US3712229A

US3712229A - Missile having a casing and containing secondary projectiles

Info

Publication number: US3712229A
Application number: US00161574A
Authority: US
Inventors: J Schock
Original assignee: Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Current assignee: Rheinmetall Air Defence AG
Priority date: 1970-07-17
Filing date: 1971-07-12
Publication date: 1973-01-23
Anticipated expiration: 1990-01-23
Also published as: CH526764A; DE2134945A1; DE2134945B2; IL37320A; DE2134945C3; BE770114A; NL7109753A; GB1355862A; SE368085B; IL37320A0; CA945004A; JPS513159B1; FR2101786A5; NL148701B

Abstract

A missile of the type having a casing composed on individual segments containing movable secondary projectiles, the segments in a locked position being mutually parallel, and means for allowing a head wind striking the missile in flight to swing the segments radially outwards. Each segment contains a plurality of secondary projectiles. The segments are hingeably deflectable through an angle of approximately 170*. During the outward swing of the segments the secondary projectiles are slidably ejected from the segments by the centrifugal forces generated by the outward swing of the segments. This arrangement does without an ejecting charge for each secondary projectile and therefore saves space. In addition there is a relatively wide range of scatter of the secondary projectiles.

Description

ilnite States Patent n91 Schock I MISSILE HAVING A CASING AND CONTAINING SECONDARY PROJECTILES [75] Inventor: Julius Schock, 8102 Oberengstringen, Switzerland [73] Assignee: Werkzeugmaschinenfabrik Oberlikon-Buhrle AG, Zurich, Switzerland 22 Filed: July 12,1971

21 Appl. No.: 161,574

[30] Foreign Application Priority Data July 17, 1970 Switzerland ..l0902/70 [52] US. Cl ..l02/69, l02/7.2 [51] Int. Cl ..F42b 13/50 [58} Field of Search ..l02/7.2, 49.4, 58,69

I 56] References Cited UNITED STATES PATENTS 3,023,703 3/l962 Beatty ....l02/49.4 X

3,093,072 6/1963 Pigman ..l02/7.2 3,276,367 10/1966 Edwards ..l02/7.2

[ Jan. 23, 1973 3,295,444 [/1967 Cushing et al ..l02/7.2

Primary Examiner-Verlin R. Pendegrass AtlorneyE. F. Wenderoth et al.

[57] ABSTRACT A missile of the type having a casing composed on individual segments containing movable secondary projectiles, the segments in a locked position being mu tually parallel, and means for allowing a head wind striking the missile in flight to swing the segments radially outwards.

Each segment contains a plurality of secondary projectiles. The segments are hingeably deflectable through an angle of approximately 170. During the outward swing of the segments the secondary projectiles are slidably ejected from the segments by the centrifugal forces generated by the outward swing of the segments.

This arrangement does without an ejecting charge for each secondary projectile and therefore saves space.

In addition there is a relatively wide range of scatter of the secondary projectiles.

11 Claims, 11 Drawing Figures PATENTEDJAN 23 I875 SHEET 1 BF 5 6 NW 7% a, 20 I. 6 2 2 3 9 W H I h 4 2 8 l m 4 8 7 m 3 g 3 4 2 g I 44 o F .4 II/ 0 1 2 A, l 4 OJ 3 6 II. 4 5 3 3 JM AE W E JULIUS SCHOCK, Inventor BY #M Attorneys PMENTEDJAH 23 I975 SHEET 2 0F 5 9 H 425 l4 I0 24 JULIUS SCHOCK, Inventor BY Attorneys PATENTED JAN 2 3 I975 SHEET 3 BF 5 I I hr I 1 1 JULIUS SCHOCK, Inventor By $14M Attorneys PATENTEDJAN23 197s 3.712.229

SHEET u 0F 5 Fig.7

Fig. 8

'JULIUS SCHOCK, Inventcr Attorneys PAIENTEUmza m5 3.712.229

SHEET 5 0r 5 JULIUS SCHOCK, INVENTOR Attorneys MISSILE HAVING A CASING AND CONTAINING SECONDARY PROJECTILES The invention relates to a missile of the type having a casing composed of individual hinged segments containing movable secondary projectiles, said segments in a locked position being mutually parallel, and means for allowing a head wind striking the missile in flight to swing the segments radially outwards.

