured parallel to the axis 25 is such that it cannot hinder such movement of the rotor 4; for example, it is delimited downstream, if one refers to direction 27, by a flat annular face 40, oriented perpendicular to the axis 25, located approximately ccplanarly with the face 22 of the wall 29 of the base 2 .
  • the shaft 15 carries, by the external peripheral face 41, a latch 13 in the form of a sleeve which surrounds it by an inner peripheral face 42, also cylindrical of revolution around the axis 25 with a diameter substantially equal to that of the face 41 so as to ensure, by mutual sliding contact of the faces 41 and 42, an independence of the bolt 13 in rotation about the axis 25 relative to the body 1 when the rocket is at rest.
  • the bolt 13 is moreover delimited by an outer peripheral face 43, coaxial with its face 42 and having a diameter for example close to that of the face 31 of the shoulder 12 of the base 2, and by two end faces 44, 45, annular, flat, oriented perpendicular to the axis 25, the first of which abuts against the central zone 48 of the face 21 around the hollow shaft 15, and the second of which abuts against the face 36 of the flange 10 of the socket 8, itself in abutment by its face 37 against the face 30 of the shoulder 12 via the central zone of the elastic washer 11 as was said above, if we refer to the safe locking position of the rotor 4 illustrated in FIG. 1.
  • the latch 13 provides between the socket 8 and the face 21 of the body 1 a bracing preventing the socket 8 from disengaging from the countersink 7 of the rotor 4, with an axial clearance compatible with the independence of the latch 13 and of the body 1 to the rotation around axis 25.
  • the latch 13 is weakened for example by streaks such as 54 oriented parallel to the axis 25 and has an interruption 55 along a plane including this axis 25, of such that, when it rotates around the axis 25 at an angular speed exceeding a predetermined value lower than the maximum rate of gyration of the body 1, the centrifugal force which it undergoes then causes it to open, by sectioning or preferably folding along the lines of greatest fragility defined by the ridges 59, with the consequence of its centrifugal migration by homothetic deformation and the elimination of the bracing of the collar 10 of the sleeve 8 opposite the face 21 of the body 1, that is to say the appearance of a possibility of sliding of the sleeve 8 in the opposite direction to the direction 27 in the bore 9 of the base 2, that is to say of release of the rotor 4 in the direction of alignment of its axis 26 with the axis of turning 25.
  • an elastic spiral band 14 independent of the lock 13 and which has a mass, shape, rigidity and prestressing such that, at rest, that is to say when the lock 13 is stationary, this elastic spiral strip 14 is wound around the outer peripheral face of the lock 13 and encloses it so as to be integral therewith by friction, and such that they then authorize the following process of unwinding of the strip, according to which the Man of the Trade will easily determine the values to be given to this mass (in particular in terms of linear mass), this shape (notably in terms of width and length of the strip), this rigidity and this prestressing imposed on the factory winding of the strip around the face 43 of the latch 13.
  • the bolt 13 and the elastic spiral band 14 which is thus integral therewith are free to rotate about the axis 25 relative to to the body 1 thanks to the mounting of the lock 13 described above.
  • the projectile and, with it, the rocket body 1 move in a direction 56 which is here opposite to the direction 27 but could be identical, by undergoing a powerful acceleration, the value of which is for example of the order of 60,000 to 120,000 times the value of the earth's field of attraction, and the lock comes by inertia to be pressed backwards with reference to the direction 56, against any possible consideration; thus, in the example illustrated, the latch 13, by its face 45 and by means of the flange 10 and the washer 11, is pressed against the shoulder 12, which by friction ensures its attachment to the rotation around axis 25 with the body 1 in the direction of gyration such as 58; consequently, the bolt 13 and the elastic spiral band which it carries, here itself in frictional abutment against one 50 of the faces of the washer 10, are rotated about the axis 25 at the same speed as body 1, in the same direction 58, to reach the muzzle of the barrel of a maximum rotation speed which is for example of
  • the acceleration in the direction 56 ceases to be replaced by a deceleration whose value is for example of the order of 40 times the value of the terrestrial field of attraction; all the elements of the mobile device inside the body 1 then tend by inertia to move forward, with reference to direction 56, and come to be pressed against any possible counterpart and, in particular, the latch 13 crosses the axial clearance mounting for coming to bear against a counterpart of the body 1 towards the front, with reference to the direction 56, that is to say here against the central zone 48 of the face 21 which provides support for its face 44.
  • the outer turn of the spiral strip 14 tends to disengage outward under the action of centrifugal force and to come to press against the lower peripheral face 23 of the body 1, so that it follows the total centrifugal unwinding of the spiral band 14, of which it will be noted that for this purpose, the winding is such that the zones of the spiral band respectively increasingly closer to the axis 25 succeed one another in the direction 58 of gyration, determined by the direction of the gun barrel stripes ( Figure 5).
  • the spiral strip 14 is completely wound between the inner peripheral face 23 of the body 1, and secured to the latter by friction due to centrifugal force, and the outer peripheral face 43 of the latch 13 is completely released. .
  • the latch 13, thus freed from the action of the spiral band 14, is subjected to a centrifugal force equivalent at least to that resulting from the speed of rotation of the body 1 of the projectile and opens freely or breaks to come to its turn, by a centrifugal movement, apply against the spiral band 14 which ensures its friction drive at a speed such that it maintains on it the action of a centrifugal force sufficient to keep it away from the end 47 of the washer 11.
  • FIG. 1 illustrates the initial state of the device, the spiral strip 14 being wound around the bolt 13 itself closed on the shaft 15, while FIGS. 2 and 3 illustrate states in which the spiral strip 14 is pressed against the inner peripheral face 23 of the cavity 22, the latch
  • the latch 13 imposes by means of the washer 11, due to the shape of the face 21 of the body 1, against which it is then forced to move, a sliding movement of the sleeve 8 inside the bore 9 in the opposite direction to the direction 27, to cause the release of the rotor 4 in the direction of alignment of its own axis of inertia 26 with the axis of gyration 25.
  • the washer 11 can be rigid or, preferably and as illustrated, semi-rigid but elastically deformable from an initial plane conformation, perpendicular to the axis 25, in which it is illustrated in Figures 1 and 4 with reference to which it will now be described; it has a central orifice 20 intended for its passage through the sleeve 8, and which for this purpose has a cylindrical shape of revolution around the axis 25 with a diameter greater than that of the face 34 of the sleeve 8 but less than the diameters respective faces 38 and 31 respectively of the collar 10 and the shoulder 12 of the base 2.
  • the face 21 of the body 1 is characterized in turn by a concave shape, defined by a ramp 18 placed opposite the outer periphery 47 of the washer 11 if one refers to the direction of the axis 25, and which connects the central zone 48 to a peripheral zone 49.
  • the central zone 48 which projects the shaft 15, is annular, flat, perpendicular to the axis of gyration 25 and it is delimited on the one hand by a circular internal periphery of junction with the external peripheral face 41 of the 'hollow shaft 15 and on the other hand by an outer periphery, also circular, of connection with the ramp 18;
  • the peripheral zone 49 is also annular, plane, perpendicular to the axis 25, and it is delimited by a circular external periphery for connection with the face 23 of the cavity 22 and by an internal periphery also circular for connection with the ramp 18.
  • the peripheral zone 49 is offset relative to the zone 48 in the direction 27, and the ramp 18 which connects them has the form of a truncated cone of revolution around the axis 25, diverging in the direction 27, with a taper such that, during its centrifugal movement by homothety linked to its opening, the massive latch 13, which tends to keep its average orientation along the axis 25, comes to bear on the one hand against the ramp 18 and on the other hand against the face 50 of the washer 11 which is placed opposite the face 21 and against which the flange 10 of the locking sleeve 8 is supported by its face 37 around the central orifice 20, to cause during the continuation of the centrifugal movement the application to the washer 11, in a zone located in cantilever with respect to the shoulder 12 of the base 2, of a thrust in the direction 27 resulting in a tilting of the washer 11 relative to the axis 25, of the presses on the shoulder 12.
  • this tilting is accompanied by an elastic deformation of the washer 11.
  • the area of the outer periphery 47 thereof serving as a support for the bolt 13 moves in the direction 27 relative to the shoulder 12 while by leverage, that is to say by pivoting of the face 51 of the washer 11 turned in the direction 27 on the circular edge 52 of connection between the faces 30 and 31 of the shoulder 12, the zones of the washer 11 located beyond the support of its face 51 on the edge 52 move in the opposite direction; this movement can be carried out freely insofar as the solid bolt 13 no longer constitutes a spacer maintaining the washer 11 applied flat by its face 51 on the face 30 of the shoulder 12 of the base 2 via the flange 10 of socket 8; this results in a thrust applied in the opposite direction to the direction 27 on the face 37 of the flange.
  • the rotor 4 gains by gyroscopic effect a position in which its own axis of inertia 26 is coincident with the axis 25 and in which the countersink 24 is placed opposite the bush 8; for this purpose, the angular offset ⁇ brought back to the center C, between the two millings 7 and 24 is less than 90 °.
  • the washer 11 escapes from the bolt 13, entirely located at outside its outer periphery 47, and the washer 11 resumes by elasticity a flat conformation, which allows the bush 8 to return to a projecting position inside the housing of the rotor 4 in a position of alignment of its channel 28 with the inside of the socket 8 and with the channel 53, as illustrated in FIG. 3.
  • socket 8 to return to a locking position; such a return can be caused by inertia, such as the movement of the striker 17 in the direction 27, as the case may be during percussion with an obstacle if the advancement of the rocket takes place in the direction 27, for example in the case of an explosive projectile, either during an acceleration exceeding a determined value, in the case of a projectile advancing in the opposite direction to direction 27, as may be the case of a propulsion rocket.
  • inertia such as the movement of the striker 17 in the direction 27, as the case may be during percussion with an obstacle if the advancement of the rocket takes place in the direction 27, for example in the case of an explosive projectile, either during an acceleration exceeding a determined value, in the case of a projectile advancing in the opposite direction to direction 27, as may be the case of a propulsion rocket.
  • the parts in relative rotation or in relative translation will be designed and treated so as to minimize friction forces.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Spinning Methods And Devices For Manufacturing Artificial Fibers (AREA)
  • Ceramic Products (AREA)
  • Inorganic Fibers (AREA)
  • Centrifugal Separators (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Lock And Its Accessories (AREA)
EP83402314A 1982-12-07 1983-12-01 Vorrichtung zum Sichern von Drallgeschosszündern Expired EP0117373B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT83402314T ATE25769T1 (de) 1982-12-07 1983-12-01 Vorrichtung zum sichern von drallgeschosszuendern.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8220466A FR2537265A1 (fr) 1982-12-07 1982-12-07 Dispositif de securite a organes de verrouillage annulaires pour projectile giratoire
FR8220466 1982-12-07