A known missile of this type contains an ejecting charge for each secondary projectile. Such an ejecting charge occupies a fairly considerable space and it is therefore desirable to do without such a charge. Moreover, in this missile each segment contains only one secondary projectile which is ejected after the segment has swung out through an angle of about 90. The range of scatter is therefore restricted and it is an aim of the invention that this range should be improved.

According to the invention there is provided a missile having a casing composed of separate hinged segments containing movable secondary projectiles, said segments in locked position being mutually parallel and means for allowing a head wind striking the missile in flight to swing the segments outwards, in which a plurality of secondary projectiles are contained in each segment, the segments being hingeably deflectable through an angle of substantially 170, and in which the outward swing of the segments the secondary projectiles are slidably ejectable from the segments by the centrifugal forces generated by their outward swing.

The invention is illustrated by way of example with reference to the accompanying drawing in which:

FIG. 1 is a longitudinal section taken on the line II of FIG. of a missile according to the invention prior to its discharge, some of the parts being shown in elevation;

FIG. 2 is a section taken on the line Il-II of FIG. 5, on a larger scale of a first example of a hinge of one of the segments;

FIG. 3 is a section taken on the line IlIIII of FIG. 2;

FIG. 4 is a section taken on the line IV-IV of FIG. 1, on a larger scale, of unlocking means for one of the segments;

FIG. 5 is a cross section taken on the line V-V of FIG. 1;

FIG. 6 is a longitudinal section of the missile of FIG. 1, in flight shortly after the secondary projectiles have begun to move;

FIG. 7 is a drawing similar to FIG. 4 of another example of unlocking means for one of the segments of a missile according to the invention;

FIG. 8 is a section taken on the line VIllVlII of FIG. 7;

FIGS. 9 and 10 are drawings similar to FIG. 2 of the two further examples of hinges of the segments of a missile according to the invention, and

FIG. 11 is a section taken on the line XIXI of FIG.

Referring first to FIGS. 1 and 4 a flange 1 formed with a collar 2 is attached to the casing of a rocket motor. The flange 1 is formed with a forwardly projecting coaxial hub 4. A tube 5 filled with explosive 6 is fitted into the hub 4. The front end of the tube 5 is closed by a cap 7 and this end carries a bush 8 (FIG. 4). The missile has a head 9 having an inwardly projecting flange 10 forming a hub portion 11. The hub portion 11 is screwed to the front end of the bush 8. An impact fuse 12 forms the nose of the head 9. Coaxially located inside the head 9 is a sleeve 13 which rests on the flange 10. A time fuse 14 is contained inside the sleeve 13. The direct action impact fuse 12 and the time fuse 14 are of conventional construction and are therefore not described in detail. An annular chamber defined by the sleeve 13 and the head 9 of the missile contains an explosive charge 15.

A piston 16 having the form of a recessed disc is provided with a central bore in its crown l7 and in its base 18. The bore in the crown 17 is of smaller diameter than the bore in the base 18. The piston 16 is slidably movable on the bush 8 and guided in the head 9 of the missile. A ring 19 is screwed on to the bush 8, spaced from the hub 11 in the head 9 of the missile. As can be seen in FIG. 4 the crown 17 of the piston 16 in a position of rest bears against the ring 19 and the side of the bore in the base 18 is in contact with the edge of the flange 20 of the bush 8. A pyrotechnic charge 21 comprising a gas and a smoke generating component is accommodated in a recessed cavity of the piston 16. The bush 8 has a blind bore 22 parallel to the missile axis which is in communication through a transverse bore 23 with the recessed cavity in the piston 16. A container for a priming charge 24 is attached to the cap 7 of the tube 5 and covers the bore 22 in the bush 8. The priming charge 24 is adjacent a detonator cap 25 of the time fuse 14.

As shown in FIG. 2 a ring 26 is slidably mounted on the hub 4 of the flange 1. A collar 27 projecting from the flange 1 in the forward direction forms an internal step 28. A ring 29 is fitted into the wider diameter portion 30 of the collar 27 and bears against the step 28. The

rings

26 and 29 are each formed with six

slots

31, 32 disposed in pairs at equiangular intervals, so that their planes of symmetry coincide with axial planes of the missile.

With reference to FIGS. 1 to 5 the cylindrical casing of the missile between the collar 27 and the piston 16 consists of six segments 33 of equal size, the abutting edges 34 being parallel to the missile axis.

Machined into these edges 34 are grooves of semicircular cross section extending the entire length of the edges. The longitudinal axes of all these grooves 85 are parallel to the missile axis. The grooves 85 in each two abutting edges 34 enclose a cord 86 of circular section. The cords 86 serve for sealing the joints between adjacent segments. They also prevent the external face of any edge 34 of a segment 33 being bent outwards and projecting beyond the corresponding edge of the abutting face 34 so as to form a cutting edge when the missile is in a launching tube or impairing the flying properties of the missile. Another annular seal 87 is secured tov the collar 27 of the flange 1 and seals the joint between the collar 27 and the rear ends of the segments 33. Each segment is formed on its inside with two ribs 35 that extend the full axial length of each segment and which are located at equal distances from the axial plane of symmetry of each segment 33. The ribs 35 have faces 36 which are parallel to the missile axis, and which are contained in planes that intersect in the missile interior. Moreover, the ribs 35 also have faces 37 which forms parts of a cylinder having an axis contained in the plane of symmetry of the associated segment 33. At its rear end each segment 33 is formed with prismatic block 38 (FIG. 3) to which a plate 39 extending across the missile axis is attached. As can be seen in FIGS. 2 and 3 a slit 40 having an enlarged portion 41 is machined into the block 38. The planes of symmetry of the

slits

40, 41 coincide with the planes of symmetry of the segments 33 and of the

rings

26 and 29. Machined into the walls of the slit 40 are slots 42 parallel to the missile axis.

The missile includes three cranked

levers

43, 44 of identical construction having arms of different lengths as shown in FIG. 2. The longer arms of the two levers 43 are connected by a pin 45 which engages the slot 42 in the block 38. The shorter arms of the levers 43 engage a slit 32 in the ring 29 and are hingeably attached to a hinge pin 46 in the ring. The lever 44 is located between the two levers 43 and is fulcrumed at its vertex to pivot about a pin 47 which is fixed in the vertex of each of the levers 43 on either side. The shorter arm of the lever 44 is hinged to a pin 48 which crosses the slit 41, and which is fitted into the block 38. The longer arm of the lever 44 engages a slit 31 in the ring 26 and is hingeably attached to a pin 49 in this ring. The

pins

45, 47, 46, 48, 49 are parallel and their axes are perpendicular to the missile axis. The

levers

43 and 44 form a hinge connection between a segment 33 and the collar 27 of the flange 1 as described and illustrated in the published unexamined specification of German Pat. application No. I4 53 819.

The piston 16 is provided with studs 50 projecting rearwards parallel to the missile axis. The studs 50 bear against the faces 36 of the ribs 35 of the segments 33 (FIG. and retain them in the position shown in FIG. 1. A sleeve 51 is mounted on the tube 5 and interposed between the bush 8 and the hub 4 of the flange l. The sleeve 51 is formed, as shown in FIG. 5, with five equiangularly disposed enlarged portions 52 of semicircular cross section. The radial side faces 34 of the segments 33 are contained in the planes of symmetry of the enlarged portions 52. Facing the center region of each segment 33 the sleeve 51 carries a steel blade 53. The blades are formed by leaf springs which are retained in a cocked position as will be hereunder described.

Each segment 33 embraces a set of secondary projectiles 54 placed nose to tail. The secondary projectiles 54 are held between the surfaces 37 of the ribs 35 of the segments and between the inside surface of the segment 33 and two enlarged portions 52 on the sleeve 51. The secondary projectiles 54 have radially projecting studs 55 which bear against the faces 35 of the ribs on the segments 33. Between the rearmost secondary projectile 54 of a set and the plate 39 is a fully compressed double conical helical spring 56. The leading projectile 54 ofa set is kept in contact with the base 18 of the piston 16 by the spring 56. The segment 33 is urged by the spring 56 acting through the

levers

43, 44 and the

rings

26, 29 against the flange l. The forward ends of the blades 53 bear against the secondary projectiles 54 and are thus kept in an energized position.