Publications (2)

Publication Number Publication Date
EP0117373A1 true EP0117373A1 (de) 1984-09-05
EP0117373B1 EP0117373B1 (de) 1987-03-04

Family

ID=9279854

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83402314A Expired EP0117373B1 (de) 1982-12-07 1983-12-01 Vorrichtung zum Sichern von Drallgeschosszündern

Country Status (4)

Country Link
EP (1) EP0117373B1 (de)
AT (1) ATE25769T1 (de)
DE (1) DE3370073D1 (de)
FR (1) FR2537265A1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2714169B1 (fr) * 1993-12-17 1996-02-09 Manurhin Defense Dispositif de sécurité pour verrouiller un percuteur et procédé de fabrication de ce dispositif.
FR3039267B1 (fr) * 2015-07-24 2017-07-14 Nexter Munitions Dispositif de securite et d'armement pour une fusee d'ogive et fusee comportant un tel dispositif

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1563418A (en) * 1924-10-09 1925-12-01 Adelman Arthur Fuse
US3076410A (en) * 1957-04-25 1963-02-05 Brevets Aero Mecaniques Centrifugally armed fuze for rotating projectile
US3489089A (en) * 1966-02-21 1970-01-13 Junghans Gmbh Geb Rifled projectile fuzes with head pin bolt
DE1926640A1 (de) * 1969-05-24 1970-11-26 Diehl Fa Drallgeschosszuender
FR2233593A1 (de) * 1973-06-13 1975-01-10 Diehl
FR2293688A1 (fr) * 1974-12-07 1976-07-02 Rheinmetall Gmbh Dispositif de securite pour le detonateur d'un projectile raye

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1563418A (en) * 1924-10-09 1925-12-01 Adelman Arthur Fuse
US3076410A (en) * 1957-04-25 1963-02-05 Brevets Aero Mecaniques Centrifugally armed fuze for rotating projectile
US3489089A (en) * 1966-02-21 1970-01-13 Junghans Gmbh Geb Rifled projectile fuzes with head pin bolt
DE1926640A1 (de) * 1969-05-24 1970-11-26 Diehl Fa Drallgeschosszuender
FR2233593A1 (de) * 1973-06-13 1975-01-10 Diehl
FR2293688A1 (fr) * 1974-12-07 1976-07-02 Rheinmetall Gmbh Dispositif de securite pour le detonateur d'un projectile raye

Also Published As

Publication number Publication date
FR2537265B1 (de) 1985-05-24
ATE25769T1 (de) 1987-03-15
DE3370073D1 (en) 1987-04-09
FR2537265A1 (fr) 1984-06-08
EP0117373B1 (de) 1987-03-04

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