The manner in which the described arrangement functions is as follows.

When in course of the flight of the missile the time fuse operates, the detonator 25 is fired in a conventional manner and ignites the priming charge 24 in turn fires the pyrotechnic charge 21 through the

bores

22, 23 in the bush 8. Since the crown of the piston 16 exceeds the base of the piston in area the gas pressure that builds up in the recessed cavity of the piston, by virtue of the combustion of the charge, forces the piston forwards. The threads of the ring 19 shear off and the piston 16 together with the ring 19 are thrown forwards against the hub 11 of the missile head 9 (FIG. 6). At the end of its displacement the base 18 of the piston is in a position in front of the edge of the flange 20 of the bush 8. The dark colored gas escapes to the outside through the opening 57 thus formed which indicates that the ejection of the secondary projectiles 54 has begun. By the displacement of the piston 16 the studs 50 are withdrawn from the faces 36 of the segments 33 and these are therefore released.

The effect of the thrust of the leaf springs forming the blades 53 is now to pivot the segments 33 about the

hinges

46 and 49. As the angle of tilt of the segments increases the cross sections of the segments 33 exposed to the head wind become greater. The secondary projectiles 54 experience an acceleration in the axial direction of the segments 33 by the centrifugal forces generated by their outward swing. The secondary projectiles 54 are guided by the segments 33, i.e., by the ribs 35 and the studs 55 and consecutively leave these guideways, flying away from their segments 33 at different speeds and in different directions. The secondary projectile 54 that is originally located closest to the hinge of its segment is accelerated away quickly by the action of the spring 56 until major centrifugal forces can take effect. As the segments 33 open, the ring 26 is pulled forward by the lever 44. Since all the hinge levers 44 are pivotally attached to the ring 26 the segments 33 swing outwards in unison. When the angle of tilt of the segments 33 is nearly (indicated in FIG. 6 by a dot-dash outline) and the hinge levers 44 strike the edge 58 of the collar 27 of the flange 1, they will have discharged all their secondary projectiles 54.

Furthermore, when the missile which has discharged its secondary projectiles 54, flying with its segments 33 widely opened and eventually hitting the ground the impact fuse 12 in the nose ignites the priming charge 15 in a manner not illustrated in detail and the priming charge in turn fires the explosive charge 6 contained in the center tube 5.

Should the time fuse 14 have failed during flight, either by not having been correctly set or for other causes, so that the secondary projectiles 54 have not been ejected, then impact on the ground will cause the explosive charge 6 to detonate, as already described. Detonation of this charge also fires the explosive charges of the secondary projectiles 54 and destroys them. This prevents explosive charges lying about on the battle field when it is occupied by friendly forces.

In FIGS. 7 to 11 like components are identified by the same reference numbers as used in FIG. 1 to 6. Components that differ in shape are distinguished by a suffix a or b. Original components are given a new reference number.

With reference to FIG. 7 the head 9a of the missile has a rearward sleeve-like extension 60. A peripheral groove 61 in the end face of the extension 60 has two intersecting flanks 62, 63. The flank 62 which is furthest away from the missile axis forms part of the surface of a cone which diverges towards the rear. The inside wall of the extension 60 contains another peripheral groove 64 of triangular cross section. As can be seen in FIG. 8 the inside surface of the extension 60 also contains triangular grooves 65 disposed at equiangular intervals. The crests of the grooves 65 are parallel to the missile axis and intersect the crests of the two grooves 61 and 64.

The forward ends of the segments 33 engage the groove 61, the segments being thereby kept closed. The bush 8a has a flange 66 which with its outer wall bears against the inside of the extension 60. The bottom 59 of the missile head 9a and the flange 66 an annular chamber 67 containing a pyrotechnic charge 21. The annular chamber 67 communicates with the priming charge 24 through

bores

23 and 22.

Briefly, this arrangement functions as follows:

The charge 21 is fired by the priming charge 24, as has already been described. The gas pressure which builds up in the annular chamber 67 destroys the extension 60 by fracturing it along the lines of weakness defined by the grooves 62, 64 and 65, the fragments being thrown outwards. This releases the segments 33 which are accelerated by the outwardly projected fragments and lifted off the missile to be swung out by other forces in the manner already described with reference to the missile shown in FIGS. 1 to 6.

In the arrangement shown in FIGS. 9 and 11 the collar 27a of the flange 1 contains a bore having two different diameters divided by a step and provided with axial slits 68 at equidistant angular intervals. A coupling ring 69 is slidably movable on the hub 4 of the flange 1. The coupling ring 69 has as many slits 70 as the collar 27a. The planes of symmetry of the slits 70 are axial planes of the missile and coincide with the planes of symmetry of the slits 68. Two slots 71 having planes of symmetry normal to the missile axis are machined into the flanks of the slits 70.

Each segment 33 is firmly attached to a connecting member 72. A hinge arm 73 is affixed to the connecting member 72. The arm 73 extends from the connecting member 72 along the hub 4 to the rear and in outwardly off-set to form a kind of hook. Two studs 74 are fitted to the hook-shaped end 75. The vertex of the hook-shaped portion 75 extends into the slit 70 in the coupling ring 69, whereas the studs 74 are guided in the slots 71. The end of the hook-shaped portion 75 is received into a slit 68 in the collar 27a and linked therein to a hinge pin 76. The outer shank of the hooked portion 75 is straight and the inner shank is bent slightly inwards.

This arrangement functions as follows:

During the simultaneous tilt of all the segments 33 together with the arms 73 about the hinge pins 76, the studs 74 slide in the slots 71 of the coupling ring 69 and this is pulled forward. Shortly before the rear ends of the segments 33 strike the collar 27a (this position is indicated in FIG. 9 in dot-dash outlines) the studs 74 leave the slots 71 in the coupling ring 69.

The advantage of the hinge illustrated in FIGS. 9, 11 over that shown in FIG. 2 is its simpler design.

In the arrangement of FIG. a ring 77 is tightly fitted into the bore of the collar 27b of the flange 1. The ring 77 has slits 78 disposed at equiangular intervals and having planes of symmetry that are axial planes of the missile. Furthermore, a coupling ring 69 containing slits 70 is slidable on the hub 4 of the flange. The planes of symmetry of the slits and 78 coincide.

Slots

71 and 79 respectively are cut into the walls of the slits 70 and 78. The planes of symmetry of the slots 71 are normal to the missile axis as well as to the planes of symmetry of the slots 79. A hinge arm 80 is connected to a segment by a connecting member 72. The hinge arm 80 is parallel to the segment 33 and has two arcuately curved ends. The rear portion 83 of the arm 80 substantially forms a circular arc towards the outside which carries a pair of studs 74 and 84 which engage the slot 71 in ring 70 and the slot 79 in ring 77.

The arrangement functions as follows:

When the segments 33 have tilted a short way about the axes of the studs 84 the inside surfaces 81 of the arms 80 make contact with the edge 58 of the collar 27b. However, the arms 80 and the segments 33 can nevertheless continue to be deflected because the arms are pulled forward by the reactive resistance of the edge 58, the studs 84 sliding to the forward ends of the slots 79 (the final position of the segments 33 is shown in FIG. 10 in dot-dash outline). In the same way as in the arrangement shown in FIG. 9 the ring 69 is pulled forward whilst the arms 80 swing, until eventually the studs 74 ride out of the slots 71. The advantage of this hinge over that in FIG. 9 is that it affords a larger deflection angle for the segments 33 within a short structural length.

Iclaim:

1. A missile comprising, a casing formed of separate hinged segments, secondary projectiles contained in said segments, said segments in a locked position being mutually parallel, means for allowing a head wind striking the missile in flight to swing said segments outwards wherein the improvement resides in each of said segments containing a plurality of said secondary projectiles, saidsegments being hingeably deflectable through an angle of substantially and said secondary projectiles being slidably ejectable from said segments during its outward swingof said segments by the centrifugal forces generated by said outward swing.

2. A missile as defined in claim 1 including guideways contained in said segments to guide said secondary projectiles and prevent them from lifting off.

3. A missile'as defined in claim 2 including slots defined by said guideways, and studs mounted on said secondary projectiles which engage said slots to prevent said projectiles from lifting off said guideways.

4. A missile as defined in claim 1 wherein said means for allowing a head wind striking the missile in flight to swing said elements outwards comprises a piston operable by gas pressure and adapted to keep the segments together in their locked positions and to release the segments when displaced in the axial direction of the missile.

5. A missi'ie as defined in claim 4 including a recessed cavity defined by said piston, and two facing surfaces of different size bounding said cavity so that gas pressure generated in said cavity will displace said piston in a direction for releasing said segments.

6. A missile as defined in claim 1 including a missile head, a rearward sleeve-like extension formed on said head and embracing the front ends of said segments, an annular chamber defined by said extension, a pyrotechnic charge contained in said chamber, and grooves defined by said extension defining lines of weakness to enable said extension to be shattered when said pyrotechnic charge explodes and to release said segments.

7. A missile as defined in claim 1 including hinges linking said segments to the missile and an axially movable ring to which all of said segments are operatively coupled for opening said segments in unison.

8. A missile comprising a casing formed of separate segments hinges linking said segments to the missile, a plurality of movable secondary projectiles conformed in each of said segments, said segments in a locked position being mutually parallel, means for allowing a head wind striking the missile in flight to swing said elements outwards, said means comprising a piston operable by gas pressure and adapted to keep the segments together in their locked positions and to release the segments when displaced in the axial direction of the missile, and an axially movable ring to which all of said segments are operatively coupled for opening said segments in unison, said segments being hingeably deflectable through an angle of substantially 170 and said secondary projectiles being slidably ejectable from said segments during its outward swing of said segments by the centrifugal forces generated by said outward swmg.

9. A missile as defined in claim 8 including a recessed cavity defined by said piston, and two facing surfaces of different size bounding said cavity so that gas pressure generated in said cavity will displace said piston in a direction for releasing said segments.

10. A missile as defined in claim 8 including a missile head, a rearward sleeve-like extension formed on said head and embracing the front ends of said segments, an annular chamber defined by said extension, a pyrotechnic charge contained in said chamber, and grooves defined by said extension defining lines of weakness to enable said extension to be shattered when said pyrotechnic charge explodes and to release said segments.

11. A missile as defined in claim 8 including guideways contained in said segments to guide said secondary projectiles, slots defined by said guideways and studs mounted on said secondary projectiles which engage said slots to prevent said projectiles from lifting off said guideways.

Claims

1. A missile comprising, a casing formed oF separate hinged segments, secondary projectiles contained in said segments, said segments in a locked position being mutually parallel, means for allowing a head wind striking the missile in flight to swing said segments outwards wherein the improvement resides in each of said segments containing a plurality of said secondary projectiles, said segments being hingeably deflectable through an angle of substantially 170* and said secondary projectiles being slidably ejectable from said segments during its outward swing of said segments by the centrifugal forces generated by said outward swing.

3. A missile as defined in claim 2 including slots defined by said guideways, and studs mounted on said secondary projectiles which engage said slots to prevent said projectiles from lifting off said guideways.

5. A missile as defined in claim 4 including a recessed cavity defined by said piston, and two facing surfaces of different size bounding said cavity so that gas pressure generated in said cavity will displace said piston in a direction for releasing said segments.

8. A missile comprising a casing formed of separate segments hinges linking said segments to the missile, a plurality of movable secondary projectiles conformed in each of said segments, said segments in a locked position being mutually parallel, means for allowing a head wind striking the missile in flight to swing said elements outwards, said means comprising a piston operable by gas pressure and adapted to keep the segments together in their locked positions and to release the segments when displaced in the axial direction of the missile, and an axially movable ring to which all of said segments are operatively coupled for opening said segments in unison, said segments being hingeably deflectable through an angle of substantially 170* and said secondary projectiles being slidably ejectable from said segments during its outward swing of said segments by the centrifugal forces generated by said outward swing.